ML20040C827
| ML20040C827 | |
| Person / Time | |
|---|---|
| Site: | Sequoyah  |
| Issue date: | 01/15/1982 |
| From: | TENNESSEE VALLEY AUTHORITY |
| To: | |
| Shared Package | |
| ML20040C823 | List: |
| References | |
| NUDOCS 8201290281 | |
| Download: ML20040C827 (160) | |
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7, i' 1 1 1: ' TENNESEE VALLEY AUTHORITY SEQUOYAH NUCLEAR PLANT 4 i; l RESEABCH PROGRAM ON HYDROGEN COMBUSTION AND CONTROL j QUARTERLY PROGRESS REPORT #5 k+ JANUARY 15,- 1982 5: 1 3; l! l 8201290281 820122 - PDR ADOCK 05000327 P pyg
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1 i~ . TABLE OF CONTENTS i I. Introduction II. Task Description, Schedule, and Status A. Industry Degraded Core (IDCOR) Program /TVA B. Electric Power Research Institute (EPRI)/TVA/ Duke /AEP I C. Westinghouse /TVA/ Duke /AEP - CLASIX D. TVA/ Duke /AEP j D.1 Fogging D.2 Singleton Testing E. TVA E.1 Browns Ferry Probabilistic Risk Assessment (Pickard, Lowe, and Garrick) E.2 Sequoyah Full-Scale Safety and Availability Analysis (Kaman Sciences Corporation) E.3 Consequence Analysis E.4 Severe Accident Sequence Analysis (SASA)/(ORNL) 1 : E.5 Ice Condenser containment Code j III. Appendices l. A. Program Details (. I A.1 EPRI Program Overview 1-A.2 Igniter Development - AECL Whiteshell A.3 Hydrogen Combustion - AECL Whiteshell A.4 Hydrogen Control Studies - Acurex, Inc. A.5 Fogging Studies - Factory Mutual i A.6 Hydrogen Mixing and Distribution Studies - Hanford I i l i I l
l
'l j
d
,i q. } I. Introduction )
ij This report is the fifth and last of a series of research i j summaries presented on a quarterly basis to the Nuclear Regulatory Commission (NRC) by the Tennessee Valley Authority jh (TVA) to satisfy the following condition of the Sequoyah Nuclear Plant units 1 and 2 operating licenses:
'?
- t During the interim period of operation, TVA shall continue a q
;, research program on hydrogen control measures and the
,: effects of hydrogen burns on safety functions and shall
; submit to the NRC quarterly reports on that research program.
l This report provides the results of research that TVA has conducted and participated in with Duke Power, American Electric Power ( AEP), and the Electric Power Research Institute (EPRI). In addition, this report provides the current status and schedule of TVA's involvement with the Industry Degraded Core Rulemaking effort and our' work in the area of Probabilistic Risk Assessment. II. Task Description, Schedule, and Status
, The major emphasis of TVA's current research program was to discover, collect, and evaluate enough information about degraded core events and potential mitigations for their risk reduction to be able to justify the permanent hydrogen mitigation system (PHMS) selected for Sequoyah Nuclear Plant.
TVA believen that with the information available frem this
T N i' J
^
re:41rch effort that the permanent systet can be shown to _ _ 3 j provide an adequate hydrogen control system with adequate safety margins. j
~
This section provides a summary of each individual or group effort in which TVA is actively involved that is reL,ted to hydrogen combustion and control, risk assessment, or overall { de3raded core studies. Here, current updates of each effort are summarized with further details presented in the appendices. t 1 A. Industry Degraded Core (IDCOR) Program /TVA (identified in
- j. the first quarterly report as AIF proposal)
A.1 Scope No update necessary.
.)
A.2 Schedule d No update necessary.
+
A.3 Status i As reported in the fourth quarterly report, the IDCOR j program plan has been finalized with the selection and (j definition of 24 major tasks to be accomplished by July .' } 1983 The program plan is currently on schedule and approximately half of the major tasks have been contracted out. Four reference plants have been selected: Peach Bottom - BWR - Mark I containment Zion - PWR - large dry containment l' I . . - . - .
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.. -. Gran.. sd Gulf /Hartsville - BWR - Mark III containment t ~ . <
6 Seqgoyah - PWR - Ice l Condenser containment w % * % s B. Electric Powsr.hesearch Institute (EPRI)/TVA/ Duke /AEP .
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- B.1 Scope .
x -s The scope,of the four EPHI research programs is
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} B.2 ScheQule s y~.
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Testing has been completed at three of the four
. - facilities. Whiteshell is the only facility where
\4 N testing is still Deing' conducted. Whiteshell's
- s,. ,. .
scheduled date for completing all testing is February
, m ik ,
s , 22, 19?2. They expect that their final report would be s s
- issued 4poroximately one mouth after testing is
~
T~ x .. \ ~ completed. Final reports froin the other three k facilities' will bT issued by EPRI in the near future.
.- s' B.3 Status s . . .f' <
_ The revised Appdn'op ,A.1 includea preliminary reports on thE 'tcatira conducted at each of-the four
' s fad itiea. The repori od'the testing-conducted at FactoryMutualwasprbpdredbythatorganization. The '
~
.L other three reports individually address research q.
performed by Acurex,gInc., Hanford Engineering
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. Developmend LaboratodL[4M the White.1 ell Nuclear 3 s b u ,s s __ ,
Research Establishment, 60t were pelncipally prepared
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'7 by-Duke, TVA, & AEP, respectively; based on progress x -- . -
,- s reports and draft final reports fror., the contractors.
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; The contractors are currently completing data analyses and preparing the final reports which will be issued by EPRI.
C. Wastinghouse/TVA/ Duke /AEP - CLASIX
.. A response to the July 8, 1981, letter from R. L.
- s >
f Tedesco to H. G. Parris has been submitted to NRC. This, response included analyses performed by TVA using the CLASIX code. No additional CLASIX analyses are l
, , presently envisioned.
=p ~,. D. TVA/ Duke /AEP D.1 Fogging
/ ~i D.1.1 f , Scope
. No update necessary.
D.1.2 Schedule No update necessary. D.1 3 Status ' The testing at Factory Mutual and Acurex on fogging was completed recently. Preliminary reports on the testing conducted ac these facilities is included in Appendix A. l D.2 Singleton Testing D.2.1 Scope
- No update necessary.
D.2.2 Schedale l Testing complete. t
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D.2 3 Status ] LJ Please refer to L. M. Mills' letter to.L. S.
. Rubenstein dated December 1, 1981, for test .i results.
l i A The results were submitted as our response to question No. 3 of the Additional Questions on j Hydrogen Control System for Ice Condenser Plants
; submitted to TVA by the Containment Systems
~
- } Branch of the NRC.
E. TVA In addition to the preceding, TVA is independently pursuing other areas of degraded core studies which are outlined in this section. E.1 Browns Ferry Nuclear Plant Probabilistic Risk Assessment (Pickard, Lowe, and Garrick) i E.1.1 Scope r No update necessary. ?;
- l. E.1.2 Schedule i.
The study began 10/80. Date: for major milestones 8
. Data analysis and fault trees - 1/82
. Explant consequence model assessment - Complete
. Seismic analysis reports - Draft Complete
. Event trees 5/82
. Explant consequence analysis - 3/82
. Final report - 6/82 d
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1 'I 3 ,4 E.1 3 Status ~5 { Tasks completed or presently underway: .4
, . Event sequence diagrams i . Event trees I
! . System quantitative analysis 1
. Maintenance and test data j . Seismic analysis
. External events analysis
. TVA code conversion Near future tasks:
. System quantitative analysis
. Containment analysis E.2 Sequoyah Nuclear Plant Full-Scale Safety and Availability Analysis (Kaman Sciences Corporation) 4
. E.2.1 Scope No upf'te necessary.
.f E.2.2 Schedule Phase I (preliminary availability assessment) 1/81 Phase II-A (preliminary safety uar.essment) 5/81 Phase II (final assessment) 10/82 E.2 3 Comprehensive system models have been developed for six systems (Auxiliary Feedwater, Main
, Feedvater, Safety Injection. Residual Heat Removal, Ice Condenser, and Control Air)
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1 Preliminary models have been developed for all i 2 other systems which are included in the
+ analysis.
Preliminary availability and safety assessments il
. have been made.
E.3 Consequence Analysis E.3 1 Scope
- i No update necessary.
E.3.2 Schedule Evaluate MARCH and KESS as to similitudes
, and differences in the prediction of
-1 LWR Class 9 accident sequences (EPRI/SAI) 12/81 Comparison of postulated accident sequences for SQN using MARCH and KESS (EPRI/SAI) 4/82 E.3 3 Status l Completed training in use of MARCH, CORRAL 2 and dose prediction codes 3/81 High probability accident sequences l identified 4/81 i l Obtained CRAC2 computer program from Sandia 9/81 i. E.4 Severe Accident Sequence Analysis (SASA)/(ORNL) l' l E . 4 '.1 Scope No update necessary. l A
m i q ll 1
- i E.4.2 Schedule
.j I. Analysis of Station Blackout Sequence for Browns Ferry Unit One-t- A. Complete Analysis and Issue Final Report j for Accident Sequence Analysis 10/81 D' B. Complete Analysis and Issue Final Report 7 for Fission Product Trnasport Analysis 2/82 II. Analysis of Small Break LOCA Outside Containment I for Browns Ferry Unit One
. 'I
] A. Complete Analysis and Issue Final Report for Accident Sequence Analysis 7/82
; B. Complete Analysis and Issue Final Report for g Fission Product Transport Analysis S/81, III. Analysis of Small Break LOCA Inside Containment for Browns Ferry Unit One A. Complete Analysis and Issue Final Report for 12/82 Accident Sequence Analysis B. Complete Analysis and Tssue Final Report for 2/83 Fission Product Transport Analysis E.4.3 Status 10/81 Final Report of Station Blackout Accident Sequence Analysis Published 10/81 Draft Report of Station Blackout Fission I Product Transport Analysis Issued 12/81 Analysis of Break in Scram Discharge
$ Volume in Progress E.5 Ice Condenser Containment Code
- , E.5.1 Scope No update necessary
)
. . , s.
il i
- s 4
j E.5.2 Schedule No update necessary
- s E.5 3 Status Part I - No update necessary.
Part II - Comparison has been made between MONSTER and CLASIX for an S D event. 2 Both codes provide similar results
- 2. showing multiple burns in the lower
. compartment and upper plenum. The ; CLASIX results are more conservative than those obtained from MONSTER.
Comparisons between MONSTER results. and the Fenwal test data showed good agreement. '( Part III -General improvements to the code will continue on an as-needed basis. 4 4 i 7 4 i 1 4 i
1 e E t 9 r i 4 4 s k 7 APPENDIX A EPRI PROGRAM 4 3 h 4
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APPENDIX A.1 EPRI PROGRAM - OVERVIEW f 1.0 Introduction i
< In order to justify installation of a permanent hydrogen
.{ mitigation system at Sequoyah Nuclear Plant, several questions concerning hydrogen management are being addressed. TVA, } j American Electric Power (AEP), and Duke Power. entered into a } } research effort with the Electric Power Research Institute (EPRI) .) to study hydrogen mitigation and control under degraded core ]
'I accident conditions. ! 1.1 Objectives and Technical Issues. This program was intended
'I t to meet the following limited objectives;
- 1. Determination of whether and when hydrogen can burn in postulated ice condenser accident environments resulting l
- from degraded core scenarios;
- 2. Demonstration that if a hydrogen burn does occur, its effects will not exceed the realistic survival capabilities of equipment and containment; and 3 Demonstration that reasonable control methods can provide adequate safety margins assuring the integrity of the containment and of key safety-related squipment.
Determination of the effects of hydrogen deflagrations on containment and equipment requires investigation of several questions, in particular:
- a. What are the lower flammability limits under degraded
, core accident conditions and how effective are thermal i ignition sources;
\
'l
- 1
- b. What is the character of deflagrations in various geometries and how can the effects be mitigated;
- c. What is the nature of hydrogen mixing and distribution in large compartmentalized volumes; and s
- d. What is the potential for the acceleration of deflagrations, or for flame propagation between compartments in turbulent mixtures.
1.2 Program Elements. We - feel the following projects will
+ provided the information needed to satisfy the program i
objectives. The projects were related, and consisted of:
; 1. Development and pseliminary testing of thermal igniters for a deliberate ignition system (AECL Whiteshell);
- 2. Experiments and analyses on basic hydrogen combustion
> phenomena including the effects of steam, turbulence, and flame propagation between compartments (AECL Whitesheil);
3 Experiments on hydrogen control methods including water spray and fog (Acurex/ Factory Mutual); 4 Measurement and analyses of hydrogen mixing and distribution in a large compartmentalized volume (HEDL- W ). In the following appendices, we have included preliminary reports on all four of the facilities listed above. HCCQPR
i t 4 APPENDIX A.2 IGNITER DEVELOPMENT CONDUCTED BY AECL WHITESHELL i i i l 1-i t l l l l J
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;; STUDY OF HYDROGEN CCMBUSTION
;c NEAR LOWER FLAMMABILITY LIMITS
.y DiTERIM PROJECT REPORT l DECEMBER, 1981
. Prepared by:
')'.c K. K. Shiu, American Electric Power F. G. Hudson, Duke Power Company J. J. Wilder, Tennessee 7 alley Authority l *
.;l Project Conducted at:
'.:l Whiteshell Nuclear Research Establishment
'} Project Sponsors:
.3 American Electric Power Service Corporation Atomic Energy of Canada Limited Duke Power Company
\ Electric Power Research Institute Tennessee Valley Authority Ontario Hydro 4
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- 1. INTRODUCTION
- . 2. DESCRIPTION AND INSTRUMENTATION OF TEST FACILITY-2.1 Description of Test Facility
? 2.2 Instrumentation 3 EXPERIMENTAL PROCEDURE 31 Preparation of the Mixture 32 Sampling ';P 33 Turbulent Combust 4.on Experiments 4
h
@ 4. RESULTS AND DISCUSSION
. 4.1 Combustion at low Concentrations 4.2 Combustion at Relatively High H Concentrations 2
, , 43 Effect of Turbulence t< 4.4 Effect of Turbulence with Steam Addition 4.5 Effecc of Hydrogen Concentrations with Turbulence
- 4.6 Effect of Steam Addition and Turbulence on Combustion with Central Ignition 4.7 Effect of Ignitor Location 4.8 Temperature Effects on Flar"nability Lin ts i S. CCNCLUSICNS -
. :t cl TABLES AND FIGURES
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Hl i 1. INTRODUCTION 1 , This report provides preliminary information on the
' Whiteshell combustion study currently underway at the H Contaiment Test Facility at Whiteshell Nuclear Research Establishment. Included in this report are static and
.s-turbulent test results obtained for varying pre-mixed hydrogen mixtures. Data on the effects of turbulence are also presented.
}
- 2. DESCRIPTION AND INSTRUMENTATION CF THE TEST FACILI*Y D
2.1 DESCRIPTION
OF THE TEST FACILITY
$ The test configuration consists of two test' volumes: a i '.1 sphere and a pipe which may be interconnected. The '( dimensions of the two vessels are shown in Table 1. .' For the series of experiments reported here only the l
Y sphere is used, Figure 1. The pipe / sphere geometry experiments are being conducted at the test facility.
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The sphere has three large openings and several small ones. The smaller openings are used for mounting
- j instruments and measurement probes. The sphere is insulated and trace heated with steam. The temperature
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of the spherg can be maintained at any desired value up to about 275 F (135 C). Steam is injected into the sphere through one of the ports when it is required. A d view of* the sphere is shown in Figure 1. Two fans driven by air motors are mounted diametrically cpposite
.l to each other as shown in Figure 2. Some of the fan
.]
, :1
' characteristics are shown in Table 2.
l 2.2 INSTRUMENTATICN t.3 I A schematic of the instrumentation within the sphere is The transient pressures during ld shown in Figure 3 combustion are measured by three piezoelectric type of I'] transducers with a rise time of 2 microseconds and a I
]) Rosemottnt capacitance transducer with a response time lj of 0.2 seconds. The piezo-transducers were mounted i I flush with the inner surface of the flanges. A fi resistance temperature detector was employed to monitor
!.l the steady state temperature of the gases. It was not ,] intended for fast transient measurements. l A spark ignition source was used for all the tests j i perfor=ed in this facility. The use of a spark made it ! 1: I easier to instrument these experiments. ,I
.l The passags of the flame front was detected by two seven point ion probes mounted appecximately in the radial direction cpposite to each other as shown in l , Figure 3 The departure fece the radial direction was
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of the probes can be assumed esdial. Each of the seven z points consisted of two electrodes of .04 inches (1 mm)
. diameter bare wires separated by .08 inches (2 mm) gap. The ion probes for these experiments were
[ developed by Liu et. al. and details are presented in
'l . reference (1). ,N Li
- The signals from the piezoelectric transducers and ion probes were processed by an analog to digital convertor
; with a scan time of 1.5 millisecond per scan. For low hydrogen concentration experiments this was considered c adequate. A two channel transient recorder was available for any selected two channels, if required.
All the transducer and probe amplifiers were mounted as
.j close to the vessel as practically possible in purgt boxes and explosion proof casing so that the cables ]q connecting the transducers and the amplifiers were not excessively long. 'Il. The gases in the sphere before and after combustion l were measured using a gas chromatograph employing a 1 Hydrogen Transfer System (HTS). The details of the chromatograph, its calibration, and sampling technique are given in reference (2). A schematic of the i sampling loop is shown in Figure 4.
I d EXPERIMENTAL PROCEDURE 3
.]
l'l 3.1 PREPARATION CF THE MIITURE 'd First, the vessel was egacuated to a sufficiently j hI low pressure 0.73 lb/in (5 kPa absolute). Next, hydrogen was introduced to the appropriate partial pressure, followed by the introduction of steam ! DJ and air to their partial pressures. The gases
] were further mixed by turning on the fans for about 30 seconds prior to the initiation of any
.}
i test.
. 32 SAMPLING
!)i Before any sampling was initiated at least two calibration mixtures were run through the gas
}'
j chromategraph (GC) several times to ensure the j
- proper performance of the GC. Only when the GC measurements were repeatable, was the sampling i loop activated. The sampling lines run from the
, I sphere to the control room and are steam trace heated all the way to the injection port. f a !] '1 t
.-w* * .%e =-- a . . = - = e -
e .*e+.. . = * = = = . . = > . > - - = = . . . . . , . . p J
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t . 1 w H 3 The sampling line was thoroughly flushed by the
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mixture in the sphere for at least 5 minutes to ensure that the sample passing through the GC was
'. the same as that in the sphere. Two samples were lj normally taken and, if the two GC measurements ] agreed with each other and also with the amount of j hydrogen introduced by the partial pressure method M within the limits of accuracy, it was assumed that j the constituents were in the right amount to carry out the test. The same procedure was repeated for J l sampling the ccabustion products. The products E) were mixed by turning on the fans betere sampling. .j Table 3 shows the precision of the gas chromatograph. The accuracy shown represent the upper limits. However, the measurements tended to ? be much more accurate than what the numbers ] indicate. For example, a calibration mixture with j 9.62% hydrogen was measured by the partial l
pressure method by the GC within +0.2%.
.i f 33 TURBULENT COMBUSTION EXPERIMENTS In this case the fans were turned on for a short .! time ( 1 minute) before ignition and were kept operating during the test. Though the fan speed can be varied, the present series of experiments j have been done at a constant fan speed of about
'j 1500 rpm. Measurements of the turbulence created by the fan I have been made in the open atmosphere simulating
- if conditions prototypic of those in the sphere. The results are shown in Figure 3. The turbulent intensities which can be represented by the root j mean square of the difference between the local velocity squared and the mean velocity squared indicate the degree of local fluctuations in the l* velocity components at that particular location.
.I For instance, at a location ten inches away from
] the fan in the axial direction and ::ero inches i away frem the central axis, the RMS velocity is j about 9 5 feet per second, whereas at the sa=e mj axial distance, but at a radial location four
, inches away, the RMS velocity increases to 10.5 1 feet per second,.which indicates an increase in 4 'he degree of turbulence of the second location.
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q n.. H y 4 h j 4 RESULTS AND DISCUSSIONS i 4.1 CCMBUSTICN AT LCW CCNCENTRATIONS 'D Combustion of hydrogen at low concentrations of
.] around 5% hydrogen by volume is characteri::ed by low burning velocities and a low degree of burn ))
29 completeness. Only about 20% of hydrogen is burned. Figure 5 shows the pressure time history
? for a 5% H 7 in air and steam-air mixtures. In In this ca5e, it appears that combustion is mi -. dominated by buoyancy effects. The fireball 'i ;
initiated at the bottom moves upward at a speed greater than the burning velocities of the mixture ' ' , and no downward propagation is possible. Thus for low initit hydrogen concentrations only a small ~U fraction is burned. Larger concentrations result in correspondingly increased amounts of hydrogen l burned and higher peak pressures. Once the
.) fireball reaches the top, it gets quenched and the pressure in the system decays.
4
; The middle curve of Figure 5 shows the pressure time history of 5% hydrogen with 15% steam added, l The behavior seems to be similar to the dry case
.1 except that the peak pressure in the system is 1 lower. The extent of ccmbustion is virtually the
-h same and the reduced pressure can be attributed to the increased heat capacity of the mixture due to
'd the presence of steam. This results in reduced flame temperatures and thus in reduced peak *
* .] e pressures. The behavior of a 30% steam case is
.l similar to that of a 15%.
d
- .} 4.2 COMBUSTICN AT RELATIVELY HIGH H, CONCENTRATIONS The extent of ccmbustion at higher hydrogen concentrations, around 3% by volume, is r characteri
- :ed by 100% burning. The pressure peaks
,1 are much higher than the 5% tests depicted in 4 Figure 5 as can be expected. Figure 6 shows ij combustion at 8% H,. Addition of 15% steam has y not altered the shape of the curve very much. The 1 reduction in peak pressure, as explained earlier, is due to increased heat capacity of the mixture t
'(' yielding lower flame temperatures. Combustion in
'j both dry and 155 steam case resulted in 100%
! hydrogen consumption.
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4 W 9 The bottom curve of Figure 6 is for 30% steam 3 addition. In this case only about 38% H i burned and the peak pressure is about 25$ was that of d the fully burned case. Larger quantities of steam
# appear to reduce the burning velocity of the
, mixture by decreasing the flame temperature and increasing the radiation loss from flame to steam.
-?p( As the burning velocity is reduced, the combustion is again governed by buoyancy effects and downward
.} flame propagation is negligible.
.I fj These findings agree with the findings of Liu et al (3) that moderate (0-15%) steam additions do
]'/.q not affect significantly the degree of combustion for bottom ignition.
H 43 EFFECT OF TURBULENCE t l
,f It has been well established that turbulence h enhances the rate and degree of combustion.
,.{
. 3ecent investigations of Abdel-Gayed et al (4) have shown that turbulence effects are large even
'g for hydrogen. Preliminary results from these
,,j tests appear to confirm their conclusion. This is 1 illustrated in Figure 7 by plotting pressure as a
- 4 -
function of time for the combustion of 5.5%
;f hydrogen-air mixture with and without fan. The dashed curve is for the quiescent mixture. The degree of burn is only 26%, showing the dominance .1 of buoyancy. The corresponding pressure rise is 3 only a small fraction of the calculated adiabatic
l pressure rise. '4 hen turbulence is produced by {.l turning on the fans, the rate of combustion is increased drastically and nearly 33% of the ! ,' . l hydrogen initially present is burned. The peak ?.J l 3 pressure observed is close to the adiabatic j pressure expected for 83% burn. The peak pressure d seasured is 15.2 psi (105 kPa) and the pressure l J calculated for adiabatic burning is 18.6 psi (129 l kPa). The adiabatic pressure rise is 6.1 psi (42
,d kPa) with 26% burn and the =easured is about 3 5 l ;j psi (24 kPa).
*i
. .y A further comparison of combustion with and without turbulence is shown in Figure 9 which is l ,Tj 'l for 7% hydrogen. Data for both 7% and 85 (figure 9A) hydrogen cases show complete com*)ustion with l "j} or without fan turbulence. For bottom ignitien seven percent hydregen with quiescent burning
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& 6 Mi I appears to be the minimum goncentrgtion for d complete combustion at 212 F (100 C). All other
- #j concentrations above 7% result in complete a burning. This value is lower than the 8.5%
hyd5 8'" li=1t f " ' "plete combustion at 86 F j]N (30 C). Increase in initial temperature results in an apparent shift in the downward propagation J ,} limit, thus allowing more complete combustion. A,- 1 Figure 10 is a summary of several tests with and o without turculence. The mixtures were ignited dl either at the top or at the bottom as shown.
;{ For cases with the fan in operation, data
']%
. - consistenty revealed more complete combustion and a noteable increase in combustion peak pressure.
dEI The lowest concentration at which the downward y i propagation could be achieved in a quiescent mixture was observed to be 8.5% hydrogen for top ignition.
.j
% . 't EFFECT OF TURBULENCE WITH STEAM ADDITION g
1
; Figure 11 shcws the effect of added steam when
! turbulence is present. Norsally, 30% steam would l exhibit limiting effects on combustion of the mixture when no turbulence is present (see figures
.i 5 and 6) But as can be seen from figure 11, its
.I effect on combustion in the presence of turbulence l 13 minimal. The peak pressure with steam is -
reduced due tc the increased heat capacity of the 1l mixture. j Steam and turbulence have ccmpeting effects on l'-i combustion; whereas the addition of steam tends to !:j , reduce the rate and degree of ecmbustion, turbulence promotes rapid and more complete combustion.
.i 4.5 EFFECT OF HYDROGEN CONCENTRATIONS WITH TURBULENCE i .I
! .: As the hydrogen concentration is increased from llij 5.5% to 8% cembustion progresses from a partially ! burned to a fully burned situation. The rate of combustion also appears to increase with d concentration.
.I 1
J; Figure 12 presents the resulting pressure rise as 1 a function of time for various hydrc6en
; concentrations with turbulence. It can be noted I that as the concentration is increased, the time i.
- ' to reach maximum pressure is shortened.
.a l ^!
mM
- _ _ _N[ - J- . 4 w.' ._ ~ . --~ . _ e..,. r -- u.4c--- w .. .. ~ ~ . - - .;J d
s
& 4 7-5 Though most of the results presented here are for
& bottom ignition, it is expected that similar
, arguments hold true for central ignition.
d 4.6 EFFECT OF STEAM ADDITION AND TURBULENCE ON fj COMBUSTION WITH CENTRAL IGNITION
'j eigure 13 shows the relative effects of steam and b I turbulence on the rate of burning. At 7% . hydrogen in air the pressure rise at first is slow indicating that the fireball is moving upwards.
I' When it reaches the top, the downward propagation if starts and the entire combustion occurs in about lJ 12 seconds. Hydrogen was nearly fully burned. I Addition of 15% steam to such a mixture almost
. completely suppressed combustion. The pressure 1 rise was trivial indicating that only very little
'i hydrogen was burned. Gas chromatography
.q measurements showed that less than 0 5% hydrogen
. was consumed. The apparent difference in combustion behavior between what is shown on t figure 13 and figure 5 can be ascribed to
' principally a hydrogen concentration difference
] and possibly the difference in igniter location.
'l
}
The effect of steam disappeared once the fans were
,] turned on indicative of the ability to promote q combustion by turbulence.
] 4.7 EFFECT OF IGNITOR LOCATICN
, at !I Ignitor location affects the degree and rate of
? burn significantly in lean quiescent mixtures.
l This is illustrated in Figures 14 and 15. Figure
)l 14 shows the difference between central and bottom l ,3 ignition with 8.5% hydrogen at room tgmperature
- t and Figure 15 with 7% hydrogen at 100 C. It is I
i clear from the figures that bottom ignition
- .j results in faster combustion at these l j concentrations. This is in contrast to combustion j at hydrogen concentrations in excess of 10% where l.*1 central ignition will exhibit faster combustion than bottom ignition due to the diminishing l
- l effects of buoyancy. For a spherical vessel, with l
'I central ignition the flame will propogate in all directions over a distance of the radius of the shere; whereas for bottom ignition at 10% hydrogen l
,q the flame will propogate over twice the distance j of the radius.
Li l [ , a I
- Mdit. =x . n . 1.~ v ~.t a... ,.T .i : . m ,s. u, . : .:i:.. v.x. l, . -, w.s ~. , .. .. . ... . .; : :. . + ~ s .. .:. .?..q 4
4 Q
!d 3 3 y- 4.8 TEMPERATURE EFFECTS ON FLAMMABILITY LIMITS 1
s Though the purpose of the present series of 9 experiments has not been one of establishing the (' limits af propagation, it does in a way shed some
$ light on the process that must be taking place.
A Figure 16 shows the combustion peak pressures
'T plotted against hydrogen concentration. quiescent mixtures, the pressure rise is abrupt above about 8% hydrogen suggesting that the nature of flame propagation or combustion has changed. Agreement -4. between the present data and the data of Furno et al (5) is good.
Figure 17 is similar to Figure 16 except that it k is drawn for bottom ignition. Here also the
- threshold concentration is around 8% hydrogen.
- This can be compared with Figure 10. The shift to the left of threshold concentration at elevated f temperature is obvious. A test was conducted to establish if indeed the downward propagation limit has shifted to 75. A mixture containing 7%
7 hydrogen was ignited at the top. The sixture j failed to ignite even after several attempts under
'l'. quiescent conditions. However, the sixture could be ignited down to 5 5% when fans were turned on.
g Using the information provided in references (6)
. .; and (7) and assuming that the f1:mmability limit i for downward propagation as 95, the estimatedg
,} vabe for the downward limit at 100 C is about
.I 8.5% hydrogen agreeing with present work. The
*] downward propagation in the sphere experiments i when ignited at the center or bottom =ay not i
i necessarily be related to the propagation limit. The propagation under these conditions may be due to some turbulence or circulation currents set up ,J l by the moving flame ball. 9 Figure 18 shows that combustion is possible even
}l at 5 7% when turbulence is present. From these it a
j could be inferred that the absolute limit of 2 propagation is the limit for upward propagation.
..f
- 5. CONCLUSIONS N
3 The following conclusions can be made from the present investigations.
-l
- 1. For small quantities of steam addition, the nature
, and degree of ecmbustion is not affected very =uch
- i. ,
with bottem ignition. Only at higher stea:
, i concentrations, around 30% or above would steam
\
t 1
. .. - ~ . -. .
. - . . _ . ~ . . . . . . . . -.
a.' .. .< . w-- _L. h . w -- --- a : r Q ' . J .w , n .,. . . . - . . . . . . . . ..v.. -. .~ a ..
- 3. 5
}il }
h 51 begin to have significant effects on combustion. 3; 5H 2. Turbulence increases the rate and degree of burn in 5 g . almost all cases. i 3 Bottom ignition results in highest degree of burn 7 and is more effective in establishing a flame even i at very low hydrogen concentrations, with or
.' without fans.
i
- 4. Central ignition ccmbustion is more susceptible to
' l the influence of steam in lean mixtures than bottom
' ignition combustion. ,
. 5. For low steam concentrations, around 155, steam effects if any are not significant in the presence f'.]. of turbulence.
l1 -
^;
l I
- ,1 REFERENCES l 1. Liu, D. D. S. et al, " Development of Instrument for Combustion 9 Studies: Part I, Test of Ionization Probes for CTF Applications",
j ~4NRE-512-1, (1981). I 11 2. Howe, P. T. and Myers, M. E. , "On-Line Gas Analysis for the ,q Containment Test Facility", WNRE Report, WNRE-217. 1
] 3 Liu, D. D. S. et al, ' Canadian Hydrogen Combustion Studies Related
.t to Nuclear Reactor Safety Assessment", paper 80-33, Western States 1 Section/The Combustion Institute, 1980, 1980 Fall Meeting at Los
-j Angeles, Calif, Oct. 20-21 (1980).
7 4 Abdel-Gayed, R. G. and 3radley, D., Sixteenth Combustion
. (International) Symposium pp. 1725-1735, (1976).
1 il
'I
- 5. Furno, A. L. et al, "Some Observations of Near L1=it Flames", 13th Combustion Symposium, pp. 593-599, (1971).
t 5
.j 6. Shapiro, Z. M. et al, " Hydrogen Flammability Data and Application to PWR Loss-of-Coolant Accident", Bottis Plant, Pittsburgh, j] WAPD-SC-545, 1957. ~jl 7. Edmundson, H and Heap, M. P., "The Burning 7elocity of f Hydrogen-Air Flames", Combustion and Flame, 16, 161 (1971).
J E71351.29 t e a
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s . Figure -8
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s . s f EFFECT OF FAN TURBULANCE ON H 2 COMBUSTION ' IE '
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RELATIVE EFFECTS OF STE AM AND TURBULENCE l ;ju re- 13
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.i l i i 4 APPENDIX A.3 HYDROGEN COMBUSTION CONDUCTED BY AECL WHITESHELL 4
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.a 5
'd COMBUSTION BEHAVIOR STUDY OF GLOW PLUG IGNITOR
..d . 'M IN HYDROGEN-AIR-STEAM MIXTURES
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,I' '. J i: i l
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? .l, l INTERIM PROJECT REPORT
.J December 1981
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' 'l Prepared by:
. :- d K. K. Shiu, American Electric Power
.I F. G. Hudson, Duke Power Company J. J. Wilder, Tennessee 7 alley Authority
)
.}
a ' Project conducted by:
- Whiteshell Nuclear Research Establishmer.'.
'I 1
l
- s Project Sponsors:
I gj American Electric Power Service Corporation 8 Atomic Energy of Canada Limited
'l Duke Power Company
.i Electric Power Research Institute
.j Ontario Hydro 1 Tennessee Valley Authority 1
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$ TABLE OF CONTENTS
;'D li
= 1.0 Introduction C
k . 2.0 Experieental Setup 3 ie il-30 I2strumentation
,jl 11 Pre-sure Measurements . s~
- l' 32 Flame Arrival Detection
-=
{j, 33 chemical Analyais
- i .)
4.0 Ecperimental Results
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1.0 INTRODUCTION
O One of the research efforts undertaken at '4hiteshell Nuclear Research
.):
Establishment pertains to investigating the effectiveness of the glow plug igniter in a more detailed and comprehensive manner and of other
.'f potential igniter types. This report presents the GM AC Model 7G glow ] . plug igniter test results observed to date.
l h -
,d ,j 2.0 EXPERIMENTAL SETUP A 17-litre quasi-spherical vessel with a pressure rating of 600 lb/in 'i j (4 MPa) was used in this study. Figure 1 shows schematically the vessel and the components used in these experiments. The vessel has a l.] } pair of 3 9-in. (100 mm) diameter viewports on a horizontal axis for flacu visualization and photography.
i
't i
q j There are two 3/4-in. (1.9 cm) pipes welded to one of the convex
'I walls. Cne of these is used for gas injection and sampling. A branch 'l Trom this pipe is connected to a strain gauge (Data Instruments,
- t
,'} Incorporated Model RS-101) for measuring the static pressure before q
.; and after ignition tests. The other 3/4-inch pipe is not used in s
.- hese experiments and was capped. The other convex wall has a 600 b
'I 'b/in2 (4 MPa) safety rupture disk.
i I 0
.l Figure 2 shows a schematic of the gas supply system. All lines are i
standard 1/4-in. (6 mm) stainless steel tubings. Steam is provided
.i from distilled water in a 100 m1 flask heated by a hot water bath.
.)
'. J The vessel and gas piping are electrically trace heated to 176-212 7 f (80-100 C) to prevent steam condensation inside. Eight
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i 7 - l [ chromel-alumel (type K) thermocouples attached to the outside vessel and pipe surfaces are used to monitor this temperature.
, 30 INSTRUMENTATION a
1*{ The in.strumentation is shown in figure 1, and the specific components N D described below are numbered in the figure for clarity. N
'Q
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- ] An ionization gap probe (No. 1) coated with sodium bicarbonate
. .. j .
. (NaHC0 ) is supported by a 1/8 in. (3 mm) steel rod (No. 2) at about 3 ~ '.l' j 1 58 in. (4 cm) below the upper wall for detecting flame arrival.
j The support rod is mounted on the bottom flange.
]
, ;.1 4 1
; A similar rod (No. 2A) screwed to a strong magnet (No. 7) is used to 1
> support the following: a .010 in. sheathed K-type thermocouple (No.
.j j 3) to measure gas temperature, an ionization gap probe (No. 4) to
'1
-[] determine ignition and the GM AC Model 7G glow plug (No. 5). The ion
. probe and thermocouple are located approximately .32 in. (8 mm) above
-j the glow plug and at an angle of 45 away from the central axis. Two
.j type K thermocouples (No. 3A) have been spot welded to the bottom ti
' "]j surface of the glow plug to determine its temperature history. As t
; seen from Figure 3, this assembly is bcund with high temperature tape and inserted into the vessel such that the glow plug is horizontal, cj about .39 in. (1 cm) above the lower edge of the viewport to permit -l j flame photography.
I u Si
-1
. . , A small fan (No. 6) with aluminum blades 2.76-in diameter (70 =m)
*{ .
ounted en a magnet (No. 7) is available for forced convective flew i j experiments. All of the electrical wires (No. 8) penetrate the flange i
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via Conax fittings (No. 9). A Kistler 603B1 piezoelectric transducer ~ '4 (No.10) is flush-mounted on the flange to =easure the pressure transients. A slow response 1/16" type K thermoccuple (not shown in b] s] ' figure 1) located near the lower vessel wall level is used to measure initial and final gas temperatures. il 4 [l Although the two thermocouples, which are spot welded to the bottom [ surface of the glow plug, are similar, they do show a somewhat different response time, as shown in figures 4 and 5 The higher of i the two glow plug temperatures is consistently used for glow plug A surface temperature evaluations. 1
..'1 The therr.occuple for gas temperature is clearly too slow to properly determins the peak temperature, but it does provide clear indication
~l* of ignition. Maximum gas temperature is more reliably obtained from
. 1
] the application of the ideal gas law based on the more accurate a pressure measurement of the strain gauge pressure tranducers, i
.i 31 Pressure Measurements k
-j A Data Instrument, Incorporated, Model 101-25 strain gauge transducer 1
,] is used to measure the initial partial pressures and the final 1
Y pressure. This transducer is connected to a Data Instrument Model
.j (RS-100) digital readout system calibrated to better than2 02 . Ib/in2 (0.133 kPa). .)1 '.)
- l+ 2 1
Since the strain gauge transducer will record up to 25 lb/in absolute J. (170 kPa), it also serves as added confirmation of pressure history
- ~
measurement. a
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'd d For fast pressure transients, a Kistler 60331 piezoelectric pressure
~ hj transducer, flush-mounted on the flange and connected through a i Kistler 504E charge amplifier to the recorder, is used for pressure measurements.
. -{
.d
- .]
e 3.2 Flame Arrival Detection
.d ^
The two ionization gap probes, used to detect flame arrival, are . connected directly to the recorder. Although in principle they can be j used for flame speed determination, the slow recorder speed limited 1 their use to confirming combustion. A i The gap probes are operated at 200V de, and each probe has a single RC l coupling circuit. Since hydrogen flames produce few ions, the probes are coated with sodium bicarbonate to provide detectable signals. _} 1
- )
j The central probe tends to pick up 60 H: noise more readily than the
j upper probe as a result of its close location to the 60 H: power
? source for the glow plug. However, the ccmbustion wave signals were d.i
?
~i Still strong enough even for lean mixtures to determine flame arrival.
ti 1 3 3 chemical Analysis g d Partial pressure data have been used as the principle method in 3
-fj determinin6 initial concentrations due to its reliability and I consistency. Also, when available, the mass spectremeter.has been b
,') used to measure gas concentrations before and after ignition. Like I J most commercial systems, this device does not measure steam concentration. Nonetheless, the extent of ccmbustion can be readily
'e
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'h evaluated by comparing the hydrogen / nitrogen ratios before and after .]
j ignition. ., 4
%~
1
'i -h 4.0 EXPERIMENTAL RESULTS T
Most tests were performed with quiescent hydro 6en-air-steam mixtures 2, ( using a 14V ac supply to the glow plug. A limited number of tests
'* :1 have also been done with 127 ac supply and with the fan on. .I' ..a Typical measureinents made in each test are presented in figure 6. ,
They include the two-time traces of the ionization probes, glow plug surface temperature, and the pressure data. The extent of reaction can be estimated from three different
, measurements: (a) mass spectrometry analyses before and after 1
reaction, (b) static pressure :neasurements before and after ignition,
.i and (c) peak pressure :neasurements. From the mass spectrometer 'I measurements, the extent of reaction is defined as follows:
j i extent of reaction = 1 - (H 2/N2) ti"*1 t (H /N ) i"it181
] 2 2 1
- The estimate of extent of reaction from static pressure is based on f the fact tnat there are two moles of gas after combustion for every l
j three = oles of fuel and oxidizer reacted. The following for=ula for I fj the extent of reaction can be derived: Il extent of reaction 2(? g 1g/? final} ~ 2 * (2 initial# final) j 'a'here gH is the volume faction of hydrogen prior to ecebustion. I
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, .l J Q , 3 3ecause the differences in pressure are small, the calculated results are very sensitive to the measured pressures.
~.< ~
e igure 7 summarises the results of the experiments. Ignition 3 criterion is defined as detection of flame arrival by the upper
}1 ionization probe. For marginal ignition, the pressure and temperature }
rise were small and often barely recorded. For a pressure rise less than 1.8 lb/in (12 kPa) but with a detection of flame arrival by the upper ionisation, ignition is defined as marginal. It can be seen that the ignition region limit is similar to flammability limit y curves. 1
..l Figure 7 depicts the ignition limits of hydrogen air mixtures in
}
j various steam concentrations. Majority of the data points are for
-l static mixtures; turbulent mixture tests are still being conducted.
.)
'l
'j-.
. The range of steam concentration investigated varies frem 0 to about
! 60 percent. At about 55-percent steam concentration, only marginal ignition was observed for hydrogen mixture of 20 percent. The initial ,
N preJsure for these tests is essentially' 3tmospheric, and the maximum i '1 pressure observed is about 54.7 lb/in g (372 kPa).
..i.; .)
N The surface temperature of the ignitor at which ignition occurred was I >j ^ recordad for each test. The results are presented in figure 8. It is 1 I cbvious that as the steam concentration increases, so does the 1
! ignition surface temperature. The maximum temperature observed is
't l about 1560*? (350 C).
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THE SCHEMATICS OF THE INSTRUMENTATION FOR THE J sy IGNITION EFFICIENCY TEST USING A GM AC NO. 7 GLOW PLUG IN A 17-LITRE VESSEL. FIGURE 1
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W o $ ,- ~ GLOW PLUG SURFACE 1<4R " _ TEMPERATURE cm DN t ! f I
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l__ 2 STRAIN GAGE
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] ilME AFTER TURNING ON THE POWER / SECONDS I
1
+ FIGURE 6 1
l OBSERVED TRANSIENTS IN Tl-lE IGNITER EFFICIENCY TEST. A GM AC NO. T CLOW PLUG OPERATED AT 14 VAC IN A 12.G%- , j HYDROGEN / 20.5%-STEAM MIXTURE IN A 17-LITRE VESSEL.
. . . _. ~ _._ -~_ ._w.:
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- j fi2 IGNITED MARGINALLY NO GAS E
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e 2 w
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. PROPOSED LIMITS FOR TURBULENT M, -
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i USING A GM AC MODEL NO.7 THERMAL GLOW PLUG LOCATED
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" " * " ' " * * * * * ' ' ' " ~ * * * ~ ~
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Y:' . t APPENDIX A.!l HYDROGEN CONTROL STUDIES C0tGUCTED BY ACUREX, INCORPORATED
~ - - . . ,~
.7 .
_ _ _ .. : . . ~ . . -~ 4 t .; ll' \; li \?u ie~ l>, f: I w. [ EFFECT OF IGNITOR LOCATION ANO WATER FOGS ON HYOROGEN COM8USTION WITHIN AN ENCLOSED COMPARTMENT a PROJECT REPORT December, 1981 p" Prepared by:
~
F. G. Hudson, Duke Power Compcny J+
~
K. K. Shiu, American Electric Power i; R. C. Torok, Acurex Corporation J. J. Wilder, Tennessee Valley Authority Project Conducted by:
}1 Acurex Corporation 485 Clyde Avenue Mountain View, California
.} Project Spcnnors:
American Electric Power Service Corp. Duke Power Company Electric Power Research Institute Tennessee Valley Authority j
}
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ia 1 c TABLE OF CONTENTS 1-1- s
- 1. 0 Introduction
- 2. 0 Test Facility 3.0 Test Matrix nd Procedures 4.0 Test Results
- 5. 0 Conclusions Appendix Gas Chromatography Analysis
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d' i:!' y l Tl x ; a q q4 r lj' Section 1 Introduction t' Approximateiy ten hours into the accident at Three Mile Island, a hydrogen burn occurred inside the containment. Although this burn posed no real threat to , t.he TMI containment, it did create interest in hydrogen combustion and its
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effects on containment structures. The operating license applications for McGuire and Sequoyah Nuclear Stations contributed to the growtt. of this interest if into a major safety concern, especially for ice condenser containments. The individual and joint activities of the three utilities owning ice condenser stations (American Electric Power, Duke Power Company, and the Tennessee Valley
;; Authority) are well documented in various licensing submittals or licensing i
i proceedings and will not be repeated here. However, when the three utilities i decided to install a distributed ignition system as a hydrogen mitigation s system, the question of ignitor location within a compartment arose. Additionally, concJrrent with the design of a distributed ignition system, several independent
) organizations suggested coupling a water fog system with the distributed ignition system to act as a pressure suppressant during combustion. To investigate
..j the effect of ignitor location on hydrogen combustion within a compartment, the
.] three utilities', in conjunction with the Electric Power Research Institute, con-i tracted with Acurex Corpcration to conduct a series of tests. These tests were conducted at the SRI International Explosives Test Site near Livermore, California.
l Although analyses had shown a pressure suppressant was not necessary fra ice
; condenser containments, the utilities believed that investigating the effect of water fogs on hydrogen combustion could be of some potential interest to the Ri 4
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=i E. I industry. Therefore, an investigation of water fog effects on hydrogen combustion l was added to the Acurex project. This report presents the 'esults of that project. m I
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!b i . i. e .J ' . Section 2 Test Facility 2.1 TEST VESSEL AND MECHANICAL SYSTEMS The test vessel selected for this project has a volume of approximately 630 i ft 3. Vessel dimensions are: internal diameter - 7 ft., overall height - 21 -il;' ft., and " barrel" height - 17 ft. Auxiliary mechanical systems provide the ability to: 1) injact hydrogen or a hydrogen / steam mixture into the lower portion of the test vessel, 2) supply a water spray or microfog from the upper
} portion of the test vessel, 3) obtain pre-test and post-test vessel atmosphere samples, and 4) provide a means of premixing the vessel atmosphere for quiescent tests. Additionally, the capability to ignite the vessel atmosphere from the top, middle or bottom of the vessel was provided. A schematic of the test vessel and its auxiliary mechanical systems is presented in Figure 2-1.
A propane-fueled boiler supplied steam for the facility. This steam served as I a parameter for several tests, as well as to preheat the test vessel to the desired temperature. The steam flowrate was monitored with an annular flow
.; sensor and a differential pressure gauge. When steam was not required as a i
8 test parameter 7 the boiler was isolated from the test vessel after preheating
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':i was completed. Bottled hydrogen served as the hydrogen source for the test
;j vessel. The hydrogen flowrate was monitored with a rotameter and controlled with a control valve.
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s_._.. ...:,;.c _. .s._._ .__.. u .~ .n f A three horsepower electric motor and gear pump supplied water to the test vessel spray nozzles. A bypass loop was included to control the flowrate. Utilizing a closed loop spray system, i.e., recirculating the spray water, avoided the potential problems associated with accumulating large volumes of
.j water within the vessel. Fcr the Phase 1 tests, a single Sprayco 1713 nozzle, ;i ~'
15 gpm flowrate, was mounted at the top of the test vessel. A manifold containing nine Sprayco 2163-7604 pinjet nozzles was mounted at the top of the test vessel for the Phase 2 tests. Depending on the pressure drop across the nozzles, the
, total spray flowrate for the Phase 2 tests varied from 1.1 to 1.4 gpm. The soray manifold was constructed so as to provide an even spray distribution throughout the test vessel.
An air-operated fan was mounted inside the test vessel to assure a well mixed i vessel atmosphere prior to the quiescent tests. Use of an air-operated fan eliminated the potential of an electrical malfunction resulting in a spurious ignition. The fan's air exhaust was vented outside the test vessel to avoid diluting the vessel atmosphere. i Two 4 inch butterfly valves located at the top and near the bottom of the test
.l vessel allowed the vessel to be purged following the completion of each test.
1 11 A squirrel-cage' blower attached to the lower butterfly valve provided the d a motive force for purging the vessel. The vessel contents were vented to the
! atmosphere through the upper butterfly valve. The vessel was not vented until' 1 'q post-test samples were obtained.
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;j Vessel atmosphere sample taps were located near the top and near the bottom of
'l the test vessel. A remotely operated solenoid valve isolated each of the two l
, sample lines from the test vessel. When a solenoid valve was open, the vessel -
atmosphere sample was pumped through a cold trap to remove water. The sample then passed through a silica gel trap to remove.any remainir.g moisture. The sample then flowed through a gas meter into a glass sample bottle. A sample was extracted from the sample bottle by a syringe and injected into a gas chromatograph. (A detailed discussion of the gas analysis methodology is presented in Appendix A). J Two ignitor assemblies supplied by Duke Power Company were mounted inside tns test vessel. The ignitors were located on the vessel centerline at either the j top, middle or near the bottom of the test vessel. Only two ignitor locations were occupied at one time. The top ignitor location was not used during the J Phase 1 tests requiring sprays or during any of the Phase 2 tests = since an i i 4 ignitor assembly located at the top effectively created a significant spray / fog maldistribution within the test vessel.
- 2. 2 INSTRUMENTATION .
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.] The test vessef was instrumented to provide the following information: vessel atmosphere temperature, vessel wall temperature, flame front propagation, and 9
j vessel pressure. Three mil Type K thermocouples were used to measure temperatures 4 l and detect flame front propagation. Strain gauge pressure transducers and i J piezoelectric pressure transducers were used to measure vessel pressures. A 1. schematic of the test vessel instrumentation is presented in Figure 2-2. I a N. .
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'J As just mentioned, 3 mil thermocouples were used to measure temperatures and detect flame front propagation. Male Type K thermocouple jacks were used as attachment points for the 3 mil thermocouple junctions to increase the robust-
; ness of the thermocouple. The junctions were located between the jacks with the leads attached directly to the jacks. Vessel. wall temperature thermo-couples were welded directly to the vessel wall.
< To determine the flame front propagation pattern within the vessel, a special electronic circuit was developed. This circuit used a high input impedance 8
.] operational amplifier com?arator to detect the temperature rise in the 3 . ail
- s Type K thermocouples located within the vessel. A schematic diagram of the
'q flame front detector circuit is shown in Figure 2-3. Five circuits were used, each circuit monitoring seven thermocouples located in a vertical array within the vessel. The 5 x 7 grid was located vertically on a plane formed by the diameter and centerline of the test vessel as shown in Figure 2-2.
When one of the thermocouples in the grid was exposed to the flame front, the thermocouple output voltage would rise and trigger the comparator. This,-in turn, placed a signal at one input point of the digital-to-analog converter.
-. The output from the OAC was then recorded. Since the input signals from the
_j thermocouples efould be considerad as binary bits, every voltage that was 1 generated by the DAC corresponded to a discrete combination of hot thermocouples. Thus, by comparing the output voltage against time, the instant that the flame front arrived at each location could be determined, and a map derived chowing flame front propagation.
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a. I "i Two types of pressure transducers were used. Bell and Howell-CEC Model 1000
, strain gauge pressure transducers were used for static and slow response conditions. These were powered by CEC 1-183 strain gauge signal conditioners located within a CEC 1-080 power supply chassis. To record high frequency
. transient pressure pulses, PCB Piezoelectronics Model 111A24 piezoelectric-
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pressure transducers were used. These transducers were powered by a Model 484810 power supply, t s v Two recording systems were used for data acquisition. A twenty eight channel FM tape recorder, EMI Modal 7000C, was used to record all potentially fast
, response data. Frequency response of the unit was 10kHz or greater. An Autadata 9 datalogger recorded relatively slow response signals and served as a backup to the FM tape recorder.
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L; Section 3 Test Matrix and-Procedures u 3.1 ' TEST MATRIX
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,d- The test program was designed to investigate the effects of ignitor location and water fogs / sprays on hydrogen combustion. Test parameters were selected 4
based on degraded core analyses conducted by American Electric Power, Duke 3.e
.7 Power Company, and TVA. Flowrates for steam and hydrogen were scaled by the
}j ratio of test vessel volume to the combined lower compartment and deadended
'i J compartment volumes of an ice condenser containment. These scaled flowrates
. were derived from the average steam and maximum hydrogen release rates dur-Ing the hydrogen generation portion of an 5 2 0 accident sequence. Containment resoonse analyses conducted by the aforementioned utilities indicated that 160 F i: -
was a maximum atmospheric temperature that would be encountered in the lower
'!I and deaden;est compartments at the onset of hydrogen generation. Hydrogen or i
, hydrogen / steam mix +.ures were iniected into the lower portion of the test vessel t
-) since many subcompartments within an ice condenser containment are accessed
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O:l' h: l! L lj' Spray nozzle fTowrates were determined by the desired mean droplet diameter. The Sprayco 1713 spray nozzle, a model used in containment spray systems, was Ih; opera.ed at a AP of 40 psi. This provided a flowrate of 15 gpm and is the (' 'lj designed operating condition in a containment spray application. Vendor r i
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flowrate is 200p. Based on studies conducted by Factory Ms J-l Research l, 3-r e I
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] Corporation, the Sprayco 2163-7604 nozzle was selected for use in the water fog tests. Measurements taken at Factory Mutual Research Corporation 1 indicated that wnen operated at aP's of 20 psi and 30 psi- the resulting number mean dreplet diameters were lip and 8p, respectively. The total fog flowrates from the test vessel's nine nozzle manifold were 1.1 gpm and 1.4 gpm, respectively.
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'y Tests outlined in Table 3-1 were intended to investigate the effect of ignitor
-c location on combustion. Both hydrogen and hydrogen / steam mixtures were injected to account for the potential variation in the transient conditions within an ice condenser containment. Tests with sprays were included to account for the presence of subcompartment sprays in some containment designs. As mentioned
' il earlier, the steam and hydrogen flowrates of 2.1 and-0.035 lbm/ min were based , '.) on transient analyses. Tests 1.6 and 1.7 were conducted with the hydrogen flowrate arbitrarily increased by a factor of thrae. Test 1.11 was conducted j to coserve the effect of a lower preneat on combustion characteristics. The l
duration of tests was determined by the time required to cbtain the same relative hydrogen mass injected in the test vessel as is calculated in the previously ment:oned degraded core analyses. All tests were conducted with the test j vessel atmosphere initially saturated.
<j 12alosh, Robert G., " Water Fog Inerting of Hydrogen Air Mixtures," Factory Mutual Research Corporation, September, 1981.
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The water fog test matrix is presented in Table 3-2. Quiescent tests were conducted as a basis of comparison to observea results of tne dynamic tests.
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The basis for all remaining test parameters was discussed above.
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- 3. 2 TEST PROCEDURES 1
Two types of tests were conducted: quiescent and dynamic. A known amount of
, hydrogen was injected into the test vessel for the quiescent test prior to
[ energizing the ignitor assembly. The dynamic tests consisted of injecting b hydrogen or hydrogen / steam into the vessel with the ignitor assembly pre energized. For all tests, the test vessel was pre-heated to the desired temperature and the instrumentation and data acquisition system was checked and calibrated. l After the completion of each test, the test vessel fan was turned on and a post-test sample obtained. Subsequently, the test vessel was purged.
.1 Test procedures varied slightly for the quiescent and dynamic tests. For the
'N quiescent tests, the vessel fan was turned on after completing the pre-test activities mentioned above. A known amount of hydrogen was injected into the i vessel and a pre-test sample was obtained. The vessel fan was then tur1ed off l ':l ' and, if required, vessel sprays actuated. At this point, the data acquisition
.; system and the ignitor assembly were energized. For the dynamic tests, the i '. t i ignitor was energized after completion of pre-test activities. If necessary, vessel sprays were then actuated. The data acquisition system was energized prior to the initiation of hydrogen injection.
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1ABLE 3-1 - { ;' Ignitor Location Test Matrix ^ ;. Ignitor Ilydrogen Flow (lbm/ min) Steam Flow (lbm/ min) Spray Flow i. Test location 0.035 0.105 2.1 15 gpa l' 1.1 Top X X
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1.8 Center X- X X l ' 1.9 Center X X - 0 g: 1.10 Center X {. 1.11 Bottom X X X lW . Test vessel was preheated to 160*F for all tests except 1.11. Test 1.11 was U performed with 120"f preheat. 1 j.. h' p r. l', f, ,' , t (..* [' . i:
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i TABLE 3-2 U i-Water fog Test Hatrix a ( ,s , flydrogen flydrogen flow (Ibm / min) }~ < r Steam flow (lba/ min) fog Nozzle Pressure (psi) }l' Test #' v/o 0.035 0.105 2.1 20 30 ' I' . 2.1 5.0 '.'- ! 2.2 7.5 i 2.3 10.7 *
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-il [d d Section 4 Test Results p 4.1 DEFLAGRATION CHARACTERISTICS j, Based primarily on p essure and flame front detector data, two distinct types of deflagrations occurred. These deflagrations were termed " discrete" and
" intermittent". A " discrete" deflagration was characterized by a rapid pressure t..
and temperature rise. The duration of the burn appeared to be dependent on the f> fraction of the vessel volume that could support a propagating hydrogen flame.
]..,P- By comparison, an " intermittent" deflagration appeared as repeated burns accompanied by much slower and lower pressure / temperature rises. Observed deflagrations were further categorized as " major" or " minor". A " major" ;) deflagration, whether discrete or intermittent, occurred throughout the test
, ;q 38 vessel. A " minor" deflagration, on the other hand,.was localized in nature. d Pressure and temperature histories typical of a major-discrete deflagration are
. presented in Figure 4-14. " CENTERLINE T1" and " CENTERLINE T4" are centerline s!
.i thermocouples located near the top and bottom of the test vessel. " VESSEL
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'j PRESSURE 2" is a strain gauge pressure transducer located in the lower portion
; of the test vessel. As seen in the figure, the test mixture ignited approxi-mately twenty seconds into the test. The periodic disturbances in the two temperature traces were caused by the datalogger scanning these channels. The flame front detector output for the same test is presented in Figure 4-15. The five data channels correspond to the five vertical columns of transducers shown 1
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Il d j in the inset figure; each channel receiving the output of seven flame detectors. y The size of each step is determined by the comoination of detectors that
'] triggered. A fullscale reading indicates that all seven detectors within a 1
channel have triggered. Of the channel outputs presented in Figure 4-15, only channel 5 was not reading fullscale. The flame front detector data indicated that approxin.ately 95% of the flame front detectors triggei ed. This, therefore, was classified a " major" and " discrete" deflagration. -i Figures 4-5 and 4-6 present temperature, pressure, and flame front detector data typical of major intermittent deflagrations. The flame front detector data in Figure 4-6 indicate that all channels were triggered, signifying that a major deflagration occurred. Temperature data in Figure 4-5 shows a ; harp, but not l extremely large, temperature increase that remained relatively constant for several minutes before starting to slowly decay. This indicates that intermit-tent deflagrations were occurring. Note that near the end of this particular "L test, a major discrete burn occurred.
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,3 flame front detector data presented in Figures 4-21 and 4-22. Flame front 1
} detector data, Figure 4-22, indicate that few flame detectors were triggered
{ during this test. This characterizes a " minor" deflagration. The temperature
; and pressure data in Figure 4-21 show the small and gradual increases characteristic of intermittent burning. Figure 4-3 also provides temperature and pressure
- ] histories indicating minor intermittent deflagrations. Note that near the end I
a of this test, several minor discrete deflagrations occurred. l O%
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4.2 INSTRUMENTATION UNCERTAINTY
,a Test data was primarily test vessel pressure / temperature histories and flame 'j front detector output. Additionally, vessel atmosphere constituents were deter- ]j mined via a gas chromatograph. To properly evaluate the test data, it was A
11 necessary to know the errors associated with the instrumentation used.
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Sources of error in the thermocouple data were: thermocouple material and junction uncertainty, thermocouple amplifier error, test facility offset errors ff due to electrical ground loops, tape recorder input and playback error, analog to digital conversion errors and plotter inaccuracy. Standard Type K thermo-couple error estimates were 2.2*C from 0 to 278 C and 3/4% above 278 C, ANSI
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Standard C96.1. The low temperature range error corresponded to approximately
!3% when peak temperatures were around 100*C. The estimated gain error for each
() of the three signal amplifiers was tl%. Errors associated with the analog to
]I digital conversion and plotter inaccuracies were considered negligible.
Therefore, using the root-mean-square metnod, the total random error for low temperature cases was approximately,
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- s. 4 dl j-l Pressure data were obtained from two strain gauge pressure transducers mounted D1 at the top and near the bottom of the vessel. Althougn data from the piezoelectric pressure transducers were recorded, the observed pressure transients
;. ,: did not warrant use of the piezoelectric instead of the strain gauge pressure transducers. Sources of error in the pressure data were: transducer error,
- g the transducer amplifier errer, and the same tape recorder amolifier errors encountered in the thermocouple data. The manufacturer's estimated error for
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the transducer was .25% of full range. This corresponded to :0.5% of the signal resulting from a large aP, i.e. , a major deflagration, and :2.5% for a small AP. Using the root-mean square method, the total randem error for high aP cases was approximately, i t 4
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l [2.52 12 + 12 + 12]h = 3. 0%. i Calibration and test gas chromatograms were analyzed using the peak height j method. Water vapor corrections were made to convert dry gas sample analyses i
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Uncertainty estimates for the resulting gas constituent volume percentages were based on the repeatability of sample analyses. Normalized mean peak heights
*t i were calculated from the analyses of each test run. The ratio of the largest i deviation from the mean to the mean for each test run was used as an estimate 6'
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with the manufacturer indicated that filament oxidation was hampering performance.
. .n, 4.3 IGNITOR LOCATION TEST SERIES Tests were conducted by varying the ignitor location in three test environments:
hydrogen injection, hydrogen / steam injection, and hydrogen / steam injection with sprays. Two additional test.s were conducted with tne hydrogen flowrate arbitrarily 9 increased by a factor of three. The final test of this. series was conducted with a reduced vessel pre-heat. A summary of the results obtained from this test series is presented in Tables 4-1 and 4-2. l j l Figures 4-2, 4-4, and 4-10 provide the pressure histories from ignitor location n i; tests without steam or spray (tests 1.2, 1.5, and 1.10). At lean hydrogen con-j centrations, flame propagation is only upwards. With this in mind, it was anti-cipated that while localized burning was occurring in the vicinity.of the i top ignitor, the hydrogen ~ concentration would increase throughout the remainder of the vessel.' When the flammability limit for oownward propagation was reached, j a major discrete deflagration would occur. This appeared to be the sequence of 1 { events in test 1.2 with minor intermittent deflagrations beginning at 300 seconds
; followed by a major discrete deflagration at 580 seconds. The maximum pressure j rise was expected to ae smaller for the center ignitor location (test 1.10)
, than the top location because of the increased vessel volume that would be 4
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. - - . . . . . . . . . -.-....n ..u. . - . . . . . - - -
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h exposed to upward propagating flames at lean concentrations. Table 4-1 shows
. 4 l that the pressure rise was lower by approximately a factor of three. Minor l'l ,e intermittent deflagrations began around 220 seconds and continued throughout Il the test. The lowest ignitor location was expected to produce an even milder 1 ,a i pressure rise since a substantial partior, of the vessel would be exposed to f upward propagating flames. However, as Figure 4-4 shows, that was not the
{ case. Apparently, the relative locations of the injection port and the lowest jjug ignitor location precluded the ignitor from igniting hydrogen early in the test.
'l The major discrete deflagration that occurred at 450 seconds indicated that the
..e. L injection flow apparently bypassed the -ignitor until most of the vessel contained
']
,1 a flammable mixture. The resulting deflagration produced a higher pressure rise
! than that attained by the top ignitor for two apparent reasons: 1) The top ignition was preceeded by localized deflagraticns; thus reducing the mass of f
hydrogen within the vessel; 2) Flames propagate slower downward than upwaro; thus allowing more time for heat transfer.
! +
i l Figures 4-1, 4-3, and 4-9 shcw that results from the tests with hydrogen / steam 'al ; injection (tests 1.1, 1.4, 1.9) were similar to those obtained from the hycrogen injection tests. It was anticipated that the hydrogen / steam injection tests
- ) would yield milder pressure increases.
; This was due to steam impeding the
~I combustion process as well as acting as a diluent; thus reducing the flame j propagation velocity. This would result in increased heat transfer and decreased temperatures / pressures. Additionally, adding steam increased the injection velocity from approximately 0.7 ft./sec. to 5.7 ft./sec. This was believed to increase mixing within the vessel and thus allow deflagrations to occur at leaner 1
i s
.;. .O.. .
. . . . . . . . . . . .m.. . . . .. ..... . . ~ . ~ . . .
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.' 1 nydrogen concentrations. Table 4-1 indicates that the peak pressures at the
]z three ignitor locations were rt3Ced with steam added to the injection flow.
9
~ .1 The most dramatic :,hange was with the bottom ignitor location. Apparently, the t
l increased mixing provided by the steam flow allowed the lowest ignitor to function as discussed previously. The top ignitor provided the largest pressure
- rise, with the center and bottom ignitors being approximately a factor of three
;! i less.
l
- ( j The addition of a water spray was expected to create some amount of turbulence
-]
.- within the vessel that would enhance mixing and allow combustion to occur at leaner hydrogen concentrations. It was also anticipated that a water spray would act as a dispersed heat sirx; thus further reducing temperatures and
, pressures. Table 4-1 shows that the addition of water spray, tests 1.3 and 1.3, did reduce the maximum pressure. The bottom ignitor yielded only a very slight pressure rise with no corresponding flame front detector activity. However, post-test atmosphere analysis indicated that combustion had occurred. These j deflagrations must have been very localized near the ignitor and apparently relied upon spray induced turculence for a continual supply of lean hydrogen I mixtures. Figure 4-8 shows that the center ignitor provided a series of minor discrete burns. The pressure rise was slightly higher than obtained from the bottom ignitor:' Test vessel design did not allow a spray test to be conducted with the upper ignitor location.
Two tests were conducted with the hydrogen flowrate arbitrarily increased by a' factor of three. One test was conducted with hydr:, gen injection, test 1.7, and the second with hydrogen / steam injection, test 1.6. The bottom ignitor was used
' 1,,
?;, s
. I.
;l s
q.
,j for both tests. Comparing tests 1.7 with 1.5 and 1.6 with 1.4 shows that the h
1 transients were similar to their low thw counterparts, with the exception of
.1 i ignition occurring earlier in the transient. In test 1.7, ignition occurred
. l-
>q slightly earlier than the 150 seccnd ignition expected from a higher flow rate 1
- j (see Figure **.7). It is possible that the increased injection velocity had a i
slight effect on mixing within the vessel. This would allow an ignitable dd mixture to reach the ignitor earlier. This would also explain the slightly d
/ lower pressure rise from test 1.7 since less hydrtgen would be present within y the vessel at ignition. Note that the high flowrate pressure rise was 85% of a
the low flowrate pressure rise and that the high flowrate ignition time was 85%
,j -
of the anticipated 150 second ignition time. Adding steam to the high hydrogen j flowrate, test 1.6, yielded deflagrations similar to the low flowrate counterpart, "i test 1.4, but a pressure rise essentially identical to that obtained from test f 1. 7. Figure 4-5 shows that ignition occurred at approximately 100 seconds, one i third of the 300 second ignition time for test 1.4. The ensuing intermittent deflagrations were more severe in test 1.6 because the higher hydrogen flowrate apparently resulted in a higher energy release rate. Why these intermittent deflagrations were not followed by repeated discrete deflagrations as seen in test 1.4 is uncertain. One possible explanation is that witt. vessel atmosphere temperatures in excess of 400 F for over one third the duration of test 1.6, a fraction of the' water collected at the tank bottom from vessel pre-heating was vapori:ed during the intermittent burning. This coulo have caused the defla-grations to be very localized, similar to those obtained in test 1.3. Thus, 4 j hydrogen could have built up in the vessel while the steam was slowly condensing 1 until an ignitable mixture was ence again obtained. The result would be a lull - in flama front detector activity followed by a major discrete defl/gration.
I '
.- ~ _ 1
- _ . . . . . . . _ . _ . . . . . . . .. - - - . - . . ~ - -
k.
- . F V4 41 1
fl Figures 4-5 and 4-6 show such characteristics. Some credence is lent to this possibility by noting that the post-test water concentration from test 1.6 was 50% larger taan that obtained from test 1.4. - One test was conducted,1.11, with the vessel pre-heat reduced to 120 F from j3 160 F. The results obtained were very similar to those obtained from 1.3, an f.$ I identical test with a 160*F vessel pre-heat. A very slight pressure rise s f occurred with ne corresponding flame front detector activity observed. This lg indicated tha's the bura, as in test 1.3, was very localized.
.1 q.
' ;j 4.4 WATER FOG TEST SERIES
-j
.I 1 Tests were conducted to investigate the effects of a water fog on hydrogen t
i cnmoustion. The fog nozzle, Sprayco Model 2163-7604, created different fog ,j characteristics depending on the pressure drop across the nozzle. Tests were
.; conducted witn two different fogs. Based on data obtained from factory Mutual 7
; Research Corporation, a 20 psi aP yielded a fog with a number mean croplet i
diameter cf 11p, waile a 30 psi aP /ielded a number mean croplet diameter of Sp. Two types of tests were conducted: quiescent and dynamic. The dynamic tests were conducted with and without steam. All tests utilized the bottom L i ignitor. A summary of the results obtained from this series of test is presented [ in Tables 4-3 and 4-4. I l ,t 1 3
- t.
7j y d N
- d;l 4.4.1 QUIESCENT TEST SERIES To provide a baseline of information for evaluating the dynanic fog tests, a j series of quiescent tests were conducted. Nominal hydrogen concentrations of t
;, 5, 7.5, and 10% were selected. Table 4-4 indicates that the completeness of comoustion for those tests without fogs (tests 2.1, 2.2, and 2.3) was approximately i
,i 30%, 90%, and 99%, respectively. This data agrees reasonably well with published
.!I data. The temperature and pressure histories of those three tests are presented
.-l in Figures 4-11, 4-12, and 4-13. Furthei tests with 5% hydrogen were not con-i I ducted.
t
- l
'l !
Reccating these tests with fogs present, a significant decrease in pressure rise was anticipated. Due to the large surface area present within a fog, the fog i was expected to act as a dispersed heat sink; resulting in reduced temperatures
; and pressures. However, as Table 4-3 indicates for the 7.5% hydrogen tests, 2.6
; and 2.7, tr.o observed pressure rises were slightly higher. Taole 4-4 shows that the comoleteness of combustion increased from apptoximately 90 to greater than 99%. This indicated t"at these particular fogs acted very much like sprays for lean hydrogen concentrations. The turbulence created by the fog flow apparently enhanced the completeness of comoustion; thus increasing the pressure rise. The heat sink effect of the fogs was evident from the sligntly lower temoeratures (compare Figure 4-12 with Figures 4-17 and 4-18). The fogs had no I apparent effect on the peak pressure rise in the 10% tests, 2.4 and 2.5.
1 6 4
~. - _ - _ -
i g:
~;
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q?, O Jj 4.4.2 OYNAMIC TEST SERIES d Hydrogen injection tests 2.8 and 2.12 were identical to tese 1.5 except that y fogs were included. Results from 2.8 and 2.12 indicated only minor intermittent
", deflagrations (see Figure 4-23). The observed pressure rise was an order of 3
j magnitude lower than that observed in test 1.5. It would be reasonable to J. assume that a great 6eal of the pressure reduction was due tQ fog flow induced
)
mixing, which allowed a flammable mixture to reach the ignitor earlier. Note J that the effect of adding steam to test 1-5 (test 1.4) was minor intermittent burning early in the transient with a pressure rise of 2.3 psi; the same effect 5 observed in tests 2.8 and 2.12 (see Figure 4-3). I
'j ;
Figure 4-19 shows a pressure history typical of that obtaired from hydrogen / steam injection tests with fog present, tests 2.9 and 2.13. The observed pressure l rises were similar to that obtained in test 1.4, hydrogen / steam injection with 1 i no spray. In both cases, with and without fog present, ignition occurred at approximately 300 seconds. However, in test 1.4 the result was minor intermit-
. tent deflagrations eventually oecoming minor discrete deflagrations. Tests 2.9 and 2.13 provided minor discrete burns immediately upon ignition. As a result, it appears that more hydrogen was consumed in the fog tests than in the non-fog tests. This would also appear to indicate that a major contribution fr .a r
the generation of fog in this test series was to provide uniform mixing within the vessel. i One tes,t was conducted with the hydrogen flowrate arbitrarily increased oy a factor three in the presence of a fog, test 2.11. Figures 4-21and4-22shkw - a 4 t
.a. .. . . . .. . . . .. . . . . . -. $b* .cj t
q. the pressure history and flame front detector activity obtained from this test. This test provided an indication of the neat sink effect of a fog as well as its effect as a source of turoulence. Note on Figure 4-21 that ignition occurred approximately 20 seconds into the test, while in test 1.7, an identical i test without fog, Figure 4-7 shows that ignition did not occur until 130 seconds into the test. This difference in ignition time could be accounted J
- p l for by the mixing created by the fog. The heat sink effect was apparently 1
jyl demonstrated since the peak temperature of test 2.11 rcmained around 200 F, j while the peak temperature in test 1.7 hovered around 400 F. In test 2.11, fog 1 produced turbulence apparently prevc.ited a major discrete burn by inducing
-i
; intermittent deflagrations early, thus precluding the relatively hign hydrogea
'l concentrations needed for a major discrete deflagration. Additionally, the fog acted as a heat sink during the resultant intermittent deflagrations; thus minimizing pressure and temperature increases. Camparing test 2.11 with test 2.12,
, an identical test with the lower hydrogen flowrate, the deflagration character-istics were similar with the high flowrate test having an earlier ignition.
Finally, data on the effect of fan induced turbulence was cotained when the mixing fan was accidently actuated prior to test 2.10. The result was that ignition occurred earlier (see Figure 4-20) than in a similar test without the I fan operating (see Figure 4-23). Other than the innition time, '.be results of both tests were relatively similar; minor intermittent deflagrations with very slight pressure rises. 0 1 ; l z 9
r . J. : .2.._.;
. ;._ _ , __.x.. .
. . . . .. . . . - - . - . . . . . . - i 2 a L._ .- . . - u k.- ...up. . .
I i s IABLE 4-1 . Suunary of Test Results: Ignitor Location Test Series Max. AP lest # fest Characteristics Ignitor location jpsi)_ Deflagration Characteristics 1.1 Low 11 2 . steam Top 13 Minor, major intermittent
- 1. 2 Low 11 2 Top 20 Minor intermittent, major discrete
- 1. 3 Low 11 2 . steam, spray Bottom 1 Minor intermitter.t 1.4 tow 11,2 steam Bottom 4.5 Minor intermit 4 cat , minor discrete ,
1.5 Low 11 2 Bottom 28 Hajor discrete, minor intermittent 1.6 liigh 11, 2 steam Bottom 24 Major intermittent, major discrete 3
- 1. 7 liigh l1 2 Bottom 23.5 Major discrete, minor intermittent 1.8 Low !!2 , steam, spray Center 2.7 Minor discrete i r
- 1. 9 Low 11 2 . steam Center 4 Minor intermittent 1.10 tow l1 2 Center 6 Minor intermittent 1.11 Same as 1.3, lower preheat Bottom 1 Minor intermittent ,
t k I i i e I
?
t
i TABLE 4-2
'i Test Vessel At:nospnere Constituents: Ignitor Location Test aaries Test # Post-Iest
,; H2 (v/o) H2 0(v/o) 02 (v/0)
.1
'! 1.1 11.0 li.6 3.9
.i l ;
- 1. 2 2. 6 23.8 15.1
- 1. 3 6.5 19.8 6.1
'. 1. 4 7.9 21.0 5. 7
..i 1. 5 2.1 38.2 12.2
;' 10.9
- 1. 6 32.1 6. 5 a 1. 7 12.7 37.6 1. 7
- 1. 8 7.9 30.1 7.2 1
- 1. 9 3. 6 46.1 5. 2 1.10 0. 4 36.3 5. 7 1.11 3.5 27.3 2.6 I
i t I .*' t ,
- - -- . .~ .. . _ . . . . . .. - . _ _ . .
; J:
.j-
-l TABLE 4-3
].
Summary of Test Results: Water Fog Test Series i j Max. AP q Test # Test Characteristics (psi) Deflagration Characteristics
- ci
.i 2.1 Quiescent, 5 v/o H 2 8 Minor discrete
,'j '
- 2. 2 Quiescent, 7.5 v/o H 2 36 Major discrete 1 2.3 Quiescent, 10.7 v/o H 2 48 Major discrete i 1
..i 2. 4 Quiescant, 10.7 v/o H2 , fog 30 47 Major discrete 2.5 Quiescent, 10.7 v/o Hz , fog 20 50 Major discrete 2.6 Quiescent, 7.5 v/o Hz , fog 20 40 Major discrete
- 2. 7 Quiescent, 7.5 v/o H2 , fog 20 39 Major discrete
. ' :j 2. 6 Dynamic, low H2 , fog 20 2 Minor intermittent 1 2. 9 Oynamic, low H2 , fog 20, steam 5 Minor discrete 2.10 Dynamic, low H2 _, fog 30, f an 1 Minor intermittent 2.11 Oynamic, high H2 , fog 30 2.9 Minor intermittent
,-' 2.12 Oynamic, low H2 , fog 30 1 Minor intermittent 2.13 Oynamic, low H2 , steas, fog 30 1. 6 Minor discrete i
4
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-_.__......_....-.._.7_..a.:
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'?
TABLE 4-4 Test Vessel Atmospere Constituents: Water fog lest Series Test # Pre-Test Fost Test il(V/0) 2 18 2 0 (v/o) H2 (V/0) Il0(v/o) 2 02 (V/0) 2.1 4.7 25.6 3.4 33.2 11.5 1 2.2 7.8 20.1 0.9 43.2 10.0 2.3 10.2 24.9 (0.1 40.4 10.9 2.4 -9.7 23.8 (0.1 44.9 8.7 l ' 2.S 10.2 25.4 (0.1 40.4 9.2 ' 2.6 7. 2 32.9 (0.1 47.6 8.4 2.7 7.6 29.4 (0.1 41.6 11.4 ' 2.8 3.3 30.1 6.8 2.9 6.2 45.5 S.1 2.10 2.3 49.2 2.7 2.11 . 13.S 35.1 (0.1 2.12 (O.1 37.0 9.2 2.13 3.7 45.4 3.7 T 4
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s
- 1. Location of an ignitor within the test vessel does affect the cnaracteristics
-l j af hydrogen deflagrations. Lowering the ignitor location produces milder
} aressures during hydrogen comoustion. This appears to be a result of i
-i increasing tne fraction of the vessel volume exposed to upward propagating
-1 i
flames in lean hydrogen concentrations. The addition of steam and water f .; sprays also reduced the pressure rise. However, the lower ignitor
.i locations still produced milder pressures than the top location.
t 1 2. Fogs were thought to reduce the pressure rise resulting from hydrogen combustion. This was the case for dynamic tests, but not for quiescent tests. Water fogs apparently enhance the rate of comoustion. Thus, heat i t transfer is not as significant in quiescent tests causing the deflagration g t to be more like an .dibatic deflagration. For dynamic tests, water figs -- promotemixingandallowp>ignitiontooccurearlier,resultinginlower - energy release rates. 1
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' ), APPENDIX A
. i
,a cil Gas Chromatography Analysis oj y Test vessel samples were obtained through nonhetted k inch stainless steel
.i
. probes located near the top and bottom of the vessel (See Figure 2-1.). Each fl1' !
probe was connected to the inlet of a Thomas diaphragm pump. Vessel isolation was provided by solenoid valves. A inch stainless steel line connected the disch'arge of each pump to a stainless steel condenser coil submerged in an ice r bath. Ta ed silica gel columns were located at the outlet of the condense ( - J coil to remove any remaining moisture. h inch stainless steel tuning carried
! the sample from the silica gal columns, through a dry gas meter, and into a 250
'l..
mil glass bulb. Thermocoup'es monitored the inlet and outlet pressures of the
-j gas meter. Solenoid valves isolated the sample tulb. When the sample was
, collected, the sample lines were purged.
.j Sample analysis was conducted by using a Carle Model 8700 gas chromatograph.
Instrument specifications are presented in Table A-1. This unit was equipped with a thermal conductivity device. The output was recorded with a Linear Instruments Model 252 dual pin recorder. All samples and calibration standards
- were analyzed using repeat injections. A ten foot by 1/8 inch 0. O. stainless I
steel column packed with Molecular Seive 13x, 80/100 mesh operating at 195*F, was used to separate the component gases. The gas chromatograph operating conditions are presented in Table A-2. Calibration standards consisted of several known concentrations of hydrogen (0.595%, 5.12*.,13.19%,18.27%, s 4
_. . . . . .. .r . -
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4
-4
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. 'j . .i balance nitrogen) and oxygen (5.0%,.18.1%, balance nitrogen). These standards were analyzed at tne beginning and end of each sampling day.
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GAS CHROMATOGRAPHY SPECIFICATIONS. Sensitivity Variable, two level detector. sensitivity d,; switch 1. l ., Attenuator Eleven ste? binary type,1024 to 1
'a' .l Detectors Oual chamber, 100 1 volume with 8-10K, 1 j 0.013 dia. matched thermistors
;'d Power Requirements 115V, 60 Hz
.. t Temperature Control Ambier.t :o 200*C rq 1
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- g s-GAS CHROMATOGRAPHY OPERATING CONDITONS 7
, Argon Carrier Gas Flow 20 ml/ min @ 25 psi
{* .. . 0ven Temperature 90*C [j , Column 10' SS tubing with molecular l ,a sieve 13x, 80/100 mesh 7; '
- j; Detector Temperature Low Position
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I k APPENDIX A.5 'i FOGGING STUDIES CONDUCTED BY FACTORY MUTUAL RESEARCH CORPORATION e { 1 l l l
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WATER FOG INERTING CF HYDROGEN-AIR MIXTURES Final Technical Report, September 1981 EPRI F-oject E 932-1 (Task 5) 1 ! s Prepar M by: FACTORY ,WTUAL RESEARCH CORPORATICN 1151 Boston-Providence Turnpike Norwood, Massachusetts 02062
- DiRC Project Manager Robert G. Zalosh t
i
',lj Principal Investigator
' Satya N. Bajpai 1
-l I FMRC J.I. OG2RS.RK
}
070 (A)
} 1 4
4 1 'i e Prepared for: { Electric Power Research Institute i 3412 Hillview Avenue j Palo Alto, California 94304 i j . EPRI Project Manager Loren Thcepson Nuclear Safety and Analysis Department i i
; / -
- ;3;__&,, _-
._ a .r_.
.w ABSTRACT This report presents an experimental evaluation of the effects of water fog density, droplet diameter, and temperature on the lower flammable limit (LTL) of hydrogen-air-steam'mixturse. The results show that the LTT, for hydrogen in air at 20*C is
' only marginally higher with fog than without. Most of the nozzles tested at 20*C raised the hydrogen LTL from 4.0 vol % to 4.8%, corresponding n dense fogs with volume-average drop size in the range 48,490 micrces. The lewer flammable limit at y 50*C was typically 7.2% corresponding to dense fogs with drop size in the range 25-50 microns. The lower flammable limit at 70*C was typically 7.6%, ranging from 6.8-8.5% depending on noz=le type and pressure. Typical fog concentrations ranged
.; frem 0.03-0.09 vol % at 20*C and decreased with increasing fog temperature. The 1
; results demonstrate that water foo inerting of hydrogen-air-steam mixtures is more e
pronounced with reduced droplet si:es and increased temperature, cenditions that
'}
favor rapid droplet vaporization rates. 4 1
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ACXNCWLEOG4ENTS 9
' The authors would like to thank the Electric Power Research Institute, Duke Power Company, Tennessee Valley Authority and the American Electric Power Company for .
[ their joint, financial support of this program. We acknowledge the enceuragement, P l' guidance and support provided by the Program Manager, Dr. Loren Thompson of
..g .
Electric Power Research Institute. Mr. F. Gregg Hudson of Fuke, Mr. J.J. Wilder
-[ of TVA and Mr. Kelvin Shiu of AEP also provided valuable suggestions during the i
program. We also acknowledge the assistance of Mrs. Vicky Hwa of FMRC for con-ducting the computations of average drop sizes and fog concentrations. i* 4 g i !'~ l , 1 l o
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CONTENTS E
i Section Page YI' 1 INTRCDUCTION 1-1
;' TEST APPARATUS AND EXPERI.W AL PROCEDURES 2-1 2.1 Hydrogen-Water Fog Inerting Apparatus 2-1 2.2 Droplet Si:e And Concentration Measurement 2-3 f:
2.3 Hydrogen-Water Fog Inerting-Experimental Procedure 2-6 . ;_ . 3 FCG CONCENTRATICN AND ORCPLET SI E DATA 3-1 4 FOG INERTING DATA 4-1 5 CONCLUSICNS- 5-1 4
, REFERENCES 6-1 APPENDIX A SUPN.RY OF EXPERIME2 CAL OATA A-1 APPENDIX 3 LOG-NCRMAL DRCP SI 2 DISTRI3UTIONS 3-1 1
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- -J Figure Page l 2-1 Hydrogen-Water Fog Inerting Experimental Setup 2-2 2-2 Fog Nozzles Used in Inerting Experiments 2-4 I:
;, 3-1 Crop Size Variation With Pressure And Temperature 3-2 4
- 4. 4-1 IJ quid-Vagr Conversion And Water vapor Saturation Relationships 4-5 i 4-2 Detonation and Flammability Limits %r Air-Hydrogen-Steam Mixtures 4-6
.4 4-3
;I I Fog '.cncentration As A Function Of 24ep Size To Achieve-Indicated Inerting Levels 4-6 i~I 4-4 Fog Concentration Versus Drop Size Requirements For Inerting to 4.76 Hydrogen at 20*C 4-9
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. Table Page 4-1 Hydrogen-Water Fog Inerting Data At 20*C 4-2 7 . 4-2 Hydrogen-Water Fog Inerting Data At -50*C 4-3
; l 4-3 Hydrogen-Water Fog Inerting Data At ~70*C 4-4
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1 i i 1 G l$ b St;MMARY
. As a result of the Three-Mile Island accident, there is renewed concern about hydro-gen control measures during degraded core accidents. Cne premising hydrogen centrol measure is a distributed ignition system to burn the hydrogen at a controlled rate ;j as it is released into the containment building, It has also been suggestec that 'l water fog in the containment could further reduce hydrogen ecmbustien temperatures
- and pressures. On the other hand, there has been some concern that the fog could
! inert hydrogen-air mixtures and inadvertently prevent controlled combustion. Moti-vated by these concerns, this report addresses the question of hydrogen-air-water 'l 'l vapor mixture flammability in the presence of highly cencentrated water fogs.
4
,4 A laboratory-scale fog-inerting apparatus was constructed to acquire pertinent in-erting data. Tests were conducted with gas mixtures containing 4.0 vol 4 to 9.7
]
; vol % hydrogen at temperatures ranging frem 20*C to 70*C. Cense water fogs were generated in the inerting tube by using a series of five different fog no::les vnich produced volume-average drop diameters of 20-115 microns at water pressures of 10-40 psig (69-276 kPa) . Tests involved ignition attempts with both spark ignitors j sad glow plug igniters. Successful ignition was monitored by thcraccouple response j_l and by actuation of pressure relief dises at the top of the inerting tube. Prior i
to the inerting tests, fog drop size and cencentratien data were obtained with a j hot wire probe 1ccated at the igniter position in the inerting tube.
.i i
1 ; . Room temperature inerting test results indicated that dense fogs caused only a mar-ginal increase in the hydrogen icwer flammable limit (LTL) concentration. Specifi-cally, the hydrogen LTL for upward flame protagatien was raised fr:m 4.0 vol % for a
~
i dry hydrogen-air mixture to 4.4-5.3 vol 4 with four different hydraulic no::les at
.j various pressures. An air-driven not:le, which produced smaller drops than the j hydraulic no::les, increased the LTL to 7.2 vol 4 at 20*C.
l Tests run at higher gas / fog temperatures resulted in somewhat greater increases in the hydrogen LTL. For a typical hydraulic no::le, the hydrogen LTL increased from 4.8 vol 4 at 20*C to 7.6 vol % at 70*C. This increased inerting is due in part to
! water vapor dilutien and it. part to liquid phase water heat sink effects associated i
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.t with rapid vaporization of the smaller drops at. elevated temperatures.
Fog densities required tc 4.chieve a given level of hydrogen inerting increase with increasing characteristic drop size of the fog. It is difficult to accurately
.i quantify this effect because of uncertainty and scatter in the present fog density
' data. However, the data do indicate that fog volume mean drop size would have to be well under 20 microns and that fog densities would have to be well abave 10' g/cc-gas to raise the IEL above 7-8 vol % hydrogen, even at temperstures as *
~
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- i-J o l 4 Section 1 INTRCDUCTION il As a result of the Three-Mile Island accident, the Nuclear Regulatory Commission requires operators of certain containment structures to determine and implement an effective method for controlling hydrogen evolved during degraded core accidents.
One of the hydrogen control methods that has been suggested is a water fog system, probably in conjunction with a distributed ignition system. The water fog system would fill the containment volume with a high-density fog prior to and during con-trolled combustion of hydrogen by a distributed ignition system. It has been j suggested (1) that heat absorption by the eater fog would maintain peak combustion temperatures and pressures within acceptable values as evolved hydroq9n is gradually consumed. Adiabatic, complete isochoric combustion calculations of Berman et si (l_) , which include fog droplet evaporation effects, indicate that fog concentrations on
-l -4 3 g-water /cm -gas-mixture can significantly reduce containment pres-the order of 10 ]
1 sures ce= pared to dry combustion at the same hydrogen concentration. i
)' In order for a water fog system and distributed ignition system to be compatible, i
the fog should not inert or quench flama propagation. Fog inerting or quenching rc-
, quires ryid droplet vaporization. Vaporization rate calculations cf Ber=an et al 1
- indicate that droplets with a diameter less than about 8 um will vaporize en-(1)
.f!
,' tirely within the flame zone and, thernfere, are capnble 9f inerting. The order-i of-magniture of this calculated result is consistent with the experi= ental data of Sapko et.a1 (2_), who otserved that droplets smaller than about 10 um diameter sus-
- pended in methane-air mixtures vaporize sufficiently rapidly to provide the same in-I j . erting capability as their equivalent mass of water vapor.
I j . It is important to confirm and further quantify the suspected inerting capability j of water fog suspended in hydrogen-air-steam mixtures. This report describes the i
. results of an experimental program in which the effect of water fog ~ density, drep-
,= j let size, and temperature on the lower flarmable limit of hydrogen was studied, i The 'axperimental approach has been similar to that used by Sapko et al for methane-l air mixtures. Experimental procedures and equipment are described in Section 2. 4 h 4 i i 1-1 4
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g I d c L Section 2 i TEST APPARATUS AND EXPERI.v!NTAL PRCCIOURES 2.1 HYDROGEN-WA N FOG INERTING APPARATUS
- A schec.icic view of the experimental setup is shown in Figure 2-1. The inerting tube (1) is a 15-cm 1.d. ,1 meter long (18-liter) P15.siglas tube, vertically ori- ; ented and supported on a Unistrut frame. The tube is equipped with a cap (2) on-top which supports the vents and the gas mixture and water supply lines. A poly-propylene Buchner funnel at the bottom, aids in water collection and eliminates air j updrafts. The vents are 4-cm i.d. openings, spaced symmetrically on the cap and
- ] .
covered with aluminum disks. With the inerting tube at atmospheric pressure, the
+1 i vent disks stay in place to prevent hydrogen-air mixture leaks trem the top or ad- ;1 ; mission of outside air into the tube. However, the vent disks open to act as a 1 pressurn relief device (and to verify combustion) when the hydrogen-air mixture is i
':! ignited.
- !i Ignition electrodes - (6) ara located at the center of the inerting tube for most tests. The electrodes are machined from a ~6 mm brass rod to assume the needle-i l
point shape. The electrode body is insulated with a shrink-fit tubing throughout the entire length except at the needle point and the flat ends projecting out of the t
! tube. A spark gap of ~3 mm is allowed between the needle points. During an ig-
{ nition attempt, the electrodes are energized by a Oonegan Model transformer with seccndary coil (i.e. , output) voltage of 8,400 V and current of 20 =A. The calcu-J j lated spark energy is 2.8 Joules / cycle. ,) i j In a few tests, the electrodes were replaced by a glow plug (General Motors Model 1 - q 7G AC). The glow plug was energized by a 14 V AC transformer. Flame propagation in
-i the inerting tube was monitored by three chremel-alumel thermocouples with a head l diameter of -0.3 mm. Two thermocouples are located 5 cm above and 5 cm below the
! ignition electrodes and the third thermocouple is 15 cm above the electrodes. The j
; beads of all three thermocouples are approximately at the centerline of the inerting tube. Thermoco'uple response signals were fed to an oscillograph to indicate whether or not the hydrogen-air mixture was ignited. That is, if either of the three thermo-
-i couples responded during an ignition attempt, the mixture was considered to be i
.1
.i h
i 2 _ _ _ _ - _ - _ _ -. - - .
ua_. <
- . . __p -
wa i m ;s - a :s ..s...,..
. Q. -. ,1 :
i t 8 1. Inerting Tube (Plexiglas) i ^ ~ 4
- 2. Vent S Plumbing Support Cop 2L, y p g _.J ,d io ,g 3. Funnel
- 4. Vent Disks ( A total of four )
i i f o 5. Soroy Nonle I QS j8
- 6. Electrodes 7
^ 7. Thermocctele Probes 33 8. Hecting Tore
,j j j
- 9. Flash Arrreter 4,
//' 'gs IG.Rotometers
'# i ii s> II. Hydrogen-A.t: M.ter 1
l' \ 7 1 12.Chcck Volves
/
j, . lng, \g 'i i, ' 12 12 13. Hot Water Tonk 1 i l* 7 14. Solenoid Volves 1
',,I lli' i to
- 15. Pressure Regulators
] i l' l ll !'i !
10
- 16. Water Collector
{
/,1, I 'tl' , 14 h14 14 D
bi'{tl C g l e;\\ l' : I 'f I 15 15 15 te'iI 1
' I gl i .
g li' I H2 Air N2
. l
..s*
/ .n /
- I6
; 'f_ .'
b f[?..' *~l$$l:f I i Figure 2-1. Hydrogen-Water Fog Inercing Experimental Setup 2 1
.i l
l i l, I o i , 2-: , , ,,
.1 . . _ . . _ - . .._
a . w m - .- ,. w _ _ _ -~ - '-. -
}}
- t. ,
- i. t h flanumable a . Whenever there was flame propagation, the pressure relief vents pro-
.I vided at the top of the inerting tube also fluttered, thereby providtng visual con-firmation of combustion. J The hydrogen and air used in the inerting experiments were obtained from Linde with
.j each :;.v having a minimum purity of 99.954. Hydrogen and air streams were metered 1 using Matheson flow meters after passing through check valves the streams meet at the inlet port of the hydrogen-air mixer, which is a 75 cm 1cng, 25 mm i.d. stainless steel tube packed with glass heads. The mixed hydrogen-air stream at a nominal flow rate of 10-20 1/ min is fed to the inerting tube after passing through a flash ar-4 rester. Water for the fog nozzles was supplied from a liter electrically heated
; hot water tank (Dayton Midget Watttrimaner) . The tank is pressurized by nitrogen and distilled water is fed to the nozzle after passing through a rotaaeter. The i spray nozzle is located ~20 cm below the top of the inerting tube and -33 cm above
.1 j the ignition electrodes.
l Five different nozzles were used to obtain a range of fog concentrations and drop sizes. The nozzles were: 1) a SPRACO impingement-type nozzle (#2163-7604), 2) a I SPRACO hollow cone noz=le (#2020-1704), 3) a SPPACO hollow cone misting nozzle 1 (#1806-1605), 4) a SPRACO impactor type nozzle (#1405-%04) , and 5) a Sonicore t 4 (Model 35H) air-driven fog no::le". Figure 2-2 is a photograph of these five i no::les. ij lT l 6t 2.2 DROPLET SI::E AND CONNT::CN MEASUREMCIT t _i i j The dreplet size distribution and dreplet concentratica in the fog noz:les used in i
. this study were determined by means of a KLO Associates (Huntingten Statien, N.Y.)
- C-2 Crep Size Measurement Prebe. The operaticn of this KLD Orop Size Measurement l:l 4 Probe is conceptually similar to hot-wire-anemometer operation. Local cooling i' j l caused by dreplet attachment to a hot wire changes the electrical resistance of the l1 wire. A portion of wire covered by the droplet is cooled approximately to the d:cp-let temperature. With a canstant electrical current ficwing through the wire, a measurable voltage d:cp can be sensed between the wire terminals. ~hus, the voltage R
4 in dry air is reduced by an amount proportional to the dreplet diameter when a drop-I let is attached to it. With appropriate counting elect onics, the freplet size dis-
~
tribution can be cbtained. A more complete discussion of the KLD try ~,1:e measure-
) m e t technique is provided in a paper by Magnus et al Q).
Cnly the thermocouple above the igniter actually sensed the presence of flame; thus, flame propagatien was upward enly.
. " ydrogen-air H mixture was used as the atemizing medium in these tests.
{ 2-3
i l .-
^
- .- ...anu.a.c2-u .w :.. - a. .m. ~...2.~..--
i . t .i
. . . . . . - . - . . . . - - . - , . -v..,-...---~~..-----.-- .m
)
~
I 1 l
. .. ~.. ..~. ~
_i , SPRACO SPPJ.CO SPRACO SP.uCO Sorucore I Honow Houcw Impingemset Impactor 035H Cone Misting Cone and Modal 2183- Model 1405-l; l Moce! 1806-1605 Fine Sprar 7604- C604 .. t' Model 2020- - i 1704 t 1 - t : g. r. .n m ; 1 l' 1
....~~j'- - . .--
t - I t Figure 2-2. Fog Nozzles Used in Inerting Experiments i I 1 l: I l i
/4 1
-l i
l 1 t l l i 1 1
- t 4
I
-e-
- . - -- . . . . , , . . . . . . , .; . .m . -
- . ,- ,
s.. ,
,.,w- _. _
+,
. g _.m j
-{
l c .;
*i Drop size measurements using the proba were made in both the inerting tube and in an I
s 14 unconfined fog. In the inerting tube, the probe was located at the ignition lo-4 cation, i.e., about 33 cm below the ner.zle. In unconfined fogs, the probe was also i located about 33 cm directly below the nozzle centerline.
-}
If droplet velocities are known, fog concentrations can also be obtained from the droplet counts and sample collection time. Thus, the drople*. number density may be defined as the number of drops counted divided by the sample volume. The drop-let number density, ng , corresponding to each droplet size interval is calculated by the expression: L i_ K, Ng Dro9s/c=3 (2-1) lq n = i v.t.dD,.,), d
;l where K g = cr.ytive area factor, i.e., small droplet trajectory / velocity deviation caused by wire sensor. The factor is unity for drops >0.7 um:
N g = droplets counted in the ith channel; v = flow velocity (cm/s); t = counting time interval (s);
> 1 = sensor length (0.1 cm):
}
Dg = average droplet diaminter for the ith channel (varies from 1.3 to 366 um) : d = sensor wire diameter f5 x 10 cm). f I i
.l Fog mass con.entration, C(g/cm ) , is related to the number density distribution by 1
3
.3 3 C = 7/6 p ngD g (2-2) i where p is water density and n g is given by Eq. 2-1. Fog volume fraction is cal- ');
w 4 culated similarly, but without the density factor, in Eq. 2-2. l. 9 Fog concentrations computed in this manner are only as accurate as the accuracy of
'i the assumed flow velocity, v, in Eq. 2-1. Two alternative calculaticn procedures l have been used with two different assumed values for vs 1
j 1. The average gas velocity, v,, flowing through the tube was used.
; However, this velocity was only 1-2 cm/s, which is less than the "I terminal velocity, v , for the larger dreps in the fog.
- 2. Therefore, a second calculation procedure was also used in which the droplet velocity in Eq. 2-1 was assumed to be either v, or v,,, depending on which value was larger for a channel of given si:e.
Lj ' 2-5
- . . - , <. t. .
. . . ..s .r.- . , , . - .
-aw.
, ._ .x;
_ . . _ .a ; _.. , .L . _ 3 -
' In view of the mcartainty 2.nvolved in using the DC-2 probe data to calculate fog concentration dats, another independent method, previously used by Sapko et al Q),
was used here also. This consisted of simply collecting water for a known interval in a Pyrex dish of -14 cm 1.d. inserted into the bottom of the inerting tube such that there was a clearance of ~5 :en between the tube and the ec11ector dish. By knowing the rate of water collection anr* the volu:::etric flow of the hydrogen-air mixture, the water / gas flux ratio was calculated. To the extent that the droplet and gas mixture residence times in the tube are comparable, this flux ratio is also a measure of fog concentration. I. 2.3 HYDRG-I21-WATER FOG INERTING-EXPERI.ENTA
I. PROCEDURE
Inerting experiments began by purging the inerting tube with the desired premixed
'i stream of hydrogen and air. At 1. east six inerting tube volume changes were effected to achieve uniform composition throughout the tube. The water spray with desired temperature was t m ed on 2 min before an ignition attemet and the temperature of the spray and mixture were continuously monitored using chromel-alumel thermoccupies.
If
, Ignition was attempted by energizing the electrode or glow plug transformer.
the mixture was flammable, the flame was sensed by chromel-alumel thermoccupies and
-v their response ecorded en a Honeywell oscillograph. A second indication of the presence of flame was provided by the fluttering motion of the vent disks as they opened to relieve pressure in the inerting tube caused by the flame. Another im-portant visual feature of the experiments in which flame pr pagatien occurred was the appearance of dense steam fo11cwing flame propagation.
i l k i1 1 l i U
.i J
9 0 2-6 i . . _
? .
^ ..
l1 4 fi
't il
;J Section 3 FOG CCNCE!PrRATICN AND ORCPLET SIZE OATA Oata from the KLD drop size probe have been processed to deter =ine water fog concen-tration and drop size distributions. Cumulative log-probability plots of the drop si=e distributions are presented in Appendix 3 for all five no::les operated at vari-ous pressures and torperatures. The linear relationship shown in these plots im-
;j plies Q) that the drop diameters satisfied a log-normai distributien. The " average" diameter in these distributsons has seen represented by number median diameter, number mean diameter, volume mean diameter, and Sauter mean (volume to surface area I
; ratio) diameter. Tabulated values of these average diameters and the leg normal I standard deviations for the various test conditions are listed in Appendix A.
b
~.
-l For a given pressure and temperature, the five no: les produced average drop sizes 1
! that usually increased in the order: Scnicore (air driven) 35 H, Spraco 2'.63,
*4 j Spraco 1806,'Spraco 2020, and Spraco 1405. For example, at a pressure of 2025 psig and a. temperature of 4523*C, the volume mean d:cp diameters for these five no:=les
{:
- were 22 us, 35 pm, 43 um, 50 pm, and 92 um, respectively.
i h i A comparison of the drop size measurements made in the tube and on unconfined fcgs
. shews that the drop sizes for all Spraco no::les are larger when the measurement is I done in the open than when it is dona n the tube. For example, under identical operating conditiens of 20 psi and wato- at 20*C, the number median drop size for
] Spraco 2020-1704 no::la was reduced from 10.421.6 um (measured in open) to 621.7 um j i (measured inside the tube). *his shift in distribution can be attributed to droplet
/ breakup in striking and rebounding off the walls of the inerting tube.
-i
)
[ For a given no::le, the average drop size decreased with increasing pressure and 4 U. with increasing terperature. This effect is illustrated for Spraco no::les 2163 and , i 1806 (two comparable no::les) in Figure 3-1. i t j Foy concentrations calculated using the three methods described in Section 2.2 are
; also tabulated in Appendix A. For the Sonicere air-driven no: le and the Spraco 1405 no::le, concentrations ebtained from the KLO prebe data (assuming v = v ) agree fairly well with concentrations based en the water / air flux ratio (called the col-lection method in Appendix A). Ter the other three no::les, the fcq cencen.ratiens 3-1
-~ .-- - .
.a:
..= wan .. . :. .-- :.4 -
f s. 50 . . . . . .
$)Sproco 2163-7604 afSpraco 1806-1605 40
~ -
- m 1
I
? \ .- }
Aa
/4 30 -
ui \ c \ J ^ w c. e 50*C \ 20*C 2C - A\ s'O -
, \ s s
N N N N N N 10 -
^\ 0-
~1 O 80 20 40 GO 10 0 12 0 14 0 Vol. Mean Drop Size. Microns
)
-1
' Figure 3-1. Drop size Variation with Pressure and Temperature
,. i I
- J-2
k'
* ^
. ~ . . u.: ...u. i .... :_ l.' ~ _ - - -- .. ;-2 ._
a fi I:j calculated from the probe data with v = v,were an order of magnitude smaller than .9 those based on flux ratios. This implies th.c the gas and water drop residence times
'd l in the tube are comparable for small-drop fogs (Sonicore noz:le) and large-drop spray I
~l (Spraco_1405 nozzle), but the two residence times are quite different for moderate- l j
4 drop sizus in the range 30-100 tan. Thus, the water collection technique is not a 4 reliable method for determ'r.ing concentratiens of fogs with drops in this size range. Fog concentration calculation based on probe data with v equal to the larger of ei-her v,. or v, were consistently at least an order of magnitude smaller than con-centrations based on the other two techniques. Thus, concentrations based on v, and
)
y
-5 -3 3 gm water per em of gas while cencontratiens based on l
i
- ranged from 10 to 10
;I -4 -2 3 *] the other two techniques ranged from 10 to 10 gm/cm .
1 1 The discrepancy in fog concentration data is an unfortunate consequence of the in-herent inaccuracy in the measurement techniques employed. Other techniques, based on optical attenuation or scattering phenomena (for example, Reference 5) tre more ac-curate although more complex, and are recommended for future measurements of fcq i density. Fog concentration data listed in Table 4-1 are based on the prebe method l (using v,) since the authors feel this method is the ecst accurate of the three tech-
! niques used.
1 1
'1 t
4
- )
1 i I} t
?
l 3 i ai e i i 1 3 4 3-3
. .. . a , ,. .._, -. , .
a . . y_ : .._.a.,. ___ .c - = .
-c. -
- n:, .a.-
4
- 1 1,
21( Section 4 FOG INIRTING CATA Hydrogen lower flamable limit (LFL) data in the presence of water fog are shown in Tables 4-1 to 4-3 for gas / fog temperatures of 20*C, 50*C, and 70*C. Data are pre-sented for all five noz les operated at pressu:?s of 10-40 psig. For the Spraco hydraulic nozzles at 20*C, the hydrogen LFL was 4.4-5.3 vol % (neglecting any water vapor diluting). These values are only marginally higher than the hydrogen LFL for dry air; i.e., 4.0 vol 4, which was also verified (a value of 4.03% was measured) in the present apparatus using both spark and glow plug igniters. 4 J! The Sonicore air-driven fog noz=le at 20*C caused the hydrogen LFL to increase to 5 7.2 vol s. This increase is undoubtedly due to the smaller drops produced by the Sonicore no==le compared to the Spraco hydraulic no::les. 1 At 50*C, hydrogen LFL's in the presence of water fog varied frem 5.6 to 7.9 vol % l dependin's on no::le type and pressure. At 70*C, the hydrogen LFL was 6.8-8.5% for b the two nozzles tested. Most of the 20*C and 50*C inerting data were obtained with
^l a spark igniter, but some repeat tests with a glew plug produced almost identical j results. The 70*C data were obtained with the glow plug.
I 1 The observed increase in LFL with increasing temperature is similar to that reported i by Sapko et al (1) for water spray inerting/ quenching of methane-air mixtures. It I can be attributed to the following effects:
- 1. The hydrogen-air mixture is diluted by additional water vapor, which is presumably present at the saturation values shown in Figure 4-1.
f 2. As initial droplet temperatures increase closer to the atmospheric pressure boiling point, i.e. ,100*C, the droplets can vaporize more ,] . rapidly to quench a growing kernel of flame.
; 3. The drop size is reduced with increasing temperature. The smaller i drops evaporate oore rapidly than larger drops to quench an in-cipient flame.
, The dilution effect is illustrated by plotting the observed LTL values on the three-I component (hydrogen-air-water vaper) flar= ability triangle diagram shewn in Figure 4-2. Since the LFL data with fog fall within the flammable envelope in Figure 4-2, it is clear that water vapor dilutien alene is not sufficient to explain 4-1
- .. _ .._ ... .. A ^i .
. L. !-
,t* z .~ ,,3 :
_[' ',? . Q." . __
~; '
,f,'. '~
s
.'s i Table 4-1 ' 1; I
L~
! ILYDROGEN-WATER FOG ItiERTING DATA AT 20*C Spray Vol. cm 11 0 18 O Flux Ave. I'nerting 3 2 Press. Angle Mean Dia. No. Median Conc. Conc. of H y !, l 'i 3 3 2 t Hozzle (psi) (Full Angle) Micron Micron cm Mix cm /cm min (%) ,.
l -4 Spraco 10 11.1 9.811.9 8.1x10 0.10 4.42 l 2163-7604 20 >60* 54.5 4.711.5 3.8x10~ 0.36 4.76
..O.
-4 .
~60* 25 44.1 6.411.4 2.7x10 0.25 4.76 i 2.8x10~ 0.16 4.76 I i 30 ~60* 20.6 1.511.3
- 10 61* 139 1312.1 3.6x10~ 0.75 4.64 ,f Spraco
~4 2020-1704 20 86.2 611.7 8.5x10 0.20 4.76 l, , 25 58.4 4.811.5 2.9x10~ 0.20 4.76
~4 30 80* 35.7 5.611.7 1.5x10 0.23 5.26 '
e
! Spraco 10 136 1312 9.4x10 0.18 4.40 g 1806-1605 20 59.3 511.8 6.0:.10~ 0.22 4.76 f, 25 66 412 5.7x10~ 0.16 4.76 f
30 ~40' 47.0 6.411.4 3.2x10 0.12 4.65 Spraco 10 136 1412.1 4.5x10~ 1.04 4.64 1405-0604 10 110 1011.9 2.2x10~ 1.17 4.76 (20-30*) 25 114 1111.8 2.7x10~ 1.04 4.76 ', 30 20* 115 1411.8 3.3x10~ 1.12 5.26 )
, n.
I Sonicore 20 - 5 1.1x10~ 0.104 7.2 03514 (' f ,: i I.; . i b
!j
}
v.;
,e3, ,a .
..o
. . . . . ._ s . .._ _
. . . . . _ , . _ , . . r,_,. .. . - .
.a. ___,,,,f,. , g_
4, ~2 ' . _ q. u a, j
.4
..'i. . .l Table 4-2 HYDROGEN-WATER FCG INERTING DATA AT ~50*C 3
.j Vol. cm H O 2
H2 O Flux Ave. 2ner-ing Jj Nozzle Press. Mean Dia. No. Median Conc. 3 3 2 Conc. of H 2
; (psi) Micron Micron cm Mix em /cm min (%)
i
~4 Spraco 40 33.1 5.221.2 1.4x10 0.N 7.2
~
21.4 8.1x10 0.16 5.6
) 2163-7604 30 4.221.2
~4 20 34.5 4.521.4 1.9x10 0.36 5.6 4
s -s 7.2 Spraco 40 24.5 3.821.3 9.3x10 0.23
~
2020-1704 30 27.1 4.221.2 1.1x10 0.23 7.2 20 50.3 6.211.5 4.0x10 0.20 6.32 4'
-!, Spraco 10 - - - -
4.98 1806-1505 20 - - - - 5.44 30 - - - - 5.44
. 40 112 3:1.06 1.9x10~ 0.097 5.18
-2 j Spraco 40 87.8 9.621.7 3.2x10 1.12 5.6 1405-0604 30 91.8 11.5tl.7 2.0x10~ 1.12 5.6 l ~
I 25 115 14:1.8 1.7x10 1.04 5.6
~
Sonicore 25 24 2.4:1.2 1.1x10 0.12 7.93 035H 20 24.4 2.8!1.07 1.1x10~ 0.11 7.2 25 24.4 2.3 1.25 1.1x10~ 0.12 7.92 i
,i .
1 h 4-3
- - + . ~ , - .s 3.,y. .,R,.,. . . , . _ --
- u _. _ -
- 'u,-..e. . . , _ . .
_- j;
-J w'I 3 .
)
.4 1
l i, Table 4-3 .
?. 'IPIDROGEN-WATER FOG INERTING DATA AT ~70'C * ,; 3 Vol. cm H O H2 O Flux Ave. Inerting 2
No. Median Conc. Conc. of H 2
': Nozzle Press. Mean Dia.
Micron 3 3 cm Mix em /cm min 2 (%) (psi) Micren
- - - 6.76 Spraco 10 -
- - - 7.18 2163-7604 20 -
- - - 7.62 30 -
- - - 8.46 40 -
- - - 5.88 Spraco 10 -
i 1 - - - 6.32 e 1405-0604 20 - 9
- - - 7.62 30 -
- - - 7.62 40 -
.l - - - 4.98 Spreco 10
- - - 5.43 1806-1605 20 -
1 - - - 5.43 30 -
- - - 5.43 40 -
3>
'. )
e
?
] .
t
.?
4 J t 4-4 J 1 1
. ' = w w.-+.**. - - _ . , , - y --
ww -- - -
+
_g
.w- ;- w . ,:, ; . ; . ~_
2 : a.. _. . au.. . . . w . z. 1
,?
5' 1l Temperature, *C 0 20 30 40 50 60 70 80 90 00 , , , , , , , , 90 - - I' 80 - - E
. e
, u j ; 70 - -
; a.
l e E j 60 -
. o i > Liquid- Vapo r
'j ,
i u 50 - conversion curve h - c N 4 a o 40 - - a. l o i >
- w 3o 30 - -
5 y Wa t er Vapo r 20 - g saturation - Curve 10 - - t 1 f f , I t i O I 2 3 4 5 6 7 8 9
~4 3 l ,
X 10 , Fog Conc., Cm 3 H2O(2)/ Cm Gas Mix l Figure 4- 1 Liquid-Vapor Conversion and Water Vapor Saturation Relationships 4-5
- . -. . ., -. ,. . - . ...,,.3...
_ u. . . .. , . ,, , ,
- 2. .2A's ._ _~ _m m c_.,_;,:,.;c ;&. _ : -. : ,;
,3 ! m v. mn OH Inerting at 20 C 2 ' AH Inerting at 50 C 2 ]
i; 80 20 t'
' e
[ LO , 40 Sp A ASSUMED 4, 1-l d XTONATICN # c] ,[ uMc $ . y m I ' w
' LAMMA8 UTY UMIT 20 '
/ \/ \/ \ go
.i.
/ \
'00 *. *z SO 60 40 20 toov. sTE4u PERCENT H 2 Figure 4-2. Detonation and Gammability limits for air-hydrogen-steam mixtures J
Data Points represent water fog inerting data obtained j in this study for nozzles and include water vapor saturation
.)
concentrations (Curves are from ref. 6) i, i i i 1 4-6 1
~l
- - - ~ . . . . . , _ . . .
s i e
-- a a,n __ - - J _._ g gg. , , ._ ,q .
d the observed data. Thus, liquid phase water must also be providing a heat sin.'c to contribute to the increased LFL. 4 l s Water fog densities required to achieve s given level of inerting depend on the tog
;il
! characteristic drot., size. This is shown in Figure 4-3, which is a plot of fog dansi-tf (based on probe data with v = v f) versus volume mean diameter for inerting to a hydrogen LFL of 4.764 at 20*C, and 7.2% at 50*C. Although the 50*C data in Figure 4 4-3 refer to smaller drops than the 20*C data, best fit lines through both sets of
~
data are approximately colinear on the log-log plot. The data in Figure 4-3 refer
.i to four nozzles. Data from the fifth nozzle (Spraco 1405) were more scattered than for the other fon; nozzles, but did indicate that the linear relationship in Figure 4-3 could possibly be extrapolated to somewnat larger drop diameters and fog densi-y I ties, as shown in Figure 4-4. -l -1 The trend of the data shown in Figure 4-3 is analogous to that observed by Sapko I
et al with methane (see Figure 3 of Reference 2) . !!cwever, in view of the uncertain-ty in the fog density data, the results shown nere are not sufficiently accurate to generate a quantitative design basis. 1 4 1 4
'I s
i i
)
i t 1 1 e a ls
} ^4 1
1 4-7
. ~ - ~
- . ~ . . . . _ . . x__ u s.___._ _ .. w ., u i .
~
- j A
^
'O 20*C 50*C 2 -
O.l0
'l 3 10'3 . . . . . . . .
o.og
~
9 /- 0.08 1 oSpraco 2163-7604 y - ~
~g 8 ASproco 1806-1605 / o.o7 A 7 -
vSproco 2020-1704 / - - E
/
0.06 g
.. g6 - OSonicore 035H _ _
e ae
= l 0.05 a.
S 5 - e3 - - j /476% H2 - 0.04 E Non-Flammable Zone , in Air At _ _ y e 4 -
,o 20*C 3 y , -
.5 a' 0.03
~
j Flam<nable - - 8 2 3 .
,' 7 Zone i g
- p E
- v. d5 QO2 0 m 2 -
o (2% 7. H2 In Air - - E o E o At ~ 50* C o s 3 O O N N I O "E
$# 0.01 810-4 t 10 20 30 40 50 60708090 j
1 ie Volume mean diameter, microns i I l Y E 1
! o
- o I
l Figure 4-3. Fog Concentration as a Function of Drop Site to l Achieve indicated nerting Levels 1l.; l 1 i I l i 8 i 4-0 1 l I-
x
. . . . . , .; .~ . . - . . . .:-. . .
- = Lu. _ =.:x a.w. .._.._m. a....:u ay sk. 2:2 4
1 ii
-' e r ,
. . > > . . . . . . ....g . ....a 7 .
g .
= :
v 4 S : oSpreco 2163 - d- 3 - oSpraco 1405-0604 -
~
3u - OSpraco 2020-1704 O _ vspraco 1806-1605 a u. o _ a _ 8
=*, 10-2 -
o - _ m - _
.! = - _
-i ax . a _
-1
! 2 - -
! m
! E - _
4 o
\
t
~f O j f IO'3 :- --
' - i m : i E - -
-1 u _ _
i 5 o O - 3 *
. .c U
^
0 ' ' ' I ' ' I i ' ' ' ' 10'" 10 10 0 200
- ; Volume mean diameter, microns
{l Figure 4-4 Fog Concentration versus Drop Size Recuirements for
, Inerting to 4.76 Hydrogen at 20 C i
i s
- 4-9 l ;
I L ~.
" ' a.
{ ,' .- .
- w. ,a_.x_w% >
u.u~ ~- . I i l I Section 5 CCNC:.USICNS
. 1. Dense water fogs applied to hydrogen-air mixtures cause only a marginal
- k
- increase in the hydrogen lower flannable limit (LFL) concentration at room
..l temperature. Four fog nozzles used in this program caused the hydrogen ;j j LFL for upward flame propagation to increase from 4.0 vol % to 4.4-5.3 vol 4. ) Fog generated from an air-driven nozzle (which generated smaller drops jl *J than the hydraulic nozzles) resulted in a hydrogen LFL of 7.2% at 20*C.
- 2. Increasing temperature causes large increases in the hydrogen IEL in the presence of water fog. For a typical hydraulic type fog nozzle used in the project, the hydrogen LFL increased from 4.8 vol % to 7.2 vol % and to 7.6 vol % (based on dry hydrogen-air mixture) as initial temperatures increased from 20*C to 50*C and to 70*C. This increased inerting is due
~~i j in part to water vapor dilution and in part to liquid phase water heat sink effects associated with rapid vaporization of the smaller drops at i elevated temperatures.
I
- 3. Fog densities required to achieve a given level of hydrogen inerting are strongly dependent on the characteristic drop size of the fog. For ex-a ample, reqaired fog densities increased by an order of magnitude (frem
-4 3 -3 gm/cm 3
-gas) as volume mean drop diame:er in-10 gm/cm -gas to 10 j
creased from about 20 to 100 um. y
'I t
i 4 k f j 5-1
~ - .
n... ,
. . a.s.- - u a. -
l i .. 2. u. . --- a. a u'. ~ t REFERENCES l
- 1. M. Ber. nan et al. " Analysis of Hydrogen Mitigation for Degraded Core
- Accidents in the Sequoyah Nuclear Power Plant," NUREG/CR-17625 and 80-2714, March 1981.
fh 2. M.J. Sapko, A.L. Furno and J.M. Kuchta. " Quenching Methane-Air Ignitions I with Water Sprays," Bureau of Mines Report RI8214, 1977.
>J'
- 3. D.E. Magnus, et al. " Sensing of Droplet Size and Concentration in Pollution Control Equipment," Proceedings, 4th Joint Conference en Sensing of Environmental Pollutants, American Chemical Society, 1978.
) 4. J.D. Stockham and E.G. Fochtman, eds., Par-icle Size Analyses, Ann Arbor Science,1977.
i 5. W.D. Bachale. " Method for Measuring the Size and velocity of Spheres j .l by Dual-Beam Light-Scatter Interfarometry," Applied Optics, g , i p. 363, 1980.
]
- } 6. H.A. McLain. " Potential Metal-Water Reaction in Light Water Cooled
.! Power Reactors," CRNL-NSIC-23, p. 90, 1968.
4
~!
- i a .
1 I r ji I i. 3 ! I 1 !.i 4 f I s I e l l
.i 6-1
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g._ d w J .1- .id',O S [,f U C h . ,J.,-;f. ;,g ... i 1. fL3 .; de . . 4 9
. 9
'.7, t 1 n e APPENDIX A i I
.j ;1
SUMMARY
OF EXPERI.%TIAL CATA
<1 '. l u -1 a
i 4 1 1 i i 4
.1 l
JJ~4 1 I f
)
I
. t.
i l
- l.
-t f
f j 4 9 s t 1 4 i e
-?" - - e . - _-
.au ,e: c.:. .. s, n . m.:.e . .-. ._ . - . _ ! . . . . Ca.. .'L.m__,.,... . . .s . . m i __a .; . . _ 1 .. , - a_, g, ,_g.m_,ca. - '
WATLk FOG INLkTING OF HYDNOGEN-Alk MIEV>kES .}. Concentration . pi ens t e.r 3 3 (ca styO/cm ala) h .' p Ave. Water Water Based on it -Air Flow L.. Flum Vg based on 2 g Water clu/ing edell Spray Number Sauter W. 3 V based ou Mtu 2 ramme Press. Flw kun -' ' " Temp. Nan Vol. N an Mean Median Collection F1w Conc Propagation Nomale (pall (cc/ min! (cc/ min! (*C) (cal (ca) (cm) (p) cm '[(mini t h t ).od (1/m) (volt) (Yes/pki)
-2 auli 10 350 160 20 5.61m10~ 1.36m10~ 2.52m10 1512.1 1.04 1.51 10'* 4.45m10~ 20(air) - -
20 545 180 20 3.97ml0' 1.1 al0" 2.24x10~ 1031.9 1.17 5.44x10 2.21 10 1.73m10' 10.42 4.03 m
~3 -2 -2 2.69ml0 1.54x10~ 10.42 No 25 480 It,0 20 4.37m10 1.1410 2.27m10 1111.8 1.04 6.6 mio 4.03 3
30 550 173 20 4.70mli 1.15 10' 2.71x10' 1481.8 1.12 7.97m10' 1.69x10" - 20 - - SPkACO 30 540 luo 50 3.59mlo' 9.18 10 1.88m10~ 11.521.7 1.17 7.96m10 2.02x10~ - 10 - - '. 40 540 150 45 2.91m10' 8.78x10' 2.01x10~ 9.611.7 9.74m10~ 1.33m10' 3.22x10~ - 10 - - 3 1405- 20 540 100 53 3. 33 mli 9.11 10 1.96x10~ 1011.5 1.17 1.15x10' 2.88m10" - 10 - - . 30 550 173 20 4.21 10~ 1.1 mio" 2.2 al0' 1481.8 1.12 6.94ml0~ 3.27m10 1.66m10 10.42 4.03 No 20 545 160 20 3.97m10~ 1.1m10" 2.24x10' 1011.9 1.17 5.44x10~ 2.21:10~ 1.72m10~ 10.465 4.44 No 25 4gJ 160 20 4.37x10~ 1.14 ali 2.27mlo" 1111.8 1.04 6.6 m10" 2.6vm10~ 1.53x10~ 10.465 4.44 No
-3 30 550 173 20 4.2ia10 1.1 x10~ 2.2 al0' 1111.8 1.12 8.94m10~ 3.27x10- 1.65x10~ 10.465 4.44 Ho y 20 545 160 20 3.97m!O' 1.1 x10' 2.24x10- 1011.9 1.17 5.44x10 2.21 10~ 1.71m10~ 10.535 5.07 Yes
-2 25 400 160 20 4. 37mli 3 1.14m10~ 2.27m10~ 11:1.8 1.04 6.6 m10' 2.69m10~ 1.52m10 10.535 5.07 Yes
-2 30 550 173 20 4. 21m li 1.1 alo" 2.2 m10 1121.8 1.12 8.74x10' 3.27m10' 1.64x10' 10.535 5.17 No .
~3 30 550 173 20 4.21 10 1st m10~ 2.2 alo" 11 1.12 8.94ml0' 3.27m10~ 1.64m!O~ 10.575 5.44 Yes [
30 540 180 42 3.59m10~ 9.38m10~ 1.88x10~ 11.521.7 1.17 7. % s10 2.02m10' 1.70mli 10.575 5.44 No 30 * " 44 " " "
- 1.70ml0~
-2 10.575 5.44 No (
30 " " 45 " " " " " " 1.70x10 10.6 5.66 Yes [ ' }. 25 480 160 44 4. 7t.m 10' 1.15 30
-2 2.21x10~ 1411.8 1.04 7.w7x10' 1.69ml0 1.51x10~ 10.6 5.66 Yes b' 25 " " 44 " " "
1.51x10~ 10.575 5.44 t;o 40 540 150 39 2. 91 mli 8.78m10~ 2.01 10' 9.611.1 9.74 1.33x10~ 3.22 10~ 1.42m10- 10.6 5.66 Yes [. 40 " " 47 " " " " " 1.42m10~ 10.575 5.44 No k
~
30 520 173 20 4.76mli 1.15m10~ 2.21:30~ 1411.8 1.12 7.97m10
- 1.69x10' 8.65m10 20(alr) - No .
~A 10 350 160 20 5.61m10 1.36x10' 2.52m10~ 1582.1 1.04 1.51x10' 4.45m10 7.64m10' 20.95 4.53 No t;
10 *
- 20 * * * * " " "
7.62m10~ 21.00 4.76 Yes '( 10 - - 70 - - - - - - - ~ - 6.1 Yes .. 10 - _. 70 - - - - . -. - 5.66 No . . 20 - - 70 - _ - - - . - - - 6.54 Yes p/i I 20 70 6.1 No p. 30 - - 70 - - - - - - - - - 7.83 Yes O 30 - - 70 - - - - - - - - - 6.98 No I$ 40 - - 70 - - - - - - - - - 7.83 Ym y 40 - - 70 - - - - - - - - - 7.41 No e if.
-- .- . - _ . . _ L w.' _ ,.; _ ;;r
~ '
" ~ .~
~ ' " ' '
"" m7-s
,;~,-
3..%--.-
- m. u ..
I f WAttH FOG 1hLatiteG C7 ItVDid!!.k.84-AIM MIX 11J10.5 (Continued) t Concentration 5 Diameter (ca 4tyO/cm min) , f f I' Wter based on Ave. W ter Vg based on g,2,gg, Flum y riow. Ex-3 V based on Mia 2 Flame l cluding Wil Spray habur Sauter No. Wates ** *^ Collection riow Conc Psopagation Ps ess. Flow temp. Nan Vol. Mean was. Median I sun-ott (col (c ) (p) cm (min) Mett.od (1/m) (volt) (Yes/No) ('c) t
; nosate 4e 8 ) tec/eln) (cc/ min) (cm) 4
- 1. ll m10' 2.22:10~ 9.821.9 1.04 10' 3.74m10' 8.11 10 810 20(Air) 10 JesO 16 20 4.24m10 3.2410' 2.41m10'# 3.7m10' 10.42 4.03 na 25 515 39 20 1.46ml0' 4.u910 1.50x10' 7.53m10' 2.53m10' 3.13x10' 2.73m10' 3.7m10 10.42 4.03 sao r stCACO 25 515 39 20 1.41 10 4.41m10' 3.08:10 6.421.4 20(Alg) - I i I"I ""*" 20 4.e4m10 2.06m10' 8.83x10 1.511.3 2.53ml0' 1.1 ml0 2.7tm10'* -
30 550 39 4 g mdel 216 3- 2.84alO 1.93m10 - 10(Air) - - y.
? '
7604 20 410 55 45 1.11:10 3.45ml0 8.18:10 4.611.4 3.57m10 ' 24 53 8.u7m10'* 2.14 10' 4.32m10 4.221.2 1.56m10' 2.71m10' 8.86ml0' - 10 ( Air) - - 30 590
~3 1.38m10 10(Air) - - . ,
1.u9:10' 3. 31mli 8.63m10 5.211.2 2.43m10'I 2.72m10 I 40 6uo 37.5 53 ' 3.541.4 1. 56 m 10' 3.52m10' 2.44m10 2.3 mio' 10.42 4.03 leo 30 590 24 20 1.08m10' 3.65ml0 9.59m10 55 20 1.74m10 5.45m10 1.31:1 8 4.711.5 3.57m10' 3.06 10' 3.83m10'4 5.3 al0' 10.42 4.03 No .
) 20 470 '$
5.26m10 10.465 4.44 No 20 470 55 20 1.74m10' 5.45m10~ 1.31mli ' 4.711.5 3.57ml0'I 3.06 10' 3.83m10 3.73m10 10.465 4.44 leo ;. 25 515 39 20 1.41m10 4.41 10~ 1.08:10' 6.481.4 2.53x10' 3.13 10' 2.73m10 2.3 x10~ 10.465 4.44 No I .*. ; 30 590 24 20 4.u410'* 2.06m10 8.83x10' 1.511.) 1.56m10'I 1.1 al0' 2.76ml0 20 1.74m10
~3 5.45x10
~3 1.31m10' 4.741.5
-5 3.57m10'I 3.06 10 3.83m10 5.22 10'I 10.535 5.07 Yea .'
7 20 470 5' 2.53ml0'I 3.13m10' 2.7 3m10'# 3.73m10' 10.535 5.07 Yes [ 25 515 39 20 1.41 10' 4.41m10 1.Ouml0' 6.421.4 2'l 4.04 10 2.0610' 8.83m10~ 1.511.3 1.56m10' 1.1 m10' 2.76m10' 2.3 m10' 10.535 5.07 Yes p. 3 3d 590 24 55 50 1.11 10'3 3.45m10 8.19:10' 4.611.4 3.57m10' 2.u4x10~ 1.93m10 5.2 m10 10.575 5.44 No - 20 470 f " * - " " * " " " 5.19 10 10.6 5.66 Yes N 20 50 4.211.2 1.56m10' 2.71m10 8.06 10' 2.26m10' 10.6 5.66 Yes [
- 30 590 24 50 e.u7m10'4 2.1410' 4.32x10'
= " " ." "
10.575 5.44 No
- 30 " = m * = "
5.241.2 2.43m10'I 2.72m10' 1.38m10'* 3.54x10' 10.6 5.66 No 40 660 37.5 51 1.09:10' 3.31 10' 8.63m10
- " * * * " " 3.52x10' 10.650 6.1 No
.:
- 40 50
* " " " " " " " 3.50m10' 10.7 6.5 h 40 So
" " = " " " " " "
3.49m10 10.75 6.97 No [ 40 50 40 -
- So " " = " * " " 3.47m10 lo.tso 7.41 Yes f
-3 4.32m10' 4.211.2 1.56m10" 2.71m10 8.06 10 1.14m10' 21.050 4.99 Yen [
30 590 24 20 e.87sto'4 2.14m10
* " " " " " " " 20.900 4.31 No f 30 - "
20 2.22m10' 9.881.9 1.04 10' 3.74m10' 8.11 10 7.6 ml0 21.050 4.99 Yam 10 380 16 20 4.24m10 1.14m10
" " * * " "
- 7.50ml0 18.100 5.21 Yes 10 *
- 20
* " * * * * *
- 7.61m10'* 21.00 4.76 Yes 4
10
- 20
" * * * * * *
- 7.63m10"* 20.950 4.53 Yes la "
20
' *
- 20 " " * " " *
- 7.66m10' 20.900 4.11 No . .
B0 1
. . U
_ _v -..s..
..n. ...._4
.~ ,_". .._. . ._, . u. _ 2 ,_m-, _ _
.< . m ,, , _
,, _..,':.. ~ ~
+
A;-%Wy ewiw-j
, (
. .e.
WAT1.k I'Lui IHt.HTlHG GF ltyp>0Q24- Ath H1311J143 (Cosittn'aeJ) t - I. t. Concentration [ ' Llan=ter (ca 883 0/cm min) Ave. Wter htst bened on 88 -Air Flow, l' a - Flum Vg Dased on 2 g Wter ciud1hg W11 2. pray had.es *. uter No. 3 Vg had a Mu 2 H ame Pream. Flow Run-Oti Temp. Nan Vul. Mean Maan Ndian Collection Flow Conc Propagation men s (ges t ) (cc/ min) (cc/ min) (*C) (cm) (cm4 (cm) (p) cm (min) 6 htl.od (1/m) (volt) (Yos/No) SPkACO 10 70 6.54 No I*P8 h95=ht 70 6.98 bes a44.1 2163 10 20 70 6.9d No 7604 20 70 7.41 Yes
,0 ,0 ,.41 ~ .. .
(
,0 70 7.83 ... p ,l '
40 70 8.25 W 40 70 8.65 3em , , s ;
~I 20 10 355 115 -20 6.07x10" 1.39m10~ 2.46ml0~ 1312.1 7.47ml0 1.11 10~ 3.62x10~ - - - 1
~
20 360 30 20 2.58x10~ 8.62m10 2.14m10~ 6 1.7 1.95mlo
-I 3.3 uto 8.45m!O
- 2.9 m10~ 10.42 4.03 m LPHACO 25 500 30 20 1.65m10" 5.84x10~ 1.67m10' 4.821.5 1.95m10 2.44m10 2.89x10 2.9 m10~ 10.42 4.03 do 30 550 34 20 1 22m10~' 4.2 m10~ 1.17m10' 4.511.3 2.21 10~ 1.21:10~ 1.1 m10~ - 20 - -
3 rane Slamy 40 635 35 50 8.33x10~ 2.45m10' 5.75ml0 3.841.3 2.27x10"I 2.61x10~ 9.33m10~ - 10 - - .. I 5 -4 ! n aal 2020- -4 - 10 0 555 36 65 8.85x10 2.71x10 -3 7.26x10 ) 4.211.2 2.34x101 2.94m10 1.1410 - - - 1704 ~4 20 455 50.2 1.72m10
~4 5.02ml0
~3 1.11 10~ 6.211.5 2.ols10
~I 3.6 x10 a ml0 3.1 x10~ 10 - - !P" 31
-3 5.681.7 2,34x10~ 1.53x10 3.45mlo" 10.42 4.03 No 30 500 36 20 1.72mlo" 3.57m10 5.91x10 2.35x10~ N 20 460 30 20 2.18m10' 6.79mlO~ 1.68m10" 641.7 1.95m10~ 3.19x10 5.11 10~ 2.9 m10~ 10.42 4.03 No ). (
~3 -I 5.11 10~ 2.87m10~ 10.465 ra 20 4e 0 30 20 2.18 10~ 6.79m10 1.68mlo" 621.7 1.95mle 3.19 10 4.44
~
25 500 30 20 1.65x10 s.84x10 ' 1.67x10" 4.811.5 1.95m10"I 2.44x10~ 2.89x10~ 2.87m10~ 10.465 4.44 No E.
~
30 %0 36 20 1.72ml0
- s.57m10~ 5.71x10" 5.611.7 2.34ml0"I 2.35m10~ 1.53x10~ 3.44x10~ 10.465 4.44 No .,
20 4LO 30 20 2,18 10~ 6.79ml0~ 1.68m10" 621.7 1.95m10~ 3.1910~ 5.11 10~ 2.85mlG 10.535 5.07 vem hj-25 500 30 20 1.65m10~ 5.84m10~ 1.67mlu' 4.881.5 1.95x10"I 2.44m10 2.89m10 2.5 ulo 10.535 5.07 You f,. 10.535 No I,b I I' 30 560 36 20 1.72x10~ 3.57m10~ 5.91mlo" 5.621.7 2.34x10~ 2.35x10 1.53m10 3.40m10~ 5.07 l 30 500 36 20 1.72mlo" 3.57mIO' 5. 9 h l 0' ' " 2.34m10~ 2.35m10 4.53mno 3.40ml0~ 10.575 5.44 You [ ! l 40 635 35 47 8.33mlo 2.45m10~ 5.74ml0~ 3.811.3 2.27m10~ 2.6tx10 9.33m10 3.32x10 10.535 5.00 No 40 " " 51 * * * * " " " 3.31m10~ 10.565 5.15 No
- 40 " "
53 " * * * " " " 3.31m10 10.575 5.44 No
- l 40 " "
51 * * * * * *
- 3.29m10~ 10.650 6.10 No 4 j f'
~
40 * " ou * * * * * * * " 3.27m10 ' 10.70 6.54 W 40 -
- 47 * * " " " " "
3.26x10~ 10.750 6.97 m j
- a " * " * " " "
3.24m!O
~' 10.800 7.41 ye z . ;
40 dl 4 O a J l L. I i
..u .
~ -. :.L
_.4 . ..- - - 6 , , s s ...%._,% .. .. ..a m ., ..L - .. .a,..
. ..a . .a-- % L. + web. - - -. _ d 'w....-- * ^' ' ' '
- k.L .
I t
' WATEh tM 1ht'kTING (W NYbhobLN-AIR MIXTUhES (ContanucJI Concentration Diemuter (ca'88 0j"" *l'i 2 ,
Water bened on Ave. Wates Based on 2 t'l um Vg Flow, an- Flaw Based w Him 2 water ciudh.3 Wall f6' ray Hundse s Sauter m. 3 V, Collectlon Flow Conc Propagation {' , { Run-Off Temp. Nan Vol. Mean Mean Med as s Press. Flow (*C) (col (cm) (ca) (p) cm (min) t htigad (1/m) (volt) (Yes/No) 1 I Nwaale (pell (cc/ min) (cc/misd u.u5alo 2.71a10 7.26alO 4.211.2 2.34 10' 2.9 al0 1.14m10 3.33m10 10.000 1.41 Yes b
. bekACO Ju 555 36 60 3.33m10~ 10.750 e.97 No .
lio!!w 33 . . ,g 5.0210' 1.11m!O' 6.211.5 2.01 10' 3.6m10 4 al0 2.87a10' 10.000 7.41 Yes
$ sy 20 455 31 40 1.72m10' 2.88ml0~ 10.750 6.97 Yes mdel 2020 20 " " 41
_3 1704 2.9 x10 10.70 6.54 . Yes 20 " 43 No f 2.91x10 10.650 6.10
*
- 52 20 30 550 34 20 1.22a10' 4.2 mio~ 4.2 m10' 5.611.7 2.21 10' 1.21:10" 1.1 m10 1.7 ato 5.49x10" 20(als) 20.950 4 53 m f'
b 10 355 115 20 6.07a10~ 1. 39mli 2.46m10' 1312.1 7.47m10'I 1.11 10' 3.26ml0 j 5.48m10' 21.00 4.76 na lo 20 ; 5 3.2 ml0' 9.4 mlo' - 20 - - l ,'
-10 20 5.45x10~ 1.36ml0 2.59m10' 1382 -
32 2.0910' 5.b9m!O' 1.33 10' - -
- 11a10
. 9.15x10 10 k
>. 2u 3.42x10'* 10 f, 25 32 2.3 miO~ 5.69mlo 1.12:10' - - 2.62mlo b SPMACO 30 20 2.17a10
~
6.35m10' 1.52x10' 6.421.4 1.42m10 1.07 10 20 h' ing 20 59 15.5 el 1.5 m10' 4.32x10'
~
9.83x10 ' 4.921.7 lalo' l.15x10 9.11 10 1.55m10~ 10
" 3.14alo" 3.311.13 1.52m10 7.77m10~ 1.(4m10~ 10 l ~ 10 76 23.5 40 6.25alo 1.52m10 2.08 10~ 321.06 9.74x10~ 1.34x10~ 1.68x10' 10
; 40 85 15 47 5.35ml i ' 1.12m10' '-
~
3.33m10' 3.16m10' 1.7 3a10' 10.42 4.03 No 30 ?) le 20 2.06m10 4.7dm10' 9.1 ml0' 6.411.4 1.17m10 20 2.04 10' 5.93ml0 1.36m10 521.8 2.21m10' 4.61ml0' 6.05m10' 3.3 miO~ 10.42 4.03 No 20 60 34 20 6.0 al0~ 1.3bx10' 412 1.62m10~ 3.09x10 5.72 10 2.4 m10 10.42 4.03 No I J5 74 25 2.4 alu 511.8 2.21 10" 4.61mlo' 6.05 10' 3.25x10~ 10.465 4.44 No 40 to 34 20 2.04a10~ 5.93m10' 1. 36 m10' 20 2.4 alo 6.6 mio" 1.36m10~ 1.64x10' 3.09m10' 5.72mlo 2.39mlo 10.465 4.44 No b 25 73 25 18 20 2.06ali 4.7unti 9.1 m10' 6.411.4 1.17m10" 3.33ml0 3.16m10 1.72a10~ 10.465 4.44 No 30 73 20 2.04m10" 5.93mlo" 1.36a10' 511.8 2.23m10~ 4.11mli 6.05mli 3.23a10 10.535 5.07 Yes 20 00 34 20 6.6 ali 1.36m10' 4t2 1.62m!O' 3.21m10' 5.72ml0
- 2.37a10~ 10.535 5.07 Yes 25 ?) 25 2.4 ato I
- 2. 06m li 4.78mli 9.1 m10' 6.41.4 1.62ml0 3.33a10 3.16m10 1.70s10~ 10.535 5.07 Yes ,
30 13 18 20 1.07m10 1.23m10~ 21.0$0 4.99 Yes to 65 26 20 2.17alO' 6.35ml0" 1.52a10~ 6.411.4 1.69m10 1.42m10
* " " * * * ." " 1.24m10 20.90 4.31 No 30 (25 26 20 10 25 18 20 5.45ali* 1. 36mli 2.50alo' 1322 1.17ml0~ 3.2 ml0' 9.4 ml0 0.55mli 21.050 4.99 Yes
" " * " " *
- 8.61m10' 20.90 4.31 No be 25 18 20
- 10 J5 18 20 * " " " " *
- 8.57mli 21.00 4.76 Yes u.59aiO-4 20.950 .'
i! io 25 18 20 - . . . . . . ,So ,,, e, , 3 i ,
. , g-,-
i l
~~
y s7 . cy. t . , , eaj u. . - g+
..s.. .. , . . . ...a._.-.-.._a-...- . . . . _
}.
WATtH FOG int'kTING Or liYDNOtEH- Alh HIK1VIW.S (Concluded)
=
Concentration { 3 3 ( Dias =ter (ca H O/cm man) ; i Ave. Water Water basmJ on Flots. Ex- Flum Vg Bamed on ,,2 Water ~ cluding Wall Spsey Nus4=a Sauter N. 3 V Based on Mi n ' ,2 Flame h ess. F1w Run-Off Te ag a . Nan Vol. N an Mean Ndian Caltection rioes Conc Propagation Humals (pell fcc/ min) (cc/ min} (*C) (cm) (ca) (4;m) (p) cm (min) L Nothod (1/m) (volt) (Yes/Nul , SFkACO 10 50 5.21 Yes 1
- I I" 10 50 4.*t6 m Cons Misting 20 50 5.21 No b I I
~ 20 50 5.66 Yes 1605 -
4 30 to 5.21 % ... i. 30 r? ,
- 50 5.66 Yes "I 40 50 4.76 No 40 50 5.60 Yes g a. <
7.n; N 20 *I ~4 175 16 45 6.39m10 2.2 m10~ 6.87m30~ 2.311.5 1.04x10 3.21 10 1.08x10' 10
-4 h
20 175 16 52 5.99x10 2.44ml0' 9.64x10 2.811.07
- 3.18 10 1.1 m10~ 10 / ,
25 - - 53 6.2 ulo~ 2.4 ml0'3 9.Ola10' 2.411.2 " 3.34x10~ 1.1 m10 10 h TSONICOkE 20 175 16 20 " 1.48x10' 30.8 7.41 Yes u mdel 3515 20 -3 175 16 20 " 10.750 6.97 1.49 10 No .x-
~#
25 210 18 45 6.2 mlo' 2.4 m!O~ 9.03m10~ 2.411.2 1.17x10~ 3.34x10 1.1 m!O 1.73x10' 10.420 4.03 No .
; 25 210 18 44 6.2 m10
- 2.4 m10' 9.03 10~ " "
3.3 x10' 1.1 x10~ 1.86m10' 9.70 7.2 No *
~
25 210 18 45 6.2 m10' 2.4 m10 9.03x10~ " " 3.3 m10 1.1 m10~ 1.84x10 9.80 8.16 Yes - 25 210 ~4 lu 44 6.2 ano 2.4 x10~ 9.03m10~ " " 3.3 m10 1.1 m10 1.85m10~ % 35J 7.69 No g, 160 ~I 20 17 52 5.99x10 2.44x10' 9.64mlo 2.811.07 1.10x10 3.18 10 1.1 m10~ 1.58m10' 10.750 6.97 No a
~3 20 160 17 52 5.99x10' 2.4410 9.64x10~ " "
3.18x10'* 1.1 m10~ 1.57m10~ 10.800 7.41 Yen s 25 210 18 52 6.2 alo" 2.44ml0 9.03x10' 2.411.07 1.17m10~ 3.34x10 1.1 x10~ 1.84alO~ 9.8 8.16 Yee . J3 210 Its 52 6.2 al0~ 2.44ml0~ 9.03x10' " " 3.34ml0 1.1 x10~ 1.85m10' 9.750 7.69 No kk b . '.i y, ?; r. I 4 e. e, [.' t e s
' - tc, i,
4
_ _ _ _ _ _ _ _ _ _ - _ - - _ - - v------W^"--'" - g 9,g,49h , m O M * ' _. ,,. --. 'd,U/mJid wb SN l' * * *18 "-**d'
. ****M=* "' "'*** *'*" '# * '" '" " ~~
9I ,1 .( v.'.A I APPDIDIX B
. LOG-NCRMAL DRCP SI::I DISTRIBUTICNS J
.1 i
)
i i l1 t
.i i
i i I i. 4 i 0 0 e i
. l j.
i s g i.1 i e t l 1 t 9 i e i
- 4. '
. . . , _ ,;ema - , e.c21:9. ;wi .,,;, , : _.,m _. a
. _;.,,,.,_,.,_,, _ ., ,. ;;as
- s.
r-
- + .
'! ! 3 i i i i i i i i
- .- 10 i i i i i i a - ~~)
dI -
]
J Nozzle: Spraco 2163-7604 Nozzle Pressure: 20 psi t. a Spray Temp: ~20 C
; - Probe Iocation: 35.5 cm below Nozzle Centerline 9 t
j , inside the Inerting Tube ,;
,J y 1
f 1.. 2 _ 10 -
"j _
.4 -
~j - 7 i -
-:s
.4 6 E
e i J. : a E o j .c - i I
,i 4
1, 10
- i I
.j -
I 4 , ', .1 i . e -. I i i 1
.j e i i i i I i i i
; i i ! I !
! I 1 5 10 15 20 30 40 50 60 70 80 85 90 95 98 i
Cumulative Percent Probability 4 t i 3- 1
~
gSp- , - , , ,a.e . y + y +w - e 4- -- - - -
- -- w ;c .e .
.._m_ __ _ _. n _ %.
)
~1
.1 3
- 10
_ i i i i i i i i i i i i g I J 1 1 Nozzle: Spraco 2163-7604 j Nozzle Pressure: 25 psi - f Spray Temp: ~20 C Probe Location: 35.5 c:s below Nozzle Centerline -; inside the Tuerting Tube [ ; - 1 i, I t 2 a' to - i 4 ,
- t. -
i
~1' i
4 E -- s :. _ I m I
- 3
=
t
, 5_ ' !
e Q
.! 1 I ' . ;
~
i i 10 _ 4 i _ _I i Lij _ i ' I i . 1 -
! l i l
,. i i [I:i i
; ' ! ! ! ! I I ! ! ! I I t a l
, ; 5 10 15 20 30 40 50 60 70 80 85 90 95 96 Cumulative Percent Prebacility ( I 3-2 ! I j
. ._ m..
? iesa! . in-' r.$ e kr.m - ' - 1 A'1'h , ih.OME hm
.s Z. ' . ~. . L . - l
. .w. '. ~ ..C a .. -m =
3 i i 10 i i i i i i i i l 4
'h, -
Nozzle: Spra co 2020-1704 Nozzle Pressure: 20 psi f Spray Temp: ~20 C
- Probe Iocation: .33 cm below Nozzle Centerline -,
inside the Inerting Tube j
- I
- 4. .
e A i 2 _ 10 . _ l _ l
~
- l-
! s _
4 2 _
~ i w
i 1 l 15 .
, o *
. 6 I
-) .
i { i
! 10 - -:
a - 1 _ i _
.i _
' l
, i . 4 1
'
- J t
i I I I I I i 1 I i i I i
! 96 5 10 15 20 30 40 50 60 70 80 85 90 95 Cumulctive Percent Procacility i
. B-3 Is
~~~ ~ ~ . -- _ . _ .
- 7. . .. ..
~'-
u_
.-9*,
i *
..]
I!
; .1 10 3
i i i ! i i i 1 6 i i )
]
i Nozzle: Spraco 2020-1704 I Nozzle Pressure: 25 psi j Spray Temp: ~20 C l Probe Location: 33 c:n below Nozzle Centerline -l inside the Inerting Tube i 4 i
' i 10 2 _ -l
-l i
a p =. _ 5 l 1 1 E .
'I o i,
4 1 { i l " iO 1, _ 1 .
.-j !
I l _ l, _ i - - t i I ! I i !
! t I I I I I I l 98 5 10 15 20 30 40 50 60 70 80 85 90 95 I Cumulative Percent Probacility 3- 4 l k i.
?
. . . . . . . . - - . _ . .. -._._a
7
- j ;, w ia ._w
-- _x - - !.ii 3
--j l 10 _ i 1 i i i i i i i I 6 i y
]
a q Nozzle: Sp ra co 1806-1605 l Nozzle Pressure: 20 psi
]
Spray Temp: ~20 C ] Probe Location: 33 cm below Nozzle a - 7
- I .
Centerline inside the Inerting Tubb, t I
- , j r
.. I
!{ 2 -
J
, 10 _.
i _
.: 4 I
i a -
!l . .m .
. i 1 , _ .
! e
$ */ _
l s 1
, , i
~
10 - t 4 i i ' 1, 6 t I ! I I I , t ! I I I ! I i 5 to 15 20 30 40 50 60 70 80 85 90 95 96 Cumulative Percent Procability i s.' 4 2 3- 5 _ m -,e4. - .. , . - .m=. .. . _.
--- - -e- . . - :o. , .~. n . ,, .. . . ,
- j
._- - . - a_ _ , _.
2,2,,,- _ _ _ , . . . c .- - 3 3._, 3 i i i 10 i i i i i i i a i
- 1,:: i t 1
J I Nozzle: Sp ra co 1806-1605
- Nozzle Pressure: 25 psi !
o Spray Temp: ~20 C i I
- Probe Location: 33 cm below Nozzle Centerline ii inside t.he Inerting Tube !
- 4. -
.i
' 2 -
10 e ,i
.l -
i _ .1 _ , e - 2 _ i
.~
o - i
~
'.T E
- ,i ._e , '
j -j c _ e e i 10 - ~. !.9 - ! - t _ l
. .I. _
i - l ' :'1 I-1 ; Ia
- 5 -
i l i t
- . i t
i * -
) _
i . .t ,- i I t i I .. I I ! ! I I I i ,, l 96 5 10 15 20 30 40 50 60 70 80 85 90 95 Cumulative Percent ProbcDility
! B- 6
< 6 4
+ ,p =g se+,+=**e = * . = > .-,-.a +-e-,..e , e ,,
* * - * = -meg-e-*- o== +
w e- *ai e-+
1
-u. ~.Sfa ssn. ,, t,,_m _, o c ,,,; ,,- ,;,3, , , , , , ,, .
4 ,,
- .1
[3 10 3 i i i i i i i i i tj _ i yJ a I
~
Nozzle: Spra co 1405-0604 J Nozzle Pressurs: 25 psi l j Spray Temp: ~20 C I Proce Location: 33 cm below Nozzle Centerlinc - 9 inside the Inerting Tube 'j e
- e. -
'1 :
- H. ,
3 i ti i 2 _; [ 10 e +
- O l.
e j .t j - :
.I
. g
- e i o -
i % - E ,
._c ,
t c - i i '.t *
-i j
- I il '
.; 10 _
- l 4'
i -
'-i e .
I I I ! t I I I II I I l 5 10 15 20 30 40 50 60 70 8C 85 90 95 98 Cumulative Percent Prcoacility
,6 Z
B-7
- n. -
__- _ _ _ . =
i -- - - . - ma.- ,, _, ,
~
C m a n w .:.a.a.: u. - ;.z-;. :_ _ _ 4
,.f u1 3 i i 10 i i i i i i i i i i
- 7
~
i,
~
Nozzle: Spraco 1405-0604
~
Nozzle Press re: 21 psi o Spray Temp: ~20C Probe location: 33 cm below Nozzle Centerline I i inside the Inerting Tube ;
. I Ji i
t , I I 2 _ 10
. q e
f-
- q. _
- i. _
l a !
. t i
E I e i 1
,' 3 i 1
1 1
,1 iO -
J , e i
+
4l I I I I I I I I I i i ! !
.i I
-t 5 10 15 20 30 40 50 60 70 80 85 90 95 98 Cumulative Percent Probability
.i 3- 8 i
h ..-. . . . . . . . . . . . . . . . . - . . . . . .. n
+ . > . . . . . . . . . . . . . . .
-,r..-s. a L na --= - e ..C..a. .. ._. -2_.s.t . _m; _, ,m;. ;_ .. ,;_., ,,_ ...
[I:! I ! ;. 4, \. . '1 3 i 10 i i a i i i I 4 6 ' ') _ i i _ II - G- ,
~
?I Nozzle: Spraco 2163-7604 ]_
~
Nozzle Pressure: 30 psi j i Spray Temp: ~20*C Probe Location: 33 cm below Nozzle Centerline _
- i j inside the Inerting Tube ;
2 . 1 1 p i i I 1
- { 2 _
i 10 _ . 1 4
- 4, -t, _
{3.
- 1 _ ,
l e d - e
.s -
. ; I
.t e
47 E l c . l
-O _
' t I.
i l
' l I
10 . _ l e 6 a l I i 4 J l i I f ? ! ! I I I ! I l 5 10 15 20 30 40 50 60 70 80 85 90 95 98 Cumulative Percent Probacility i
.t 3- 9
_ ... ; -a. .. - - - _ aa. - s. .
- { . . . . _ . ._ .
- . . . . .._. .-
- .1 l1 .
'!' 3 i i ,;a 10 i i i i i i i i 6 J,
. 6 J
.j Nozzle: Spraco 1405-0604 l Nozzle Pressure: 30 psi ' _ o ' Spray Ternp: ~20 C _ Probe Locacion: 33 cm below Nozzle Cancarline _ i inside the Inerting Tube a ( 'u ! r i i 1o 2 _ y f 8 - l su
- . i l
I i E
. e i 6 I
!, i t I i
l I
.l to -
.g - .
1 ,
. . i i
1 1 - 3 3 . I
'. i i I
)
i
+ _
- {.
.s
*t
- l, i
,j g i I ! ! t ! I I I I I
- 5 10 15 20 30 40 50 60 70 80 85 90 95 98 Curnutative Percent Probocility
^l
, B-10 f
*9 ."
.s . 1 a l'J 3 10 i i : i i i i i i i i a q 4 _j u i Nozzle: Spraco 2020-1704
~
J i Nozzle Pressure: 30 psi i o H Spray Temp: ~20 C I Probe Iocation: 33 cm below Nozzle Centerline ~ i g
,} inside the Inerting Tube '
t i , .,.4 . , i , =I, . 10 2 _ _j 1.) 1 - -; i m s I. i = -
! Is ,
! E i j .2 *
; o 1 1
' \
j 10 - . , r I l i = i 9
- I I I I I I I I I I I !
- l 5 10 15 20 30 40 50 60 70 80 85 90 95 98
- Cumulative Percent Probability 3-11 i
I.
- - a. , ,.- .- . .: . -n. . - .- -~ .: - .uu .. -, .
s 3
,-- 10 _ i i i i i i i i i i I i 8 q
, I Nozzle: Spraco 1806-1605 Nozzle Pressure: 30 psi j
~
~
Spray Temp: ~20 C Probe Location: 33 . cm belosa Nozzle Centerline _I s inside the Inerting Tube j l i i 10 2 _ q
~
_ a i Q- a -
= - < I -
j e e - -: i t
; I 4 o
- t i
5 1 8 I I I l ! i,
- l0 -
4 e ; j _ l -
.i I * -
j _ 9
~ I.
'l
' t i ! i I ! t ! I i ! !
' I 5 10 15 20 30 40 50 60 70 80 85 90 95 95 Cumulative Percent Proccoility 3-12 i
. - . . . _ _ _ . . . . . . . . _ . . .. .. . . _ . . . . __ . _ _ _ .._..s_. _.
- . -- -,. ,;_- - wa_ . _ . . _ . _ . _ _ . _ .
.L , .i..
N.- , i' 3 ,- 10 i i i i i i i i I I i 6 3
- - i _
- 0 -
- 1 Nozzle: Spraco 1403-0604 i.
Nozzle Pressure: 20 psi i
~
Spray Temp: ~ 530C _ Probe Iacation: 33 cm below Notzle Centerline _ 4
;;) inside the Inerting Tube l
a 2 _ _ 10 ,
, _ m 1 - 4
- 4,
. ~.
t
'il a i
i
-.j q q -
1 - .
.I. E !
! .2 .
Q '
'j _
.e.
d.. d 10 > c'I. _ . - j _ - I I s 'i . i . i l
',,1 e
i
; I I I I t i t ! 1 ! I I
' o*
'I.
5 10 15 20 30 40 50 60 70 80 85 90 o8
, Cumulative Percent Probability i
.)
1 k
! 3-13 t
t. l _. . . _ . . ,- . . . . . - . . - . . . . . - . . , . . .. . . . . ... ..- _.
- -wuw-.- .
~ . .....-. ---
.I ,
3 i i i 10 - - i i i i i e i 1 4 _ _j I
' ~ ,, ~
Nozzle: Spraco 1405-0604 ~ 1 Nozzle Pressure: 40 psi I Spray Temp: ,v 4 50C Prot,e Location: 33 c=i below Nozzle Centerline _ inside the Inerting Tube .
. l 1
l , -j . 2 _ _; 10 F
- 9
.. - q l
- i
., ?
e s B S e
~
G *
- l. I e :
; e j 5 _
e i i . .
- '. 10 9
~
1 . t , i - t -8
~
l \ - I
- e -
P, ; . , t
! ~
! :i - l 1 i 1 1 ! I I I I l l 1
-! I 1 4
1 5 10 15 20 30 43 50 60 70 80 85 90 95 98 a Cumulative Percent Probooility i l s 3-14 i a 4 - _ . , - . . . _ . _ . . . . . ,
+w -
,. 3 ., - .. ,
..u. . - .-
3 i 10 i i i i i i i i i i 6 6
- -1
_ q I
- i Nozzle: Spraco 1405-0604 ]~
Nozzle Pressure: 30 psi l Spray Temp: ~505c Probe Location: 33 c:a below Nozzle Cen:erline - inside the Inerting Tube ! e !
.1 'i . !
I 1 1 2 _ , 10 - 3 _ j _ t J _ J s . I a _
- I
. e -
1 ;; _
- I 2
s . J
; . .e.
i
, O -
l l q
.10 -
- 4 i l
1 4
, I I I f i I i t ! l ! ! i I
5 10 15 20 30 40 50 60 70 80 85 90 95 98 Cumulative Percent Probacility i 1 3-15
. _ _ _ - ._ _. . . _.,.. . . _ . . _ . _ . . . . - . _ _ . . , _ _ ..~ g. .-.. , , , . . - . . . _ _ , , -
~ ~ -- - .:-. . .. .
6- - - A- =.J-- - - -
.., _,,,g _,_,-
r .
; i 10 3
i -i i i i i i i i i q J
- t Nozzle: Spraco 2163-7604 l t
Nozzle Pressure: 40 psi - i
~
Spesy Teatp: 530C Probe tocacion: 33 cm below Nozzle Centerline _l n inside the Inerting Tube ,
~ s.
i i i 2 _ 10 y _ J
' l s -
2 %
~ i w ,
e - g
.2 i O -
4 l
-l 10 -
i 1
.'l
' - . i
'l .
i i _ 1 i I i 1 1 I I j i i ! I I g 15 20 30 40 50 60 70 80 85 90 95 98 l 5 10 Cumulative Percent Probability i l- B- 16 3'
' .iI I
~ . - -- - -.- ~ .... .. . , , , , _ , , , ,_ , , _ , , ., _
n
- -. .a :...= . - - _ _ . . . ......:. . ... ... .. ... . _ _ _ .
a, 3 d i i i i i i J
, 10 .. : : i d
- 1 I
~
~ Nozzle: Spraco 2163-7604 l
- ); _
Nozzle PreJsure: 30 psi
~
l
~
Spray Temp: ~53 C Probe Location: 33 c:n below Noz:le Centerline
. l inside the Inerting Tube ,
I i l t i 1 . ; i
.) '. . ! io 2 .I _
H - H
~
3 s
*i ,, i 1 h l i 8 .. ,] ;; ,
I E : I .E i
; o I l .
i i t . 6
+
to t 1 q -
' I l .
l' - k e l 4 I i I I ! I I 1 1 1 1 I i I i i 5 10 15 20 30 40 50 60 70 80 85 90 95 98 Cumulative Percent Prebacility I 3-17 i i- -
= = _ - - _ _ _ _ _ _ - _ _ _ _ _ - - , - - - - - -- - - . .
. . . . . . .- , . . n. . . , _
- i. . s. .., ; - .. : a ;.:..~ . - --a.-w..._,..._.. -
t i .
- 1. -s 10
- i i i 6 i i 1 i I y
- t. -
l i -
~
< Nozzle: Spraco 2163-7604
~
l Nozzle Pressure: 20 psi Spray Temp: ~ 450C
~
_ Probe location: 33 cm below Nozzle Centerline _, inside the Insrting Tube .I 1 J . 4 2 1 10 Q . i - l 1 -
. i s a _ ,
~
. l.
1 E 2 11 1
.0 _' l 6
l
,)
4 i
'1 i
. ,i 10 -
i - d i l i l J I
- 1 i
4, _ t i l i i f f I ! ! ! ! I i I I l 1 5 10 15 20 30 40 50 60 70 80 85 90 95 98 l
- Cumulative Percent Probability 9
4 3- 10 { t i, N' '* "* 4 +6SS w amvs +.we ,g g .g g , ,g,g,, ,,
. -. . . . . . .- ., .. :. . . _ m . :. . . . . _ . . _ . .._. _ . _ . . . . . _ . . . . .
a. [l - 3 _j
- j ,
10 _ i i i i i i i i i i
~
Nozz!a: Spraco 1806-1605
]
Nozzle Pressure: 30 pst j 5
"~
Spray Temp: ~400C
'j _
P:obe Location: 33 cm below Nozzle Centerline _
'] inside the Inerting Tube f> ~1 -
i t
-- l 2 J
.i't 10
==
f, 'h - 1 _
- a ~
1 a _
.,\ .. i.
i E i t e 3 _ i i f t
- l 10 _
- . i J
^1 f
. I
-4 _. i _ m
,s i
i i ! I f f I I I i 1 ! ! I 5 10 15 20 30 40 50 60 70 80 85 90 95 98 Cumulative Percent Probability 4 B-19
?;
~ -u .: a_- _ _ .
..t. .
;' o i
't 10 i i i i i i i i i i .I t.
f. m
=
_J
~
Nozzle: Spraco 1806-1605
~
Nozzle Pressure: I.0 psi l
~
~
Spray Temp?. ~39 C j _ Probe Location: 33 cm below Nozzle Centerline __ inside the Inerting Tube f I t W
- r 1
2 _ 10 , _ q. l i. _ m l
. .i i
-a ._
i J i e - s
. i E '
! .2 o I i
I i 1 i
.4 .
10 1 o}, _ , J I ! i i , t . I f i ! l _ J t l 1 i i i i I i e i i i ! I I ! ! I lii 5 10 15 20 30 40 50 60 70 80 85 90 95 98
, Cumulative Percent Probability
, i 3-20 I
, _._m-a
2 . ,. . _ _ .. _ . a
. - ~ . O n,^ eo a. a. ._s .s. .. -.u ._ . .._, .w....,. . .ee....
. i i.
- 10 ' i i i i i i i i i i i i i _
~
l _ i _ Nozzle: Spraco 1806-1605 - { Nozzle Pressure: 20 psi ; I
~
Spray Temp: ~43 C f _ Probe Incation: 33 cm below Nozzle Centerline ] inside the Inerting Tube 1 a.. _ + 1 i
. I 10 2 _ y
,9 -
. I 1 J; a .
- i
.e. _ -
.., e
- i t E i 4 e !
i 5 m i i ! I ;
.; i 1
i 10 7-j _ j _ -
- ~
- i. --
I i i
- . i
.; _ .a e
i . i 1 1 i i ! ! i ! I i ! ! ! l 5 10 15 20 30 40 50 60 70 80 85 90 95 98 i Cumulative Percent Probacility 3-21 r . y g-m m 4
= ~
-me s nv e e .ve. m a
- u-. . . n.._ ... . . . , ,
' .. :.:.__ w ..= ? - -_,- _ _ _ _ u ._:_ . _
s :; e4 .
- fl
'4 10 ' - i i i 'I i i i 7 I I i i 1 s'
~
j Nozzle: Spraco 2020-1704 9l Nozzle Pressure: 20 psi
~ 0 Spray Temp: ~50 C ,
- Probe Iocation: 33 cm below Nozzle Centerline -
i
! inside the Inerting Tube l i.
i t e
! 2 _
10 - o - I I
+ 1, 2 _
~
E l
' .9 l I C i ,
I I 10 t i.
' I.
>j .
+4 '
.I I
i i, - l 4, I I I I I I I I I I !
. I I l 95 98
}
5 10 15 20 30 40 50 60 70 80 85 90 Cumulative Percent Probability 3-22 i
. . - - _ _ _ . - _. . . . . . . . . . _ . . . - _ . _ . ..____..__......m._sx._
. ' .I 4' '
' # l 10 i i i a i i i a i i I
~
Nozzle: Spraco 2020-1704 -
~
Nozzle Pressure: 30 psi l
~
~
Spray Temp: ~ 65*C Probe u cation: .33 c:n below Nozzle Centerline -
- i inside the Inerting Tube l
' l 1 .
a d 4 l, 1 i
~
iO 2 _ H
- i, 1 _
J
=
E e b - _I
< ,i
'I l ~
- l 10 -
J; 1 i- ,
- ! 4 i
i - t . l
- I q s i
6 e - 2
.i 4
' ! I 1 I I I I I I I I 1 !
I 5 10 15 20 30 40 50 60 70 80 85 90 95 98 i i Cumulative Percent Probacility
; 3-23 i
2
,~. ~ ., ..v u . .a .
^
. m.2. ,, .. ., . ; :. . . . _ - . . , , .
,;. . m .;.;2.,___.. _: w -
.- -; . - - ;L :e M 3 ' '
!l 10 _ i l i i i i i I I 3 I d
-)
i Nozzle: Spraco 2020-1704 l Nozzle Pressure: 40 psi ! o ~ Spray Temp: ~70 C l Probe Location: 33 cm below Nozzle Centerline - 5 inside the Inerting Tube f a -
- f. :
. i 4 , .
>I- !
2 a
! 10 J
i , - l.i
. I e; .
s .- e
. =. i i w
, o _
i % - E :
.2 i c -
; i I
i 1 ! 4 1
<' t
; lo -
_ . i l
\ -
I a 1 I j .. i 4 i i i 1. t i i i i i i I I I I 5 10 15 20 30 40 50 60 70 80 85 90 95 BS I Cumulative Percent Probability i
$ 3-24.
1
. ~ . . . - . . . . , . . . . . . , , . _
' = .--~;... -
. . . . - . . . . . . . . . . . _ . . . _ , . . . .._ i . .a.
'e
- 1 !
'1 1
* . 4
.;.j 10 i i i i i i i i i i i 6 _ !
~j _ ,
; _ )
"i
~
.d j
_ Nozzle: Sonicore 035H ]
- i Nozzle Pressure: 20 psi j i Spray Temp: ~45 C
~
I - Probe Location: 33 cm below Nozzle Centerline i 1 Ul inside the Inerting Tube l
';4 . a l
.J 2
.1
.4 .
.?
. .i 2
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4
! I I I
! I I ! ! ! ! ! 1 I
5 10 15 20 30 40 50 60 70 80 85 90 95 96 Cumulative Percent Probability i 3-25 y,
.-. 7,....~.
. .. ..- . . :. a - -
_, : -_.- ----mu 3 i i i i ' 10 i i i 1 i 6 i 8 d_ Nozzle: Sonicore 035H - Nozzle Pressure: 25 psi ; Spray Temp: ~53 C Probe Location- 33 - cm below Nozzle Centerline !
;: inside the Inerting Tube f 4
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l I
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I 15 20 30 40 50 60 70 80 85 90 95 98 l 5 10 l . j Cumulative Percent Probability k ! B-26 4 i
- - - ~ - - -- -
? . _ . . . . . . . . . . - - . . - -
-.- ;~~
2..... . ._. p ,- --
-- .. . . . . . _ _ _ . . . . . . _ . . .__. ___..__...,_.s.m> .. _. .
4 3 !j 10 i i i i i i i i i i _ _ i W,\
\
L Nozzle: sonicore 035H g Nozzle Pressure: 20 psi
.A J
4 Spray Temp: ~ $2 C j I l Probe Locacion: 33
'j
~ i cm below Nozzle Centerline j
i inside the Inerting Tube i
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! I I f 1 1 1 1 I I I I i
5 10 15 20 30 40 50 60 70 80 85 90 95 98 Cumulative Percent Probability i j 3-27 9
. . , . . . . . . . . ~ -
3 __
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' 3 i i i i 6 6 10 i i i i i i _
~
l Nozzle: Spraco 2163-7604 Nozzle Pressure: 30 psi Spray Temp: ~20 OC I t i _ Probe Location: 33 cm below Nozzle Cancerline - inside the Inerting Tube
~
a ' l. i. !)' ;o 2 _ _;
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I I I I ! ! 1 I I 1 I I l 5 10 15 20 30 40 50 60 70 80 85 90 95 98 Cumulative Percent Probability
.i
. 3-28 4
1
1...,._,......- ,e. . .i < , ~j i 10 3 i i i i i i i i i i 1 6 6 ': j i1 _
~
l Nozzle: Spraco 2020-1704 ; Nozzle Pressure: 30 psi Spray Temp: ~20 C l
- m
. Probe Location: 33 cm below Nozzle Centerline I i
inside the Inerting Tube ; m I .
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l !
- 1 I
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7 4
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t 10 - 9 l - i i l l
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1 I i 1 ! ! l ? I I I I l 5 10 15 20 30 40 50 60 70 80 85 90 95 98 Cumulative Percent Prceaoility
- 3-29 P
l 2
= = ,++ - e. .wa.
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- s Nozzle: Spraco 1*U3-0604 j J
i - Nozzle Pressure: 30 psi . l _ Spray Temp: ~20 C _ Probe Iocation: 33 cm below Nozzle Centerline . .,. ll e inside the Inerting Tube _] . i e
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h 4 I I I ! I I I I i 1 1 1 1
} ,
I 5 to 15 20 30 40 50 60 70 80 85 90 95 98 i Cumulative Percent Proboeility i
'e 3-30
'! 1
~ . - , . . . =_ . . . .. .. . .. . . - -
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