ML20072T440
| ML20072T440 | |
| Person / Time | |
|---|---|
| Site: | 05200003 |
| Issue date: | 08/30/1994 |
| From: | Peters F, Piplica E WESTINGHOUSE ELECTRIC COMPANY, DIV OF CBS CORP. |
| To: | |
| Shared Package | |
| ML20072T425 | List: |
| References | |
| WCAP-14168, NUDOCS 9409150210 | |
| Download: ML20072T440 (114) | |
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{{#Wiki_filter:_ _ _ - _ - _ _ _ Westinghouse Non-Proprirtary Class 3 WCAP-14168 CONDENSATION IN THE PRESENCE OF NONCONDENSIBLE GASES: AP600 CONTAINMENT SIMULATION September 1994 i ( l C 1994 Westinghouse Electric Corporation All Rights Reserved l l l ADO . 5 3 9 A
AP600 DOCUMENT COVER SHEET TDC: IDS: I S Form 58202G(5/94) lt:\ocatwpt1x) AP600 CENTRAL FILE USE ONLY: RFSt. RFS ITEM st: 0058.FRM REVISION NO. ASSIGNED TO AP600 DOCUMENT NO. PCS-T2R-040 0 Page 1 of WORK BREAKDOWN #: 2.6.6.3 ALTERNATE DOCUMENT NUMBER: DESIGN AGENT ORGANIZATION: Westinghouse Electric Corporation AP600 TITLE: Condensation in the Presence of Noncondensable Gases: Containment Simulation
. DCP #/REV. INCORPORATED IN THIS DOCUMENT ATTACHMENTS: REVISION:
l CALCULATION / ANALYSIS
REFERENCE:
ELECTRONIC FILE FORMAT ELECTRONIC FILE DESCRIPTION ELECTRONIC FILENAME N/A N/A (C) WESTINGHOUSE ELECTRIC CORPORATION 15L94 O WESTINGHOUSE PROPRIETARY CLASS 2This document contains informaten proprietary to Westinghou purpose for whsch a a furnished and returned upon request Thas document and such infortnation rs not to be reproduced, transmNted, disclosed or used otherwise in whole or in part without prcr written authortzaten of Westinghouse Electne Corporabon, Energy Systems Business Unit, subiect to the legends contained hereof. O WESTINGHOUSE PROPRIETARY CLASS 2CThis document is the property of and contains Propnetary In i suppliers. It is transmitted to you in confidence and trust, and you agree to treat this document in strict accordance wrth the terms and conddens of the agreement under which a was provided to you.
@ WESTINGHOUSE CLASS 3 (NON PROPRIETARY)
COMPLETE 1 IF WORK PERFORMED UNDER DESIGN CERTIFICATION OR, COMPLETE 2 IF WORK PERFORMED UNDER FOAKE. l 1 @ DOE DESIGN CERTIFICATION PROGRAM - GOVERNMENT UMITED RIGHTS STATEMENT [See page 2) Copyright statement: A license is reserved to the U S Govemment under contract DE ACO3 90SF18495 l
@ Subiect DOE CONTRACT to specified exceptions, DELIVERABLES disclosure of this(DEUVERED data is restnctedDATA) until September 30,1995 or Design Certificaten under DOE contrad DE ACO3-90SF18495, whichever is later.
EPRI CONFIDENTIAL: NOTICE: 10 2 3 0 4 0 s O CATEGORY: AO eO CO D E F0 1 2 0 ARC FOAKE PROGRAM - ARC UMITED RIGHTS STATEMENT [See page 21 Copyright statement: A license is reserved to the U S. Government under corf.ract DE FCO2 NE34267 and subcontract ARC 93 3 SC-001. O Subject ARC to CONTRACT specified exceptions, DEUVERABLES (CONTRACT disclosure of this data is rest % underDATA) ARC Subcontract ARC 93 3 SC 001. SIGN . ORIGINATOR F F potern kd / k ~'/ APPROVAL ATE i AP600 RESPONSIBLE MANAGER SIGfdT
- E. J. Piplica , 9, t
& b complete all required reviews are complete,4*ectro4c file i6 attached and document is
' Approval of the responsible manager signifies that docum reisased for use
Pcge 2 AP600 DOCUMENT COVER SHEET UMITED RIGHTS STATEMENTS Form 58202G(5/94) . DOE GOVERNMENT UMITED RIGHTS STATEMENT These data are submitted wtth Emited rights under government contract No. DE AC03-90SFt 8495. These data may be reprodu (A) used by the govemment with the express limisbon that they wil not, wthout wrtion permas4on of the contractor, be used for purp of manu acturer ror disclosed outside the govemment except that the govemment may 4 r disclosure: Thcs *Propnetary Data' may be disclosed for evaluation purposes under the restrctions above 0) (II) The 'Propnetary Data
- may be disclosed to the Electre Power Research Instrtute (EP restnciens above -
This notee shall be marked on any reproduction of these data, in whole or in part. (B) ARC UMITED RIGHTS STATEMENT: The propnetary data, fumished under Subcorarset Number ARC-93 3 SC 001 with ARC may be duplicated and used by the ARC. subted to the limaations of Artsene H-17.F. of that subcontract, wrth the express h the Subcontractor, except that further disdosure or use may be made solely for the following purposes' This proprietary data may be disclosed to other than commercial competitors ofi Subcontractor for evalusion purposes ofINs subc the ssstnction that the propnetary data be reta.ned in confidence and not be further disclosed. and sub ect to the terms of a non disclo agreement between the Subcontractor and that orgaruzation. excluding DOE and as contractors. OEFINITIONS CONTRACT /DEUVERED DATA - Consists of documents (e.g. specifications, drawings, reports) which are generated under the DOE or ARC contracts which contain no background propnetary data. EPRI CONFIDENTIALITY / OBLIGATION NOTICES NOTICE 1: The data in this document is subject to no confidernialay ob6gabons. NOTICE 2: The dat a in thrs document is propnetary and confidential to Westinghouse Electric Corperaten and/or its Contractors. It rs for to recipient under an obhgaten of Confidence and Trust for hmited purposes only. Any use, drselosure to unauthorized persons, or co this document or parts thereof ts prohibned except as agreed to en a3vance by the Electre Power Research instaute (EPRI) and Westinghouse Ebectre Corporaten. Recipient of this data has a duty to inquire of EPRI and/or Weshnghouse as to the uses of the informaten contaaned herein that are permrtted. NOTICE 3: The da!s in this document es proprietary and confident <al to Westinghouse E)ectne Corporaten and/or its Contractors. It ss forw to recipient under an obhgation of Confsdence and Trust for use only in evaJuaten tasks specifically authortzed by the Electre Power Resear Institute (EPRI) Any use. disclosure to unauthorized persons. or copying this document or parts thereof as proNbned except as agreed to in Recipient of tnis data has a duty to inquire of EPRI and/or Westinghouse as to the cdvance by EPRI and Westingnouse Eiedne Corporaten The document and any copies or excerpts thereof that may have been generated usss of the snformaten conta,ned herein that are permitted are to be returned to Westinghouse, directly or through EPRI. when requested to do so The da:a in this document is proprietary and confidential to Westinghouse Electne Corporaten and/or its Contractors. It is being NOTICE 4: revealed in confidence and trust only to Employees of EPRI and to certain contractors of EPRI This for kmrtedand Document evaluaten tasks any copies or authorized by EPRI Any use, discsosure to unauthor ted persons, or copying of this document or parts thereof a prohibnedexc Access to The data in this document is propnetary and confidential to Westinghouse Electre Corporaten and/or vts Contractors Any use, disclosure NOTICE 5: this data es given in Confidence and Trust only at Westinghouse tela.es for hmited evabaten tasks assigned by EPRI.Neither this docume to unauthorized persons. or copying of this document or parts thereof as pronibited be removed from Yvestinghouse facsht,es EPRI CONFIDENTIALITY / OBLIGATION CATEGORIES CATEGORY 'A' - (See Deltvered Data) Consists of CONTRACTOR Foreground Data that is contained in an rssued reported CATEGORY *B' - (See Deltvered Data) Consists of CONTRACTOR Foreground Data that is not contaaned in an issued report, except fo computer programs CARGORY 'C' - Consists of CONTRACTOR Background Data exce;;t for computer programs CATEGORY 'O'- Consists of computer programs developed in the course of performing the Worit CATEGORY 'E' - Consists of computer programs developed pror to the Effective Date or after the Effectrve Date but outside the scop the Work. CATEGORY *F' - Consists of administrative plans and administrative reports x l l
i Executive Summary ne Westinghouse Electric Corporation has designed an advanced pressurized light water reactor, AP600. This reactor is designed with a passive cooling system to remove sensible and decay heat from the contamment. De heat removal path involves condensation heat transfer, aided by natural convective forces generated by buoyancy effects. A one-twelfth scale slice of the proposed upper region of the reactor containment has been constructed at the University of Wisconsin to simulate conditions anticipated from transients and accidents that may occur in a full scale contamment vessel under a variety of conditions. Similitude of the test facility was obtained by considering the appropriate dimensionless group for the natural convective process (modified Froude number) and the aspect ratio (H/R) of the contamment vessel. De support suucture was constructed of steel and aluminum with a front and back face of clear polycarbonate plates to allow visualization of the developed flow pattems in the cavity. De test section incorporates the ability to vary the flow rate of pressurized steam through a steam injection port located at the bottom of the facility over a wide range of conditions, allowing appropriate quasi-steady state conditions to develop at atmospheric pressure. Previous investigations have been conducted to measme the heat transfer coefficients of a condensing surface in the presence of non-condensable gases, however they primarily consist of small cavities with one fixed orientation of the cooled condensing surface. He present test facility has been designed with a horizontal and a vertical condensing surface made of two 3.81cm thick aluminum 2024 plates positioned in the comer of a (152.4 cm x 228.6 cm x 30.48 cm ) rectangular cavity. The aluminum condensing surface was coated with a 0.0095cm thick layer of inorganic zinc paint similar to the actual AP600 surface treatment. His promoted filmwise condensation l and simulated the actual containment vessel surface wetting conditon. l
i An experimental investigation to determine the heat transfer coefficient associated with the condensing surfaces, along with axial temperature pmfiles of the test section at several different inlet steam mass flow rates and test section temperatures was conducted. In this series of experiments the air mass fraction varied between (0.9 - 0.4) with corresponding mixture temperatures of 60-90 *C. The heat 2 transfer coefficient associated with the top horizontal surface varied fmm (82 - 296) W/m K and the 8 venical side plate heat transfer coefficient varied from (70 - 268) W/m K. 'Ihe heat transfer coefficients were found and compared using two independent methods, an energy balance on the coolant used to cool the condensing plates and a differential temperature measurement at various locations in the aluminum plate. The heat transfer coefficients for various test section temperatures were measured with the two different methods of measurement (Type E thermocouples were used in both measurements and the millivolt readings were collected by a Keithley 500 Data Acquisition System). Several tests were conducted to ensure reproducibility of the facility. Results were found to yield values of the heat transfer coefficients to within a few percent of any given test, at each of the various conditions. The results were then compared to previously published studies of smaller scale similar configurations and were found to be consistent with past reported results [1]. The repon discusses this data in some detail along with the effect of various steam inlet flow pattems and gas compositions. This facility differs from previous studies in that it has a similar aspect ratio to the AP6')0. In past tests this was not the case and some of the imponant aspects of heat transfer phenomena may have been overlooked. Among these effects is the possible enhancement of the overall heat transfer rate due to mixed convection effects as the length scale increases. The design of the facility allows possible visual observation of gas mixture flow patters as well as velocities. One major draw back to the present facility is the inability to acquire data at higher pressures (2-4 bar absolute). A similar test section design has been proposed to handle these higher pressures. s
- - - - . .~. e
iii Nomenclature A Ama C, Discharge coefficient C, Vapor Concentration of bulk C. Vapor Concentration at Wall C, Heat Capacity D, Diffusion Coefficient h Heat Transfer Coefficient
; i Enthalpy k Conductivity L Length M Molecult.r Weight m mass p Pressum q" Heat Flux Tw. Back of Condensing Plate Temperature T,,, Bulk gas Temperature T, Coolant Temperature T. Mixture Temperature T. Coolant WallTemperature V Volume Flow Rate V, Atomic Volume of air V, Atomic Volume of H2O x mass fraction
l iv i l 1 Dimensionless Numbers t ( Gr GrashoffNumber Fr Froude Number , Nu Nusselt Number Pr Prandit Number Sc SchmidtNumber Greek Symbols
% Mass Transfer Coefficient p Density '
c Errorin Value I Summation of Elements O Correction Factor for Mass Transfer Cormlation l I l l l : l l t
d r V 1 , 1 Table of Contents 1 Ex e cu ti v e S u m mary . . . ... . .. .. . . . .. .. . . . . . . . . . . . . . .. . . . . . . . . . . . . . .. . . . . . . .. . . .. . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . .. . .. . .. . i N o men cla t u re . . . . . . . . ... . . . . . . . . . . .. . . . .. . . .. . . . . .. . . . . . .. . . . . .- . . . . . .. . . . . - ~ ~ ~ .. . ~ . ~ . ~ . ~ . ~ . - ~ . iu. . u s t o r ri g or es . . . . . . . . . . . ... ... . .. . ... . . . .. . . . . . .. . . . .. . .. . . . .. . . . . . . . . . . . . . . .. . . . .. .. . . . . . . . . . . . . . - . . .-- - - . vii ListofTables.............................................................................................................ix 1 Introduction 1 1.1 Air /S team E xperim e nts.. . ..... . .... ...... .. ....... . .. .. ... .. ......... . . .. ... ........... 4 1.2 Air / Helium / Steam Experiments... ................................... .... .............. 4 1.3 S te am inje ction.. .. . . .. .. .. . . . . .. .. . .. .... .... . ... . ...... . .. .. . .. ... .. ... .. ... ... ...... 5 2 Lite:ature Review 6 2.1 RecentWork..................................................................................8 l 2.1.1 Sep arate Effects S tudies...... ............... ............................... ..... 8 2.1.2 Inte gral Experiments.. .. .. .. .... .. ................... ....................... 10 2.2 Justification for Curnmt Study.................. ...... ... ...... . .................... 12 l j 3 Experimental Scaling Considerations 14 i 3.1 Goveming Dimensioniess G roups........ . ... ........... .... ........................ 14 3.2 M ode lin g Analysis... .. .. . . . ... .. ..... . ... . . . ... ... . . . .. . . ... . . .. . . . ... ......... .... ... ...... 15 , t f t t ( 4 Experimental Apparatus 19 4.1 S um m ary Description... . . ... .. .... .... ... .. ....... .... .. .. .. . . . .. . .. ... . ..... . ... .. .... .. . . . . .. 19 4.2 Te st Fa cilit y. . . ... . . . . ... . . . . .. . .. . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . .. . . . . . . . . . .. . . . ... . . . . . .. . 2 0 l 4.3 Condensing Plates........ .. . . . . . ...................................................24 ; i
l I vi i l l 4.4 S te am Inj e ction S ystem.. . . . . .. ... ...... ..... . . ... ... . . . .. . .. .... .. . .... . . .... . ... ....... . 27 i Measurement Techniqu es... ....... . ...... ...... .......... ............. ............... 27 4.5 4.5.1 Secondary Measurement Techniques........ .......... ...................... 32 4.6 G as S am pling. . . .. . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . .. . . . . . . .. . . . . . . . . . . . .. . . . .. . . . . . . . . . 3 5 4.7 Data Acquisition S ystem. .. .. . ... ...... . . ... ... . . .. . .... ..... . .... .... . .. . .. .... . ...... ... . . 3 7 5 Air / Steam Experiments 38 5.1 Summary of Experimental Procedure.. ......... ..... ....... ......................... 3 8 l 5.2 Three Dimensional S tudy.. . .. .... ... ..... .... ......................... . ... ....... 4 3 i 1 5.2.1 Description of Test............... ........ ....................................43 5.2.2 Results / Discussion.. ... .. ... . .. ... ... . . . . . ...... . .. ... . . .. ... . .... . . ...... . ... . 4 3 5.3 Unifonn S team inje ction. . .. .. ... . . .. .. . ... .. . . ... . . . ...... .. . .... .. . .... ... ...... ......... 4 3 5.3.I Description of Test..... . . . . .. ...... . . ... .. ......... . . . .. . . ... . . ... ...... ..... ... . . 4 3 l 5.3.2 Results / Dis cussing.. . . . ... ....... . . .. . . .. .. . . .. . ...... .. . . ... .. .. ...... .. ..... . 4 5 5.4 Steam Generator Pipe Rupture Injection.. ............. ..... ..... .... ... .......... . 54 5.4.1 Description of Test.. .. .. . .. . . . . .. ... .. .. . . . . . .... .. .. .. . .. . . .. ... .. .. .. .. . . . 5 4 5.4.2 Results / Discussion.... .. .... . ........ . . ..... ........ ... ..... ....... 54 6 Air /IIelium! Steam Experiments 60 6.1 Summary Description of Experimental Procedure... .... ........... .. ...... . ... 60 6.2 Results / Discussion... .. .... .. ...................................62 l 7 Observations and Future Work 69 Bibliography 71 Appendix 1 Thermophysical Properties of Aluminum Condensing Plate 73 ! Appendix 2 Data Reduction Program 85 t ( Appendix 3 Error Analysis 90 Appendix 4 NIST Calibration of Turbine Meter 94 l Appendix 5 Bibliography of Work Done at the University of Wisconsin 100 i l I
vii i i List of Figures Passive Saftey Featun:s of Westinghouse AP600 3 1.1 Schematic of Pemsteiners Experimental Apparatus 11 2.1 Essential Components of Experimental Facility 21 4.1 22 l 4.2 Schematic of Test Section Condensing Plates with Nylon Inserts 23 4.3 Steam injectionFlanges 25 4.4 4.5 Cooling Plates 26 4.6 Uniform Steam Injection System 28 l 4.7 Steam Injection Nozzels 29 f 4.8 Steam Generator Pipe Rupture Injection System 29 4.9 Heat Flux Meter Probe 30 4.10 Orifice Flow Meter 34 4.11 Gas Sampling Apparatus 36 5.1 Consistancy in HTFM (Horizontal Condensing Surface) 41 5.2 Consistancy in HTFM (Venical Condensing Surface) 41 5.3 Consistancy in CEB (Horizontal Condensing Surface) 42 l 5.4 Consistancy in CEB (Vertical Condensing Surface) 42 5.5 Three Dimensional Effects (Horizontal Condensing Surface) 44 5.6 Three Dimensional Effects (Venical Condensing Surface) 44 l 5.7 60*C lleat Transfer Coefficients (Horizontal) 47 5.8 60"C Heat Transfer Coefficients (Vertical) 47 5.9 70"C Heat Transfer Coefficients (Horizontal) 48 l l
1 4
- g i 70'C Heat Transfer Coefficients (Vertical) 48 5.10 I
4 80*C Heat Transfer Coefficients (Horizontal) 49 I 5.11 80'C Heat Transfer Coefficients (Venical) 49 5.12 5.13 85'C Heat Transfer Coefficients (Horizontal) 50 j i 85'C Heat Transfer Coefficients (Vertical) 50 f 5.14 1 51 i 5.15 90'C Heat Transfer Coefficients (Horizontal) 51 ! 5.16 90*C Heat Transfer Coefficients (Vertical) 2 8 SPGR Location and Velocity Probe Location 56 1 5.17 ! 57 i 5.18 Temperature Distribution 90*C SPGR a 4 Essential Components of Helium Experimental Facility 61 i 6.1 1 6.2 Effects of Helium 70*C (HTFM Horizontal) 65 66 i 6.3 Effects of Helium 70'C (CEB Horizontal) 4 6.4 Effects of Helium 70*C (HTFM Vertical) 67 6.5 Effects of Helium 70*C (CEB Vertical) 68 f i i 1 l l I i l 4 1 4 4 _ - _ - - . _ . , , ,_ q.
ix List of Tables
.l 2.1 Litterature Review Separtate FJfects 7 2.2 Literature Review Recent Work 9 5.1 Mass Flow Rates (Uniform Injection) 40 5.2 Typical Average Heat Transfer Coefficients (Uniform Injection) 46 5.3 Pemsteiner's Reported Results 53 i I
5.4 Theroetical Heat Transfer Coefficients 53 l 5.5 Typical Average Heat Transfer Coefficients (SGPR) 58 5.6 Mass Flow Rates (SGPR) 58 5.7 Prelinunary Velocity Data 59 6.1 Typical Average Heat Transfer Coefficients for Various Helium Concentrations 64 ) l l I v- . n e ~ - ,,-
1 1
< l 1
l i I l i Chapter 1 ; 1 a 3 I Introduction l 1 l A primary concem involved in the safety of nuclear power generation is the prevt.ntion or mitigation of an accider.t occurring in which radioactive by-products may be released into the ( l
- atmosphere. To mitigate such an accident it is necessary to provide a containment system sufficient to 2
contain these materials , under several accidental scenarios. One such event is a primary system pipe break, in which a large amount of primary system water discharges and flashes into steam. This will cause an increase in pressure and temperature in the containment atmosphere. This increase in the l 4 j pressure and temperature must be controlled by some mechanism before the containment structural I integrity is compromised. The mechanisms which are currently in use for operating light water reactors rely principally on active safety systems to spray cold water into the coatainment to condense this steam. These active systems require the use of AC power to drive the injection pumps, which must be supplied 2 by either backup diesel generators or off-site power. This not only adds further cost to the plant construction but also more mechanical components whose reliability must be considered in the event of an accident. New advanced reactor designs have included the use of passive cooling techniques which seek to take advantage of the natural circulation processes within containment climinating costly
2 i mechanical components and adding improved reliabihty. The Westinghouse Electric Corporation has designed a 600 MWe pressurized light water reactor (AP600) that utilizes these concepts integrated into i ^ the passive safety systems. The AP600 utilizes a passive containment cooling system (PCCS) to transfer sensible and core decay heat from within the reactor contamment to the atmosphere in the case of an accident vdthout compromising the containment vesset lhe PCCS incorporates large water reservoirs situated above the containment vessel that are opened and allowed to flow by gravity over the contamment shell, assisting natural circulation in removing heat primarily during the imtial hours of an accident when the core decay i heat is high. Figure 1.1 shows the layout of the AP600's proposed design. A water film is developed from the flow of water over the outer surface of the steel containment which provides evaporative cooling i 2 thus increasing the heat transfer coefficient on the oc. side of containment. As a result of the cooled steel i j containment shell, the steam inside the containment condenses on tile inner contamment wall, which can increase the heat removal ability to the containment structure. The energy transfern:d and steam condensed on the inside of the contamment is controlled by the presence of noncondensable gases in the containment volume, which forms a barrier that the steam must diffuse through before condensing. It is the combination of these heat transfer coefficients which determine the overall heat removal rate; each 4 being a significant heat transfer resistance. It is vital to have good estimates of the heat removal rate i associated with the evaporation of the water film on the outside of the containment and the energy i transferred by condensation of the steam in the presence of noncondensable gases [1] on the inside of containment, to ensure that the reactor contamment will be able to remove the necessary energy required to keep the contamment intact, during the various stages of an accident A series of experiments investigating the condensation of steam in the presence of noncondensable gas was conducted to model such accident scenarios and to measure the resulting heat transfer coefficient from steam condensation on the inner wall of containment. Several tests were i 4 I
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4 L preformed with differing ratios of air, helium, and steam to quantify the effects of noncondensable gas that may be present in the containment during an accident. He effect of the noncondensable gas barrier may also be related to the position and the location of the injected steam therefore, tests varying the location of steam injecticas were conducted. In an effort to understand the heat transfer coefficients found during the experiments it is necessary to obtain data on the natural circulation velocity field developed in the test section, so methods are being developed to meastue and quantify the associated velocities near the condensing walls. Some prelimmary data is provided in this area. 1.1 Air / Steam Exoeriments To investigate the condensation of steam in the presence of the noncondensible gas we explored l f the effects of the heat transfer coefficient on a horizontal and a vertical cooled wallin an environment of l varying concentrations of air and steam. De tests were conducted at atmospheric pressure and various temperatures of saturated steam. These scoping tests provide the heat transfer coefficients under a range of conditions where a break in a pipe would cause an influx of steam to rise and condense on the cooled steel containment structure. De experimental observations were then compared with previous experiments of the same nature [1,2,3] and used as a reference to cornpart tests with varying light gas concentrations and more prototypic geometries, 1.2 Helium / Air / Steam Exneriments In the event that primary system cooling water is lost and temperatures in the reactor core rise to l I levels high enough for water to start reacting with the fuel cladding of zircaloy metal, hydrogen gas may be produced. Oxidation of the cladding due to the presence of water may introduce hydrogen in bulk concentrations of 0-10% molar. His production of a light noncondensable gas may alter the rate of ) I 1 l
~ ~ - -.
t 0 5 1
} steam candedon on the containment structure not only by increasmg the layer of noncondensible gas the steam must diffuse through, but also due to the small molecular weight of hydrogen which may i preferendally collect near the upper condensing surfaces. Derefore,it is necessary to examine the effects l 5
j on the heat transfer coefficient due to the introduction of a light weight noncondensable gas. i i j Tests were conducted to study these effects using helium gas instead of hydrogen. His was l i chosen due to the obvious hazards of working with hydrogen and the close similarities between the two
- l. l 1
! gases. In these experiments air and helium were mixed so the helium molar concentrations varied from .J 3-32% prior to the injection of steam. Then steam was injected at mass flow rates which would produce
) l steady state temperatmes of 60-90 *C.
- I i
i i i '13 Steam Inlection l ! Two different steam injection configurations have been considesud. The majority of tests were } conducted with a uniform steam injection system located at the bottom of the test section. This consisted f of a 1"1PS alummium pipe with 19 uniformly spaced injection nozzles with an inside opemng of 3/16". i ! His injection produced a uniform distribution of steam into the test section with mass flow rates between i l (0.0012 kg/sec - 0.0058 kg/sec). ne second steam inlet configuration was constructed to model a pipe i ! rupture in the steam generator room of the AP600 contamment. In this scenario steam would enter the containment atmosphere at a level of approximately 4 meters above the operating deck of the AP600 [ through an opemng of about 25 sq.m. He position of the steam generator can be seen in the schematic in } j Figure 1.1. This steam injection system consisted of 1" IPS pipe formed in a configuration that would i ! represent a scaled version of a steam generator rupture. l 4 4 4 i i _ - . . - . .- . - . . ,
- _ _ _. _ . ._ m _ . _
e ! 6 i a , i 5 i Chapter 2 i ! Literature Review i f i j A complete review of earlier works was discussed in detail by Huhtiniemiin 1991 and updated i l by Pernsteinerin 1993. The following re. view of work in the area of condensation heat transfer was adapted from Pernsteiner. Two separate classifications of the research were formed to allow for a i i consistent way to present the different studies. j i
- 1. Separate Effects Experiments i
i In this classification a simple relatively small test geometry is used to isolate one or a few of the l effects of condensation. Typically, time dependence is climinated, and the tests are conducted at ) steady state temperatures to simplify the measurement procedure. I
- 2. IntergrallLarge Scale Experiments l This classification includes large facilities that are designed to study realistic flow geometries 1
1 j along with transient behavior to simulate actual contamment situations. Generally these tests are i j too complex to obtain much information about individual factors that contribute to the heat l transfer. ! An investigation of these two different classifications is given in Reference [2]. Table 2.1 gives some of i I j the measurements found in different separate effects tests. i i
i 7 I Parameter Barry[18] Dallmeyer[19] Debhi[20] Gerstmann [21] Henderson[22] Gas air air air,He air air Vapor steam CCL.,C H, steam freon-113 steam 51.3-88.2 95 sat NA NA T ,["C] m)m, 0.47-0.92 0.02-0.16 0.25-0.9 trace 0.1-0.83 vo[m/s] 2.1-6.9 l-13 0 0 NA 180 90 90 0-90 180 4[*] 0.1 sat 0.15-0.45 0.1 Na P(MPa] 26.3-63.2 55-85 10-65 4.3-39.4 Na AT [*C] Geom ph.te plate tube plate tube UD 610 410 3500/38 457.2 1220/29 Cho[23] Kroger[24] Kutsuna[25] Robinson [26] Siegers[27] Spencer [28] air Ar,He air air air N,Co,He 2 2 steam potassium steam steam steam freon-113 sat 598-768 85-90 sat 26.7-65.6 sat 0-1.4e5 Na 0.42-0.55 0.16-0.87 0-0.01 0-0.03 0 0 4-5.3 <2m/s,Na 0 0 0 0 180 90 90 90 0.31-1.24 sat 0.1 0.27-6.2 0.004-0.03 Na 35-100 2.3-733 5.0-15 4.0-10 1.4-20.8 Na disk disk plate disk plate tube 137 101.6 800 46 127 Na/Na Table 2.1 Summary of Previous Investigations
8 2_.1 Recent work l 1 11.1 Seoarate Effects Studies Since the extensive review by fluhtiniemi there has been some new and relevant work done in l the area of condensation heat transfer. A summary of some of the separate effects results is given in Table 2.2. De following summary of previous investigations into condensation heat transfer was adapted form Pemsteiner Ref. [3], with the addition of a short description of his work. Lu and Suryanarayana (14] investigated vapor flow inside a horizontal rectangular duct. The vapors used in the study were R-113 and its proposed replacement FC-72*. The heat transfer coefficient was found to increase with inctuasing inlet vapor velocity, and an enhancement of the heat transfer coefficient was observed upon the appearance ofinterfacial waves. These effects have been observed before, and were verified here for the CFC R-113 and its replacement. De results were correlated by two separate l l l equations for the wave free regime, and another for the wavy regime. 1 Fox et. al. [15] studied steam-helium and steam air mixtures inside a reflux condenser tube. It was found l that transport phenomena were greatly affected by the stability of the component combinations used in l the condenser. In general, stable flow pattems were observed when helium gas, with a molecular weight less than that of vapor, was used in the condenser, and unstable flow pattems developed for the cases I when a noncondensable gas heavier than the vapor was implemented. Stable conditions were observed for both noncondensable gas loadings at high vapor mass fractions (0.95). It was found that certain unstable conditions exist which result in oscillatory recirculation regions which exhibit small temporal l fluctuations, ne results indicate that simple models which assume a stable gas / temperature front are not valid when using noncondensables with a molecular weight greater than the condensing vapor. l Siddique et. al (16] measured the local condensation heat transfer coefficient of steam, in the presence of air,in a vertical tube, with a downward flow. He experiment was developed to model condensation heat transfer inside the isolation condenser, a component of the General Electric SBWR passive cooling
i 9 i 4 4 Parmeter Fox [15] Siddique[16] Kang /Kim[17] LU [14] , l Gas none air,He air air Vapor R-113/FC-72 steam steam steam i Na 1 T ,[T] 50/60 sat 100-140 mjm. - 0.75-0.95 0.10-0.35 0-1.0 v,[m/s] 0.3-4.4 0.2 Na 3 I80 90 90 184.1
$[*] l l
l P[Mpa] sat 0.1 sat 0.1 I Geom plate tube tube plate i l UD 40 8.1 55 15.2 l 4 Table 2.2 Summary of Recent Work i i l J i i i i 4
10 system. The inlet air mass fraction ranged from 0.10 to 0.35, with mixture inlet temperatures of 100,120 and 140*C. The local Nusselt number increased with the mixture Reynolds number and decreased with increased noncondensable mass fraction. A model was developed to predict local heat transfer coefficients on the inside of the tubes, for the range of condition studied m the test series. Kang and Kim [17] investigated the effect of noncondensable gas and a wavy water film on condensation heat transfer A water film was injected into a 1.52 m long rectangular channel, at steady state thennal conditions, to produce a wavy film condition. Data was collected for varying air mass fractions (0-0.78), mixture velocities (1-7 m/s), and film flow rates. Even small amounts of noncondensable gas were seen to greatly affect condensation heat transfer rates. The waviness of the condensate film also increased the heat transfer as listed previously. Pernsteiner [3] investigated a series of forced flow tests with a horizontal, downward facing condensing plate coated with inorganic zine paint. The tests were conducted with variable mass fractions varying from 0.65-0.78, velocities ranging from 1.0 to 2.1 m/s and helium concentrations between 0 and 39 percent of the total noncondensible content. A second series ofinvestigations was conducted to study the effects of natural convection. These tests were conducted with the condensing plate in a vertical position. The mass fraction of noncondensables was varied from 0.33 to 0.92 with helium molar fractions ranging from 0 to 30 percent. It was found that the previously reported inhibiting effects of the light noncondensable gas (helium) was not observed except when helium concentrations became greater than 307c. Figure 2.1 is a diagram of the experimental facility used. 2.1.2 Inteoral Exneriments Separate effects tests provide increasing knowledge of the processes of condensation heat transfer, however they may not always be scaled to larger facilities. This leads to the importance oflarge scale tests to investigate effects not seen by the separate effects studies,ie mixed convection, gas
b l 11 f N att JAC11 DES
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12 concentrations, temperatures, Cow fields, and system pressure that would occur in contamment during an accident. Westinghouse has carried out several large scale tests involving an extemally cooled containment stmeture similar to that pmposed for the AP600. The testing of an 1/8th scale facility allows measurements oflocal heat fluxes and heat transfer rates at both the inside and outside of containment. Rey have studied the effects of steam injection location and noncondensable mixturt mole fractions on the total heat transfer along with several other investigations. A second series oflarge scale integral tests is being performed at the Paul Scherrer Institute, which is very similar to the work being done by Westinghouse, except for the SBWR . They have constructed a 1/10 linear scale SBWR at full height to provide experiments to General Electric on the performance characteristics of their new simplified boiling water reactor and its passive contatnment system. 2.2.fustification for Current Study Be major motivation behind the cuntnt experiments is to find representative values for the condensation heat transfer coefficient under a wide variety of conditions from a facility similar to the Westinghouse AP600. Westinghouse has employed a combination of separate effects experiments along with integral experiments to try to document the effects of the heat and mass transfer phenomena. He University of Wisconsin has shared in this effort by conducting several separate effects tests over the I years. Barry, Kim, Huhtiniemi, and Pemsteiner have investigated the heat transfer rate on metal surfaces with similar finishes as the AP600 contatnment (see Appendix 5 for bibliography). Rey have investigated several different parameters that effect this heat transfer (ie. temperature, mass ratio, gas 1 composition, pressure, and cold wall orientation). One of the major limitations to the previous studies conducted is the representation of only a small ponion of the cooled containment wall. This limitation was necessary to evaluate some of the previously mentioned parameters, howeverit may have also l
l 13 caused them to overlook important aspects of the heat transfer phenomena. One major aspect is the enhancement of the heat transfer due to mixed convection effects. 'Ihis was first noted by Huhtiniemi in his experimental results [2]. The present invesdgation is an effort to gain additional understandmg of the heat and mass transfer phenomena in this mixed convection regime. 'Iherefore, the experimental facility was constructed with a similar aspect rado to that of the AP600 containment. The design of the facility is such that velocity fields, which are imperative to the understanding of the heat and mass transfer can be . observed through clear polycarbonate sheets on the front and back of the test section and measured at particularlocations. l l \
14 1 l Chapter 3 Experimental Scaling Considerations 1 3.1 Governing Dimensionless Grouos The experiments were designed to represent a two-dimensional slice of the upper dome of the l AP600 contamment; i.e., from the radial center to the wall of the relatively open region above the operating deck in the containment. This representation assumes that any flow pattems are axisymmetric l along the center of containment. In addition, the size of the experiment is small enough (1:12 linear l scale) that we must consider how the goveming dimensionless groups are affected by these geometric j distortions. In the past, our method ofinvestigation of the condensation heat transfer upon the cooled , l surfaces similar to the AP600 walls indicated that for a large number of conditions a mixed convection I regime may be present in the containment for low forced convective velocities; i.e., less than 1-3 m/s. Based on this analysis it seems that the most appropriate dimensionless group to preserve in our experiments is a modified Froude Number given by the expression: 1 Pr= pv lapgL m where p is the density of the gas mixture, Ap is the difference in density between the bulk gas and the gas mixture near the interface with the cold wall, v is the bulk gas velocity, g is the gravitational acceleration
4 I 15 l l l )i and L is the characteristic length. For our analysis we have assumed that the gas velocity can be , l t represented by the steam velocity enteting the upperdome containment from a compartment below the- ( 1 operating deck up to the top of containment. This dimensionless group is felt to be the most important I i because it is the ratio of the natural convection forces to the forced convection inertial forces in the
- I J volume.
To give an illustration of the quantitative magnitude of this grouping consider an accident sequence in the AP600 where due to some pipe rupture and initial blowdown, a quasi-steady state is established in which steam is injected into contamment at a rate which matches the condensation on the i i cold walls at a particular pressure. This is mmtinr to the situation developed in the 1/8th scale containment experiments conducted at Westinghouse. Let us assume that the characteristic velocity for steam injection is I meter /sec, which corresponds to the mass flow of steam generated from core decay i heat and entering the containment through an area similar to the steam generator compartments. For a l
- containment pressure of 3 bar, with saturated steam present, the Fmude numberis about 0.0043. If we e
assume the same velocity the mmunum Froude number is about 0.055 for our experimental apparatus. This value is higher in direct proportion to the smaller length scale of our facility. However, this ) distortion can be reduced by decreasmg the input flow velocity while holding all other parameters ) i I constant. His reduction must be realistically balanced by the quasi-steady conditions attainable within
- the apparatus. Although this is a distortion in the dimensionless group, it is of similar magnitude.
l 12 Modeline Annivsis In an effort to compare the experimental results to boundary layer heat and mass transfer theory we took an approach similar to Westinghouse [11] which we found to be appropriate for heat transfer modeling. He scale on the experimental facility is such that the heat and mass transfer may be govemed
- 16 by tuIbulent free convection. Therefore, the use of McAdams correlation for free convection would approximate the heat transfer from the test section atmosphem to the cooled walls by:
4 Nu = 0.13Gr /3 Pr 1/3 (2) To obtain a similar correlation for the mass transfer which accounts for the majority of the total heat
- transfer the McAdams correlation was used with the momentum, heat and mass transfer analogy, thus the Nusselt Number is replaced with the Sherwood Number and the Prandit Number with the Schunidt 4
Number. 4 Sh = 0.13Gr 1/3Sc 1/3 (3) - The above correlations which were developed from similarity arguments are dimensionless and independent of the length scale. The above correlations were arrived at using the Grashoff Number based on thermal expansion rather than the Grashoff Number based on the total density difference. In our 2 case, the density is a function of both the temperature difference and the steam concentration which would result in an increase of the driving force for heat transfer. Because of this increased density 4 difference, it is more appropriate to use the Grashoff Number based on the total density difference, rather than just the thennal differences. The mixture properties of the bulk were used along with the properties at the wall in both the calculation of the convection heat transfer coefficient and the condensation heat transfer coefficient. The convection heat transfer coefficient can be determined directly by the definition of the Nusselt Number: NU= (4)
17 It is first necessary to calculate the mass transfer coefficient (to obtain the condensation heat transfer coefficient from the Sherwood Number. The Sherwood Number is defined as:
" l (5)
Sh = "Do l l .i i where D, is the diffusion coefficient, and 4 si the mass transfer coefficient. An approximation of the diffusion coefficient of steam in air was calculated from the following equation recommended by Rohsenow et.al (Ref 10). Do = 0.0069 M, +Ms1 (6) P(V1*+Vl")2 Where T is in Ranbne, V, and V, are atomic volumes given in table 14.1 of reference 5, and P is in - atmosphere. The mass flow rate can then be calculated by the following equation: b = Km(Cg - Cw) (7) where c, and c, are the local vapor concentrations of the bulk gas and the wall respectively. The condensation heat transfer coefficient is then found by substituting the previous equation into the expression: b6 v. bulk-it.wa) gcand_~ (8) Tsuix-Twa
'Ihe total heat tmnsfer from the bulk to the wallis the sum of the contributions from the convection heat transfer and the condensation heat transfer (h, = h_, + ha). The above mass transfer correlation was
18 l l developed considering tangential flow across a plate neglecting normal flow. In our situadon there is an l I additive effect due to the normal component of the velocity. His will result in an increase in the heat I transfer coefficient due to condensation. To take into account these effects Bird et.al. [4] suggests the addition of a correction factor to the mass transfer correlation. . Sh = 0.13Gr SSc14 0 (9) where 0 is a correction factor for the effect of mass transfer on the transfer coefficients : 0 = '"## g (10) R = "1-xo (11) and varies between 1.5 and I for the conditions of our tests. Chapter 5 and 6 of the report indicate that the above correlations produce good agreement with the uniform injection experiments. l I
4 i 19 1 i i i i i e Chapter 4 i Experimental Apparatus t ! 4.1 Summary Descrintion of exnerimental facilities The facility for testing the effectiveness of the AP600's PCCS heat mmoval capabilities consisted
' of a rectangular cavity 8 ft. (243.84 cm) tall,6 ft. (182.88 cm) wide and 1.04 ft. (31.75 cm)in depth.
Air or air / helium mixtures are initially in the test section at atmospheric pressure, then steam 1 supplied by a Sussman model ES-7L boiler is added through a steam injection configuration at l
- the bottom of the test section. The 72kW boiler which is able to produce 0.027kg/see of steam is 4
equipped with a Mercoid Da 531 Bourdon tube pressure switch, which has a dead band of 3 psi so that the boiler pressure fluctuations are minimized resulting in a minimal variation of the p l steam temperature. Energy is removed by horizontal and vertical oriented condensing plates located in the right hand comer of the test section. The aluminum condensing plate was held at i a temperature of approximately 30*C by cooling plates located on the back side. Coolant water, supplied by a Neslab HX-150 constant temperature water bath able to provide 4500W of cooling power at 20*C, passes through a series of Dwyer RMC-141 flow meters into the cooling plates. The steam flow rate from the boiler was then controlled by a needle valve until a steady state
20 temperature of 60,70,80,85, or 90 *C was achieved. Figure 4.1 is a schematic of the essential components of the experiment. f.2 Test Facility Figure 4.2 is a schematic diagram of the test facility. It consists of a front and back sheet of 1/2" thick polycarbonate (Lexan*). He sides, top, and bottom are also made of Lexan with the exception of the aluminum condensing plates. The bottom and left side are endrely Lexan while the top and nght side house the aluminum condensing plates. The condensing plates are attached to the Lexan sheet with a butt joint and a 1" x 2" phenolic coupling piece used to seal the joint. The two condensing plates are also connected in the comer with a 2" x 2" phenolic coupling joint. Nylon screws were used to connect the phenolic pieces to both the condensmg plates and the Lexan. His was done to reduce any changes in the properties of the materials. De aluminum condensing plates were 12" wide as compared to 12.5" wide Lexan sides so that a thermalinsulator could be placed between the plates and the carbon J steel frame which held the structure together. A 1/8" rubber gasket and a 3/16" thick piece of G-10 phenolic were used to seal and insulate the condensing plate from the frame. The Lexan sheets were then l pinned into place with 3/16" x 3/4" dowel pins that went through the steel frame and into the cross section of the Lexan. 5/16" x 1" dowel pins were used to hold the condensing plates in position. These
-I pins went through the steel support structure through the phenolic insulation and into a nylon insert placed in the condensing plate (Figure 4.3). This construction insured that the condensing plates were l
l thermally isolated from any significant mode of conduction heat transfer to the rest of the test section. I I De sides were then sealed with silicon sealant on both the inside and outside of the test section. De front and back faces were sealed to the steel frame with silicone sealant, and a second frame made of 1/4" thick 2" aluminium angle was placed over the front and back surfaces. He whole test section was i sandwiched together with a series of 3/8" threaded rod positioned 6" apart around the perimeter of the ] l
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24 4 4 aluminum frame. Two 7.5" diameter access holes were placed in each side of the test section with the center of the hole located 6" above the bottom plate to provide mountings for the steam injection system. Aluminum flanges were constructed to house the steam injection system and seal the access holes Figum 4.4. He entire test section was supponed by a Unistrut support structure and insulated with 2" thick R-12 polystyrene foam insulation, so that the only fann of energy removal was fmm the condensing surface. 43 Condensine Plates The two condensing plates consisted of 2024 aluminum plates with dimensions 3'x1'x1.5", ne 4 i test plates thennophysical properties, needed in the calculation of the heat transfer coefficient, were measured by Purdue University Demophysical Properties Research Laboratory (TPRL) and a summary of there findings are given in Appendix 1.The plates were sand-blasted then coated with a 3.75 +/- 0.25 mils thick coat of inorganic zinc paint as measured by a KTA-Tator, Inc Posi-tector 3000 dry film detector. His self curing, inorganic zine primer contains 85% zine when dry and has a therma! conductivity of 0.0209 w/cm K. Westinghouse uses the primer to protect the inner and outer surface of l the contamment facility. It was demonstrated to have good film wetting characteristics at several angles l i and to prevent corrosion to the vessels [1]. Each condensing plate was fitted with six coolant plates so that coolant flow through each plate could be controlled and monitored separately by the flow meters. A schematic of the cooling plate is shown in Figure 4.5. The 6" x 12" x 1.5" cooling plates were bolted onto the condensing plates with four 1/2 -13 x 2.5" allen head cap screws. It was found that the use of the carbon steel bolts imbedded in the aluminum would not effect the measurements more than one i
- percent. Bree sets of holes were drilled through each coolant plate and into the condensing plate to allow for the insertion of heat flux probes. 'Ihis was done to study any fluctuations of the heat transfer coefficient on positions varying from the center of the test section.
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27 3.4 Steam Infection System The first of the two steam injection systems was a uniform distribution of steam. It was constmeted of 1"IPS aluminum pipe and is shown in Figures 4.6. A blow up of the injection nozzels is given Figure 4.7. Nineteen evenly spaced Swadgelock fittings, with a mimmum opening of 3/16 inch, were used as the injection nozzles for the steam. A small hole was also drilled in the bottom of the pipe to allow any condensed liquid to flow out of the tube. Steam was supplied on both ends of the pipe to create a unifonn injection from each nozzle. De second steam injection system was designed to act as if there were a ruptute in a steam generator pipe Figure 4.8. The size and position of the injection was determined by calculating a 1:12 ratio of the actual steam generator. De steam flow rate was scaled by the ratio of the volumes of the actual contamment to the test facility. In this arrangement steam enters through one side and passes through a 1" pipe which has 90* turn at a distance of 2$ 7/8" from the left side and then a 8" high vertical inlet section. , i 43 Mensurement Technlaues Two separate methods of determination of the heat transfer coefficients were used. De first was a local heat flux measurement using thermocouple heat flux meters (HTFM) and the second was an area averaged heat transfer coefficient that was determined from a coolant energy balance (CEB). The heat flux meters are shown in Figure 4.9. Rey consist of a set of four E-type thermocouples incased in a 3/16" O.D. stainless steel tube (E-type thermocouple grade wire was chosen because both elements have a low thermal conductivity, good resistance to corrosion and a high Seebeck coefficient) . Four 0.039" precision holes were drilled in the side of the stainless steel sheath. Thermocouples with a bead of no more than 0.025" were inserted into the hole and a silicon sealant was injected into the end of the tube to hold the thermocouples in place. Each probe was then independently measured and the location of the
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i mw] j or t s 4 4 1 Figure 4.7 Steam Injection Nozzels e d a 5 l 1 l I 1 4 Stean Generator Pipe Rupture i f i ' Lexan s w _. 4 nu i i E8' Acess st,an - g 1** 3 steen :np h** l reon rent
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30 l l l l Type E-Thermocouple Vires i i Cooling Plate l 3.00' r- C.:1125' typ Condensing Plate - 0.5625' I O.25'd Mgum 4.9 Heat Rux . Meter Probes i i
I 31 junctions recorded with an error ofless than 0.01". The thermocouples were then tested for accuracy at the National Standards Laboratory. This was done by placing the pmbes in a bath of mineral oil and measuring the temperature with a platinum thermometer while the millivolts produced by the junctions } were recorded on a digital volt meter. These measurements were then compared to the IPTS-68 standards. l 1 To determine the heat flux the HTFM's were set in holes drilled through the cooling plates into the aluminum condensing plate. An equation of a line defining the temperature distribution of the plate i was found from the temperature measurements and positions of the thermocouples . The slope of this i line is the temperature gradien'.in the aluminum plate and the y-intercept is the back plate temperature. Then using the following analysis we could determine the heat transfer coefficient at the location of the probe. g d*r (8) h = Tar-Tsus j Assuming a linear temperature dependance the temperature of the plate is given by the equation l Tatum(X) = j;"'X + Teacu (9) i ! A similar equation govems the temperature in the zine coating layer. We included the existence of the l l 1 coating, however we neglect any contact resistance between the aluminum and the zine coating. With knowledge of the slope and intercept of a line through the aluminum plate we could calculate the surface temperature and with the corresponding measured mixture temperature we could calculate the heat transfer coefficient. The slope and intercept of the temperature distribution in the plate was found using a i linear least squares fit to the recorded probe temperatures [12,13]. The specified errorin the l thermocouples reported by the manufacture (Omega Engineering) was +/- 1.0'C. This is the error in the
1 i 32 thermocouples absolute temperature reading, however we were concemed not with the absolute temps.rature but the difference in temperatures of the four thermocouples. If all four thennoccuples are calibrated so that they read the same temperatures at zem heat flux then the resolution or a statistical < standard deviation of the sampling of a ensomble of measurements can be used as the enor in the linear least squares determination of the line. This was done by the program htf6.exe which is given in i Appendix 2. The second method of determination of the heat transfer coefficient was a coolant energy balance. Temperature controlled water was passed through a flow meter and then through the coolant channels in the coolant plates. 'Ihe temperature of the water was measured with an E-type thermocouple at the inlet of the coolant plate and subsequently at the exit of the coolant plate. An energy balance on the liquid would yield the energy removed from the condensing plate and thus the heat transfer coef5cient associated with the area under the coolant plate. 4 is pecoloo ( AT) Qi = p, (10) oi) h = Tmx-Tawr 4 This method of determination of the heat transfer coefficient is different than the heat flux meter probes in that it is an area averaged heat transfer coefficient. Each coolant plate was used to obtain an average !, heat transfer coefficient where the HTFM's measure the heat transfer coefficient in the vicinity surrounding the probes. An error analysis of the above equations is givenin Appendix 3. 4 51 Secondary measurement devices
1 33 i i j Re test section was also equipped with several temperature probes to measure axial variations in 1 1 the test section fluid temperature. Figure 4.2 shows the locations of the temperature measurements. i Swadglock fittings with a minimum opening of 1/2" were used to allow for easy installation of a variety l
! of measurement probes, ne probe holes located in the right hand comer next to the condensing plates 1
j were used as the mixture temperatures in the calculation of the heat transfer coefficient. Dese probes 1 j were located as close to the condensing plates as possible, considering the structuralintegrity of the i j Lexan sheets. These seven temperatures were recorded by the Keithley data acquisition system along i j with the HTFM and CEB temperature measurements. The remainder of the axial probes were connected 4 j to an Omega DP41-TC high performance temperature indicator. A Vaisala series HMP 131Y humidity and temperature tranunitter was used to measure the l l relative humidity in the test section. His probe's measurement of the RH is based on changes in the 4 capacitance of a thin polymer film as it collects water. It has a 90% response time of 15sec in still air at i 1
- 20*C with an error of +/-2 % RH. It also allows the simultaneous measurement of temperature with a ;
i 1 i platinum RTD sensor. De Vaisala probe junction box was connected to a Keithley DAS-8 data ) l acquisition board inside a PC computer and the probe inserted in the test section through the same holes as the axial temperature probes so that a distribution of humidity levels could be obtained. l De steam mass flow rate was measured with two different techniques. De first method of l i measurement was an orifice flow meter Figure 4.10. It consisted of an ASME spec, square edge orifice. 2 He area of the orifice opening was 2.7cm2 with a two foot entrance pipe with area 17.719cm . Two l i 3/16" pressure taps were located on either side of the orifice and were connected to a 4025 B Capsuhelic
- deferential pressure gage, ne mass flow rate could then be calculated from the equation
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' 35 i i ne discharge coefficient was taken to be 0.61 which is the suggested value by Bini et.al (4]. De a second method of measumment was an energy balance on the boiler cycle. After the test section reached i J 4 a steady state temperature the boiler cycles were timed. If the power of the heater is known along with 2 the time the heateris on one can detennine the energy supplied to the steam. If this is known then the 1 mass flow rate of the steam can be determined by the following equation: l Qt (13) II7 = ((cp(Tsar -Tin}+ifg)t t or) i ne pressure gage used to measure the pressure drop across the square edge orifice was used in only a few measurements since the silicon diaphragm was not able to handle the temperature and exposure of the steam for long periods and failed after a few uses. The second method agreed well with the measurements made by the orifice flow meter and was used throughout the experiments as the method of detenmnation of the flow rate. A Hontzsh vane wheel anemometer was used to record preliminary velocity measurements. The 4 voltage proportional signal frequency of the meter is converted into a load independent voltage by a Hontzsch flow transducer powered by a 24 VDC Marter power processor . De voltage output fmm the - transducer is read by a Nicolet 4175 Digital oscilloscope. De zero flow reading of the anemometer is 1 5.003 volts therefore a high precision voltage calibrator was used as a DC offset to increase the resolution N of the oscilloscope. De NIST traceable calibration of the velocity meteris given in Appendix 5. b 4.6 Gas Samotine 1 A gas sampling device was constructed to detennir:e the concentration of different gases that were present in the noncondensables. Figme 4.11 is the schematic of the gas sampling device used. Valve one is connected to a 1/2" copper tube, that was inserted in the test section through one of the axial
. .~. .. ._. . .- - . . . . - _ -
1 36 1
-s i i 3[ -
4 I l . b purge tank . i
/5 l
Sample vessel . i l V [5 l l-( Figure 4.11 Gas Sampling Apperatus
37 l temperature probe holes, to the rest of the sampling system. Valve two connected the sampling system to a vacuum pump so that the entire system could be purged of air prior to sampling. Valve four was connected to a purge tank so that a large volume of the gas could be taken into the sampling unit to ensure a uniform mixture. De actual sampling bottle was attached to valve t!ute. The unit was wrapped with a heating tape which was connected to a temperature controller, so that the temperature of the whole sampling system could be raised to the test section conditions. Value five was used to drain any condensed liquid. ne sample was then analyzed with a mass spectrometer. 4.7 Datn Acoultition und Recordinn A Keithley series 500 data acquisition system was used to collect the voltage signals fmm the majority of the temperature measurements. De Type E thermocouple wire AWG-30 with a Teflon coating were connected to one of five Keithley AIM 7 Thermocouple input modules. The AIM 7 module allows the connection of 16 thermocouples to an isothermal block. A cold junction reference sensoris also connected to this isothennal block to allow accurate measure ofits temperature, ne voltage signals are routed to a global system amplifier which amplifies a ADM214 bit A/D convener. He AIM 7 module has a gain of 100 volts / volt and the global system amplifier was set to a gain of 10. This produces an overall amplification of 1000, giving an effective voltage input range of 20 millivolts. Both the sampling rate and the number of samples was controlled and recorded by a personal computer. The sampling of the teenperatures was usually done at a sampling rate of 0.2hz where 30 samples were taken for each thennoccupies. The temperature data was then sent to the data reduction program Htf6.exe I where the temperatures and locations were used to determine the heat flux and the corresponding heat j transfer coefficients.
8 38 l l l l Chapter 5 Air / Steam Experiments 5.1 Summary of Ernerimental Procedure This was the first series of tests conducted in the experimental facility and as a result several tests were performed to ensure that everything functioned properly. The conditions of the outside environment were measured and recorded along with the time cach test was conducted. The boiler was started and filled with distilled water from a large reservoir. Two pumps were used to fill the boiler a
- low pressure pump was needed to pump the water supply to a high pressure pump located on the boiler, t
Once the boiler reached its operating pressure of 25psig a throttling needle valve was opened to allow steam to flow into the test section. The coolant water supply was tumed on and the flow meters and l l water temperature were set to maintain the surface temperature of the condensing plate at approximately l 30*C. The Nestab HX-150 Refrigeration unit is rated to provide 4500W of cooling power at 20*C. This l I was found to be sufficient for test section temperatures of 60-80'C, however it was unable to remove ! sufficient energy at 85'C and 90*C to hold the plate temperature at the desired 30'C. 'Iherefore building water was passed through the cooler in order to achieve a steady condensmg plate temperature of 30*C and then'was dumped down a drain. The tests were taken at atmospheric pressure due to the structural limitations of the Lexan sheets to handle higher pressures. To maintain the test section at atmospheric l 1
39 pressure a ball valve located on the bottom of the test section was opened. His valve was connected to a hose which was inserted into a pool of water so that gas could only exit the test section atmosphere. He needle valve was adjusted until the test section temperature reached the desired temperature. After a sufficient time had elapsed (no less than a 1/2 hour) for the test section to reach a quasi-steady state data was collected. De Keithley 500 data acquisition system could only read one AIM 7 temperature module at a time. His consisted of 16 thermocouple measurements. The thermocouple HTFM probes and the two thermocouples used in the measurements of the CEB were setup so each probes four temperature measurements would be measund at the same time. The sampling was usually done at a frequency of 0.2Hz with 30 temperature measurements taken for each thermocouple. Derefore it took 150 seconds to read each card. After each card was run the data had to be dumped to the hard drive of the personal computer. This took about one minute, therefore it took about 15 minutes to collect the complete set of heat transfer data. De data was then transferred to the data reduction program and exammed to see if the plate surface temperature and test section temperatures wcre at the desired values. During each test the axial temperature at each grid location of the test section was measured along with the relative humidity. The boiler mass flow rate was also measured. De pressure differential of the Capsuhelic pressure gage was taken and the boiler cycles timed. De condensed steam in the test section was allowed to eject through the same ball valve that kept the test section at atmospheric pressure. After several tests were completed at a given test section temperature the steam flow rate was increased, his elevated the test section temperature to the next desired temperature and the procedure was repeated. Several tests were taken at temperatures of 60,70,80,85, and 90*C. Table 5.1 shows approximate mass flow rates needed to achieve the desired temperatures. Figures 5. land 5.3 show the consistency in the heat transfer coefficients obtained at 70*C by the HTFM's and Figures 5.2 and 5.4 show the consistency of the CEB measurements. The labeling of the plots corresponds to the position of the HTFM meters as measured in centimeters. The coordinates of the horizontal plate heat transfer coefficient plots start from the left side I
.. . .. . . _ . - .- .- .. - . . - ~ .. .
l l 40 l i l Test Section Mass Flow Rate Temperature *C (kg/s) 60 0.00134 70 0.00238 80 ~ 0.00357 85 0.00422 90 0.00580 l l Table 5.1 Mass Flow Rate as a Function of Temperature 1 l I I l l l I
l l 41 l i i Compainen of Test 204 and 211 HTFM Hast Tiensier Coeindent 70 C Hortaereal Consensm0 Suriace ..
"M5
/ ..
r f- s .. i g n_ / " u-- { ,,,. _. / -- .. 3 .. ..
==
.= m. .a == a n,. an as a um a == ,,.a dessene,es)
Figure 5.1 Consistency in HTFM (Horizontal) Componean of Test 204 and 211 HTFM Host Teensfer Ceemeent l .. vm m m i t
- 94. =
i.- .. E '" - . .g__ I - h l .- N-. n l t 3 {
.. , =.. .. = = = . .... .
mm l l Figure 5.2 Consistency in HTFM(Vertical) l t i
42 Compertson of test 204 and 211 CEB Heat Tr.nst.t CoeNksert
- Con - oson T
'-- T l 1 l
Fr i - :' r_ f~ TT-l I .. I. f~ T 1 l l I'I 1
; it l .i. l r--
-- i l l ll l I l l j l l l l l k'
I" I I I l 1 1 l l l l l l l l l l I l l l l l l l l l l I l l
-- I 1 l. l l l ;l l l
, , i ;
I l I l l
. l . !! . .
I l I I esapese tem) I l l l Figure 5.3 Consistency in CEB (Horizontal) t YNSUEec cE v %- r-
.- F ,
? .
l ;A
.c y l i l l
E I I l l I
; -I i l
l'i l l l
; 'J_'I I I l l l l -- l l l
I I l 8 ' I i 1 1 l l l l I l 1 l 1 I 11 1 1 l l
-- I I I 1 I I l ' I I I I l l l l I I I i I I l l l I i l I l
esma mi l Figure 5.4 Consistency in CEB (Vertical)
4 43
- of the condensing plate and end at the right hand comer of the test section where the horizontal plate meets th
- vertical condensing plate. The coordinates of the venical plate heat transfer coefficient plots i'
start in the comer of the two condensing plates and continue down the condensing surface. 5.2 Three Dimensional Effects Study 511 Descriotion of test < One of the first experiments conducted was to determine whether there were any signi5 cant three l dimensional effects present in the heat transfer coefricient. These tests are classiSed as the series 100. To study this the HTFM's were moved from the center hole of the condensing plate 6.25" from the Lexan 1 front sheet to the outer locations 1" from the Lexan sheets. This test was done at 60"C. 512 Results Discuseion Figures 5.5 and 5.6 show the measured heat fluxes at the various positions. The back holes n:fer to the holes funhest from the Lexan face with the probe holes drilled in it. The front and back holes should produce relatively the same heat transfer coefficients due to symmetry arguments. The graph I shows that the heat transfer coefficients measund when the HTFMs were in the center positions straddled the values of the heat transfer coefficients measured in the front and back locations. This suggests that there are no significant noticeable three dimensional effects in the heat transfer coefficient, and the test section can be treated primarily as a two dimensional slice. The data for 60*C produces the worst relative errors due to the fact that the temperature difference through the cross section of the aluminum condensing plate is low. This enhances the error in the difference of the successive temperature measurements and causes larger relative errors than the higher temperatures, yet no presence of three dimensionality seems to exist.
44 , i l 1 Tires Oh.e smd E.ms. so C 6emesnad Censename twense
. p,
~
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,/ \s\
a-
'f
, s '- N
=.
%. - K gs e ,. . '- - f N c ~ ./
1 -- -
- %.N f-
-e n to
-Frant
-- c H.e Le.aht as -
,u. .. .
== >= . == . mi. == .
m, Figure 5.5 Three Dimensional Effects (Horizontal) flwee De - Eneses to C r _m f.
.. .. / % v/ A N s
,]*j- ) j N\ Nh s 2 -- Q ,,
y ..
~
v 7 \ i.- y
- a n -m
.. -r, n 62
-c . t
*= >= d= d == di in n's J. d, d, e, ,;,
9 i f Figure 5.6 Three Dimensional Effects (Venical) 4 3 4 2 v r s
l 45 l i j
!3 Air / Steam at Varlons Temneratures (Uniform Inf ection) 511 Descrintion of Test ne next series of tests, designated test series 200, were conducted to test the effects of the heat l
transfer coefficient with an increasing temperature difference between the test section 4tmosphere and the cooling plates. These air / steam tests were conducted with the miiform injection system shown in Figure 4.6. , 5.3.2 Results/ Discussion Table 5.2 shows typical average values for the heat transfer coefficients at various temperatures 1 measured by both the HTFM's and the CEB methods. The average values are given for both the vertical and the horizontal oriented condensing plates. Typical local heat transfer coefficients are given in j l graphical form in Figures 5.8 - 5.16 which have been taken from reference [5). A definite trend in the l heat transfer coefficiems was observed. As we move along the vertical plate from the top of the test i section down, the heat transfer coefficients decreased steadily until reaching coolant plate #10 or #11 ( a distance of approximately 46 cm dov,n from the comer of the test section see figure 5.17). At this point j
\
there is a slight increase in the heat transfer coefficient which usually continues across the last cooling plate. The behavior of the top (horizontal) plate seems to be more sporadic than that of the vertical side plate. The top plate has a consistently higher heat transfer coefScient than that of the vertical plate. There also seems to be a slightly larger discrepancy between the HTFM's and the CEB measurements in the horizontal plate. This increased heat transfer coefficient and the discrepancy in the two methods of measurement may be a result of droplet formation and the presence of rain from the top surface. Such a rough surface presented to the flow combined with the natural convective flow pattem may cause the difference, although analysis is still under way. The inorganic zine coating promotes filmwise condensation, however as noted by Huhtiniemi at angles ofless than l' and with velocities less than Im/s droplets will form on the surface. Although, the
I j t
- 46 i
i i 1 4 i <
- l 1
i I Test Section HTFM CEB HTFM CEB l Temperature HorizontalPlam HorizontalPlate Vertical Plate Vertical Plate j 2 2 -
*C (w/rn O 2
(whn O 2 (w/m O (w/rn O J " 1
- 60 88.23 82.32 70.53 71.07 1
i 112.04 95.24 99.79 3 70 115.24 ; 80 209.5 195.32 168.4 173.32 4 85 229.84 238.15 178.02 201.74 j i ! 90 296.28 303.17 230.66 267.45 l 1 1 3 Table 5.2 Typical Average Heat Transfer Coefficients ) l l 1 ) 5 l t b i l l 1 i i l.
- . . _ , . - - 4 -= -,3 m - >- - w,.
i 4 4 i;
- 47
=c Co.sm tems.f.e..for a.GO.C.(.S.eemsAN) e tMa _,
s ' R .. ,,, r .. s I v
- g. .., ..
- 3. .. ..
4G a M* 6.00 7 83 tsJa 22.80 asee 38.t4 48.72 634e m.as 08 a0 7tJB esJ2 tim M (em) Figure 5.7 60 C Heat Transfer Coefficients (Horizontal) 1 l l l l Med vTr.an.sf.er
- c. C.omm.eer.t
. geC (S.iemmens)
,M-g --
- t. ..
t L ._ I
* " '- =
T ..
~~ ..
39 = 840 7 42 10Je 82.as se es as te es ?2 Sa me m as es as 7tJe e3.33 tim a= = Figure 5.8 60 C Heat Transfer Coefficients (Venical)
48 H.a r==s.c a 7ac (m = HmmunalCondsome Swtase m.
,<r
-- ., h
,- x ..
in- ::
- s. , _
p.
-r g ,-- I {
{. .. 2 m. N=
.. to , u n. , ,
xi. n nu .. .. mm .. h tm) Figure 5.9 70 C Heat Transfer Coefficients (Horizontal) Heat Tesudet Cosmeere 700 (SeemrM v.n c- se m.
,N- w
~ -
z .- S** ' __ "f'~ -p. ~_-,. I s .1 1 l
, ,.= == ==
.= ,a u,. an au a == == an ., a
-i, Figur: 5.10 70 C Heat Transfer Coefficients (Vertical)
49 Hans Tennuser Ceses ace mar) H-=== c% w .. me- .. m- ,_
,-s ..
,/
-- s u .. s s.
y -- 1= f.
.=
.. ,....an.......
damneo tes) Figure 5.1180 C Heat Transfer Coefficients (Horizontal) 1
,, Heat Tratuser cosmeere 80C (Sinam/ As) v.a c% s. .e a.-
aus - A
- 3. -
... I ..
T
~~
;~. -.
?. -
= ,_
1,.. f .. . Go a
==
. ,. ... .. . .= .. .. ..
m--. i-> Figure 5.12 80 C Heat Transfer Coefficients (Vertical)
i i i j 50 j 4 t i i i I Heat Trs=ler Cesame, seC (StearivAs) ! Horus=al * - , Surines 4
, m. 7 i T u x /
,. I 1./ .
d, . b.,,-- -
,T -- - ' <<
4
- { ..
i t m. i 1 e j .. ,i 1 4
...=.m,..
e 4 1 I i Figure 5.13 85 C Heat Transfer Coefficients (Horizontal) i i l 1-i d Heat Trarmeer Cesneers 36C (SisenvAr) i H === C=== , se i ass . 7 1 T - 1 / .{ r
.. ,. 1 3. / ..
} ,,.. g~. ., ,- ,T' - '~ 4<
! E .. ..
- I. ...
1 1 1 1
! l
.. \
J 1 I i
. . , . . . .. == .. .. =. . .. j
) a, 4 j Figure 5.14 85 C Heat Transfer Coefficients (Venical) j 4 a 1 i
._ . . . .. . - - - . = . .
4 5 . 51 f t J - i. i
- 1 s
- l4ent Trusser Coonoment 00C (Sesam/Ar)
HorusraelCerutermsg W 1 T i j . l ,a ..
/ :
l s .. -- / i s ..1 er s .. j .. 1 5 m. i . ., ,n, as an um mis a.n au == um na am .iu f i.
- 1
! Figure 5.15 90 C Heat Transfer Coefficients (Horizontal) I, 3 l, i' Heat Trarmeer Caetnoont 800 (SomenvAr) ve, c.a.a w i = 4 % 6 '% ;- T w y 4 .. .. s, s 2 .. .
; w
- p. ..
g .. 3
! .e.
1, ... j .. , 1 1 4 . , , .
; e. , ... a. m. .. .= um .. . == . . . . :
- -- 1 4 l i i i
4 i Figure 5.16 90 C Heat Transfer Coefficients (Vertical) d 1 I d i 1 l 1 l
52 1 J visual observation was obstmeted by condensation on the Lexan side walls of the test section it was observed that there was significant droplet fonnation on the top condensing surface. There also appeared to be a liquid film on the plate accompanying the droplet formation. From visual observation the J dmplets were seen to vary in size fmm approximately 0.2cm to 0.5cm. He vertically inclined plate was observed to have pure filmwise condensation with no droplets present. He presence of the droplets could ! have many effects on the heat transfer coefficient of the horizontal surface. The droplets attached to the J upper surface effectively increase heat transfer surface area which would result in the increased heat f transfer coefficients observed on the top plate. There may also be an increase in the heat transfer due to the enhancement of turbulent mixing caused by the departure of the droplets. The random occurrence of the droplet formation and the rain dmplet departure may have also contributed to the relatively unsteady nature in the heat transfer coefficient observed in the horizontal plate. The vertical plate heat transfer coefficient has very good agreement between the two methods of measurement as can be seen by Figure 5.3 and 5.4. The data presented in figures 5.8 through 5.16 was also cornpated with otherinvestigators of condensation in the presence of noncondensables, specifically Pernsteiner since his studies closely resembled the present work although at a much smaller scale. Pemsteiner investigated condensation on a vertical wall due to natural circulation. Although the test section geometry differs slightly, a relatively close agreement between his results and the current investigations was observed. As can be seen in Table 5.3 the average heat transfer coefficients in the current facility were slightly higher than those observed by Pernsteiner, nis could be attributed to the larger test section geometries, because the present test section was significantly wider, mixed convection heat transfer mechanisms may have lead to the slight i enhancement of the heat transfer coefficient. This effect was one of the primary reasons for the present
)
test section and the hypothesis of enhancement of the heat transfer coefficient due to mixed convection ; was observed This effect also agrees with the observation by Westinghouse. Calculations were done ; with the correlations introduced in Chapter three and the results of the theoretical heat transfer I l
53 1 Test Section Heat Flux Strip Coolant Energy Balance Temperature ('whn2C) .(w/m2C) 60.7 62 56 70.9 103 104 79.9 157 149 85.3 193 182 90.2 267 251 Table 5.3 Pemsteiner's Reported Results Test Section Heat Transfer Coefficient 2 Temperature 'C (w/m C) l 60 70.15 l 70 104.43 80 159.47 85 202.39 90 267.7 Table 5.4 Theoretical Heat Transfer Coefficients
54 coefficients are given in Table 5.4. The horizontal plate heat transfer coefficients appear to be slightly higher than those calculated theoretically. His could be attributed to the raining effect observed on this l surface as discussed previously. De vertical plate hest transfer coefficients, which exhibited pure filmwise condensation, seems to agree well with the theory. 5.4 Air /Stenm at Various Temocrntures (Steam Generator Ruoture) 5.4.1 Descriotion of Test Test series 500 consists of a series of experiments designed to simulate a pipe rupture in the steam generator compartment of the AP600. De injection system was changed from the uniform injection system (Figure 4.6) to the injection system pictured in Figure 4.8. De right side of the steam inlet was plugged off and insulated so that no steam would exit and the test section would again be isolated from the environment. The test procedure was similar to the above mentioned procedure with the exception that preliminary velocity measurements were taken with a Hontzsch turbine anemometer. A 1.25" hole was drilled in the test section 16" from the vertical condensing plate and 2.5" below the horizontal condensing plate (between axial temperature locations 2 and 3) to provide for installation of I the velocity meter. Figure 5.17 indicates the placement of the velocity meter with respect to the steam injection inlet. A 3"long aluminum flange was constructed and attached to the test section so that the Hontzsh velocity meter could be inserted. To allow the direction of flow to be determined a plate with degree measurements was attached to the flange and a pointer positioned on the velocity meter, so that the relative angle of the velocity meter would be known. Velocity measurements were taken at several different angles. Zero degrees corresponded to the turbine vane wheel parallel to the top condensing surface with the flow toward the vertical plate corresponding to the positive direction. The output of the meter was read from a Nicolet Oscilloscope as described in chapter 4. l 5.4.2 Results/ Discussion
i l i 55 De average values for the heat transfer coefficients are presented in Table 5.5. The heat transfer coefficients increased dramatically from those obtained with the uniform injection system especially at i the higher temperatures of 85* C and 90*C. Table 5.6 gives an idea of the mass flow rates needed to
! achieve a given steady state temperature in this test series. Although sufficient testing or analysis has not been completed the enhancement in the heat transfer coefficient could be a result of the effect of a jet of 1
steam impinging on the upper cooled condensmg surface. In the uniform injection tests the steam would 4 have dispersed more evenly and not created sach a jet effect. The temperature profiles indicate that there l is a plume of hot vaporin the vicinity of the injection, as would be expected Figure 5.18. Table 5.7 i show the velocity measurements as a function of temperature and angle. Although these are preliminary 1, l velocity measurements they indicate that the horizontal flow is too small to be detected by the velocity meter (less than 0.5 ft/sec). Some oscillation was observed at angles of approximately 60* and 120*. ] i his could be due to the inertia required to spin the turbine vane wheel. If the flow velocityis not fast enough there is not sufficient energy to overcome this inertia and the vane wheel may oscillate back and j fonh rather than spin in one direction, thus causing fluctuating voltage readings. When the velocity meter was rotated 90* so that the vane wheel was parallel to the vertical surface an upward velocity was seen to appear at 80*C, although it was only slightly above the velocity needed to overcome the inertia of the wheel, ne velocity was observed to increase as the steady state temperature of the test section and correspondingly the mass flow rate was increased. This indicates that there may be some jet ! . i
! impingement on the upper condensing plate due to the modified steam injection system. These velocity measurements were mainly done to test the use of the meter and measurement techniques. Many more ! test will have to be conducted before a accurate determination of the velocity field can be obtained.
k i
i 3 l 1 l 1 l y 56 i
- Velocity Probe Location 1
d l r1 r1 j i l 1 2 3 4 5 6 g i i r d '--------- i i i i i i ', L, ' I
~
7 1 o o oo o . 1 8 o o o o o - l l 9 l - I 10 I o o o o o - 1 1 11 I . I 12 I o o o o o i . 1 I I i i l I o o o a l I l I i l i I I I o o o o l I I I I I I I I I I I I I I I I I I I i i I I y I I l r" L I LJ LJ Figure 5.17 SGPR Location and Velocity Probe Location I 1 l l l 1 i
i . 57 4 ? i 1 } n !"1 , 11 1 pJ L_________ , , , , , , L, i L, ' J o e o o ~ M50 9040 M43 . 90.16 o o e o o - I l" I 9146 M90 9t0! 9L00 90A4 , I J l
- I o o o o o .
< l 4 1 9047 M90 9L14 9040 90A3 I . I I i I e o o o o j 90.50 M70 9L49 90.90 99.% g 4 I' o o o o j I 9027 M90 9L60 90A0 i 1 . I j I o o o o j l M90 M92 9L60 9022 . I 1 4 I . l
. 1 I I l
i 1 1 1 l l i 1 I 1 llI ! I i rd '- i
- L _________________________
LJ LJ i i ( i j Figure 5.18 Temperature Distribution 90C SGPR f i i. J 4 4 1 s
* $8 i
! 4 3 1 i i Test Section HTFM CEB HTIM CEB HorizontalPlate Horizontal Plate VerticalPlate Vertical Plate J Temperature
'C (w/m O 2
(w/m'O (w/m'C) (w/m'C) 1 97.43 85.66 79.1 72.92
! 60 154.26 141.46 112.15 112.75 70
) 174.19 179.53 139.44 123.52 i 80 4 317.98 300.28 210.48 233.53 i 85 i 90 512.73 488.82 371.3 387.47 e f Table 5.5 Heat Transfer Coefficients i i Test Section Mass Flow Rate Temperature *C (kg/sec) J 60 0.00164 { )' 70 0.0022 f 1 80 0.00312 f 85 0.00467 i ! 90 0.00781 l t
? Table 5.6 Mass Flow Rates as a Function of Temperature i
L r i 2
f 59 NPemum Tempemum Tempemum Tmpemum CmPCNum Angle. 60 70 80 85 90' O 40 Ductuadm . ~ Ductuadon 80 fluctuadon amund 0.5(ft/s) around 0.5(Ws) 0.88(ft/s) 1.37(ft/s) 1,45(Ws) 90 SPoradic around 120 - fluctuation fluctuadon 0.88(Ws) 180 - Table 5.7 Velocity Measurements l l l I
60 l Chapter 6 Air / Helium / Steam Experiments 6.1Summnry Descrintion of Ernerimental Procedure The pmcedure used in the series 300 experiments (air / helium / steam) was the same as that mentioned in chapter five with the air / steam experiments except that helium was added in various molar l l concentrations. The facility depicted in Figure 4.1 was modified slightly to allow the injection of a l l helium air mixture. Figure 6.1 is a schematic of the experimental apparatus containing the additional features. Building air and industrial quality helium (99.9% pure) was passed through two separate Dwyer RMC series air flow meters into a tee section, where the gases mixed prior to entering the test section. The flow meters were factory calibrated for air, themfore a correction factor for the diffemnt mass of helium was used: i Q2=O1 sg , where Q2 is the actual flow corrected for the specific gravity, Qi is the observed flowmeter reading and ( l s.g is the specific gravity of helium. The flow rates of the meters were adjusted so a particular molar percent of helium in air was entering the test section. A sufficient volume of the gas mixture was allowed to flow through the test section so that a uniform concentration existed. Gas samples were taken after the mixing tee and in the midsection of the test facility to ensure that the there was an even distribution of ! 1 1 1 I
. . - - . - . . - - . . . .. . -. = - . , ~ . . . - . . - . _ _ .
l l l
- 61 l
l-hPressure
@Tegerature
@ Flow Coolant manWolds El l' l't',
x
. . . . ,-- . sta.
~
HX-150
-- water P -
C bath He h cn . . . . O Suppty Test Section _.6, I
% a T F Q
Sussman Boiler l Dram l OO e
-O Hign Pressure Boaer feed water I water pump 1
! Arr Supply supply ! Low Pressure ! feed water pump r l l I l t l l Figure 6.1 Esential Components of Helium Experiments 1 1 r l
' ' ' --1-, -w ..-m, ,, _ _ _
1 1 i l 1 62 4 the gas mixture, ne gas samples were analyzed on a mass spectrometer to ensure the proper mixture j existed in the test section. Prior to taking a gas sample tne gas sampling apparatus (discussed in chapter i 4) was evacuated to a pressure of no more than 2 torr. He purge tank was filled with test section gas and 1 a sample was taken. De two gas concentration measurement techniques (volume flow rate and mass i spectrometer analyzed gas sample) yielded similar results that were within the ermr of the volume flow 4 meters. He volume flow meters had the drawback that they were only able to measure the initial gas 1 concentration therefore the gas sampling technique was needed to allow the sampling of the test section l ^ gas laterin the test. After a molar percent of approximately 4,8,16 or 30 was achieved (as measured by the mass spec.) the boiler was turned on and steam allowed to enter through the throttling needle valve until one of the steady state temperatures was reached. Gas samples were taken at each of the separate i steady-state temperatures so that the noncondensible gas mixture would be known. I His procedure produces slightly different results than what would occur in an actual accident scenario. The steam entering the contamment atmosphere would react with the metal cladding material. his oxidizing reaction would replace some of the steam with hydrogen gas. In our experiments the 4 amount of helium (substituted for hydrogen) to air ratio stays constant while the total noncondensible gas 1 fraction decreases with increasing test section temperature. However, this difference in introduction of the light gas species does not effect the experimental results, j 6.2 Results/ Discussion I, Table 6.1 shows the average heat transfer coefficients at various temperatures and helium concentrations. The local heat transfer coefficients can be found in reference 4. Figures 6.2 to 6.5 show the effects of the various concentrations of helium at a temperature of 70*C. A trend was seen in the heat transfer coefficients as the helium concentrations were increased from 0 to 30 percent molar. There appears to be a degradation in the heat transfer coefficient in the vicinity of cooling plates #5 and #11. His usually 1
63 occurred when the helium concentrations were above appmximately 4% molar, however some tests with helium concentrations above this value did not exhibit this phenomena. Some air / steam only tests (series 200) were repeated after this phenomena was observed to check for possible systematic errors but none were found and the air / steam only tests compared well to previously measured tests. The origin of this degradation is not known,it is possible that it is some sort of random flow phenomena caused by light helium gas accumulation, orit could possibly be some yet undetected systematic error. < Other than the unexplained dip in the heat transfer coefficient at plates #5 and #11 the air / helium / steam experiments produced heat transfer coefficients similar to the air / steam only experiments. This phenomena was also observed by Pernsteiner. He made an attempt to explam this similarity in helium 4 and air experiments by considering that the increase in the diffusion coefficient with helium present was off set by a stratification oflight gas next to the condensing plate. The increase of the diffusion coefficient of steam with the presence of helium increases the mass transfer coefficient and thus increases the heat transfer due to condensation / evaporation. He suggested that this incitase of the heat transfer was suppressed by a stratification layer that may have formed next to the plate. l 3 ) i 4 1 s
I 64 Test Section Molar H7FM CEB HTFM CEB Temperature Fraction He Horizontal Horizontal Vertical Vertical 29.3 71.96 69.74 64.89 60.27 60 17.2 78.1 77.13 69.37 65.76 7.74 86.66 83.08 69.88 73.14 l 3.8 78.77 79.05 69.57 73.28 27.9 94.73 96.61 87.41 79.62 70 ( 15 119.46 113.8 101.42 100.25 7.13 126.99 112.82 101.59 101.34 4.35 103.64 103.49 94.28 90.94 80 31.8 148.35 158.11 130.9 135.34 14.18 183.77 171.95 152.6 145.75 8.81 205.28 183.11 163.03 156.31 3.68 203.62 184.64 162.52 150.34 85 29.7 182.9 217.39 162.61 180.26 16.5 247.69 245.02 199.98 204.78 8.8 194.6 224.74 216.49 201.2 4.06 199.01 228.97 173.85 192.55 90 27.96 239.13 274.76 200.37 224.07 l 16.38 315.83 310.62 252.54 261.67 7.37 308.84 206.14 247.79 265.32 1 4.06 239.82 249.51 190.48 205.17
65 Eneasof %%wnConsenwason 130 WTFM 70 C Hensemel Plass 180-Y 140-
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000 15% He r 40 - 052 27.9% He i i to - I 0 ' 0.00 712 15'.24 22586 30548 3d10 4d72 $I34 60!96 68558 76'.20 83.82 91'.44
-e r Figure 6.3 1
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20 - O , , , , , , , , , , , , 0.00 7.62 15.24 22.86 30.48 34.10 45.72 53.34 80.96 64.58 78.20 83.82 91.44 ! ammm. m Figure 6.4 l 1
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i 40 - 090 15% He l t352 27.9% He i, m-J ! 0 , , , , , , , , , , , , 0.00 7.62 1524 22.06 30.48 38.10 4172 53.34 60.96 68.L8 76.20 83.42 91.44 4 3 i l Figure 6.5 1 i < f i i k ei 4i ia 4 J 9
69 I I Chapter 7 Observations Experiments were conducted to determine the beat transfer coefficient, of steam in the pmsence of noncondensable gases, on a horizontal and venical cooled condensing plate with a sunilar surface finish as the Westinghouse AP600 contauunent. Preliminary scoping tests seem to indicate the following: - A slightly higher average heat transfer coefScient on the top condensing plate than on the vertical condensing plate was observed. This is assumed to be a result of the presence of droplets on the upper surface which results in an increased heat transfer area. - Comparisons of air / helium / steam tests to the air / steam only tests did not show any significant change in the heat transfer coefficient for helium molar ratios between 4 and 30 percent except the reported l l degradation near plate #5 and #11. The presence of this degradation is unknown at the present time. - The steam generator pipe break injection system showed increased heat transfer coefficients over the uniform injection system. This may be as result of a steam jet impinging on the surface of the upper plate. Unfortunately velocity measurements could not be obtained for the uniform injection series and only preliminary measurements were conducted with the SGPR injection system.
i 70 Some work luis been done to try to visualize the developed flow pattems in the test section, but the Presence of condensate on the side walls has slowed the effort. l i I l l l l l l
l 71 l l Bibliography 1 [1] Westinghouse Electric Corporation, Tests of Heat Transfer and Water Film Evaporation From a Simulated Containment To Demonstrate the AP600 Passive containment Cooling System, Westinghouse Report NSE-90-0013, Jan.1990 [2]Huhtiniemi I. K., Condensation in the Presence of a Noncondensable Gas: The Effects ofSurface ; l Orientation, PhD Thesis, University of Wisconsin,1991 ; [3)Pernstiener A. P., Condensation in the presence ofnoncondensable Gas: Efects ofHelium Concentration, Ms 'Ihesis, University of Wisconsin,1993 ; [4] Bird R. B., Stewart W. E., Lightfoot E. D., Transport Phenomena, John Wiley,1960 ; I [5] Anderson M. H., Data Book of Condemation E2periments, University of Wisconsin,1994 l l [6]Incropera E.P., Dewitt D.P.,Introdue; so Heat Transfer, John Wiley,1990 l . [7JShell Flow Meter Engineering Handbook, edited by Preston T. S.,1968 l I [8]Glasstone Laidler, Eyring, Theory ofRate Processes, McGraw-Hill,1941 i [9]Hirschfelder, Molc>ular Theory of Gases and Liquids, John Wiley,1954 l l [10]Rohsenow W. M., Heat, Mass, and Momentum Transfer, Pretidce-Hall,1961 [11] Woodcock J., Spencer D. R., Kennedy M.D., Howe K. S., Westinghouse - GOTHICt A computer Codefor Analyses of Thermal Hydraulic Transientsfor Nuclear Plant Containments and Analliary - l Buildings, Westinghouse Report WCAP- 13412 [12] Shepherd J.P.G., Data Analysis, University of Wisconsin (River Falls),1992 i [13] Box G.E.P. Statisticsfor Experimenters, John Wiley 1978 [14]Suryanarayna N. V., Malchow G. L., Film Condensation on inclined Plane Surfaces, Transactions of ASME, J. Heat Transfer, vol. 97(1), pp 79-82,1975 [15] Fox R. J., Nagasaki T., H1hikata K., Peterson P.F., Heat Transfer and Stability Phenomena in Gas ) Loaded Condensers, Dept. of Nuclear Engineering, University of Califomia, Berkeley. [16]Siddique M., Golay M. W., Kazimi M. S., Local Heat Transfer Coefficientsfor Forced Convection Condensation ofSteam in a Vertical Tube in the Presence ofAir, Dept. Of Nuclear Engineering, MIT l t - -_- - . - , -
72 l l 4 (17] Kang H. C., Kim M.H., Characteristics of Condensation heat Transfer with Wavy interface in the Presence ofNoncondensable Gas, NURETH 6 Conference l18]Barry JJ., Effects ofInterfacial Structure on Film Condensation, PhD Thesis, University af Wisconsin,1987 i l19]Dallmeyer H. Stof-und Warmeubertragung bei der Kondensation eines Dampfes aus einem Gemisch mit einem nicht knodensieren Gas in laminarer und turbulenter Stromungsgrenzschicht, VDI-Forschungs-Heft 539, pp. 5-24,1970 [20]Dehbi A. A., Analytical and ExperimentalInvestigation of the Efects ofNon-condensible Gases on Steam Condensation under Turbulent Natural Convection Condition, PhD Thesis, Dept. Of Nuclear l l Engineering, MIT, Jan.1991 [21] Gerstmann J., Grifilth P., laminar Film Condensation on the Underside ofHorizontal and inclined Surfaces, Int. J. Heat Mass Transfer, vol 10, pp. 567-580,1967 (22]Henderson C.L., Marchello J.M., Film Condensation in the Presence of a Non-condensible Gas, Transactions of ASME, J. Heat Transfer, vol. 91(3),pp. 447-50,1969. [23]Cho D. C., Stein R.P., Steam Condensation on the Underside of a Horizontal Surface, Proceedings of'Ihird Intemational Topical Meeting on Nuclear Power Plant 'Ihermal Hydraulics and Operations, Nov.1988 (24)Kmger D. G., Rohsenow W. M., Condensation heat Transfer in the Presence of a Non condensible Gas, Int. J. Heat Mass Transfer, vol.11 pp.15-26,1968 [25)Kutsuna H., Inoue K., Nakanishi., Film Condensation ofBapo Containing Non-condensible Gas in a Horizontal Duct, Int. Symposium on Heat transfer, beijing 1987 h (26) Robinson J. A., Windebank S.R., Measurement of Condensation Heat Transfer Coeficients in a Steam Chamber Using a Variable Conductance Heat Pipe, Proc. 2nd UK National Conference on Heat Transfer, vol.1, pp. 617-637, Sept.1988 a (27JSlegets L., Seban R.A.,lsminar Film Condensation ofSteam Containing Small Concentrations of 3 Air, Int. J. heat Mass Transfer, vol.13, pp.1941 1947,1970 (28] Spencer D.L., Chang K.1., May H. C., Experimental Investigation ofStability Efects in Laminar Film Condensation on a Vertical Cylinder, International Heat Transfer Conference, Paris, vol. 6, Paper CS 22.3,1970 l 1 4 4
73 l l Appendix 1 Thermophysical Properties ne procedum used to obtain the values of the thennophysical properties of the aluminum plate are presented along with the values used. His was done by PurdueUniversity's Thermophysical Properties Research Laboratory.
74 TABLE OF CONTENTS 1 INTRODUCTION . . . ........... . .................................. R ES U LTS AN D DISCUSS ION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 List of Tables
- 1. Specific Ilear Results . . . . . .. ... .................... .......... 3
- 2. Thermal Diffusiviiy Results .. ... . ... . ................... . ... 4
- 3. Thermal Conductivity Results . . . ................................. 4 l
l t List of Figures
- 1. Differential Scanning Calorimeter . . .. .................... ... ....... 5
- 2. Digital Data Acquisition System .. . ..... ......................... 6
- 3. Flash Diffusivity Apparatus . . . .. ..... . ....... .. . .. . 7 l
- 4. Specific Heat . ... . .... ... ..... .. .... ........ 8 l .
- 5. Thermal Diffusivity . . . . . .. ............ .... . . .... ... 9 i
- 6. Thermal Conductivity . . .... . ... ... ................... . . . . . . 10 l
[ t
75 Thermophysical Properties of Al 2024 INTRODUCTION Samples of Al 2024 were submitted for thermophysical property determinations. Specific heat (C) was measured using a differential scanning 4 .hneter. Bulk density (d) values were obtained form the sample's geometries and mass. Thermal diffusivity (a) was measured using the laser flash technique. Thermal conductivity (A) values were calculated as the product of these quantides,i.e. A = aC,d. Specine heat is measured using a standard Perkin-Elmer Model DSC-2 differential scanning calorimeter (Figure 1) with sapphire as the reference material The standard and sample were subjected to the same heat flux as a blank and the differential powers required to heat the sample and standard at the same rate were determined using the digital data acquisition system. From the masses of the sapphire standard and sample, the differential power, and the known specific heat of sapphire, the specific heat of the sample is computed. The experimental data are visually displayed as the experiment progresses (Figure 2). All measured quantitics are directly traceable to NBS standards. Thermal diffusivity is determined using the laser flash diffusivity method. In the flash method, the front face of a small disk shaped sample is subjected to a short laser burst and the resulting rear face temperature rise is recorded and analyzed. A highly developed apparatus (Figure 3) exists at TPRL and we have been involved in an extensive program to evaluate the technique and broaden its uses. The apparatus consists of a Korad K2 laser, a high vacuum system including a bell jar with windows for viewing the sample, a tantalum or stainless steel tube heater surrounding a sample holding assembly, a thermocouple or an i.r. detector, appropriate biasing circuits, amplifiers, A/D converters, crystal clocks and a minicomputer based digital data acquisition system capable of accurately taking data in the 40 microsecond and longer time domain.The computer controls the experiment, collects the
e 76 i j l data, calculates the results and compares the raw data with the theoretical model. RESULTS AND DISCUSSION The diffusivity sample was 1.271 by 1.338 by 0.3806 cm and with a density of 2.769 gm cm" Specific heat results are given in Table 1 and Figure 4. The specific heet was measured during three runs. The speciGc heat values measured during the first run increases rapidly with increasing temperature and exhibited peak near 235'C. The speciGc heat values measured during run two were smaller and the peak was about gone. The values measured in during run ihree were smaller yet and the peak had disappeared. Obviously the sample annealed during these runs. Thermal diffusivity values are given in Table 2 and Figure 5. Using these results and the specific heat values from run three, thermal conductivity values are calculated in Table
- 3. The specific heat values from run three were used because the additionalheat from the laser flash technique does not alter the annealing process so the "true" specific heat and not j the " apparent" specific heat is involved. The conductivity values are plotted in Figure 6.
l The conductivity values increases from 1.22 to 1.69 W cm K between 23 and 250'C. l l l l
t , TABLE 1 Specific Heat Results Temperature Run-1 Run 2 Run 3 (C) - (W-s/ga-K) (W-s/ga-K) (W-s/ga-K)
- 23. 0.8750 0.8750 0.8750
- 50. 0.9400 0.9200 0.9040
- 75. 0.9840 0.9480 0.9190 100. 1.0350 0.9790 0.9370 125. 1.0800 1.0030 0.9530 ,
l 150. 1.1280 1.0200 0.9640 175. 1.2050 1.0340 0.9740 200. 1.2970 1.0530 0.9790 225. 1.4040 1.1090 0.9800 235. 1.4250 1.1160 0.9810 245. 1.4160 1.0800 0.9870 250. 1.3880 1.0510 0.9920 ti 4
78 TABLE 2 Thermal Diffusivity Results Temperature Diffusivity 2 (c) {em see ~1) 23.0 0.50502 50.0 0.53243 100.0 0.53840 150.0 0.57004 200.0 0.58822 250.0 0.61410 TABLE 3 Thermal Conductivity Calcutstions samle Tom. Density Specific Nest Offfusivity Conduct. Condtxt. Tem
-11 2 -1 1 (No.) (C) (ye em 3)(W s-pa K ) (ce sec ) (W cm K 1) (BTU *) (F)
A 23.0 2.769 0.8750 0.50502 1.22359 848.94 73.4 50.0 2.769 0.9040 0.53243 1.33281 924.72 122.0 100.0 2.769 0.9374 0.53840 1.39752 % 9.61 212.0 150.0 2.769 0.9638 0.57004 1.52132 1055.50 302.0 200.0 2.769 0.9779 0.58822 1.59270 1105.03 392.0 250.0 2.769 0.9923 0.61410 1.68735 1170.70 482.0
* (BTU in hr' ft F )
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85 Appendix 2 Data Reduction Program Appendix 2 consists of the data reduction program used in the analysis of the heat transfer data. s
ww l u i201sdL5 Res c rr#4t t i w.va sikre, nS. 100 REM 4500 s ( 5, 4) = 6.645
- 4600 x ( 6, 1) = 29.299 200 REM 4700 a (6, 2) = 21.59 300 REM POSTTEST = Surface Temperature Check 4800 a ( 6, 3) = 13.881 400 REM 4900 a ( 6, 4) - 5.893 4 500 REM version 3.18 Oct 1989, for AP-600 8 test series 5000 s t?, 1) - 31.433 600 REM 5100 s t?, 2) = 23.533 700 REM Feb 1990, the error estimates corr. 5200 a ( 7, 3) = 15.964 800 REM jun 1990, DA$-8 humidity, temp data 5300 m l 7, 4) = 7.881 900 REM 5:05 a (8, 1) = 29.527 1000 REM (C) Capyright 1987 J. J. Barry, modif icat ions I.H. 5310 a(8, 2) = 21.958 1100 REM 10/0/93 M.H. Anderson (expansion to 12 heat flux meters, additio 5315 a(8, 3) = 14.203 n 5320 ste, 4) = 6.164 1150 REM of conductivity of CZn coating, 7 tmin temperatures 5325 a (9, 1) - 30.622 1200 RFM 5330 a tt, 2) = 23.106
- 5315 x ( 9, 3) = 15.13 1300 KEY OFF 5340 x (9, 4) = 7.155 1400 COLOR 15, 1, 1 5345 x(10, 1) = 30.531 1500 DIM a (12, 4), F$ (12, 4), FTCS(12, 2), t emp (12, 4), tc(12, 2), SD (12, 41, sdt c (1 5350 alto, 2) = 22.428 2, 23, sigt e (12) 5355 a(10, 3) = 15.062 1600 DIM sigmatb(12), s iqdt da (12), hfmerr(12), sdt (12), sdt deit (12) , dt s t awa11 (12), 5360 a(10, 4) = 7.086 ceberr(12) 5365 x(11, 1) = 28.905 1700 DIM Tback(12), t surf t12), Tin f ac (12) , hf (12), SERR (12), dt dx (12) , ht c(12) 5370 x(11, 2) = 2 0. 90 4 1800 DIM flow (12), HFAVG (12), ht carg (12), LENGTH (12), VAI S ( 3) , HUTE ( 3, 2), SD RUTE (3 5375 x(11, 3) = 13.119
- 2) 5380 s(11, 4) = 5.042 1850 DIM tala (12), FTEMs(12), TMIx5TD(12), qe r t (12) , edsurft12), Tinerr(12), sigqceb $385 a(12, 1) = 30.053 (12) 5390 x(12, 2) = 22.281 1900 nhfu - 12 5395 a(12, 3) = 14.31 2000 kal - 1.3179 5400 x(12, 4) = 6.312 2001 REM the value of the cond1ctivity of the C2n was taking as 6000 REM 2002 REM the arthritic mean of the range given by the manuf actures 6100 REM Set number of t/c's per heat flua meter 2003 REM range (0.0159-0.0260 w/ cmc) the error is the standard deviation 6200 REM 6300 2010 kan = .020913 6400 nt e - 4 2011 sigkal = .07178 6500 LENCTH = .3048 2012 sigra = .005 6700 CLS 2015 dcarb = .09525 6800 PRINT *MIDTEST = Surface Temperature Check Version 3B-2100 PMIDTH = .1524 6900 PRINT 2105 sigflow = .038 7000 PRINT 7300 INPUT
- Enter t he test number a *, TESTN01 2300 REM Set thermocouple positions in a!! heat flus meters ?$00 OPEN
- coolant.dat" FOR INPUT A$ 91 2400 REM measured from the backside of the condensing plates in mm 7600 FOR k = 1 TO nhfa 2505 REM probe one position locations changed to test plate 12/12/93 7700 IMPUT 01, flow (k) 7800 flew (k) = flow (k)
- 3.7853 2600 x (1, 1) = 29.733 7900 NEXT k 2700 u (1, 2) = 21.733 8000 CLOSE 01 2000 x (1, 3) = 13.733 8100 PRINT 2900 x (1, 4) = 5.733 8200 REM 3000 m (2, 1) - 30.036 8300 REM read in data file names from aetup file 3100 x (2, 2) = 21.908 8400 EEM 3200 s (2, 3) = 13.907 8500 OPEN *posttest.inp" FOR INPUT AS 61 3300 x (2, 4) - 5.906 8600 LINE INPUT $1, AS ' header record 3400 s t 3, 1) = 29.02 8700 INPUT 81, IDS, ISLOT, CHAN4, A 2D 4, ICAIN, freq, N$, ICAL, FCAL$, FTEMS(1)*tatal ,
3500 x (3, 2) = 22.2 8705 INPUT et, IDS, ISLDT, CHAN%, A2D%, I CA IN, freq, NS, ICAL, FCAL$, FTEM3(2)*tala2 3600 a (3, 3) = 14.199 8710 IMPUT $1, IDS, ISLOT, CHANT, A2D%, ICAIN, freq, MS, ICAL, FCALS, FTEM$ (3)
- talm2 3700 m (3, 4) = 6.198 8715 INPUT 81, IDS, ISLOT, CHANT, A2D4, IGAIN, freq, MS, ICAL, FCALS, FTEMS (4)*taiz3 3800 x(4, 1) = 29.794 8720 INPUT 51, IDS, ISLOT, CHAN%, A2D4, ICAIN, frog, NS, ICAL, FCALS, FTEMS (5)
- tala3 3900 x(4, 2) = 21.26 0725 INPUT 61, IDS, ISLOT, CHAN4, A2D%, ICAIN, freq, NS, ICAL, FCALS, FTEMS (6)*talm4 4000 a tt, 3) = 13.869 8730 INPUT 01, IDS, ISLOT, ChAN%, A 20 4, IGAIN, freq, NS, ICAL, FCALS, FTEM3(7)*talm4 4100 a tt, 4) = 6.096 8735 INPUT 01, IDS, ISLOT, CRANt, A2D%, ICAIN, f r eq, MS, ICAL, FCALS, FTEM3 (Sj
- tat 5 4200 m (5, 1) = 30.585 8740 IMPUT St, IDS, ISLOT, CHANS, A2D4, I CAI N, freq, NS, ICAL, FCALS, FTEMS (9)
- taim5 4300 a t$, 2) = 22.228 8145 INPUT 51, IDS, ISLOT, CHANT, A2D%, I CA !N, freq, NS, ICAL, FCALS, FTEMS (10) *talm6 4400 a (5, 3) = 14.671 8750 INPUT 01, IDS, ISLOT, CHAN4, A2Dt, ICAIN, freq, NS, ICAL, FCALS, FTEMS (11)
- talm6
arr; rrs":Tess 4 1 9#06/02 i !. .Ea
~g L}iO8i21!43.;j{ htf6, bas em 8755 INPUT 01, IDS, ISLOT, CRAN 4, A2DL, ICAIN, freq, NS, ICAL, FCALS, FTFM5(12)* tela e 7 10900 INPUT SI, IDS, ISLOT, CHAN%, A2D4, ICAIN, freq, M S, ICAL, FCALS, FS(2, 4)* 2d 8 F98 INPUT G1, IDS, ISLOT, CHANT, A2D%, ICAIN, freq, NS, ICAL, FCALS, FSTEN3' eteam 11000 INPUT 81, IDS, ISLOT, CHAN%, 82D%, ICAIN, freq, N S, ICAL, FCA L$ , FS (3, 1)*hf-3e 8800 INPUT 91, ICS, IS LOT, CHAN%, A2DS, ICAIN, freq, NS, ICAL, FCALS, FTCS (1, 1)*c11 11100 INPUT 61, ID$, !$ LOT, CHAN4, A20%, ICAIN, freq, N S, ICAL, FCA LS , FS(1, 2)* 3b n-1 11200 INPUT 61, IDS, IS LOT, CHANS, A2D%, ICAIM, freq, NS, I CA L, FCALS, FS(1, 3)* Sc 8900 INPUT 91, IDS, ISLOT, CRAN 4, A2D4, ICAIN, freq, NS, ICAL, F CA L$, FTC$(1, 2)
- clo 11300 INPUT 51, IDS, ISLOT, CRAN %, A2Dt, ICAIN, freq, N S, ICAL, FCALS, F$(3, 4)* 3d t-1 11400 INPUT 91, IDS, ISLOT, CRANt, A2Dt, ICAIN, f rog, N S, ICAL, FCALS, F3(4, 1)*h!-ta 9000 INPUT 61, IDS, I S IDT, CHAN%, A2Dt, ICAIN, freq, N S, ICAL, FCALS, FTCS (2, 1)*c11 11500 INPUT 91, ID$, ISLOT, CHAN4, A2Dt, ICAIN, freq, NS, ICAL, FCALS, FS(4, 2)* 4b n-2 11600 INPUT 81, ID$, ISLOT, CRAN %, A204, ICAIN, freq, MS, ICAL, FCALS, FS (4, 3)* (c 9100 INPUT el, IDS, ISLOT, CRAN 4, A2D%, ICAIN, freq, N S, ICAL, FCAL$, FTCS (2, 2)
- cl o II700 INPUT 01, ID$, ISLOT, CRAN %, A2D%, ICAIN, freq, 55, ICAL, FCALS, F${4, 4)* 4d t-2 11000 INPUT 61, IDS, ISLOT, CRANt, A2D%, ICAIN, freq, N S, ICAL, FCALS, FS (5, ll'nt-Sa 9200 INPUT 01, IDS, ISLOT, CHANT, A 2D t, I CA I N , freq, NS, ICAL, itALS, FTCS(3, 1)*c11 11900 INPUT 01, IDS, ISLOT, CRAN %, A2D%, ICAIN, freq, NS, ICAL, FCALS, F$ (5 2)* Sb n-3 12000 INPUT 91, IDS, ISLOT, CRAN %, A20%, ICA!N, freq, MS, ICAL, FCALS, FS (5, 3)* Sc 9300 INPUT 51, IDS. ISLOT, CHAN%, A20%, ICAIN, freq. NS, ICAL, FCALS, FTC8(1, 2)*clo 12100 INPUT 91, ID$, ISLOT, CRANt, A2D%, ICh!N, freq, NS, ICAI, FCALS, F$ (5, 4)
- Sd t-3 12200 INPUT 01, IDS, ISLOT, CRAN %, A2Dt, ICAIN, freq, M S, ICAL, FCALS, F$(6, 13'hf-6a INPUT 01, IDS, ISLOT, CHAN%, A2DL, IGAIN, freq, NS, ICAL, FCALS, FTC$(4, 1)
- c11 12300 INPUT 01, IDS, ISLOT, CRAN %, A2D4, ICAIN, freq, MS, I CA L, FCALS, F$(6, 2)* Go 9400 n-4 12400 INPUT 51, IDS, ISLOT, CRAN %, A2D%, ICh!N, freq, N $, ICAL, FCALS, F$ (6, 3)* 6c INPUT 01, ID$, ISLOT, CHANT, A20%, ICAIN, freq, NS, ICAL, FCALS, FTCS(4, 2)*clo 12500 INPUT 61, IDS, IS LOT, CRAN %, A20%, ICAIN, freq, M S, I CA L, FCALS, FS (6, 4)* 6d 9500 t-4 12600 INPUT 01, IDS, ISLOT, CHAN%, A2Dt, ICA!N, freq, AS, ICAI, FCALS, F$ (7, 1)'hf-7a 9600 INPUT 81, ID$, ISLOT, CHAN4, A2Dt, ICAIN, freq, NS, ICAL, FCALS, FTC3(5, 1)'c11 12700 INPUT 51, IDS, ISLOT, CHANT, A2D%, ICAIM, freq, M S, ICAL,' FCALS, FS(7, 2)* 7b n-5 17800 INPUT 01, IDS, ISLOT, CRANt, A2D%, ICAIN, freq, MS, ICAL, FCALS, FS (7, 3)* 7c 9700 INPUT 01, ID $, ISLOT, CHAN%, A20%, ICAIN, freq, NS, ICAL, FCALS, FTC$(5, 2)* clo 12900 INPUT 81, IDS, ISLOT, CRANt, A2Dt, ICAIN, freq, MS, ICAL, FCAL3, F3 ( 7, 4)' 7d t-5 12905 INPUT 01, IDS, ISLOT, CHANT, A2Dt, ICAIN, freq, NS, I CA L, FCALS, FS(8, 1)*hf-8a 9800 INPUT 51, IDS, I SLOT, CH AN t, A2D%, ICAIN, freq, NS, ICAL, FCALS, FTC$(6, 1)'c11 12910 INPUT 01, IDS, ISLOT, CRAN %, A2Dt. IGAIN, freq, N S, I CA L, FCALS, FS (8, 23' 8b 12915 INPUT 51, IDS, ISLOT, CRAN 4, A2D%, ICAIN, freq, N5, ICAL, FCALS, FS(8, 3)* Sc n-6 9900 INPUT el, IDS, ISLOT, CHANT, A2Dt, ICAIN, freq, NS, ICAL, FCALS, FTC$(6, 2)*clo 12920 INPUT 51, IDS, ISLOT, CHAN4, A2D%, ICAIM, freq, N S, I CA L, FCALS, f$(8, 4)* 8d t-6 12925 INPUT 01, IDS, ISLOT, CRANt, A2Dt, ICAIN, freq, NS, ICAL, FCALS, F$ (9, 1)*hf-9a INPUT 01, IDS, ISLOT, CRAN 4, A20%, ICAIN, freq, N S, ICAL, FCALS, FTCS(7, 11*c1 12930 INPUT 01, IDS, ISLOT, CRANt, A2Dt, ICAIN, freq, MS, I CA L, FCAL$, FS(9, 23' 9b 10000 In-7 12935 INPUT 91, IDS, ISLOT, CRANt, A2D%, ICAIN, freq, NS, ICAL, FCALS, FS(9, 3)' 9c 10100 INPUT 81, IDS, ISLOT, CRAN %, A2Dt, ICAIN, freg, N S, ICAL, FCALS, FTCS(7, 2)'c1 12940 INPUT 01, ID$, ISLOT, CRAN 4, A20%, ICAIN, freq, MS, ICAL, FCALS, FS ( 9, 41' 9d ot 7 12945 INPUT 01, IDS, ISLOT, CHAN%, A2Dt, ICA1N, freq, NS, ICAL, FCALS, F$(10, 1)*hf-1 10110 INPUT #1, IDS, ISLOT, CRANt, A2D%, ICAIN, freq, N S, ICAL, FCALS, FTC3 (8, 1)'c1 Da in-8 12950 INPUT 01, ID$, ISLOT, CRAN %, A20%, ICAIN, freq, KS, ICAL, FCALS, F$ (10, 23' i 10120 INPUT el, IDS, I S LOT, CRAN %, A20%, IGAIN, freq, NS, ICAL, FCALS, FTCSIS, 2)*c1 Ob ot-8 12955 INPUT $1, IDS, ISLOT, CRAhl, A2D%, IGAIN, freq, N S, I CA L, FCALS, FS(10, 3)' 1 10130 INPUT 01, IDS, ISLOT, CRAN %, A2D%, IGAIN, freq, MS, ICAL, FCALS, FTCS(9, 13'c1 Oc in-9 12960 INPUT 91, IDS, IS LOT, CRAN %, A2DS, ICAIN, freq, NS, ICAL, FCALS, F$ (10, 43' 1 10140 INPUT G1, IDS, ISLOT, CRANt, A20%, ICAIN, freq, NS, ICAL, FCALS, FTC3(9, 2} ' c1 Od ot-9 12965 INPUT $1, IDS, ISLOT, CHAN%, A2Dt, ICAIN, freq, N S, ICAL, FCALS, FS (11, 1)'ht-1 10150 INPUT 01, IDS, ISLOT, CRANt, A2D%, ICAIN, freq, N S, ICAL, FCALS, FTC$ (10, 1)*c la 11n-10 12970 INPUT $1, IDS, ISLOT, CRAN %, A20%, ICAIN, freq, N S, ICA1, FCALS, FS (11, 2)* 1 10160 INPUT 51, ID$, I S LOT, CRAN %, A2Dt, ICAIN, freq, NS, ICAL, FCALS, FTC$(10, 2)'c lb lot-10 12975 INPUT 61, IDS, ISLOT, CRAN %, A2Dt. ICAIN, freq, N S, ICAL, FCALS, F3 (11, 3)' 1 10170 INPUT 91, IDS, !$ LOT, CRANn, A20%, ICAIN, freq, N S, ICAL, FCALS, FTC$(11, 1)*c Ic 11n-11 12980 INPUT 01, IDS, ISLOT, CHANT, A20%, ICAIN, freq, N S, ICAL, FCALS, FS(11, 4)* 1 10100 INPUT $1, IDS, I S LOT, CHAN%, A2D%, ICAIN, freq, N S, ICAL, FCALS, FTCS(11, 2)'c Id lot-11 12985 INPUT 01, IDS, ISLOT, CRANt, A2D%, ICAIN, freq, NS, ICAL, FCALS, F$ (12, 1)*hf-1 10190 INPUT 81, IDS, ISLOT, CHAN%, A20%, ICAIN, freq, NS, ICAL, FCALS, FTC$(12, ll'c 2a 11n-12 12990 INPUT $1, ID$, ISLOT, CRAN %, A20%, IGAIN, freq, M S, ICAI, FCALS, FS (12, 2)
- 1 10195 INPUT el, IDS, !$ LOT, CRANt, A2D4, ICAIN, freq, NS, ICAL, FCALS, FTCS (12, 2 3 ' c 2b lot-12 12995 INPUT 61, IDS, ISLOT, CRAN %, A2D%, ICAIN, freq, NS, ICAL, FCAL4, F5 (12, 3)* 1 10200 INPUT 61, IDS, ISLOT, CRAN %, A*Dt. ! GAIN, freq, N S, ICAL, FCALS, FS (1, 1)*ht-1 2c a 12997 INPUT 51, IDS, ISLOT, CRAN %, A2Dt, IGAIN, freq, N S, ICAI, FCALS, F8 (12, 4)* 1 10300 INPUT 81, IDS, ISLOT, CRAN %, A2D%, ICAIN, freq, N S, ICAL, FCALS, F3 (1, 2)
- 1 2d b 13000 CLOSE fl 10400 INPUT S1, IDS, ISLOT, CRAN %, A2D%, ICAIN, freq, N S, ICAL, FCAL$, F$ (1, 33' 1 13100 REM c 13200 REM compute mean and stder 10500 INPUT 01, 103, ISLOT, CHANT, A2Dt, ICAIN, freq, N S. ICAL, FCALS, F3 (1, 4)' 1 13300 REM d 13105 FOR k = 1 TO nhfa 10600 INPUT 01, IDS, ISLOT, CRAN %, A2Dt, ICAIN, freq, N S, ICAL, FCALS, F$ (2, ll'ht-2 13400 OPEN FTEM$ (k) FOR INPUT AS 91 a 13500 COSUB 27600 10700 INPUT 81, IDS, ISLOT, CRANt, A2Dl, ICAIN, freq, NS, ICAL, FCALS, F3 (2, 2)* 2 13600 KMEAN = dsumf / NS b 13601 tain tk) = KMEAN 10800 INPUT el, IDS, ISLOT, CRAN %, A20%, ICAIN, freq, NS, I CA L, FCALS, F$ (2, 3)
- 2 13700 THIX STD (k ) = (ABS ((DVARS / NS) ~ XKEAN ' 23) .5
7 EM@?755%ET3f" Q94106/024 MiSM 2 htf6. bas - REM take into acount the thermal conductivity of the C2n pain 13705 NEXT k 17750 13701 OPEN FSTEMS FOR INPUT AS 01 37775 REM 13702 COSUB 27600 17800 Tinfae(k) - 38.3705
- dtentkl + Tbacktki 13703 KMEAN = dsum8 / NS 13704 TSTEAM = XMEAN 17805 REM dcarb is the thickness of the carborine coating 13800 TSTESTO - (ABS ((DVARS / NSI = KMEAN
- 23) ^ .5 17810 REM kal and kan are the conductivitles of the alustnum and sine 13900 FOR k - 1 To ante 14000 FCR j = 1 TO nte 17850 tsurf(k) = dearb
- kal / kan
- dtdx(k) + Tlafac(k) 14100 OPEN F3 (k. j) FOR '7T AS 01 17900 tsurfa = tsurf a + taurf(k) 14200 GCSUB 27600 17950 st ai nwall th) = tais tk) = tsurf (k) 14300 MMEAN = dsume / 85 10000 ht c (k) = hf(kl / dtslawa!!(kl 14400 t emp ik, j) = EME AJ 18100 NEXT k' 14500 SD(k. j) = (ABS t (DVAR G / MS) - EMEAN
- 2))
.5 18200 tsurfa = tsurfa / nhfe 14600 NEXT j 18300 REM 14700 NEXT k 18400 REM compute fitting error 6 various st attstical quantitles 14800 FCR k = 1 To nhfm 18500 REM 14900 FOR j = 1 TO 2 18600 FOR k = 1 70 nhfm 15000 CPEN FTCS(k, j) FOR INPUT AS $1 18700 var = 01 15100 COSUB 27600 18705 som = 01 15200 xMEAN = dsume / NS 19200 asqrsum = OI 15300 te(k, jl = XMEAM 19300 FOR 3 - 1 TO nte 15400 s et e (k, j) = (AB3 ( (DVAR S / NS) - EMEAN
- 2))
5 19400 TFIT = Tback(kl + a(k, j)
- dtdzikt 15500 NEXT j 19500 var = var + (temp (k, 3) = TF17)
- 2f 15600 NEXT k 20000 asqrsam = magesum + m ik, 31 ^ 21 15700 REM 20005 sum = sum + sth, j) 15800 R EM curve fitting = compete gradiente, heat flumes, 20100 NEXT j 15900 REM surface temperatures (and mean), and back temp.* s 20101 signatb(k) = SQR((var / ntc
- asqrsual / (nte
- asgream = sum
- 235 l
15950 REM linear least squares method 20105 sigotdatk) = SQR ((var
- ntel / (ate
- zaqrsum - som
- 23) 16000 REM 20150 REM 16100 tsurfa = 0 20155 REM standard error of estimate of the heat flum 16200 FOR k = 1 To thfa 20180 REM 16300 suma = 08 20300 gerr(kl = hf(k)
- SCR((sigkal / kall
- 2 + (sigotds(k) / dtes(kt)
- 23 16400 summ2 = 08 20302 REM error in interface temp used a= plate thickness, error in n .5 Cam 16500 samy = O t 20305 finerrtk) = SQR(signatb(k)
- 2 + 38.3705
- 2
- s1getdx
- 2 + dtdzik) *2*.
16600 $UMT2 = Ot 5
- 2) 16700 SUMXT = Ct 20500 NEXT k 16800 FOR j = 1 To nte 20600 REM
( 16900 s uma = suma + m (k, ji 20700 REM overall heat flux and average heat transfer coef. l 17000 summ2 - suma2 + a tt, j)
- 2I 20900 REM 17100 aumy = sumy + t emp th, ji 20805 htcavy =0 17200 SUMT2 = SUMY2 + t emp (k. j)
- 21 20$10 ht ca vu = 0 17300 SUMXT = SUMxY + a lk, 2)
- t emp t h, j) 20900 NTCAVht = Of 11400 NEXT j 21000 RTCAVh2 = 01 17405 abar = suma / nte 21100 FCR k = 1 To nhfs 17410 yba r = s ury / nt e 21105 IF (k > El THEN COTO 21605 17415 de nom = summ2 = nt e
- mba r
- 2 21200 NFAVG (k) = flow (k)
- 41828 * (t c (k, 2) = t c (k, 13) / (601
- LENGTH
- PMIDTH) 17500 dtda tkl - (SUMXY - etc
- mbar
- ybarl / demos 21300 ht cavg (k) = HFAVG(k) / dtmiswa11(kl 17501 REM these values are to calibrate the thermocouple probes 21400 HTCAVhl = NTCAVhl + btcaug(k) 17502 IF (k = 1) TREN dt da (k) = dtda lkl + .002 97 21500 HTCAVh2 = NTCAVh2 + htc(kl 17503 IF (k = 2) THEN didatk) = dtdm(k) + .004067 21600 IF (k ( 7) THEN GOTO 21690 17504 IF (k = 3) THEN dtdalk) = dtda tki - .002008769 21605 kFAVC (k) = fl ow (k )
- 41821 * (t c (t, 2) - teik, Ill / (608
- LENGTH
- PMIDTM) 17505 IF (k = 4) THEN dtdalk) = dt da t k ) - .002261769 21610 htcarg(kl = HFAVG(k) / dtmiswall(kl 17506 IF (k = 5) THEN dtdz(k) = dtda tt) + .001975949 21615 htcavel = htcavv1 + htcavg(kl 17507 IF (k = 6) THEN dtdalk) = dtds (k) + .007618656 21620 htcavv2 = htcarv2 + hte(kl 17508 Ir (k = 73 THEN dtds (k) = dtdatti + .001433856 21690 NEIT k 17509 IF (k = 8) THEN etda tt) = dtdz tkl + 01 21700 REM Coolant Energy Balance Average 17510 IF (k = 9) THEN dtda tkl - dt da tkl = .000432149 21000 HTCAVhl - HTCAVht / 6 17511 IF (k = 10) TMEN dtda(k) = dtdz(t) *CI 21805 htcavel = htcaryl / 6 17512 IF (k = Ill THEN dtdalk) = dtds{k) .0053 21900 REM Meat Flum Meter heersge 17513 IF (k = 12) THEN dtdalk) = didz(kl + .0046637 22000 HTCAvh2 - RTCAVh2 / 6 17600 Tbacktki - ybar - dtomik)
- mbar 22005 htcarv2 = htcarv2 / 6 17650 22010 REM 17700 hf tki - kal
- dtdatti = 100000I 22020 - R EM now the error estimates for heat t ransfer coefficients 17725 REM 22030 REM used propagation of errors for calculations pp 58-60 jawrnal el
- ^ " '
__:______L____-______ _..
.NWM2?MR? e -. - >. y
}V94/06/027 p $yA siiO8:2ti454 e -me htf6. bas ft 22040 FOR k = 1 TO nhfm 26200 PRINT 82, USING - 65 05049.80 +/- 05.08 68096.50 +/* 59.80 22041 edsurf(kl - SOR((dcarb / kan
- dtdatk)
- sigkall
- 2 + (kal / kan
- dcarb
- dt S et e.0"; k; hte th); hfmerrth); htcarg tt); coberrth); thtcargth) / htc(k) = 1) *1 du tk)
- sigant *2+ (dcarb
- kal / kan
- sigotda{k))
- 2 + Tinerrtkl
- 2) 008-22045 sdtdelttk) - SCR(sdsurftk)
- 2
- TMIXSTD(k) 2) 26300 NEXT k 22050 hfnerrtki - ABS (ht c(k)
- SOR((gerr(k) / hf(k)) *2+ (sdtdelttkl / dtmiswa11(k 26400 PRINT 02, j
- 3)
- 2)) 26500 PRINT 82, USING
- Norisontal plate Avera0e HTC Heat Flus Meters (HFM) =
22055 sigtc(k) = SQR (sotc(k, il ^ 2 + sdteth, 2) ^ 2) Seest.Os*; HTCAVh2 22060 sigqceb(k) = ABS (htcaug(k)
- SQR((sigflow / fl ow (k )) *2+ (si gt c (k) / (t e (k, 26600 PRINT 82, USING
- Horisontal plate Average HTC Coolant Energy Balance (CEB) =
- 2) - tc (k, 1)))
- 2 + 1.609E-053 ) 90986.00*; HTCAVhl 22065 ceberr(k) = ABS (ht caug tki
- SQR(tstgflow / flow (k)) *2+ (sigt c (k) / (t e t h, 2 26605 PRINT 02, USING
- Vertical plate Average HTC Heat Flum Meters (HFM) =
3 - tc(k, 13))
- 2 + 1.609E-05 + (sdtdett(k) / dtmimwall tk))
- 23) 88500.89*; htcavv2 l 22000 NEkT k 26610 PRINT 82, USING
- Vertical plate Average HTC Coolant Energy Balance (CEB) = j 22100 REM 0 9668.0 t*; htcavv1 j 22200 REM out put se ct ion 26700 CLOSE 42 f 22300 REM 27400 END 22400 OPEN
- THERM *
- RIGHTS (STR$(TESTNOI), (LEN (STR$ (TESTNOI)) - 1)) + ".OUT* FOR 007 27500 REM l PUT AS 62 27600 REM statistics subroutine 1 23095 PRINT #2, 27700 REM l 23100 PRINT 82, " Test section temperature Tmia:* 27800 dsume = Of l' 23105 FOR k = 1 TO nhfm 27900 DV AR S = 00 23110 IF (k - 3 OR k = 5 OR k = 7 OR k = 9 OR k = 11) THEN GOTO 23305 28000 INPUT 01, header $ -
23200 PRINT G2, USING
- 46.09*; tatu(h); 28100 f req = VAL (MIDS (header $, 43, 8))
l 23300 PRINT 52, USING * +/- 69.8 89"; TMIKSTD (k) 28200 NS = VAL (MID$(header $, 51, 73) 23305 NEXT k 28300 PRINT header $ 23310 PRINT #2, 28400 FOR I = 1 TO NS 23340 PRINT 82,
- Steam temperature: "; 28500 INPUT 01, time, TT 23350 PRINT 82, USINC "666.00*; TSTEAM; 28600 deuse = daume
- TT 23360 PRINT G2, USING * +/- 16.000* TSTESTD 28700 DVARS = DVARS + TT
- TT 23400 PRINT 82, 28800 NEXT I 23500 PRINT #2,
- HEAT FLUX METER DATA:" 28900 CLOSE $1
]
23600 PRINT 82, 29000 RETU RN 23700 PRINT 82,
- HF meter Tback Tsurf a ce dT/dm Hea 29100 END t flux
- 23800 FOR k = 1 TO nhfm 23900 PRINT 92, USING
- 59 50.09 66.00 +/- 8.650 9.8886 +/- 9.00 ,
es 99999. +/- est*; k; Tback tk); tsurf(k); sdsur f (k ); dtdath); si gotdz (k) ; hftk); qe rrtkl 24000 NEXT k 24100 PRINT 62, 24200 PRINT 92,
- COOIANT LOOP ENERGY BALANCE DATA:"
24300 PRINT 82, PRINT 82,
- C-loop Tin dT Cool Flow Heat 24400 Tout
)
flus
- 24500 FOR k = 1 TO nhfa 24600 PRINT 82, USING
- 30 50.99 89.99 0.0004 0.99 48089. 4/- Set *; k; tc(k, 1); tc(k, 23; tc(k. 2) = tc (k, 1); flow (k) / 60; HF AVG (k);
siggeab(kl ) 24700 NEXT k 24800 PRINT 02, 24900 PRINT 82,
- TEMPERATURES
- 25000 PRINT 02, 25100 PRINT $2, USING
- taurf avg = $0.0*; tsurfa 25200 PRINT 82, 25300 PRINT 92,
- tc-a tc-b te-c tc-d*
25400 FOR k = 1 TO nhfa 25500 PRINT 02, USING - se 88.86 98.69 40.99 09.0f*; k; temp (k, 1); t emp(k, 2); temp (k, 3); t e mp (k , 4)
, 25600 NEKT k 25700 PRINT 02, 25900 PRINT 92, HEAT TRANSFER COEFFICIENTS
- 25900 PRINT 82, 26000 PRINT 02,
- HT meter HTC HFM's (N/m2-C) HTC CEB's (N/m2-C) Diff.
(4 )
- 26100 FOR k = 1 TO nhfm
) So f i Appendix 3 Error Analysis Theory he use of the Linear Least Squares Fit was used to detennine the best slope and intercept of the line defining the heat flux. Since we have a slab geometry we can assume that the heat flux through the < condensing surface is linear. Therefore we wish to find the best values for the equation of a line. y = mx + b 1 If we assume that the distribution of the values obtained fmm the measurement of the temperatures in the plate are govemed by Gaussian statistics then the best values of the slope (m) and the intercept (b) are 4 given by the muumization of the following equation: D2 = Ii,a [yi-(mxi- bi)]2 4 where o is a weighting factor. The above equation can then be minimized to find a pair of simultaneous equations which can be solved for the slope and the intercept. The equations for the best value of the slope and the best value of the y-intercept are as follows: i f x yii - Ni iyi m=', 2 [ i x - N(I)2 y,=b=y-mi e s
9f Where the bar over the x and y corresponds to the average values of x and y.
'Ibe errors in the slope and intemept can then be found using the matrix Inversion method of the linear least squares. 'Ihe equation of the line can be written in matrix notation as follows:
lYl=lXIl0l Yi lYl = 8 i Yixi nd f ' f IXI = ! { { From these equations one can then find the following equations for the variance of the slope and intercept. 2 o* E x 02=b y3y _(Z2 x,)2 0* = N E x*-(E x )2 o Error in the heat transfer coefficient derived from the heat flux: The equation for the heat flux is given by the equation: ; 1 l qi = kl,'
92 Now using the theory of Propagation or Combination of errors we can find the uncertainty in the heat flux: og = q"}(y)2 +(g>)2 Where again the slope or dT/dx of the best line is given by m. In the above analysis the uncertainty in the slope is essentially dependent on the statistical standard deviation of the temperature measurements. This can be assumed if we are concemed with the difference in the temperature measurements and if the absolute temperatures are the same when no heat flux is present. We are then effectively using the measured resolution of the thermocouple as the defining error in the heat flux. The term k in the above equation is the conductivity of the aluminum plate. The value and standard error for this was taken as 1.3179 +/- 0.72 w/cmK however the absolute error in the heat flux is due to the errorin the slope. The heat transfer coefficient can be found from the heat flux with the following equation: h = q"lATrnix with an associated standard error given by: Oh = h}($)2 + ( ,47
, )2 where the error in AT, was obtained by similar combination of errors.
Error in the heat transfer coefficient derived from the coolant energy balance: An energy balance on the coolant water results in the following equation: Qi ~_p acp(vat'w): p,
93 Since the maximum change in the density and heat capacity over the range of the temperature difference is only 0.2 percent, this was neglected. The heat transfer coefficient is given by the equation: h = q"lATmix with an associated error of
^
Oh = h (y)2 +( 4r )2 +(Y)* +( AT ) Where AT is the bulk mixture temperature minus the plate surface temperature. ATis the temperature difference between the water inlet temperature and the water outlet temperature of the coolant plate. The errors associated with this was obtained from the standard deviation of the ensomble measwed. t
94 Appendix 4 4 Calibration of Turbine Meter - l M appendu consists of the calibration of the Hontzsh turbine anomometer that was done by Colorado Engineering Experiment Station Inc. i
8H81 COLORADO ENGINEERING MTORYl0FFICE. EXPERIMENT STATION INC. sesem an 37 Nw n C a 80648 Phant 354972711 FAX. dab 7 2710 CERTIFICATE OF CALIBRATION This calibration is traceable to the NATIONAL INSTITUTE OF STANDARDS AND TECHNOLOGY Model: Hontzsch Serial Number: 20163 For: University of Wisconsin Order: Data File: 94UOW1 Date: 1 July 1994 Disc: 0794-003 The uncertainty in indicated flowrate is estimated to be +/ 0 8 % of reading to 95% confidence. i The instrumentation used in the above calibration is traceable through standards calibrated under the following NIST test numbers: 737/228509, 215451, 202491. 184934. 213426. 209527, 222173, TN-249770, TN-250722, TN-246108. 811-249971, and 811/249886 This calibration was performed in accordance with PROC-010 rev 4 and MIL-STD 45662A. This Calibration is: [x] As Found [<] As Left Calibration performed by: % i V h TWW Jn N.bh<~f Dean M. Standiford Asst. Quality Assurance Manager Steve Caldwell IA Vice President 1
96
$ ! COLORADO ENGINEERING
****'CE EXPERIMENT STATION INC.
seaem u 37 Nwm Cm 00648 Phonst 35437 r711 FAX' 30807 2710 CERTIFICATE OF CALIBRATION This calibration is traceable to the NATIONAL INSTITUTE OF STANDARDS AND TECHNOLOGY Model: Hontzsch Serial Number: 20163 For: University of Wisconsin Order: Data File: 94UOW2 Date: 6 July 1994 Disc: 0794-003 ne uncertainty in indicated flowrate is estiinated to be +/- a .I% of readmg to 95% confidence. I i ne instrumentation used in the above calibration is traceable through standards calibrated under the following NIST test numbers: 737/228509, 215451, 202491. I84984, 213426, 209527, 222173, TN-249770, TN-250722, TN-246108, 811-249971, and 811/249886 This calibration was performed in accordance with PROC-010 rev 4 - and MIL-STD 45662A. This Calibration is: D() As Found [] As Left
/
Calibration performed by: 4
?o
\g Dean M. Standiford f Steve Caldwell M ,
Vice President Asst. Quality Assurance Manager I
OH81 COLORADO ENGINEERLNG m m 8 ACE. EXPERIMENT STATION INC. wo cam e r Nunn. Can 80W Pnore 32Hi?E1t FAX. EH97&10 Calibration of an Anemometer (forward flow) Model: Hontzsch Serial Number: 20163 For University of Wisconsin Order: Data File: 94UOW2 Dates 6 July 1994 Disc: 0794-003 Inlet diameter: 12 inches Throat diameter: 3.248 inches Toct gas: AIR Standard density = .074915 lbm/cu-ft at standard conditions of 529.69 deg R, and 14.696 psia Mtr vel: Meter calculated velocity (ft/sec), 13.124* Volts-65.62 Velocity: Actual mean velocity, ft/sec Volts: Meter output in vdc K Factor: Mtr Vel / Velocity Press: Inlet static pressure in psia Temp: Inlet temperature in degrees Rankina Density: Inlet density in pounds = ass per cubic foot Zero reading at no flow: 5.00244 L Volts Velocity Mtr vel K Factor Density 1 9.355 52.769 57.155 1.083 0.06121 2 8.9719 48.066 52.127 1.084 0.06121 3 8.5528 42.969 46.627 1.085 0.06123 4 8.9308 47.517 51.588 1.086 0.06123 5 8.186 38.489 41.013 1.086 0.06124 6 7.8129 34.006 36.917 1.086 0.06124 7 8.184 38.485 41.787 1.086 0.06124 8 7.4428 29.522 32.059 1.086 0.06125 9 7.0711 25.046 27.181 1.085 0.06125 10 7.442 29.511 32.049 1.086 0.06126 11 6.705 20.576 22.377 1.088 0.06126 12 6.3367 16.139 17.543 1.087 0.06126 13 6.7049 20.568 22.375 1.088 0.06126 14 5.9761 11.729 12.810 1.092 0.06126 15 5.6326 7.4973 8.303 1.107 0.06125 16 5.9722 11.727 12.760 1.088 0.06124 17 5.4128 5 5.417 1.083 0.06123 18 5.254 3.1366 3.333 1.063 0.06120 19 5.4121 5.0004 5.408 1.082 0.06120 Average values for above results: Press: 12.078 psia Density: .061238 lbm/cu-ft Temp: 532.51 Dog R Viscosity: .0000010227 lbm/ inch-sec Compressibility factor: .99971 -- - .- . - . . _ _ . Post it' brand fax trarsr-ittal merT M71 m ot meeee *
% K ric c % P%
/ N ,i A .7 LC h s.h f W '
& %p ngj
- M ^Go h - Md7 '
3%O l 6 __.
16082626707 P.02 ) E -AO-1994 13:38 FR31 2E3! TC 98 SEtti COLORADO ENGINEERING MmmCE- EXPERIMENT STATION INC. sesomy u n Mrvi Cet N688 pncre msw.mi fat 33Ht7Et2 Calibration of an Anamometer (reverse flow) Model: Hontzsch Serial Number: 20163 For: University of Wisconsin Order: Data File: 94UOW1 Date: 1 July 1994 Disc: 0794-003 Inlet diameter: 12 inches Throat diameter: 3.248 inches Test gas: AIR Standard density = .014915 lbn/cu-ft at standard conditions of 529.69 dag R, and 14.696 psia Mtr vel: Meter calculated velocity (ft/sec), 13.124* Volts-65.62 Velocity: Actual mean velocity, ft/sec Volts: Meter output in vdc K Factor: Mtr Val / Velocity Press: Inlet static pressure in psia Temp: Inlet tamparature in degrees Rankine Dansity: Inlet density in pounds mass per cubic foot Zero reading at no flow: 5.001574 L Volts Velocity Mtr Val K Factor Density 1 .72795 51.773 -56.066 -1.083 0.06124 2 1.1012 47.301 -51.167 -
'.082 0.06125 3 1.4692 42.85 -46.338 -1.081 0.06125 4 1.1484 46.705 -50.549 -1.082 0.06126 5 1.8823 37.86 -40.917 -1.081 0.06126 6 2.2462 33.453 -36.141 -1.080 0.06126 7 1.8841 37.852 -40.894 -1.080 0.06126 8 2.6067 29.05 -31.410 -1.081 0.06126 9 2.9706 24.655 -26.634 -1.080 0.06125 10 2.6068 29.047 -31.408 -1.081 0.06125 11 3.3277 20.268 -21.947 -1.083 0.06124 12 3.6856 15.905 -17.251 -1.085 0.06124 13 3.327 20.268 -21.956 -1.083 0.06123 14 4.0408 11.566 -12.588 -1.088 0.06123 15 4.3836 7.3977 -8.090 -1.094 0.06119 16 4.0403 11.569 -12.595 -1.089 0.06118 17 4.5939 4.9362 -5.330 -1.079 0.06116 18 4.7529 3.1004 -3.243 -1.046 0.06112 19 4.5941 4.9405 -5.327 -1.078 0.06111 Average values for abovs results:
Press: 12.1 psia Density: .061222 1hm/cu-ft Temp: 533.62 Dog R Viscosity: .0000010243 lbm/ inch-sec Ccapressibility factor: .99971 rn e e ne
l @ Calibration Curve for Vaine Anemometer 70 . . 60 . . 50 . . 40 . . 30 .. 20 - ' m o . v .
- 10 -
8 v
.D
- 0-8 :
o .
> Linear Regression for Vaine Anemometer Velocity (ft/sec) = A + B
- Voltage Param- Value- sd
-20 .
- A. -60.6285. +/- 0.02966 B. 12.11812. +/- 0.00531
-30 .'. R=1 SD = 0.08055, # of data points = 38 50 : .
-60 ,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,g,,,,,,,,,g,,,,,
4 5 6 7 3 9 10 11 0 1 2 3 Voltage y ,, y goyag 4,y
4 t
' 100 i
't l Appendix 5 ' i i Bibliography of Work Done at the University of Wisconsin 1 j [1] M.H. Kim Modeling of Condensation Heat Transfer in the Presence ofNoncondensible Gas. PhD
- "Ihesis 1986 [Modwl of Condensation H.T. Conclation - 2D Model) -
1 [2] 3.J. Barry Film Condensadon in the Presence ofNoncondensible Gas, PhD Thesis 1988 l [ Experiments fa Condensation ca a Horizontal Surface] , )- l ) [3) LK. Huhtiniemi Condensation in the Presence ofNoncondensible Gas: Efect ofSurface Orientation, i Ptchm "Ihesis,1990 [Ap600-1 Experiments and Initial AP600-2 Tests] 4 t i [4] I.K. Huhtiniemi Condensation in the Presence ofNoncondensible Gas:Efects ofSurface Orientation PhD 'Ihesis 1992 [AP600-2 Experimental Test Series] , l i 1 ' [5) A. Pemsteiner Condensation in the Presence ofNoncondensible Gas: Efect ofHelium Concentration MS Thesis 1993 [ Helium Air-Steam Tests with/without Forced Convection) i Refered Publications j [l] M.H. Kim, M.L. Corradini, Modeling of Condensation Heat Transfer in a Reactor Containment j Nuclear Encineerine Desien. 2.UL 1990 4 i
- [2] I Huhtiniemi, M.L. Corradini, Condensation in the Presence of a Noncondensible Gas: Efect of l Surface Orientation, AlchE Symoosium Series. No 269. Vol 85, S. B. Yilmaz, Ed. Aug.1989 {
l j [3] I. Huhtiniemi, A. Pernsteiner, M. L. Corradini, Steam Condensation in the Presence of i Noncondensible Gas: Efect ofSurface Orientation. A1ChE Symnasium Series No 283. Vol 87 S.B. Yilmaz, Editor July 1991 l I I [4] I Huhtiniemi. A. Pemsteiner, M.L. Corradhi, Condensation in the Presence ofNoncondensible ' Gases, Nuclear Encr. Desien (Accepted fct publication in 1992) i ! [5] M.L. Corradini, Natural convection Modelfor Condensation, Intemation Mtc. on Hydrocen l Behavior. Albuquerque,NM Oct 1932 [6] M.L. Corradini, Turbulant Condensation on a Cold Wallin the Presence of a Noncondensible Gas, ! Second Intemational Mtc on Nuclear Thermal- Hydraulics. Santa Barbra CA, Jan 1983 l
- i j
i i
- i. . .- _ , . -
i i j 101 i l [7] M.H. Kim, M.L. Corradini, Turbulent Condensation in a Noncondensible Gas, ANS Pmceedines of \ j the Wird International Meetine on hermal-Hydraulics. Newport, RI Oct 1985 i
- [8] J.J. Barry, M.L. Corradini, Film Condensation in the Presence offnterfacial Waves, ASME/AIChe i National Heat Transfer confemnce. Houston Tx July 1988
? ! [9] I. Huntiniemi, JJ. Barry, M.L. Corridini, Condensation in the Presence ofNoncondensible Gast The , effects ofSurface Orientation, National Heat Transfer Conf. Philadelphia PA Aug 1989 3 [10] 1. Huntiniemi, A Pemsteiner, M.L. Coradini, Steam Condensation in the Presence of Noncondensible Gast Efect ofHellum, National Heat Transfer conference. Minneapolis MN July 1991 i i i [11] A. Pernsteiner, I.K. Hyhtiniemi, M.L. Corradini, Condensation in the Presence ofNoncondensible j Gasest Efects ofHelium, Proc of NURETH-5 Mtc. Salt Lake City UT Sept.1992 1 1 i i l 1 - I l i : 4 P I l I l l l
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