ML19210B994

From kanterella
Jump to navigation Jump to search
NRC Acceptance Criteria for Mark I Containment Long-Term Program
ML19210B994
Person / Time
Site: Vermont Yankee File:NorthStar Vermont Yankee icon.png
Issue date: 10/26/1979
From:
NRC COMMISSION (OCM)
To:
Shared Package
ML19210B970 List:
References
NUDOCS 7911130122
Download: ML19210B994 (46)
v • d • e


Text

{{#Wiki_filter:.. NRC ACCEPTANCE CRITERIA FOR THE MARK I CONTAINMENT LONG TERf1 PROGRAM 1323 052 e /2 2-7911180

TABLE OF CONTENTS 1. INTRODUCTION 2. SUPPRESSION P0OL HYDRODYNAMIC LOADS 2.1 Containment Pressure and Temperature 2.2 Vent System Pressurization and Thrust loads 2.3 Net Torus Vertical Pressure Loads 2.A Torus Pool Swell Shell Pressures 2.5 Compressible Flow Effects in Scaled Pool Swell Tests 2.5 Vent System Impact and Drag Loads 2.7 Pool Swel' Impact and Drag on Other Internal Structures 2.8 Froth Impingement and Fallback Loads 2.9 Pool Fallback Loads 2.10 Vent Header Deflector Loads 2.11 Condensation Oscillation Loads 2.11.1 Torus St. ell Loads 2.11.7 ' cwncom2r Loads U 2.11.3 Vent System Pressurcs 2.12 Chuggi.ig Loads 2.12.1 T"us Sheil Loads 2.12.2 Downconer Loads 2.12.3 Vent System Pressures 2.13 Safety-Relief Valve Discharge Loads 2.13.1 SRV Discharge Device 2.13.2 Discharge Line Clearing Transient 2.13.3 Air-clearing Quencher Discharge Shell Pressures 2.13.4 SRV Discharge Line Reflood Transient 2.13.5 SRV Air and Water Clearing Thrust Loads 2.13.6 SRV Discharge Line Temperature Transient 2.13.7 SRV Discharge Event Cases 2.13.8 Suppression Pool Temperature Limits 2.14 Submerged Structure Drag Loads 2.14.1 LOCA Water Jet Loads 2.14.2 LOCA Bubble Drag Loads 2.14.3 Quencher Water Jet Loads 1323 063 i

2.14.4 Quencher Bubble Drag Loads 2.14.5 LOCA Condensation Oscillation Drag Loads 2.14.6 LOCA Chugging Drag Loads 2.15 Secondary Loads 2.16 Differential Pressure Control Requirements 3. STRUCTURAL Af.!' 'SES AND ACCEPTANCE CRITERIA 4. REFERENCES 1323 054 ii

.j. 1. INTRODUCTION The purpose of the Mark I Containment Long Tem Program is to perform a complete reassessment of the suppression chamber (torus) design to include suppression pool hydrodynamic loads which were neglected in the original design, and to restore the original intended design ~ safety margins of the structure. This reassessment will be accomplished by a Plant-ynique Analysis (P JA) for each BWR plant with a Mark I containment, using load specifications and structural acceptance criteria that are appropriate for the life of the plant. The following acceptance criteria have been developed from the staff's review of the Long Tem Program sad Definition Report (LDR), the Plant Unique Analysis Applications Guide (PUAAG), and the supporting analytical and experimental programs conducted by the Mark I Owners Group. These criteria specifically address the dynamic loading conditions. Unless otherwise specified, all other loading conditions and structural analysis techniques (e.g., dead loads and seismic loads) will be in accordance with the plant's approved Final Safety Analysis Report (FSAR), Similarly, references to original design criteria or original loading conditions shall be defined as those criteria or loading conditions which were found acceptable by the staff during the operating license review of the FSAR. For ease of reference, LDR refers to " Mark I Containment Program Load Definition Report," NED0-21888, PVAAG refers to " Mark I Containment Program Structural Acceptance Criteria Plant Unique Analysis Applications Guide," NED0-24583, and other supporting topical reports are referred to by their report numbers. A complete set of the references used in these criteria, listed in numerical order, is presented in Section 4. 2. SUPPRESSIONPOOLHYDRODYNAMIC[0 ADS 2.1 CONTAINMENT PRESSURE AND TEMPERATURE RESPONSE The pressure and temperature transients for the drywell and wetwell shall be detemined by the use of the analytical models and assumptions set forth in Section 4.1 of the LDR. These techniques have, in the past, been found to provide conservative estimates of the containmerit response to a LOCA, by comparison to the staff's CONTEMPT-LT couputer code. Plant-specific results for each break size shall be presented in the PUA, along with the input conditions, in sufficient detail to allow the staff to perform confirmatory analyses to assure proper application of these models. 1323 055

--g-The timing and duration of :necific loads are based primarily on the plant-specific containme,t response analysis for the pool swell-related loads, while the con.er.sation periods are non-mechanistically maximized. However, the duration of the generic SDA condensation loads are assumed to be limited by manual operation of the Automatic Depressurization System (ADS) at 10 minutes into the accident. Therefore, as part of the PUA, each licensee shall identify procedures (including the primary system parameters monitored) by which the operator will identify the SBA, to assure manual operation of the ADS within the specified time period. Longer time periods may be assumed fcr the SBA in any specific PUA, providedit) the chugging load duration is correcondingly increased. (_') the procedures to assure manual operation within 'he specified time period are identified, and (3) the potential for thermal stratification and asymmetry effects are addressed in the PUA. ?,2 VENT SYSTEM PRESSURIZATION AND THRUST LOADS The vent system pressurization and thrust loads shall be defined in accordance with the procedures set forth in Section 4.2 of the LDR, with the following exception. In order to assure the pron e transition between vent clearing and bubble breakthrough for those plants that propose operation with a differential pressure control, the vent clearing time shall be derived from a containment analysis assuming no drywell/watwell differential pressure and his time shall be applied to the vent system transients calculated fam a containment response with the proposed drywell/wetwell differential pressure. In addition, for clarification, in the equation for F2V in Section 4.2.lc of the LDR, P3 shall be replaced by P2. 2.3 NET TORUS VERTICAL PRESSURE LOADS The downward and upward net vertidal pressure loads on the torus shall be derived from the series of plant-specific QSTF (Quarter Scale Test Facility) tests, in accordance with Section 4.3.1 of the LDR. However, based on our review of the pool swell tests conducted by the Mark I Owners Group and confirmatory tests perforned for the fiRC by the Lawrence Livermore Laboratory, we will require that the following mar-gins be applied to each loading knase:

  • #mean + 0.215 (UPmean}

2 DOWM = DOWNmean + 2 x 10-5 (DOWN) mean where "mean" refers to the average of the QSTF plant-specific test results (1b ). load function prior to scaling the load function to full-scaleThese f equivalent conditions. The marg 1n for the downward loading function 1323 056

. shall be derived in tems of a fraction of the load at the time of the peak downward load, and that fraction shall be applied to the entire downward loading phase. The margins specified above may be reduced or omitted where minimum conservatisms (i.e., smallest parameter deviation from the nominal plant cor.dition over the range of tested conditions) in the QSTF tested conditions for a specific plant can be demonstrated by the application of the QSTF sensitivity test series (NEDE-23545-P). The sensitivity tests may not be used to adjust the mean torus vertical pressure loads. If the plant configuration is changed to the extent that a single QSTF test series no longer represents a conservative configuration of the plant, then a new series of QSTF tests shall be performed. Application of the sensitivity tests and interpolation between plant-specific test series will be reviewed on a case-by-case basis. For those plants that use drywell/wetwell differential pressure control as a load mitigation feature, an additional structural analysis shall be performed assuming a loss of the differential pressure control to demonstrate the capability of the containment to withstand this extreme condition, as specified in Sections 5.3, 5.4, and 5.6 of the PUAAG. For this analysis, a single plant-specific QSTF test run may be used to define the loading function; however, the downward and upward loading phases shall be increased by the margins specified above for the base analysis. 2.4 TORUS P0OL SWELL SHELL PRESSURES ~ The spatial distribution of the torus shell pressures during pool swell shall be defined from the plant-specific QSTF test results and the azimuthal and longitudi,nal distribution factors defined in section 4.3.2 of the LDR. However, the QSTF results shall be adjusted to incorporate the margins specified for the net torus vertical pressure loading function as .follows : 1. During the downward loading phase, the average pool pressure shall be increased by the equivalent differential pressure, as a function of time, corresponding to the margin for the downward load. 2. During the upward loading phase, the torus airspace pressure shall be increased by the equivalent differential pressure, as a function of time, corresponding to the margin for the upward load. 3. The pressure distributions shall be maintained such that the integral of the torus shell pressures will equal the net vertical pressure function with the margins included. 1323 057

9 2.5 C_0MPRESSIBLE FLOW EFFECTS IN SCALED POOL SWELL TESTS The QSTF plant-unique test series are based primarily on a " split-orifice" vent flow scaling relationship. Preliminary calculations performed by EPRI and GE indicate that compressibility effects, which could not be accurately scaled in the testing program, could result in a higher loading condition at full-scale conditions than that derived from " scaled-up" test data. The original intent of these analyses was to provide justification for the scaled flow distribution in the EPRI 1/12-scale, three-dimensional pool swell test program. The loading functions predominantly affected by this finding are the torus downward and upward vertical pressure loads, the torus pool swell pressure distribution, the vent header pool swell impact timing. and the vent header deflector impact timing. Based on our review of the preliminary analyses perfomed by EPRI and GE which were presented to the staff in a meeting on July 24, 1979, we concluded that there is sufficient margin in the loading functions to justify proceeding with implementation of the Mark I LTP, while this assessment continues. We will require, however, that the Mark I Owners Group complete the assessment of compressible flow effects and justify the adequacy of these load specifications prior to the issuance of the staff's Safety Evaluation Report, which is currently scheduled for December 1979. In the event that the adequacy of the load specifications cannot be demonstrated, these loading conditions will have to be reassessed. The vent header and vent header deflector impact timing do not, however, appear to be sufficiently conservative. Based on our review of the material presented thusfar concerning the EPRI 1/12-scale three-dimensional pool swell tests and the compressible flow effects analyses, we conclude that the downcomer orificing used for the " split-orifice" tests do not provide a prototypical pool swell response. Therefore, the vent header and vent header deflector impact timing shall be derived from the " main vent orifice" tests (using the same longitudinal load distribution methodology in the LDR), until a flow cistribution analysis, acceptable to the staff, can justify some less severe loading conditions. 2.6 VENT SYSTEM IMPACT AND DRAG LOADS 2.6.1 Vent Header Impact and Drag Loads The load definition procedures set fcrth in Section 4.3.3 of the LDR are acceptable, subject to the following clarifications: 1323 058

.. 1. The experimental data of local vent header pressure in each of the Mark I plants shall be obtained from the QSTF plant-unique tests. 2. The specification, for each Mark I plant, of the pressure inside the vent header relative to that in the torus airspace at the time of water impact on the vent header shall, be determined from the QSTF plant-unique tests. 3. The plant-unique header impact timing (i.e., longitudinal time delay) shall be based on the EPRI " main vent orifice" tests as described in Section 2.5. 2.6.2 Downcomer Impact and Drag Loads The load definition procedures set forth in Section 4.3.3 of the LDR are acceptable, subject to the following clarifications. A pressure of 8 psid is to be applied uniformly over the bottom 50 of the angled portion of the downcomer, starting from the time at which the rising pool reaches the lower end of the angled section and ending at the time of maximum pool swell height. The pressure is to be applied perpendicular to the local downcomer surface. The structural analysis for the downcommer impact shall either be dynamic, accounting for the approximate virtual mass of water near the submerged parts of the downcomer, or a dynamic load factor of two shall be applied. 2.6.3 Main Vent Impact and Drag loads The impact and drag loads on the main vent shall be evaluated in the following manner: 1. Subdivide the submerged p0rtion of the main vent pipe into six equally wide segments (see Figure 2.6-1). If this sub-division results in al < 0.3D fewer segments may be used such that al s 0.3D. 2. Determine the velocity and acceleration histories at Points 1 through 7 in Figure 2.6-1 from the QSTF data and appropriate corrections for longitudinal variations along the torus (at. Point 7, only the initial impact velocity is required). 3. Using the velocity components normal to the vent pipe, calculate the impact and " steady" drag pressure using the method in Section 2.7.1 (Cylindrical Structures). At Point 7, only impact force is to be considered. 1323 059

O bL a f y Highest pool A 3 elevation 3 i g V cos a pool elevation at l ~ V a cos a initial contact with i main vent a V = pool impact velocity at station a = pool acceleration at station Figure 2.6-1 Schematic Diagram Illustrating the Methodology for Main Vent Impact and Drag 1323 040

. Using the acceleration components normal to the vent pipe, calculate the acceleration drag pressure using the equation P, = Fstatic buoyancy Where Pa is the acceleration pressure averaged over the pro-jected area (psi), o is the density of water (lbm/ft ), D is 3 the diameter in feet, i the cross flow acceleration (ft/sec2) and g is the acceleration due to gravity (ft/sec2), c 4. Sum the pressures due to impact, viscous drag and acceleration drag and multiply by D to obtain force per unit length at Stations 1 through 7. 5. To obtain a smooth loading history for the main vent as a whole, the linear interpolation method suggested for the vent header deflector in Section 3.5 of NED0-24612 may be used. 2.7 P0OL S_WELL IMPACT AND DRAG ON OTHER INTERNAL STRUCTURES _ The impact and drag loads for internal structures above the suppres-sion pool (except the vent header, downcomers, and vent header deflectors), as specified in Section 4.3.4 of the LDR, shall be modified such that the structures are classified as either cylindri-cal (e.g. pipes), exposed flat surfaces (e.g., "I" beams), or grant-ings. The following load specifications for each of the three structural classifications shall be used to replace the methodology in the LDR. Any structures that cannot reasonably be classified as one of these geometries will be r,eviewed on a case-by-case basis. The longitudinal velocity distribution shall be based on the " main vent" EPRI pool swell tests, as discussed in Section 2.5. 2.7.1 Cylindrical Structures For cylindrical structures, the pressure transient which occurs upon water impact and subsequent drag is depicted in Figure 2.7-1. The parameters in Figure 2.7-1 shall be defined as follows: 1. The maximum pressure of impact P will be detemined by max P = 7.0 x 1 o V max ig 344 9e where Pmax is the maximum pressure averaged over the projected 3 area (psi), o is the density of water (lbm/ft ), V is the impact velocity)(ft/sec) and g is the acceleration due to gravity c (ft/secz. 1323 061

8-Pmax C45 e b in is P g ?- D w / E / 1 I TIME 7 Figure 2.7-1 Pulse Shape for Water Impact on Cylindrical Targets 5 red < 5 x 10 15 / i

- ;..p ;;;

....._..;. y. -;. . ;.._;. __ p }....{ .i. t N.9. .7 .. }._ C - - + - a-- 5 D h~~~ T V'-~~~~ D > 5 x 10 -- R ...---..t.-. /e .t. ~~ 1.0 . _ ' - ~ ~~ ~ ~ ._" _ } _... _gl.... t.. _ - _ 4.._ t ~~ T~~t~ .4.. p ~ ~ ' ' ~... ~~ ~ _____'[~~~-- ~~Q.. \\..,.."^~^~~~~~- ~ l. 4... 3._ _._-..p-a. l l

9..

..4.. a _. .1._ l___.._.._._ [ f__.... .. ___ L. .p_. .4_, 0 i ---- - - - -~*----~'t-^- - - ~ ~ - - 2. u. 6. s.;o 20. uo. 60 80. 2 FROUDE NUMBER (N = V /Dg) p Figure 2.7-2 Drag Coefficient for Cylinders Following Impact 1323 0.42

9-2. The hydrodynamic miss per unit area for impact loading shall be obtained from.ne correlation (cylindrical target) depicted by Figure 6-8 in NEDE-13426-P. A margin of 35% will be added to this value to account for data scatter. 3. The impulse of impact per 'ait area shall be determined by: b V Ip * % ITCgc where I is the impulse per unit area ( hydrodynamic mass per unit area (ibm /ftgsi-sec), M /A is the p H ) and V is the impact velocity (ft/sec). 4. The pulse duration will be determined from the following equation: t = 2I /P p 5. The pressure due to drag following impact shall be detemined by: C o P D 2 144 g C where P is the average drag pressure acting on the projected D area of the target (psi), Cn is the drag coefficient ag defined by Figure 2.7-2, and o is the density of water (1bm/ft ). 2.7.2 Flat - Surface Structures For flat-surface structures, the pressure transient which occurs upon water impact and subsequbnt drag is depicted in Figure 2.7-3. The parameters in Figure 2.7-3 shall be defined as follows: 1. The pulse duration (t) is specified as a function of the impact velocity: t = 0.0016W for V < 7 ft/sec t = 0.011 W for V > 7 ft/sec V where W is the width of the flat structure (feet) and V is the impact velocity (ft/sec). 1323 063

. 2. The pressure due to drag following impact shall be detemined by: D M P = D 2 144 gc where PD is the average drag pressure acting on the frontal area of the structure (psi), CD is the drag coefficient (CD = 2, flat strips nomal to flow, independent of Reynolds number), 3 and e is the density of water (lbm/ft ), 3. The hydrodynamic mass per unit area for impact loading shall be obtained from the correlation (flat targets) in Figure 6-8 in NEDE-13426-P. A margin of 35% shall be added to this value to account for data scatter. 4. lhe impulse of impact per unit area shall be detemined by: b V I = p A 144 gc where Ip is the impulse per unit area (psi-sec), M /A is the H hydrodynamic mass per unit area (lbm/ftz), and V is the impact velocity (ft/sec). 5. The maximum pressure (Pmax) shall be calculated from the impulse per unit area and the drag pressure as follows: P P + P = mx D 2.7.3 Gratinas The static drag load on gratings in the pool swell zone of the wetwell shall be calculated for gratings with open' areas greater than or equal to 60% by faming the product of the pressure dif-ferential (figure 2.7-4) and the total grating area (not only the area of the metal bars). The pressure differential curve in Figure 2.7-4 is based on a velocity of 40 ft/sec. If the maximum pool velocity in the area where gratings are located differs from 40 ft/sec, the force on the grating will be calculated as follows: F = t.P x A Y grating max 40 To account for the dynamic nature of the initial loading, the load shall be increased by a multiplier given by: F /D = 1 + [ l + (0.0064 Wf)2 [k for SE Wf < 2000 in/sec. 1323 044

11 - wa:mP m max m I wa: l 4 I HO t m..r w c5 E I sf P P / D / / / I T TIME Figure 2.7-3 Pulse Shape for Water Impact on Flat Targets _ _.}'. _ _ _p-7 .e. 20 s 3___. .__4_____ V = 40 ft/sec 3 .3 .....4... 1_. 4 ( ._._4 ~_._ _.. w... _.. _.+.._. l _j - q _ _.. .__.4 .. _.. _ '.__._{ 15 Z . _ 4 A... ._r_..._._. - --- - r-w g .. _ _ _j _- ... =... -. _ -. - *

L-_-

".y.--- ...4.. __.g__ y_ _.___._4 .._ p _ _. ___.___}_.____.__ .___4.. _.._.3_.._. a y_ 10 _,.,,__,,3,,_,

s

. _ __ _.i. _ _L.. z_ _.t....._.. ..4_.. .p.. m m . ____ ~. - __-___q_._.__ _ _ _ _ _... { t .-l w ...-_l,._ 2 g _. _. _ _ _. _ +.. ____._)__-.. t .y. .__q .._. y .._4.__._.___ I ._ p._. _ _..._.4_. ... __ f. ___. + _. _ t. .._._y-_.._ ... '... _ 7 ...._u. c 0.5 0.6 07 0.8 0.9 1.0 OPEN ARE A FRACTION Figure 2.7-4 Pressure Drop Due to Flow Across Gratings 1323 065

- 12 where: F = static equivalent load SE = width of grating bars, in. W f = natural frequency of lowest mode, HZ D = static drag load If Wf > 2000 ft/sec (not expected for gratings) the force on the bars of the gratings will be calculated by the method outlined above for flat-surfac3d structures. 2.7.4 Load Apolication These load specifications correspond to impact on " rigid" structures. When performing the structt'ai dynamic analysis, the " rigid body" impact loads shall be applied; however, the mass of the impacted structure shall be adjusted by adding the hydrodynamic mass of impact, except for the gratings. The value of the hydrodynamic mass shall be obtained from the appropriate correlation in Figure 6-8 in NEDE-13426-P. When the impact loading is primarily impulsive and calculations have already been performed in accordance with the LDR methodology, simple adjustments may be made to the LDR analyses. Under these conditions, a parabolic pulse shape, as proposed in LDR, is acceptable provided corrections are nade to account for the 35% margin in the impluse and with additional corrections for the drag force irmiediately following impact. For structures with a natural frequency less than 30 Hz, loading can be treated impulsively (i.e., independent of pulse shape) when the conditions fall into the region above the straight line shown in Figure 2.7-5. The following corrections must be applied to the previously calculated stresses: 1. The calculated stresses will first be multiplied by a factor of 1.35 to account for the data scatter in the impulse data. 2. The calculated stresses will then be multiplied by an additional factor to account for the presence of drag following the impact. This factor is determined as follows: 1323 066

TYPICAL IMPACT STRUCTURES: - ~- ,s' a s { l I I l lN 'u [ s W 4-W --* 4-W -->

.. n:.

. _ : :. :: =..,...._2.. p..u u.=._ _ _ } x :xr.. ;. -.: =.. t5 - . :,( -. -.. .. E,. =-.-. --- t2. :. =._ ___..-___.E___i_--- . 2.:

n.. :.

r=x. t... _.. : 2..:: .r_.

l.-

4- ...r==.. :.= l ~ -. _, q= -*===..== 2_ - r .. ar2==v f -- -+-- - -+-- - - - + g;

  • .... -..... _n.t :..-... _. _.. : : : 2.

_c.._.. .n - -- ~ j :--, - -i M=jg--ji=j[.5i-,, g;';[ :ij:fr;; g _-i ~%ffig:x.= . g =. = 3........._...... 22-g io -

f..

IMPULSIVE LOAD._;.E_...=~_.._ p.- -,l = =.:. .... _n._ =

x

=: m REGION ~ - ~ - - - - N i - r.

=.-: - -

_ :t

- - :t :.

g -*~:...~ b .,/...: i- . + . _i.r -

7.:--.

~ . g ~ ~. :g:~ ~ ~~ 'I m 5- ~ ~ ' ' -- g .._c _ _. !r:- ~. y if .. f :.; {.._:.___ 4 l-i E /r

P j jl

] l rf f! j. ..J.._::;l=,-Ep;-+=ij=:t=ij.[=3 0 f '-l- ~ ~t --

. 2 =..

..== a:.. = - - - l =+" = '- =" " -

=== }== =:: = ~ ~ = ~ * - ~ ~ ~ ' ~ ~ ~ 0 1 2 l V (feet) Figure 2.7-5 Impulsive Impact loading Region for Structures with a Natural Frequency Less Than 30 Hz 1323 067 i

. 14. Calculate the drag pressure,(Pimpactvelocitybythemethodsohg)c a. dr Sections 2.7.1 or 2.7.2. b. Form the ratio: Pdrag/Pmax where Pmu is the amplitude of the parabolic pulse used in the original stress analysis multiplied by 1.35. Determine the dynamic load factor (DLF) from Figure 2.7-6, corresponding to the two cases: (1) parabolic pulse without drag and (2) parabolic pulse followed by drag. d. M 'tialy the calculated stress by the factor DLF 1 6 drag /CLFw/o drag 2.8 FROTH IMPINGEMENT AND FALLBACK LOADS Froth is generated by (1) impact of the rising pool surface on the vent header and (2) bubble breakthrougn, as described in Section 4.3.5 of the LDR. The following load specification was derived from the high-speed film records of various pool swell tests and an analysis of pool acceleration following vent header impact. The impingement loads for Region I and Region II and the froth fallback loads, as described in Section 4.3.5, shall be defined as follows: 2 V 'Af P = f 144 gc where: P = froth impingement pressure (psi) f of = froth density (lb 'ft ) m V = froth impingement velocity (ft/sec) g = gravitational constant (ft/sec )z c Region I: The froth velocity shall be based on a source velocity equal to 2.5 times the maxim'.'n pool surface velocity prior to vent header impact, which is corrected for subsequent deceleration due to gravity starting at the 45 tangent on the bottom of the vent header, as shown in Figure 4.3.5-1 of the LDR. The froth density shall be assumed to be 20% water density for structures or sections of structures with a maximum cross-sectional dimension of less than 1323 068

- 4 max by k} r b ,P' / e h TIME i I i ~ l 3:..lf i / A l }f j e

2. 0 -

}T p N drag Z f P N Gl' (;if! fu max i Y OY -,b/:0$, X /b?< MV>& J l y' y" g.%if8. -[i. y /: /!/23 y S try M/V! f.i S I / 7 y'l//ft: 1: l' h / fi jf /l/y l 'l " 1 e '0 ~ .l / iA / V y ~ + s 2 / X AP' y;j y A *g i:.. :1 4 3 _ s l / J /Vi .E - t ~% a A 'f: f fj

j-j, f y; l

7 -7 c y fl q: T = Natural Period - / [. ~l. l: N j .l l-u O. 0.1 0.2 03 0.4 05 r/T g Figure 2.7-6 Effect of Drag Following a Pa abolic Impact Pulse 1323 069

. or equal to one foot, and a proportionately lower density for structures greater than one foot; i.e., p= (0.2/x) pw where x is the dimension in feet. The load shall be applied in the direction most critical to the structure within the 90' sector bounded by the horizontal opposite the vent header to the vertical upward as shown in Figure 2.8.1. The load shall be i assumed to be a rectangular pulse with a duration of 4 80 milliseconds. Region II: The froth velocity shall be based on a source velocity equal to the maximum pool surface velocity, directly beneath the structure under consideration, which is corrected for subsequent deceleration from the elevation of the maximum velocity. The froth density shall be assumed to be 100% water density for structures cr sections of structures with a maximum cross-sectional dimension less than or equal to one foot, 25% water density for structures greater than one foot, and 10% water density for structures located within the projected region directly above the vent header. The load shall be applied in the direction most critical to the structure within the + 45' sector of the upward vertical. The load shall be assumed to be a rectangular pulse with a duration of 100 milliseconds. Fallback: The froth fallback velocity shall be based on the freefall velocity from the upper surface of the torus shell directly above the subject st,ucture. The froth density shall be assumed to be 25% water density, with the exception of the projected region directly above the vent header which is 10% water density. The load shall be assumed to directly follow the froth impingement load, with a duration of one second. 2.9 P00L FALLBACK LOADS The proposed load definition procedures set forth in Section 4.3.6 of the LDR for suppression pool fallback loads on internal strtJctures following pool swell are acceptable. 2.10 Vent Header Deflector Loads The load definition procedures set forth in Section 4.3.9 of the LDR are applicable only to the four deflector types shown in Figure 4.3.9-2 of the LDR, and are generally acceptable, subject to the following constraints and/or modifications: 1323 070

. VENT HEACER %W TORT.;S Figure 2.8-1 Direction of Load Application for Froth Region I 1323 071

_18 - 2.10.1 QSTF Deflector Load-An individual plant may choose to use deflector load data taken directly from the QSTF plant-unique tests. This technique is subject to the following requirements:

1. If the QSTF deflector load measurement does not have a sufficiently fast response time to resolve the initial impact pressure spike for the deflector types 1 - 3.

inclusive, the loading transient shall be adjusted to include the empirical vertical force history of the spike shown in Figure 2.10-1. This impulse need not be applied for the type 4 deflector.

2. The QSTF plant-unique loads shall be adjusted to account for the effects of (a) impact time delays and (b) pool swell velocity and v:eleration differences which result from uneven spacing of downcomer pairs. The longitudinal load variation shall be evaluated at the instant when the undistrubed pool surface would have reached the local elevation of the center (half-height elevation) of the deflector. The three-dimensional load variation shall be based on the EPRI " main vent orifice" tests, as discussed in Section 2.5.
3. In applying the load to the deflector, the inertia due to the added mass of water below the deflector shall be accountec for.

The added mass per unit lengtn of deflector may be estimated by: %

  • 19c Vw 4 = hydrodynamic fnass per unit length (1b/ft) where:

I = total impulse per unit length associated with the impact transient (lb-sec/ft) V = impact velocity (ft/sec) = deflector width (ft), as sh'own in Figures 2.10-2 w tSrcugh 2.10-5 9e = gravitational constant 1323 072

. t I j F = Vertical upward force on deflector per unit length 8'- . i. E..r_ =.Eli:n d = Diameter of cylinder in _ut__ _..;.. ..t deflector types 1 - 3 .._..: _ _ - j __- _ _. } 1;.{nr.-.. - - V = Impact velocity + . ::: x_. .= \\..t.r. =.. :.:=.:. 2__n_g.._;_i_r__:lu.n_=._::3.j_2. p = Water density

g.: =_ :=_::

Z._ :-i(:_. =:-- = _t_: -lE.8.._.. t = Time from begining of impact

6. _1;N_-QiE7~ Ec-

- d =~~ 2EI EE F y 'g. . f... ...~..I=_. 2 . :'\\

iE:

it;; 2 t. __. ,k' .. j.. [. ~. {

j{ i-(

.J llj ::_--

li.

. _u i l '. \\ :l- ..j- --di:-

i---

j -NEi.ik!!:: I5:' It5bfi--IQ

~ _. 2 -:

2_

t: :
x N x

.x _rt::2..x : :.

t.A-, t:r -
xx
:: c

.j jnE iinji _j{- --jiNQiji=: E'j'ir gir_. . -- ~. !. c -i '-ij; :.p$:

Z.2ij;"

==j:- - i.r z!, =l:k,::_j:;

p,
, 72)

- - + - - - + - - - - - - + - - - - _t---- = - T --- > 0. _, _ ; f ;,_ -,, 1:

.- -_ : = rx'nx :- ' t =-

r :1.1: r. = -" 0. 0.1 0.2 Vt / d Figure 2.10-1 Impact Force Transient for Addition to the Empirical Data for Deflector Types 1 - 3. 1323 073

. 2.10.2 Analytic Deflector Loads The deflector load definition which is based on empirical expressions for impact and drag forces together with plant-specific definition of the pool swell velocity and acceleration transients, as described in Sections 4.3.9.1, 4.3.9.3, and 4.3.9.4 of the LDR, is acceptable, with the following modifications: 1. The impact transient and " steady drag" contributions to the load shall be computed from the correlations shown on Figures 2.10-2 through 2.10-5, for deflector types 1 - 4, respectively. For times past the periods shown, the last value shall be extended for the duration of the transient. 2. The three-dimensional load variation and timing shall be based on the EPRI " main vent orifice" tests, as discussed in Section 2.5. 3. The gravitatioral ccmponent of the acceleration drag shall be included in F, as defined in NED0-24612. A 4. In computing the deflector response to the load, the added mass of the water shall be accounted for, as described in Section 2.10.1.3 above. ~.11 CONDENSATION OSCILLATION LOADS 2 The following criteria have been developed in consideration of the fact that the " condensation oscillation" loads (i.e., high vent flow rate with low air content) have been derived from a single FSTF test run (M8). The condensation oscillation regime is a harmonic phenomena and, therefore, statistical variance or load magnitude uncertainty cannot be establishbd from one test run. Although we conclude that the M8 tested conditions are conservative and prototypical for the Mark I design, a reasonable measure of the uncertainty in the leading function is necessary to assure the margins of safety in the containment structure. However, based on our assessment of the phenomenological studies conducted by the industry and the llRC Office of Nuclear Regulatory Research, we believe that the following load specifications are probably conservative and fom a sufficient basis to proceed with implementation of the Mark I Long Tem Program. We will require that the Mark I Owners Group confirm the condensa-tion oscillation loads (i.e., torus shell loads, dowr. comer lateral loads, vent system pressure, and submerged drag source) by perfoming a sufficient number of additional large break, liquid blowdown tests in FSTF to establish the uncertainty in the load magnitudes. 1323 074

21 e - d --e n V 8. _ __ n x. l 1_- -[.-i l I {_. - l : ~ --- l~ i p 6. 8 _ji. fi .l. 7 2 2 ~ ~ ~ ~ - ~~ pyd 2 ~ ~ k': i{ l l ~l l ~ \\ :l' ll l 1 1 3, - i\\ i i j -j E1.:{ i-l l l l l \\j i j (C )= from Figure 2.10-2b D li l 1 i 2. { l: l l I i i '+- 1_ 9F. _ _ _ t_ _ _ ' In - .l. .i i i i i l- .I l } ) 1 0. I O.136 05 1.0 Vt/d Figure 2.10-2 Impact and Steady Drag Force Correlation for Type 1 Deflector 1323 075

2. ..1 i .J _ ...1... - - ~ _ ..l . pVd < 5 x 105 i p fu .. p a ..g t -{. ?. ..._4. _.1 . 4 }.. t__ .-.t... .-4 (C )~ ~ D Y$ i-T ~ ~ ~ "~ ~:: ~;1 _. Z ~~~ ~ ~ ~ ~ ' ~ ~.i N r 1* 4 A_. p_ ..N ..--- t -- pVd > 5 x 105 .. p ... p_. 1 U ^^ ..../ 9.. .y. _{ 1 .a. . - - ~.... .e... .-j.- ~ f-7. _. _ .t.. l .1.. --f " ~ ' - - ~ ~ ~ ~ ~ ~ ~~~ ' ' - - ~

t-4

____.7_... .. t - .. 7.. + 1 .. g _. 4 __.7___. __.4.... 9. _ __ L. _w

4. _

_ __. p.. _..g...4 1. 5. 10. 50. 100. 2 V /gd Figure 2.10-2b (C )= f r Type 1 Deflector D 1323 076

~ u - -e n i d=0.707u O i n V l l .l (( 4 93 ,{. ..-j== l- .1-4 .h, .:P l 1 EM:. i l F 7' 2 ?>- l M" pvw q 4 -t-7; .)t l \\i

l l

l- -i n

\\i

/ l i N i i Ef i fi i i !\\ i .. a c-i ..'t l i + l t 4 [ i l .-. j. j v i 1 i. j 1 ~ 1 i f ^p 1 i p }I_ .. _. o.1.._. - / 1 l 1 . /_ - 1 .i i i y i i-Jit 44 1 l l l\\ l ~~7{:/::

l :

{ ' \\, .I g ,o. t. t t .207 0. 0.136 05 0.854 1. Vt/d Figure 2.10-3 Impact and Steady Drag Force Correlation for Type 2 Deflector 1323 077

- za. +- w ---+ ? d=0.414w 1 a V g- -l-l '{-

_: l-t

. ; p.. ~7i~., i i A ' il l:~ i _. X r2 90;

f. -\\;

i. =i: 1.; .i i / \\i .l. .j. / :l i j\\l- {:

jl :!E-

._1 2 i i /- I l 1 i -1. pVW . *- a .g g 2 l I I\\ I 1 I ii' r -l t I \\ t _i-l i i l f ~" I [i ', --i l !\\i l o,7 -ry e -l i .l I \\ i l i -1 i / -l j 'j j '._ __...t. _ [_ 3 I I [ _ __ _ __._ ' _ ;- ba V.n. i ', I - I i N I .207 0. 0.136 1.0 1.60 2.0 Vt/d Figure 2.10-4 Impact and Steady Drag Force Correlation for Type 3 Deflector 1323 078

w 90 a V 4 . j :. .t ..:f;. .n;.. - u.:' fur r

:t.:

.:I r.. - t:.. ;r r.L.. rt u: =.:g.: =t.._ m:. ..y: : : .:x : -x7.._ _r. t t. --~;- ntr- -n = rntr-- n _. -- + C Zi.~ !l':.. . i!- .a {n - - :J:.-

Z:*._L

. :t:. _C { C. Int: nt: - --+; : _. ;n =. {: --- := r--- 72:..

t -
t---

t:- - - t:. r. ..rt ' ...t:r - 7;t:. f{ T

!rn.

.t r -- != rnt: - j-

t._.

--~ n,- n - ;-.. nn:-- =2: . x::- -: :n-

.. t t

F =xt :- 1-- 2=: ~~~3=r-~~=t==/2= -~- - - + - + . ; ::. _ 1..:... _ " :~ = 2:~~~ 2.I:~~~ 2 ~ ':~~ ~ ~ =

55I!~~ =#I 5= ='I i=

T~

5

'i!\\ 9i 25 ~-52=~- 2

= = " = =

. n _..... .r m- -l - +. x: -- r-

. t. _.

1 _./. f \\ 1: t g+ +

x t

-!.- :..:/;....i. j. Q!lll1 -i.i~ ~ l -l / i .. ;\\..l- .: ir =a _. W. w. T . ai.N

b.

t.= /

r.$:.... _

. k.- l- .l. __ .-) t. x:+ ... fx: =: -- - ,. r.~- t, -{:. j3 7252 3ff 5 nhn..~ [

.._l......

- i f _ 3:. f _. ~- 0 1 15 2. 2Vt/w Figure 2.10-5 Impact and Steady Drag Force Correlation for Type 4 Deflector 1323 079

. 2.11.1 Condensation Oscillation Torus Shell Loads The loao definition and assessment procedures set forth in Section 4.4.1 of the LDR for the condensation oscillation loads on the torus shell are acceptable, subject to the following confirmation: 1. Provided that the " rigid wall" load derivation technique described in NEDE-24645-P is demonstrated to be conservative, in response to Question 7 in our request for additional information (D. Eisenhut, NRC, to L. Sobor, GE, dated July 30,1979). 2. Provided that sufficient justification can be provided to exclude a condensation oscillation asyrrmetric loading condition, in response to Question 2 in our request for additional information. 3. Provided that the uncertainty in the load magnitude is demonstrated to be less that the demonstrated conservatisms in the load specification, by the testing program described above. For clarification, the load specification set forth in Section 4.4.1 of the LDR shall be used in conjunction with a coupled fluid-structure analytical model. The condensation oscillation loading for the IBA is a continuous sinusodial function with a peak amplitude and frequency range of that specified for the " pre-chug" load. We will require that the conservatism in the IBA condensation oscillation loads be demonstrated as part of the response to Question 7 in our request for additional information for the specific flow regimes of interest. 2.11.2 CONDENSATION OSCILLATION DOWNC0 iter LOADS 2.11.2.1 Untied Downcomer Loads The condensation oscillation downcomer lateral loads for " untied" downcomers shall be defined as described in Section 4.4.3 of the LDR, based on the methodology in NEDE-24537-P. However, in computing the dynamic load factors DLF P =P max 1 FLT3 1323 080

.. where: P = maximum static equivalent lateral load for max plant-unique downcomer P) = maximum static equivalent lateral load in FSTF DLF = plant unique downcomer dynamic load factor DLF) = FSTF downcomer dynamic load factor the plant-unique loading condition shall be derived as follows. The plant-unique DLF shall be calculated using a damping value consistent with the requirements of Regulatory Guide 1.61, " Damping Values for Seismic Design of Nuclear Power Plants," and a natural frequency determined from the structural analysis of the downcomer - vent header system. The plant-unique driving frequency shall be specified as that frequency in the range 4 - 8hz which produces the maximum structural response. The natural frequency and damping values for the FSTF DLF snall be conservatively established from a " pluck" test of an untied downcomer in FSTF, with a nominal water level of 3 feet 4 inches and an amplitude in the range of the response level. The dr!vir.g frequency for the FSTF DLF shall be assumed to be 5.5hz. 2.11.2.2 Tied Downcomer Loads The condensation oscillation downcomer loads for " tied" downcomers, as described in Section 4.4.3 of the LDR, are unacceptable. We will require that a load specification be derived from the maxiraum dynamic load components on each downcomer in a tied pair. The load definition and structural analysis technique shall be confirmed by comparisons of the predicteo structural responses to the measured strains in the FSTF went header and tie-bar. The FSTF natural frequency and damping values shall be conservatively established by performing a " pluck" test for a tied downcomer pair in FSTF, with a nominal water level of 3 feet 4 inches and an amplitude in the range of the response level. 2.11.3 Condensation Oscillation Vent System Pressure load The load definition procedures set forth in Section 4.4.4 of the LDR for the oscillatory pressures in the vent system during the condensation oscillation period, are acceptable subject to confirmation by the additional testing as described above. 1323 081

28 - 2.12 CHUGGING LOADS 2.12.1 Chugging Torus Shell Loads The load definition and assessment procedure set forth in Section 4.5.1 of the LDR for the chugging condensation loads on the torus shell are acceptable, provided the " rigid wall" load derivation technique is demonstrated to be conservative in response to Question 7 in our request for additional information (D. Eisenhut, NRC, to L. Sobon, GE, dated July 30,1979). This load specification shall be used in conjunction with a coupled fluid-structure analytical model. 2.12.2 Chugging Downcomer Loads 2.12.2.1 Untied Downcomer Loads The chugging lateral loads on untied downcomers shall be defined as described in Section 4.5.3 of the LDR, which is based on the methodology in NEDE-24537-P, with the following exceptions: 1. The load specification for comparison to the ASME code primary stress limits shall be based on the maximum measured resultant static equivalent load in FSTF. 2. The fatigue usage analysis for each downcomer shall be based on a statistical loading with a 95% probability of non-exceedance. 3. The multiple-downcomer loading to assess statistical directional dependgnce shall be based on a non-exceedance probability of 10-'+ per LOCA. 2.12.2.2 Tied Downcomer Loads For tied downcomers, the strains in the downcomer itself shall be evaluated exactly as in the case of the untied downcomers, using tied downconer data. The strain in the tie bar shall be evaluated by assuming that one of the two tied downconers is subjected to a dynamic load of triangular shape, with an amplitude of: RSEL (RSEL = Resultant Static F = max m ft EquivalentLoad) d whera RSEL is the maximum measured RSEL for an untied downcomer during chugging, f is the lowest natural frequency of vibration of an untied downcomer for the specific plant, and the duration of the load t, shall be assumed to the 3 milliseconds. The load d direction shall be taken as that (in tne horizontal plane) which result in the worst loading condition for the tie bar and its attachments to the downcomers. 1323 082

. 2.12.3 Chugging Vent System Pressure Loads The load definition procedure set forth in Section 4.5.4 of the LDR for the oscillatory pressures on the vent system during the chugging period are acceptable. 2.13 SAFETY-RELIEF VALVE DISCHARGE LOADS 2.13.1 Safety-Relief Valve Discharge Device The acceptance criteria set forth below for the quencher discharge loads and submerged structure drag load source strengths are applicable only to the "T" quencher configuration described in Section 1.1 of NEDE-24542-P. For plants using other types of quencher discharge devices, the SRV discharge load definition, submerged structure drag load source strength, and pool temperature limits will be evaluated on a plant-specific basis. 2.13.2 SRV Discharge Line Clearing Transient The load definition and as: 3sment procedure, described in Section 5.2.1 of the LDR, for the pressure and thrust loads on the SRV discharge line and quencher, which is based on the methodology presented in NEDE-21864-P and NEDE-23749-1-P, is acceptable. '.13.3 SRV Air-Clearing Quencher Discharge Shell Pressure Loads 2.13.3.1 Methodology for Bubble Pressure Prediction The load definition procedures described in Section 5.2.2 of the LDR and the methodology in NEDE-21878-P for predicting the quencher bubble pressurb are acceptable, with the followirig exceptions: 1. The load definition procedures set forth in Saction 5.2.i of the LDR are acceptable for SRV discharge line water-leg lengths less than or equal N 13.5 feet. In the event that the water-leg length for a pac +1cular disc.hros line exceeds 13.5 feet, the load preoittion for a 13.5 foot water-leg length shall be used. 2. The proposed methodology for predicting bubble pressures due to SRV subsequent actuations is not acceptable. The pressure amplitude predicted for the SRV first actuation shall be used in conjunction with the bubble frequency range f or subsequent actuation, as specified below, for structure, equipment, and piping assessment in response to events containing SRV sub-quent actuations. 1323 083

. 2.13.3.2 Methodology for Tore Shell Pressure Prediction Based on the predicted air bubble pressure-time histories, as discussed above, the torus shell pressures at various locations in the suppression 1001 shall be calculated by the load definition procedures described in Section 5.2.2.3 of the LDR in conjunction with the appropriate pressure attenuation model. For quenchers located on the torus center-line, the pressure attenuation model described in Section 2.4 of NEDE-21878-P in conjunction with the bounding factor presented in Section 3.2 of NEDE-21878-P shall be used. The load adjustment and attenuation factors proposed for the "off-center" T-quencher configuration presented in a meeting with the staff on May 30, 1979, are acceptable. We will require, however, that this load specification and its bases be documented in a supplement to the LDR. 2.13.3.3 Multiple - Dischart. Loads The torus shell loads due to multiple SRV actuations shall be calculated as follows: 1. The peak values of bubble pressure due to a single valve actuation shall be combined by linear superposition (ABSS method) with the accropriate pressure attenuation nodel, as discussed above. All bubbles shall be assumed to oscillate in-phase with the freauency ranges soecified below for both first and subsequent actuations. 2. In the event that the cc,mbined peak torus shell pressure exceeds 1.65 times the local predicted ceak bubble pressure due to a single valve actuation, the resultant torus shell peak pressure for the design assessment may be taken at the lower value. 2.13.3.4 Frequency of Pressure Wave Form The pressure wave form predicted by the methodology described in Section 5.2.2 of the LDR within the followinc uncertainty ranges (stretc%c or compressed time scale) that Mll produce ti.e maxinur structural, equipmut, or piping system response shall be used for the design asse sment: 1323 084

. 1. First Actuation - the frequency range shall be 0.75 times the minimum predicted frequency to 1.25 times the maximum predicted frequency. 2. Subsequent Actuation - the frequency range shall be 0.60 times the mimimum predicted frequency to 1.40 times the maximum predicted frequency. 2.13.4 SRV Discharge Line Reflood Trans_ient The transient analysis technique to compute the plant-specific reflood heights in the SRV discharge line following valve closure, as described in Section 5.2.3 of the LDR and based on the methodology in NEDE-23898-P and NEDE-21864-P, is acceptable. 2.13.5 SRV Air and Water Clearing Thrust Loads The load definition and assessment procedure for the quencher and quencher support thrust loads, described in Section 5.2.6 of the LDR, is acceptable. 2.13.6 SRV Discharge Line Temperature Transient The transient analysis technique to compute the maximum temperature loads on the discharge line and quencher device, as described in Section 5.2.7 of tr.e LDR, is acceptable. 2.13.7 SRV Discharge Event Cases The kind and number of SRV discharge e-ants shall be based on the plant-specific system configuration and a conservative assessment of plant operational history. ... following load cases shall be considered for the design assessment: 1. A first actuation, single valve discharge shall be considered for all event combinations involving SRV events. Single valve subsequent actuations shall be considered for the SRV, SB A, and IBA event combinations, as detemined from a plant-specific primary system analysis. 2. Asymetric SRV discharge, both first and subsequent actuations, shall be considered for SRV, SBA, and IBA event combinations. The degree of asymmetric discharge for each event combination shall be determined from a plant-specific primary system analysis designed to maximize the asymetric condition. 1323 085

.. 3. ADS valves discharging on first acutations shall be considered for the SBA and IBA event combinations, followed by subsequent acutations determined from a plant-specific primary system analysis. 4. The maximum number of valves that will actuate for the SRV event combinations shall be determined from a plant-specific primary system analysis for the design basis transients, which assumes that all valves actuate at their set-point pressures. All first actuations shall be assumed to occur in phase, follcwed by subsequent actuations determined from the primary system snalysis. All of the event combinations above include the earthquake events (OBE and SSE) in combinat%1 with the SRV discharge events. 2.13.8 Suppression Pool Temperature Limits As part of the PUA, each licensee is required to either demonstrate that previously submitted pool temperature analyses are sufficient or provide plant-specific pool temperature response analyses to assure that SRV discharge transients will not exceed the following pool tcmperature limits. ~, 1. Local Temperature Limit The suppression pool local temperature shall not exceed 200 F throughout all plant transients involving SRV operations, for any quencher device that has (a) the hole diameter equal to and (b) greater than or equal hole spacing than that of the generic Mark I T-Quencher. 2. Local and Bulk Pool Temperature The local to bulk pool temperature difference shall consider the plant-specific quencher discharge geometry and RHR suction and discharge geometry. The analysis of the plant-specific local to bulk pool temperature difference shall be supported by test data from either the existing Montic.ello pool temperature data or in-plant rests. The " local" temperature is defined as the temperature in the vicinity of the quencher device during discharge. For practical purposes, the water temperatures observed in the i sector containing the discharge device at shell locations on the reactor side of the torus downstream of the quencher centerline at the same elevation as the quencher device may be considered " local" temperatures. The " bulk" temperature, on the other hand, is the temperature calculated assuming a uniform distribution of the mass and energy discharged from the SRV. 1323 086

. 3. Suppression Pool Temperature Monitor System The suppression pool temperature monitoring system is required tc ense a that the suppression pool is within the allowable limits set forth in the plant Technical Specification. The system shall meet the following design requirements: a. Each licensee shall demonstrate that there is a sufficient number and distribution of pool tempera-ture sensors to provide a reasonable measure of the bulk temperature. b. Sensors shall be installed sufficiently below the minimum water level, as specified in the plant Technical Specifications, to assure that the sensor properly monitors pool temperature. c. Pool temperature shall be recorded in the control room. A sufficient number of temperature monitors shall be provided to permit the operator to establish the bulk pool temperature. Operating procedures and alarm set points shall consider the relative accuracy of the measurement system. d. Instrument set points for alarm shall be established, such that the plant will operate within the suppression pool temperature limits discussed above, All sensors shall be designed to seismic Category I, e. Quality Group B, and energized from onsite emergency power supplies. 2.14 SUBMERGED STRUCTURE DRAG.E0 ADS 2.14.1 LOCA Water Jet Loads The load definition and assessment procedure described in Section 4.3.7 of the LDR, which is based on the " Moody Jet Model" (NEDE-21472-P), is acceptable subject to the follow-ing constraints and/or modifications: 1. The plant-specific jet discharge velocity, V (t), and D acceleration, aD(t) = dV /dt (t), from the QSTF plant-D specific test series shall be used as the driving sources for the jet model. 2. Forces due to the pool acceleration and velocity induced by the advancing jet front shall be computed for struc-tures that are within four downcomer diameters below the downcomer exit elevation, even if the structure 1323 087

1 is not intercepted by the jet. The flow field shall be computed by modelling the moving jet front as a i j hemispherical cap centered one downcomer diameter (D) behind the " Moody" jet front positions, containing l the same amount of water as the " Moody" jet, and moving with the velocity of the " Moody" jet front. The formulas for the hemisphere radius (R ) and the trajectory 3 of the hemisphere center (x ) are: c l R (t) = (f +(3x (t)/D)b) 1/3 for x (t) > 0 3 f f I R (t) = 9*f(t) 1/3 for x (t) 1 D 3 ( ) f 2D x (t) = x (t) -D c f for x (t) > 0 f l x (t) = 0 for x (t) 1 0 f c where x (t) is the position of the " Moody" jet front as a f function of time, as computed in NEDE-21472-P. Using formulas 1 and 2 in NEDE-21472-P and assuming an average constant acceleration of the particles contained within one downcomer diameter behind the " Moody" jet front, the cross-sectional area in this region can be approximated by: T (1 + 1/(1-x/x )b) = xD2 A (x,t) f where x (t) is the " Moody" jet front position as computed f in NEDE-21472-P. The' volume contained in this portion of the jet can be obtained by integrating A(x,t) from (x, -D) to x for xf greater than D, and from x=0 to x = xf f6r xf f less than D. When the jet is modelled by a more realistic hemispherical cap, while conserving the total volume of the fluid, the cap radius and position is given by the equations above. The equivalent uniform velocity and acceleration at the location of the structure (x,y) shall be obtained from the time dependent potential $ (x,y,t) induced by the jet front: 3 1323 088

, fR i fdRhsi - 1 l[_R (x - x ) dx -i _ S. I rl s_ e 4j (x,y,t)= c (r, (dt / 2 (r dt where* r = { {x-x )2 + y )b and y is the transverse distance 2 ofthestructurbfromthejetaxis,and(x-x)isthedistance fromthestructuretotheeffectivejetfronfcenteralongthe jet axis. The potential is the superposition of the expansion and motion of the sphere as given in any standard hydrodynamics text (e.g. Milne Thomposon, Theoretical Hydrodynamics, Fourth Edition, pp. 455-566). The local uniform flow velocity is U,, (x,y,t) = v4) as in NED6-21471,while the acceleration is a(x,y,t) = BU. at This calculation need only be performed for r> R and x > x

  • s c

If either of these conditions are not satisfied, the methodology in the LDR will bound the load and is, therefore, acceptable. 2.14.2 LOCA Bubble Drag Loads The load definition and assessment procedures described in Section 4.3.8 of the LDR, wfiich are based on the methodology in NED0-21471 and experimental confirmation in NEDE-23817-P, are acceptable subject to the following constraints and/or modifications: 1. Flow Field a. QSTF plant-specific test results (NEDE-21944-P) will be used. b. Model E in NEDE-21983-P will be used for the method of images simulation of the torus cross-section. c. After contact between bubbles of adjacent downcomers, the pool swell flow field above the downcomer exit elevation will be derived from the QSTF plant-specific tests. l 1323 089

-3 2. Drag Load Assessment a. Drag forces can be computed for circular cylinders as given in NED0 21471, but a conservative drag coefficient of CD = 1.2 must be assumed, independent of the Reynolds number, b. Drag forces on structures with sharp corners (e.g., rectangles and "I" beams) must be computed by cons,1,dering forces on an equivalent cylinder of diameter Deq = 2'2 Lmax, where Lmax 15 the maximum transverse dimension. Lmax is defined as the dia-meter of a circumscribed cylinder about the cross-gection of the structure. For example, Lmax equals (a2 + b f for a rec-2 tangular cross-section of sides a and b. Long slender structures must be considered in segments of length c. (L), which do not exceed the diameter (D or Deg). Alternatively longer segments may be used as long as the equivalent uniform flow velocity and acceleration are evaluated conservatively for every point on any such segment. d. Interference effects due to the proximity of walls shall be considered for each structural segment that has its center less than 1.5 diameters from a boundary. Interference effects between neighboring structures shall be considered whenever the centers of the segments are less than 3D, where D = 1/2 (D1 + D ), the average diameter of the two structures. 2 For structures near walls, the multiplier (1 + Aw) shall be used to increase the acceleration drag and the multiplier (1 + Dw) shall be used to increase the standard drag. Aw and Dw that bound theory and experiments are~given below as functions xw (xw = r/D - 1/2, where r is the distance from the segment center to the boundary).

0. 05 < x, < l. 0 A, = 0. 05/x g

D,= 0.12/x, x < 0.05 A 1.0 = g D,= 2.4 For structures with neighbors that are less than 3D away and within 30 of being parallel, the multipliers (1 + A ) and I (1 + D ) shall be applied to the acceleration and standard I drag components respectively. Bounding expressions for AI and DI are given below as functions of x1 (x1 = r;2 n - 1 / where rl2 is the distance between segment centers, 1323 090

\\ , 0.05 < XI<2 AI = 0.2 D2 \\ XI D) +D2/ DI = 0.2/XI where D) is the diameter of the structure under consideration and D2 1s the diameter of the neighbor. If more than one .. neighbor must be considered, the AI and DI values may be sunned over the neighbor structures. For x! less than 0.05, the two neighbor structures shall be considered as an effective single structure. The effects of wall proximity and neighbor structures may be superimposed in order to compute overall multipliers as follows: (1 + Aw+ IAIh) k (1 + Dw + IDIk) k In situations where interference effects must be considered, but the correction techniques outlined above are not applicable, a detailed interference effects analysis shall be performed. 2.14.3 QUENCHER WATER JET LOADS The load definition procedure described in Section 5.2.4 of the LDR, which is based on the methodology in NEDE-25090-P, is acceptable, subject to the appropriate documentation of the confirmatory tests discussed in NEDE-25090 P. 2.14.4 QUENCHER BUBBLE DRAG LOADS The load definition and assessme0t procedures described in Section 5.2.5 of the LDR, in NEDE-21878, and irr NED0-21471-2, are acceptable gubject to the folloo ng constraints and/or modifications: 1. Flow Field a. The determination of the charging, formation, and rise of the oscillating bubbles is subject to the same conservative factors that are used for the quencher torus shell pressure loads, as described in NEDE-21878-P. b. Drag loads on the quencher anns and the SRV discharge line shall be computed on the basis of asymetric bubble dynamics. Either a full 1800 phase shift shall be considered for full strength bubbles on opposite sides of these structures, or a more detailed assessment of the asymmetry of the bubble source strengths and phasing must be obtained from the experimental information in NEDE-21878-P. c. Model E in NEDE-21983-P shall be used for the method of images representation of the torus cross-section. 1323 09i

. 38 _ 2. Drag Load Assessment a. Drag forces for circular cylinders shall be computed on the basis of acceleration drag alone, under the condition that UmT/D < 2.74, where Um is the maximum velocity T 1s the period of bubble oscillation, and D is the cylinder diameter. For UmT/D > 2.74, the standard drag shall bo included with the drag coefficient CD = 3.6 in order to bound the re'want experimental data, b. The constraints specified for the LOCA bubble drag load assessment also apply to the quencher bubble drag loads, with the exception of the drag coefficient. 2.14.5 LOCA CONDENSATION OSCILLATION DRAG LOADS The load definition and assessment procedures described in Section 4.4.2 of the LDR and the methodology described in NED0 25070 are acceptable subject to the following constraints and/or modifications: 1 - Flow Field a. An average source strength shall be established by considering equal source strengths at all eight downcomers in equation B-4 in NED0 25070. A maximum source strength shall be defined as twice the average source strength. For each structure,the loads shall be computed on the basis of both the average source at all downcomers and for the maximum source applied at the nearest downcomer. b. The fluid-structure inter, action effects shall be included for any structural segment for which the local fluid acceleration is less than twice the torus boundary acceleration. This may be accomplished by adding the boundary acceleration to the local fluid acceleration. 2. Drag Load Assessment a. The constraints and modifications specified for the quencher 'ubble drag loads apply. b. These loads may be applied quasi-statically to structt.res, only if the highest significant Fourier components occur at frequencies less than half the lowest structural frequency. 1323 092

,. 2.14.6 LOCA CHUGGING DRAG LOADS The load definition and assessment procedures described in Section 4.5.2 of the LDR and the methodology in NED0-25070 for the pre-chug drag loads are acceptable subject to the constraints in Section 2.14.5 for the condensation oscillation drag loads. The application for the post-chug drag, loads is subject to the following constraints and/or modifications. 1. Flow Field The maximum source strength history shall be obtained by using* a. the maximum measured pressure (not necessarily at the bottom center) in a Type 1 chug in equation B-4 of NED0 25070, with f(r) based on the single nearezt downcomer. For each structure, the phasing between the two nearest downcomers that maximizes the local acceleration shall be established. The local acceleration shall then be computed on the basis of the two nearest downcomers chugging at maximum source strengths at the above establisned phase relation. b. The fluid-structure interaction effects shall be included for any structural segment for which the local fluid acceleration is less than twice the torus boundary acceleration. This may 5e accomplished by adding the boundary acceleration to the local fluid acceleration. 2. Drag Load Assessment a. The constraints and modifications specified for the quencher bubble drag loads apply.. b. Unless the lowest structural natural frequency times the duration of the " spike" in the source strength is greater than 3. the loads shall be applied dynamically. Either sufficient Fourier components will be included to bound the " spikes" or the load shall be applied in the time domain using the source time history. The tenn " spike" refers to the short-duration high overpressure peak, such as that exhibited in Figure 6.2.1-20 of NEDE-24539-P. 2.15 SECONDARY LOADS The following loading conditions may La neglected for the PUA: a. seismic slosh pressure loads b. post-swell wave loads c. asymetric pool swell pressure loads d. sonic and compression wave loads 1323 093 e. downcomer air clearing loads

40 - 2.16 OIFFERENTIAL PRESSURE CONTROL REQUIREMENTS Those licensees that use differential pressure control (AP) as a pool swell load mitigation feature for the LTP, shall demonstrate confomance with the following design criteria as part of the PUa: 1. fhere shall be no unacceptable change in the radiological consequences of an accident as a result of the inclusion of the AP system. 2. Steam bypass of the suppression pool via the AP system shall be eliminated by appropriate system design, or such bypass shall be demonstrated to be acceptable by calculation. 3. Design and installation of the AP system shall be comensurate with other cperational systems in the plant. 4. When the aP system involves the addition of containment isolation valves, the additional valves shall be included in the plant's Technical Specifications and the valve design and arrangement shall confom to the requirements of General Design Criterion 56 in Appendix A to 10 CFR 50 and the regulatory positions in Standard Review Plan Section 6.2.4. Subsequent to the PUA, a license amendment shall be submitted to incorporate the following Technical Specification requirements for the AP system: a. Differential pressure between the drywell and suppression chamber shall be maintained equal to or greater than "X" (where X is the plant-specific differential pressure and values less than one psid will not be credited for load mitigation), except as specified in b and c below. b. The differential pressure shall be established within 24 hours after placing the plant in the RUN mode, during plant startup. The differential pressure may be reduced below "X" psid 24 hours prior to a scheduled plant shutdown. c. The differential pressure may be reduced to less than "X" psid for a maximum of four hours during required operability testing of (specify here those safety-related systems for which operability tests either release significant amounts of energy to the suppression pool or cannot be performed with the AP established). d. In the event that the specification in a above cannot be met, and the differential pressure cannot be restored within six hours, an orderly shutdown shall be initiated and the reactor shall be in a cold shutdown condition within the subsecuent 24 hours. 1323 094

. > ~. , e. A minimum of two narrow range instrument channels shall be provided to monitor the differential pressure. Error in the AP measurement shall be no greater than + 0.1 psid or the allowable AP shall be increased to offset the error in the measurement. The instrument channe's shall be calibrated once every six months. In the event that the measurement is reduced to one indication, operation is permissible for the following seven cays. If all indication of the differ!ntial pressure is lost, and cannot be restored in six hours, an orderly shutdown shall be initiated and the reactor shall be in a cold shutdown condition within the subsequent 24 hours. 3. STRUCTURAL ANALYSIS AND ACCEPTANLE CRITERIA The staff finds the general analysis techniques and proposed structural acceptance criteria set forth in the " Mark I Containment Program Structural Acceptance Criteria Plant Unique Analysis Applications Guide," (PUAAG), NEDO 24583, Revision 1, dated July 1979, acceptable. The proposed criteria will provide a sufficient basis for demonstrating the margins of safety required for steel structures and piping in the ASME Eoiler and Pressure Vessel Code and for concrete structures in the American Concrete Institute Code. Revision 1 to the PUAAG was presented to the staff in a meeting on June 29, 1979. We will require that this revision be formally submitted to complete the documentation required for this program. 1323 095

.... 4. REFERENCES (Listed by Report f: umber) NEDE-13426P " Mark III Confinnatory Test Program One-Third Scale Pool Swell Impact Tests Test Series 5805," General Flectric Proprietary Report, August 1975. NEDO 21471 " Analytical Model for Estimathg Drag Forces on Rigid Submerged Structures due to LOCA and Safety Relief Valve Ramshead Air Discharges," General Electric Topical Report, Sep.tember 1977. NEDE-21472 " Analytical Model for Liquid Jet Properties for Predicting Forces on Rigid Submerged Structures," General Electric Proprietary Report, September 1977. NEDE-21864-P " Mark I Containment Program Final Report Monti':ello T-Quencher Test, Task Number 5.1.2," General Electric Proprietary Report, July 1978. NEDE-21878-P " Mark I Containment Program Analytical Model for Computing Air Bubble and Boundary Pressures Resulting from an SRV Discht..ge Through a T-Quencher Device, Task Number 7.1.1.2," General Electric Proprietary Report, January 1979. NEDO 21888 " Mark I Containment Program Load Definition Report," Revision 0, General Electric Topical Report, December 1978. NEDE-21944-P " Mark I Containment Program Quarter Scale Plant Unique Tests, Task Number 5.5.3, Series 2," Volumes 1 - 4, General Electric Proprietary Report, April 1979. NEDE-21983-P " Mark I Containmedt Program Submerged Structures riadal Main Vent Air Discharges Evaluation Report, Task Number 5.14.1," General Electric Proprietary Report, March 1979. NEDE-23545-P " Mark I Containment Program 1/4 Scale Pressure Suppression Pool Swell Test Program: LDR Load Tests - Generic Sensitivity, Task Number 5.5.3, Series 1," General Electric Proprietary Report, December 1978. NEDE-23749-1-P " Mark I Containment Program Comparison of Analytical Model Tcr Computing S/RVDL Transient Pressures and Forces to Monticello Data," General Electric Proprietary Report Addendum, February 1979. NEDE-23817-P " Mark I Containment Program 1/4 Scale Test Report Loads on Submerged Structures due to LOCA Air Bubbles and Water Jets, Task Number 5.14," General Electric Proprietary Report, September 1978. 1323 096

..~. NEDF-24537-P " Mark I Containment Long Term Program - Development of Downcomer Lateral Loads from Full Scale Test Facility Data - Task Number 7.3.2," General Electric Proprietary Report, May 1979. NEDE-24539-P " Mark I Containment Program Full Scale Test Progr"m Final Report, Task Number 5.11," General Electric ' Proprietary Report, April 1979. NED0 24583 " Mark I Containment Program Structural Acceptance Critu 1a Plant Unique Analysis Applications Guide, Task Number 3.1.3," General Electric Topical Report, December 1978. NEDO 24612 " Mark I Con +.ainment Program Vent Header Deflector Load Definition. Task Number 7.3.3," General Electric Topical Report, April 1979. NEDE-24645-P " Mark I Containment Program Analysis of Full Scale Test Facility for Condensation Oscillation Loading," General Electric Proprietary Report, May 1979. NED0 25070 " Analytical Model for Estimating Drag Forces on Rigid Submerged Structures Caused by Condensation Oscillation and Chugging Mark I Containments," General Electric Topical Report, April 1979. NEDE-25090-P " Analytical Model for T-Quencher Water Jet Loads on Submerged Structures, Task Number 5.14.2," General Electric Proprietary Report, May 1979. 1323 097}}

Retrieved from "https://kanterella.com/w/index.php?title=ML19210B994&oldid=4913456"