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GENERAL DYNAMICS

ASTRONAUTICS

A2136-1 (REV. 6-61)

https://ntrs.nasa.gov/search.jsp?R=19660020218 2020-08-04T14:53:35+00:00Z

55D 859-5 4/25/62

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C O N V A I R A S T R O N A U T I C S I

CONVAIR DIVISION OF GENERAL DYNAMICS CORPORATION

I I ZERO-G REPORT

SETTLING OUTFLOW TEST

PREPARED BY T. u'. O'Hanlon

C. K . Perkins

APPROVED BY G. B . Wood, T e s t Lab Group Engineer

R. 5. Campbell

Te B t Labora t or i e8

APPROVLD BY

( A c t i n a ) Assistant C h i e f Engineer

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FORM NO. A-7-1 1

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Prior t o Centaur engine restart t h e a e t t l i n g r o c k e t s w i l l cause eloshlng or tu rbulence of t h e f u e l which ray e f f e c t t he c h i l l down outflow. Slosh tests were conducted i n a modified 3/20tb- s c a l e Centaur f u e l tank t o otudg t b i 8 e f f e c t . A f ixed t i m e (measured from t h e start of w t t l i n 6 ) of between 1,4 and 2.2 second8 m a 8 required before c lea r f l o w (i.e., no en t r a ined gas bubble.) w u obtained, The t i m e a t which f l e w s t a r t e d did net i n f luence the clear up time,

TABLE OF CON'I'RI'X'S

P 8 r r g r r p h

1.0

200

3 e O

3.1

3.2

303

4 a O

4.1

- #*2

TAB- - I

11

FIGURES 1

2

3

4 I

5

T i t l e - INTRODUCTION AND OBJECTIVE

TBCST APPARATUS

TEST PRoCEwRt

Prt-Ttmt C8librmtioam

O u t f l o w T e s t 8 - No Set t l ing

Slomh Outflow Teat

RESLZTS AND DIsCUSSION

O u t f l o w Test - No Settl ing

The Sloeh Outflow fcots

OUTFLOW TEST - NO SETTLING

SLCSH OUTFLOW TESTS

TEST APPARATUS

SUSll TANX

OufLETELBOw

FLOW RATE vm DRIVING PRESSURE

SWSH 0uTFLX)U TEST RESULTS

1

2

3

3

3

3

6

7

0

9

10

11

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1 .O INTRODUCTION AND OBJIETIVE:

The Centaur liquid-hydrogen f u e l will, durimg t h e coast p h u c , be d i s t r i b u t e d around in its tank. When t h e s e t t l i n g r o c k e t s f i r e , t h e forward pa r t *r the l i q u i d rill w v e a f t , causing t u rbu lence mad s l o s h i n g when It reaches t h e in t e rmed ia t e bulkhead o r t h e LH i n t h a t vicini t j . . The olo8hing u;l rpp rec i ab fy a f f e c t t he fue l - tank out f low during engine c h i l l down. The teets described in t h i a r e p o r t were i n s t i t u t e d t o determine how much and i n what manner t h e 6 losh ing a f f e c t 6 t h e outflow.

A ocale model of t h e Centaur f u e l tank ram used t o conduct t h e t e e t ~ ~ The t o p of the tank ma8 modified t o a l l o r a p o r t i o n of t h e fuel t o f a l l toward the a f t bulkhead under a one-g rccel- e r a t i o n e The r e e u l t s may be conver ted by Froude Yutrrber e c a l i n p t c Frer!ict full size Centaur olosb- ing phenomena in PGY f i n i t e a c c e l e r a t i o n f i e l d .

S t o d d a r d solvent r a s used t o d i s u l a t e liquid hydropcn because it r e t s t h e tank w a l l s . Test. were conducted w i t h no 6106hlng (i.e., no l i q u i d s e t t l i n g ) t o e s t a b l i s h a reference f o r the 8looh effect.,

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2.0 TtST APPARATUS:

The t e R t apparatus, Figwe 1, ceasisted of a modified 3/23-6crlc model of the Centaur fw.1 tank. P a r t of the "fuel" ra6 held in the upper part of the tarh by the dump valve which lam apring lorded and ranually actuated. See Figure 2. A fue l flow valve was placed below the o u t l e t elbow. 6.. Figure 3. Micro-eritchea, located on t h e fu8l flor valve and om the dump valve actuator, indicated the va lve opening6 by l ight . placed above the mutlet elbow. A motion picture camera waa umed t o WEiWr the l i q u i d s u t f l o r m d t o observe -8 lightr, TB. flow rate was controlled by variag the tank pl'e88'tllY. (Maximar opcreting pressure was 15 pig).

Total tank volume wae about 4*5 It3,

2

3 0 1 We-Test Calibrations:

The volume flow rate as a function of dririw presaure (i.e.? tank pressure plus l iquid herd) w a s determined w i t h a s t o p watch and a graduated container (c.f. Figure I). Motion picture. we- uetd to determine the tire required for the lip uid to fall to.tht intermediate brrlkherd. The liquid and the release-time light were viewed by the camera. By counting the film frames between release and liquid contact with the 81t bulkhead area, and knowing the film aped, the time for tL8 liquid to fall was determined. The average tiw for the liquid to reach the bulkherd are8 w u .32 oecond8 e

3,5 Outflow T e s t s - No Settling: Teste were f i rc t conducted with a .till pool

of liquid to estobilsh a comparison for the tffect8 of sloshing and bubble entrainment on the out flow. The time at which terrinal p u l l through started ra8 mea6ured.for various flow rate6 and liquid volumes (amount of liquid initially in the tank).

S l o s h O u t f l o w Test: - 3.3

- - To determine the effect o? ecttling, the folloring’information was recorded en mot&oa picture film:

’

1) The time of liquid releanee 2) The tire of flow valve opening. 3) The time of flow valve elo8ing. 4) The condition of flow (i.e., pull

throuKh V E ~ clear flew), 5) The % vapor present when the flow

valve wae cloaed.

5

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1.1

RESULTS AND DISCUSS IONt

Outflow Te6t - No S e t t l f n j :

Tht d e t a i l e d r e s u l t s of out f lew Irom a atUa pool are given i n Table 1. The "Voltma Remmfrir l a t S t u t of Pu l l Through" i8 t h e f i l l volttmm 10- the product of t h e flow rate m d t h e t h o bofot. t e rmina l p u l l through. The "Liquid Beight* ab- t h e peripher.1 j o i n t 1.8 c a l c u l a t e d If- t h m rohm0 remaining and 8 knowledge of t h e bulkhead 8hrp.0 The t o p of t h e o u t l e t elbow was about 3 hchoa above t h e p e r i p h e r a l j o i n t (cf Figure 3). Home the "Pul l Down Dirtanct" io the "Liquid &eight" minur three rncher. The outflow v e l o c i t y wam always high enough t h a t any ga8 p u l l e d i n t o tho elbow i n l e t was immediately c a r r i e d t h r o u a tho smaller elbow o u t l e t . Hence the top of the olbmw (rather than t h e o u t l e t tube i t o e l f ) wao taken u t h e r e f e r e n c e poin t f o r t h e p u l l down diatance. This diotancr was between one and three inchorno

402 The Slosh Outflow T t s t 8 :

4.201 S e t t l i n g durinp the outflow t e a t s cau8ed vapor pull-through a6 the f low valve r a s opened. The quantity of vapor ent ra ined decreased grad- u a l l y as t h e flow continued. There was6 no clean c u t o f f t o t h e p u l l through, bu t t h e t i m e at which the gas q u a n t i t y r a e reduced t o below a could be rough17 e e t i i n t e d . Thie i n i t i a l pul l - through w u still present f o r v a l v t opening delayn ( t i m e oS l i q u i d contact t o t i m e o f flow o t u t ) near ep. second. See Tabel I1 and Figure bo Rote that between 1.4 and 2.2 second8 a f t e r Cbe .tart mf flow the i n i t i a l pull-through c1eu.d up (ex- c e p t i n g t h e odd- 27 - 0 96 Ca6e). The t i w #or start of clear flow doer not seem t o bo I fame- t i o n of t h e t i m e t h a t the flow va lve =a8 op.red or of t h e flow rate or o f t h e "fuel" wolumo. There 8eem. to be r i a p l y a f i r e d tiw repirod f o r t h e s e t t l i n g d i e tu rbanc t t o die dorn .rough t h a t no gaa is pu l l ed through.

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4.0 RESULTS LVD DISCUSSION: (Coat imud)

402e2 Note t h a t i n th ree of t ho SI4 / SW rel\aw teat. the flow valve ra8 l e f t open uti& after t h e te rmina l pull-through a t a r k d . T e d 8 w i t h no s e t t l i n g 6hored t h a t f o r t h i a volume u1 flew rate t h a t t e rmina l p u l l occurred about 2.3 8ecend8 a f t e r opening the flow Valv8. In theme t h r t o catsea t h e flow times wero 2.16, 2*02, u d 2.00 8econdm or essentially t h e 8- a8 t ho 60-

s e t t l i n g testa. a mi1811 percentage of gas i 8 en t ra ined during t h e i n i t i a l pull-through, but the f r a c t i o n of gaa rppearcd t o bo l a r p in t h e moviea. Io meaeure of t h i 8 f r a c t i o n w a ~ u d o during the test8 nor Could a rer8OMblO e 8 t i r u t o b. -de from t h e m V f . 8 .

T h i 8 r e s u l t i nd ica t e8 thrt only

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REPORT FSFin 859 _. 5

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TEST APPAKATUS

Figure 1

FORM NO. A-702-1

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CONVAIR ASTRONAUTICS B -55 D 859-5

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GENERAL DYNAMICS I ASTRONAUTICS