8

N A S A C R - 72285

N B S R E P O R T 9293

I N T E R I M R E P O R T

CAVITATION INCEPTION IN LIQUID NITROGEN

AND LIQUID HYDROGEN FLOWING IN A VENTURI

by D. K . Edmonds, J. H o f d , and D. R. M i l l h i s e t

Prepar‘ed undef Contract N o C-35560-A

f 0 f

N A T I O N A L A E R O N A U T I C S A N D S P A C E A D M I N I S T R A T I O N

P r e p a r e d by

U.S. D e p a r t m e n t o f Commerce

N A T I O N A L BUREAU OF STANDARDS

Bou l d e r , Labor a t or ies

Boulder, Colorado

https://ntrs.nasa.gov/search.jsp?R=19680004607 2020-04-03T03:12:30+00:00Z

NOTICE *

This report was prepared as an account of Government sponsored work. and Space Administration (NASA), nor any person acting on behalf of NASA:

Neither the United States, nor the National Aeronautics

e

A. ) Makes any warranty o r representation, expressed or im- plied, with respect to the accuracy, completeness, o r use- fulness of the information contained in this report , o r that the use of any information, apparatus, method, o r process disclosed in this repor t may not infringe privately owned rights; o r

B. ) Assumes any liabilities with respect to the use of, o r f o r damages resulting from the use of any information, apparatus, method o r process disclosed in this report .

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Requests fo r copies of this repor t should be r e fe r r ed to

National Aeronautics and Space Administration Office of Scientific and Technical Information Attention: AFSS-A Washington, D. C. 20546

I N T E R I M REPORT

N A S A C R - 72285 N B S R E P O R T 9293

C A V I T A T I O N INCEPTION IN LIQUID NITROGEN

AND LIQUID HYDROGEN FLOWING IN A VENTURI

by D. K . Edmonds, J. H o f d , and D.R,Mil lhiser

p r e p a r e d f o r

N A T I O N A L A E R O N A U T I C S A N D S P A C E A D M I N I S T R A T I O N

C O N T R A C T No. C - 3 5 5 6 0 - A

August, 1967

T e c h n i c a l Management

N A S A Lewis Research C e n t e r

C l e v e l a n d Ohio

L i q u i d Rocket Techno!ogy Branch

W e r n e r R . B f i t sch

N B S - U. S. D e p o r t m e n t o f C o m m e r c e , Boulder, Co lorado

FORE WORD

This report was prepared by the National Bureau of Stan-

dards, Institute for Materials Research, United States Department

of Commerce under Contract C-35560-A. The contract was ad-

ministered by the Lewis Research Center of the National Aero-

nautics and Space Administration, Cleveland, Ohio. The work

summarized in this repor t was performed during the period 15

July 1964 to 15 July 1967.

Contract was Mr. W e r n e r R. Britsch. Mess ' rs . R.S. Ruggeri,

T. F. Gelder, and R. D. Moore of the Fluid Systems Components

Division at NASA Lewis Research Center---under the direction

of M. J. Hartmann---served a s r e sea rch consultants a d tech-

nical advisers during the course of this program.

The NASA project manager fo r the

ii

TABLE OF CONTENTS Page

FOREWORD

ILLUSTRATIONS . TABLES . ABSTRACT.

1.

2.

3.

4.

5.

6.

7.

8.

9.

10.

11.

Introduction . Apparatus . 2. 1 T e s t Section . 2. 2 Instrumentation . 2.3 Visual and Photographic Aids

T e s t Procedure . Data Analysis and Discussion . 4. 1 Data Analysis

4. 2 Discussion of Data . Summary . Acknowledgements . Nomenclature

References . Appendix A-- -Acoustic Detector

Appendix B---Method Used to Compensate the Experimental

Inception Data fo r Temperature Deviation about the

Nominal Isotherms

Appendix C---Distribution Lis t for Interim Report NASA

CR-72285 .

i i

iv

v

v i

1

2

2

8

10

10

11

23

24

25

26

27

30

A-1

. B-1

. c - 1

... 111

.

Figure

2.1

2 . 2

2 .3

2.4

2. 5

4.1

4.2

4.3

4.4

4.5

4. 6

4.7

ILLUSTRATIONS

Fage

Schematic of Cavitation Flow Apparatus

Photograph of Plast ic Venturi Test Section Installed in

System.

Fi lm Event . Sketch of Plast ic Venturi Section Showing Dimensions and

Location of P r e s s u r e and Temperature Instrumentation

Quarter-Round Contour of Convergent Region of P las t ic

Test Section . P r e s s u r e Distribution Through Test Section for Non-

Cavitating Flow . Cavitation Parameter for Liquid Hydrogen as Function of

Test Section Inlet Velocity

Effect of Test Section Inlet Velocity and Liquid Temperature

on Required Inlet Head for Cavitation Inception in Liquid

Hydrogen . Cavitation Parameter for Liquid Hydrogen as a Function

of Tes t Section Inlet Velocity and Liquid Temperature

Effect of Test Section Inlet Velocity and Liquid Tempera-

ture on Required Inlet Head for Cavitation Inception in

Liquid Nitrogen . Cavitation Parameter for Liquid Nitrogen as a Function of

Test Section Inlet Velocity and Liquid Temperature

Photograph Showing Typical Cavitation Inception in

Liquid Hydrogen

Photograph Showing Typical Cavitation Inception in

Liquid Nitrogen .

Note Counter--Used to Correlate Flow Data with

.

.

.

3

4

5

6

7

17

18

19

20

2 1

22

2 2

iv

t

ILLUSTRATIONS (continued)

Figure Page

9. 1 Acoustic Transducer for Detection of Cavitation

Inception . A-2 . with Acoustic Cavitation Detection Device A -2

9. 2 Block Diagram of Signal Conditioning Instruments Used

. 10. 1 Illustration of Method Used to Construct Nominal Isotherms

from Experimental Data . B -2

TABLES

Table Page

4. 1 Cavitation Inception Data for Liquid Hydrogen 1 2

4. 2 Cavitation Inception Data for Liquid Nitrogen 13

4.3 Experimental Data Points Which Have Been Temperature

Compensated by Means of Equation [ 10-31 for Hydrogen

and Equation [ 10-41 for Nitrogen . 14

Calculated Data Used to Construct Nominal Isotherms for

Liquid Hydrogen Inception . 15

Calculated Data Used to Construct Nominal Isotherms for

Liquid Nitrogen Inception . 16

4.4

4. 5

V

.

h te r i rn Report

CAVITATION INCEPTION I N LIQUID NITROGEN

AND LIQUID HYDROGEN FLOWING IN A VENTURI

by D. K. Edmonds, J. Hord, and D. R . Millhiser

ABSTRACT

Cavitation character is t ics of liquid hydrogen and liquid ni-

trogen in a transparent plastic venturi have been determined.

experimental data a r e presented in tabular and graphical form.

Conventional cavitation -parameter and he ad -velocity curves a r e

given over the range of experimental temperatures ( 3 6 . 5 to 41"R

fo r hydrogen and 140 to 170°R for nitrogen) and inlet velocities

(70 to 185 ft/sec for hydrogen and 2 0 to 7 0 ft /sec for nitrogen).

Minimum local wall p r e s s u r e was calculated to be l e s s than bulk

s t ream vapor p re s su re by a s much a s 323 feet of hydrogen head

and 63 feet of nitrogen head.

The

v i

I 1. Introduction

Cavitation is usually defined as the formation, caused by a reduc-

tion in pressure , of a vapor phase within a flowing liquid o r at the inter-

face between a liquid and a solid.

vapor cavities alters flow patterns, cavitation may reduce the efficiency

of pumping machinery[ 11, and reduce the precision of flow measuring

devices.

damage[ 21 to fluid handling equipment.

Since the formation and collapse of

Collapse of these vapor cavities can also cause ser ious erosion

NASA has undertaken a program[ 11 to determine various cavitation

character is t ics of different fluids in an effort to develop design c r i te r ia

to aid in the prediction of cavitation in pumps. The experimental study

described herein was conducted in support of this program.

hydrogen and liquid nitrogen were chosen as tes t fluids fo r this study for

the following reasons: (1) the ultimate goal of this program is to acquire

sufficient knowledge to permi t intelligent design of pumps for near-boiling

liquids and ( 2 ) predictive analyses[ 11 indicated that the physical proper-

t ies of hydrogen and nitrogen make them particularly desirable tes t fluids.

Liquid

The objective of this study was to determine the flow conditions

required to induce cavitation, in liquid hydrogen and liquid nitrogen, on

the walls of a transparent plastic venturi. The shape of the venturi was

chosen to duplicate the test section used by NASA[ 3-61.

ducted with test section inlet velocities of 7 0 to 185 ft/sec in hydrogen

and 20 to 7 0 ft/sec in nitrogen.

36.5 to 41"R with hydrogen and from 140 to 170"R with nitrogen in order

to determine the effects of temperature upon cavitation inception.

data reported here are intended to supplement that given in several NASA

technical notes[ 3-61 for a geometrically s imiiar , but i. 414 tiilies as large,

test section.

nitrogen at about 140"R indicates no scale effects.

Tests were con-

Inlet temperatures were varied from

The

Comparison of NASA and N B S inception d a t a for liquid

Both incipient and

1

desinent cavitation data were acquired with no noticeable hysteresis ; i. e. , the flow conditions corresponding to vapor inception a r e identical whether

the data point is approached from non-cavitating o r fully-developed cavi-

tating flow. In this report, incipience re fers to the appearance of visible

vapor cavities, whether they a r e due to incipient o r desinent cavitation.

2. Apparatus

The facility used f o r this study consisted of a blow-down system

with the tes t section located between the supply and receiver dewars;

s e e figure 2. 1.

transfer to the test fluid.

ply and receiver dewar pressures .

the supply and receiver vessels are indicated on figure 2.1.

dewar pressure control valving limited the venturi inlet velocity, V , to

about 185 f t /sec in hydrogen, while the supply dewar p re s su re rating

limited the inlet velocity to about 7 0 ft/sec in nitrogen.

Dewars and piping were vacuum shielded to minimize heat

Flow control was attained by regulating the sup-

P r e s s u r e and volume capacities of

The receiver

0

Valves located on each side of the t e s t section permi t flow stoppage

A plenum in the event of venturi failure while testing with liquid hydrogen.

chamber was installed upstream of the tes t section to a s su re uniform non-

cavitating flow a t the test section inlet.

with a 5 Kw heater which was used to heat the tes t fluid.

The supply dewar was equipped

2.1 Tes t Section

A photograph of the teat section as viewed through one of the win-

dowe in the vacuum jacket is shown in f igure 2.2. The t ransparent plaetic

venturi waa flanged into the apparatua using high compression elastomeric

"0" ringrr. Refer-

ring to figure 2.3, etatic p re r su re tap No, 1 was the only instrument port

drilled and used in the liquid hydrogen inception tests. Some liquid nitro-

gen data were acquired with all of the prerrlrure and temperature sensing

Test section details a r e given in f igures 2. 3 and 2.4.

2

W 0

U

d

Q) A U

67

.rl 42

E

3

N

N

a, k =1 M

c.l .d

4

5

0 0 -

/

c ul

8 Q .u E / v)2 c

ou-

0

/ I-

- - " I 2 I-

c

p

I 0 I CD ! 9

0 Q 9

0 0

9 cu

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w l-

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J

X

a

a -

a a -

w 0

6

M

k 0 w

0" \ X

In N

Q) k 5 M

.A

!k

7

ports instrumented, figure 2. 2. Since incipient cavitation involves very

smal l cavities at o r near the minimum pres su re point---see figures 2 . 4

and 2 . 5---the presence or absence of the additional sensing ports has no

effect on the data reported.

a r e shown on figure 2 . 4 .

using the plastic venturi as a mold fo r a dental plaster plug.

then removed and measured.

a c r o s s the quarter-round contour[ 3 , 7 ] is shown in figure 2. 5.

su re profile has been confirmed using severa l t es t fluids[ 3-51 and data 5 from this study, and applies when (Re) 5: 4 x 10 .

The design a d as-built venturi contours

The tes t section dimensions were checked by

The plug was

P r e s s u r e distribution for non-cavitating flow

This p re s -

D 0

2 . 2 Instrumentation

Location of the essential instrumentation is shown on figures 2.1

and 2. 3.

Liquid level in the supply dewar was sensed with a ten-point carbon

Tes t fluid temperature in the supply dewar was determined

Fluid tempera-

res i s tor rake.

by two platinum resistance thermometers , see figure 2. 1.

tu res a t the flowmeter and tes t section inlet were also measured with plati-

num resistance thermometers.

brated to provide temperature readings accurate within *O. 04"R.

thermometers were powered with a cu r ren t source which did not vary m o r e

than 0. 01 percent.

on a 5 digit electronic voltmeter data acquisition system.

accuracy of the temperature measurement is estimated to be within fO. 09"R.

These platinum thermometers were C a l i -

The

Voltage drop a c r o s s the thermometers was recorded

The overal l

System gage and differential p r e s s u r e measurements were obtained

with p re s su re t ransducers mounted in a tempera ture stabil ized box nea r

the tes t section.

possible to provide maximum resolution.

calibrated via laboratory tes t gages at frequent intervals during the tes t

Differential p re s su re measurements were used where

The p r e s s u r e t ransducers were

8

I

ser ies .

and their output was recorded on a continuous t race oscillograph with

Repeatability of the transducers was better than *O. 25 percent l

approximately one percent resolution.

su re measurement, including calibration and read-out e r r o r s is estimated

to be within *2. 0 percent.

ous tests.

The overall accuracy of the p res -

Bourdon gages were used to monitor the var i -

I Volumetric and mass flow rates were determined via a Herschel I

venturi flowmeter designed to ASME Standards[ $1. of this meter was verified in the s a m e l ~ l ~ A ~ - , e r as the t es t venturi.

error analysis of this flow device and associated p res su re and tempera-

tu re measurements indicates an accuracy in mass flow of about one per -

cent.

The internal contour

An

I I

An electronic pulsing circui t provided a common time base for , correlating data between oscillograph, digital voltmeter, and movie f i l m .

The data were reduced by first viewing f i l m of the test event.

actuated counter, installed adjacent to the tes t section was energized by

the electronic pulser and appears on the film, figure 2. 2. Thus, the

data are reduced at the desired instant of time by simply matching the

nulmber of voltage pulses which have elapsed.

A solenoid-

An acoustic cavitation detection device was developed and success-

fully used to determine cavitation inception.

m o r e sensitive than the human eye, i. e., cavitation inception could be

detected with the acoustic transducer before it was visible to the unaided

eye. Visible incipience is frequently used as the cri terion f o r cavitation

inception and is normally reported in the l i terature since the sensitivity

[ 9-11] of various acoustic detectors can vary appreciably. Although the

data presented he re are based upon visible incipience, fuii description of

the acoustic transducer is given for reference in Appendix A of this paper.

This device was found to be

9

2. 3 Visual and Photogrdphic Aids

U s e of a plastic tes t section, liquid hydrogen, and relatively high

pressures precluded direct visual observation; therefore, closed-circuit

television was used to observe the tests.

Movies of cavitation tests were taken at approximately 2 0 frames

p e r second on 16 mm film.

with a 75 mm lens and synchronized with a high intensity stroboscope,

providing a 3 CL-sec exposure. The stroboscope was situated direct ly

opposite the camera lens and illuminated the tes t section through a plastic

diffuser mask; this technique provided a shadow-graph or back-lighting

effect and excellent contrast between vapor and liquid phases in the tes t

section.

The variable speed camera was equipped

3. Test Procedure

The following procedure r e fe r s to figure 2.1. The supply dewar

was filled with tes t liquid and then some of the liquid was extracted through

valves A and B t o cool the tes t section and piping.

hours were required to cool the plastic tes t section without breakage.

Cooldown was monitored via a platinum resis tance thermometer in the

plenum chamber.

dewar were t ransferred through the tes t section into the receiver dewar,

and then back into the supply dewar again.

ent i re flow system in preparation f o r a test.

dewar was heated to the desired temperature .

connecting piping were kept full of liquid a t low p r e s s u r e during prepara tory

and calibration periods between tes ts , the plast ic venturi was generally

colder than the test liquid.

ized to appropriate levels and flow s ta r ted by opening valve C.

of non-cavitating flow, inception was induced by lowering the rece iver dewar

Approximately two

Upon completion of cooldown, the contents of the supply

This operation cooled the

Next, the liquid in the supply

Because the tes t section and

Supply and rece iver dewars were then p r e s s u r -

In the c a s e

1 0

pres su re and thus increasing the flow velocity until vapor appeared.

obtain desinent cavitation from fully developed cavitating flow, the receiver

dewar pressure was increased until the vapor cavity was barely visible.

Receiver dewar p re s su re was remotely controlled by means of a pneumatic

transmitter, differential controller, and vent valve arrangement, figure

2.1.

throttle valve D for some of the liquid nitrogen tests.

by closing valve C.

t ransferred back into the supply dewar for another test. As previously

mentioned, the entire tes t event was recorded on movie f i L x xhich was

subsequently used to determine incipient and desinent cavitation conditions.

To

It was necessary to increase tes t section back-pressure by means of

Flow was terminated

The supply dewar was then vented and the test liquid

I

I

1 4. Data Analysis and Discussion

I A l l of the useable experimental inception data are given in tables

4. 1 and 4. 2. compensated and presented in table 4.3.

data is described in Appendix B of this paper.

These same data points were mathematically temperature- I

Derivation of these compensated I

for liquid hydrogen Kiv' The conventional cavitation parameter,

is shown on figure 4. 1.

of experimental data and this prompted the presentation of calculated data

given on figures 4. 2 and 4. 3. The calculated data used in the preparation

of f igures 4.2 and 4.3 are derived as explained in Appendix B and a r e pre-

sented in table 4.4.

manner and plotted on figures 4.4 a n d 4. 5 from the calculated data of

table 4. 5 .

fluids on figures 4.6 and 4. 7.

Little temperature dependency is evident in thisplot

The liquid nitrogen data were handled in a s imilar

Photographs of cavitation inception are shown for both tes t

11

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03

0 d rl

co co 6 N

9 9

r- N

N 9

d IC.

00 00

In d 4

P- 0 d

Q-

P-

In r- N

Q. m 9' 4

03 0

P- dc

4

d co

r- QI N N

IC dc 9 N

6 W

m 9

r- 03

d 2

00 0 4

N Q'

I

In I-

N

03 N

9' rl

In r-

1 9'

9

m 6

W

co 9 N

6

6 N

4

In 0

r. 4

9 P-

d * 4

Q' 0 d

1 00

N 4

0 N

N

4 N

9 4

z 9 1

6

03 W

a rl rl 4

9 9

P- 4

1 9

m -4

N t-

d 2

0 rl 4

03 6

0 4 4

9 4

N

0

m d

rl

d 4

d

03 IC

9

d z

W r-4

6 4

9 P-

d m

co 0

4

rl 9

Q 4 rl rl

4 co 6

N 0

N

N rl

9' 4

t- N

9 9

6

1 4

co 03 N 4

e m e 4

0 6

P- dc

rr) 9

dc d rl

N 4 4

13

cr)

i

I

I I

14

0 1 A *-

m N

VI N

o\ m 9 9 v) rl

IC t- IC P-

Q, 00 9 w d d

0 0 0 0 0 0 0 0 0 o o m IC m (2' 0 d N r? 4 Ui 3 * 8 3

15

i m 0 0 m

0 0 * * * -P 4 4

3 la l o l n m o o o m m o m o

0 In

0 Id 2 m m

N

0

d

c- co c- oo d

In

oo aj d

r oo r- m d

o o m m m o o m o m

16

17

80 100 I20 140 I60 I80

V, , f t / s e c

Figure 4 . 2 Effect of T e s t Section Inlet Velocity and Liquid Tempera tu re on Required Inlet Head for Cavitation Inception in Liquid Hydrogen

18

\ 7 \

\

-L----- \ \ \ \ \ 7

0. N

t ---t--

\ \

\ '. b .

400

350

300

'0 0 a

250 + 0

a a c

rc - 200 0 r

I 5 0

I O 0

50 0 20 40 60 80

V,, f t / s e c

Figure 4 . 4 Effect of Tes t Section Inlet Velocity and Liquid Tempera tu re on Required Inlet Head for Cavitation Inception in Liquid Nitrogen.

20

\ \ \ \

\ \

R

rf) u)

0 u)

ln In

0 ln

0 Q) u)

r o ' * = c.

0 >" e

In M

0 M

In N

0 0a

21

Figure 4. 6 Photograph Showing Typical Cavitation Inception in Liquid Hydrogen

F igure 4. 7 Photograph Showing Typical Cavitation Inception in Liquid Nitrogen

I 4. 1 Data Analysis

I I

I

Computed values of K. were plotted as a function of V for both 1v 0

hydrogen and nitrogen. However, inspection of the plots showed no

readily discernable temperature dependence of K. for uncompensated I 1v

experimental data (see figure 4. 1; nitrogen is s imi la r and is not shown).

The temperature dependence of K. is complicated by the fact that 1v

errors in the measured variable h

K. as follows:

a r e magnified in the calculation of 0

1v h - h

K. 1v = 2gc [ 2 v ] ;

0

[ 4 . l - l a ]

differentiating [ 4. 1- la ] at constant temperature and velocity there resul ts ,

dh . dK, = - 2gC 2 0

0 V 1v [ 4. 1-lb]

The fractional change in K.

[ 4 . l - l b l by [ 4.1-1a1,

due to a change dh is obtained by dividing 1v 0

0 d K. dh

1v - - . - - h - h .

o v K. 1v

The fractional change in h due to a change dh 0 0

is by definition

[ 4. 1-21

The ra t io of the fractional change in K

obtained by dividing [ 4. 1-21 by dho/ho,

to the fractional change in h is iv 0

23

0 h

dKiv/Kiv - - - a

h - h o v

dh /h 0 0

[ 4. 1-31

Therefore any scat ter which may occur in measuring h will be amplified 0 h

0 , which has values as large a s six f o r both hydrogen h - h

by the term o v

and nitrogen datt given in this report.

Plots were also made of h as a function of V using the experi-

mental data from this study. Both hydrogen and nitrogen data showed 0

distinct temperature dependence; however, there was sufficient experi-

mental variation about each desired nominal liquid temperature to cause

concern in constructing the individual isotherms.

o r nominal isotherm i s defined as that temperature which i s selected to

represent a specific group of dhta points with little temperature variation.

0 0

A nominal temperature

A technique was devised to evaluate the effect of temper i ture on

the datu and i s detailed in Appendix B of this report.

4. 2 Discussion of Data

It was pointed out earlier that no temperature dependence could be

determined from K vs V plots when the uncompensated experimental

data were used, figure 4.1. However, once the nominal h vs V isotherms

were established by mathematical temperature compensation, the K. v s

V nominal isotherms may be computed from the basic definition of K. . 0 1v

Data on figures 4. 2 and 4.4 represents the final "best-fit" of the experi-

mental data points, "transferred" by means of equations [ 10-31 and [ 10-41

to the nominal isotherms shown. This method of presenting the h v s V

ddta elmindites the scat ter due to experimentdl f ree-s t ream temperature

voia t ion .

trogen at 140'R; see figure 4.4.

t imes d s h r g e a s the pldstic venturi described herein, negligible s c d e

effects crre indicated.

iv 0

0 0

1v

0 0

Good agreement was obtained with NASA data[ 71 f o r liquid ni-

Since the NASA test section was l. 414

24

t Minimurn local w d l pressure wiis cdcula ted to be less than bulk

s t ream vapor p re s su re by as much as 323 feet of hydrogen head and 6 3

feet of nitrogen head. These data are obtained by subtracting h from h

in tables 4. 1 and 4. 2.

V

V

Figures 4.3 and 4. 5 a r e presented as a mat te r of interest , but it

i s to be noted that these K.

h vs V curves, and that e r r o r s in h are m p l i f i e d in K (as was shown

ear l ie r ) . Little variation in the shape of the h vs V curves i s required

to eliminate the inflection points in the corresponding K.

curves depend entirely on the shape of the 1v

0 0 0 iv

0 0

vs V curves. 1v 0

The K curves indicate the usual trends, i. e., K, increases with in- iv 1v

creasing velocities and decreasing temperatures.

isotherms for hydrogen intersecting at an inlet velocity of about 140 ft/sec.

While this intersection is theoretically tendble, i t could & i o be crttributed

to experimental data scatter.

perature dependence, and the data d s o suggests that K,

at inlet velocities grea te r than 140 ft/sec.

curves exhibit little temperature o r velocity dependence at the higher

v e loci tie s .

Figure 4.3 shows the

The data on figure 4. 1 indicate little tern-

may be invariant

Both hydrogen and nitrogen K. 1v

1v

5. Summary

Cavitation inception parameters have been experimentally measured

for liquid hydrogen and liquid nitrogen flowing in a c lear plastic venturi.

The experimental data points a r e given in table 4.1 fo r liquid hydrogen

and tcrble 4. 2 for liquid nitrogen.

Temperature compensated values of inlet head, h versus inlet 0

a r e presented on a background of mathematically tempera- vO*

velocity,

tu re compensated isotherms; liquid hydrogen data a r e shown on figure

4. 2 dnd liquid nitrogen dzta +?ear on f igure 4.4.

constructed f rom the liquid nitrogen data i s coincident with data furnished

The 140"R isotherm

25

by Ruggeri[ 71.

factor of 1.414:l; therefore, negligible scale effects a r e indicated.

mathematical technique used to temperature-compensate the experimental

data is outlined in Appendix B of this paper.

The venturi used in that experiment[ 43 was la rger by a

The , ,

I

Figure 4.1 shows experimental K. data points f o r liquid hydrogen; 1v these data have not been temperature Compensated and show no particular

temperature trends.

cavitation parameter , K

Temperature compensated values of the conventional

, are also shown on figure 4 .3 for liquid hydrogen

these curves have becn derived f rom

I I

iv and on figure 4. 5 for liquid nitrogen: l the smooth isotherms on the h vs V plots (figures 4. 2 and 4.4). The

data shows that K. increases with increasing velocities and decreases 0 0

I

1v with increasing temperatures. A t the higher velocities the K curves ~ iv indicate very little temperature o r velocity dependence.

to construct f igures 4. 2 to 4. 5 are given in tables 4. 3 to 4. 5.

The data used

The experiments showed that both liquid hydrogen and liquid

nitrogen can sustain relatively large magnitudes of thermodynamic meta-

stability; i. e . , minimum local wall p re s su re was calculated to be con-

siderably less than bulkstream vapor pressure.

stability for the various experiments is obtained by subtracting h from h

in tables 4. 1 and 4. 2.

The magnitude of meta- V

V

6. A cknowle dg em en ts

A considerable number of people have been associated with this

project at various t imes and their individual efforts are respectfully

acknowledged. Mess ' r s . Thomas T. Nagamoto, Dale R. Nielsen, Ray-

mond V. Smith, and W. Har ry P robe r t ass i s ted in the ear ly phases of

apparatus asscmbly and experimentation. Mr, Peter Pemberton partici-

pated in some design modifications and Ajit Rapial was ve ry helpful in the

reduction a n d analysis of data.

techniques used in this study are attributed to Thomas T. Theotokatos.

The photographic instrumentation and

26

0 A

C P

P E

7. Nomenclature

2 = test section inlet flow a r e a [ = 0. 008063 f t ]

= pres su re coefficient [ = (h - h )/(V 2 /2gc)]

= minimum pressure coefficient [ = (h V - h )/(Vo 2 /2gc)] x o 0

0

0 D

gC

= constants appearing in equation [ 10-11 which a r e

evaluated from best f i t curves through h v s V data

points

'n, (n=1,2---)

0 0

= test section inlet diameter

= conversion factor in Newton's law of motion, given in

engineering units as g = 32. 2(ft)(pounds mass) / ( sec 2 C

(pounds force)

tes t section inlet head corresponding to absolute inlet

pressure, f t

= 0

h

h oa1

V h

X h

= value of inlethead corresponding to a data point before

it is "transferred" to a new position, f t

value of inlet head corresponding to a data point af ter

i t has been "transferred" to a new position, f t

head corresponding to saturation o r vapor p re s su re

at test section inlet temperature, f t

= head corresponding to absolute pressure measured at

wall of plastic venturi at distance x downstream of the

minimum pressure point, f t

=

=

27

t

h'

Kiv

m

0 P

V P

0

0 T

O8 T

T ' 0

T " 0

head corresponding to minimum absolute pressure on

quarter round of plastic venturi contour, ft, computed

f rom expression for C

incipient cavitation parameter [ = ( h - h )/(V '/2gC)]

m a s s flow rate, e. g . , (pounds mass) / sec

tes t section absolute inlet p ressure

saturation o r vapor pressure a t tes t section inlet tem-

pe rature

Reynolds number based on tes t section inlet diameter

temperature in degrees Rankine, of bulk fluid entering

the tes t section

the inlet temperature f rom which a data point is to be

" tr an sf e r r ed"

the inlet temperature to which a data point is being

"transferred"

the nominal temperature chosen for construction of a

"base" isotherm due to the availability of sufficient

h vs V data a t o r near that temperature

a nominal isotherm on a h vs V plot

a nominal isotherm, different f rom T I , on a h va

v

P

o v 0

0 0

0 0

0 0

v plot 0

28

0 V

X

= velocity of tes t fluid at inlet to venturi t es t section

distance measured from minimum pressure point on

quarter-round contour along axis of plastic venturi

=

29

.

8. References

1.

2.

3.

4.

5.

6.

7.

8.

9.

Pinkel, I. I., M. J. Hartmann, C. H. Hauser, M. J. Miller, R. S.

Ruggeri, and R. F. Soltis, Pump Technology, Chap. VI, pp. 81-101,

taken f rom Conference on Selected Technology for the Petroleum

Industry, NASA SP-5053 (1966).

Erosion by Cavitation o r Impingement, STP 408, 288 pages (1967),

Available f rom ASTM, 1916 Race Street, Phila., Pa., 19103.

Ruggeri, R. S. and T. F. Gelder, Effects of A i r Content and W a t e r

Purity on Liquid Tension at Incipient Cavitation in Venturi Flow,

NASA TN D-1459, (1963).

Ruggeri, R. S. and T. F. Gelder, Cavitation and Effective Liquid

Tension of Nitrogen in a Tunnel Venturi, NASA TD -2088, (1964).

Gelder, T. F., R. D. Moore, and R. S. Ruggeri, Incipient Cavi-

tation of Freon-114 in a Tunnel Venturi, NASA TN D-2662, (1965).

Ruggeri, R. S. , R. D. Moore, and T. F. Gelder, Incipient Cavi-

tation of Ethylene Glycol in a Tunnel Venturi, NASA TN D-2772, (1965).

Ruggeri, R . S., Pr ivate communication.

Flow Measurement, Chap. 4, Part 5 - Measurement of quantity of

materials, p. 17 , PTC-19. 5;4-1959, the American Society of

Mechanical Engineers, 29 West 39th St. , New York 18, N. Y.

Kittredge, C. P. , Detection and Location of Cavitation, Plasma

Physics Lab, Princeton Univ., Princeton, N. J., Report MATT-142

(Aug. 1962). Available f rom 0. T. S., U. S. Dept. of Commerce,

Washington 25, D. C.

3 0

10. Lehman, A. F. and J. 0. Young, Experimental Investigations of

Incipient and Desinent Cavitation, ASME Paper No. 63-AHGT-20

(Mar. 1963).

11. H011, J. W . , Discussions of Symposium on Cavitation Research

Facilities and Techniques, Presented at Fluids Engr'g. Div. Confer.

Phi la . , P a . , May 18-20, 1964, Available f rom ASME, United

Engineering Center, 345 E a s t 47th S t . , New York 17, N. Y.

31

9. Appendix A---Acoustic Detector

A detailed drawing of the acoustic transducer is given on figure

9. 1 and a schematic of the instrument hook-up is given on figure 9. 2.

The transducer consists of a Barium-Titanate piezoelectric crystal

sandwiched between the body of the transducer and a machine screw,

figure 9. 1.

c rys ta l could be varied by means of the machine screw.

sensitivity of the crystal to mechanical vibration could be adjusted some-

what. Electr ical leads were attached to the adjustment sc rew and to the

body of the transducer. Coaxial electrical wire was used to connect the

transducer to a cathode-follower-arnplifier, s e e figure 9.2, The signal

was then fi l tered through a variable band-pass filter and displayed on an

oscilloscope.

of 3 to 200 k-Hz for most tests.

The mechanical coupling or initial compression level in the

Thus, the

The band-pass filter was s e t to adinit signal frequencies

The acoustic transducer was screw-mounted in the downstream

flange of the plastic venturi via pipe threads.

and noise appeared to be of low frequency and was easily eliminated with

the band-pass filter.

Most of the system vibration

Cavitation was readily discernable on the oscilloscope and was

characterized by large-amplitude, high-frequency signals.

NYLON PLU

"BAKELITE" TUBE

BRASS DISC

8-32 SCREW PIEZOELECTRIC

CRYSl A L

SCALE : TWICE ACTUAL

5/8"ROUND BRASS

L I a - CATH 0 DE-

FOLLOWER AMP L I F I ER e

Figure 9. 1 Acoustic Transducer f o r Detection of Cavitation Inception.

* BAND -PASS

FILTER

* 0

PIEZOELECTRIC CRYSTAL7

I OSCl LLOSCOPE

II Figure 9. 2 Block Diagram of Signal Conditioning Instruments U s e d with

Acoustic Cavitation Detection Device.

A - 2

10. Appendix B---Method Used to

Compensate the Experimental Inception Data for

Temperature Deviation about the Nominal Isotherms

(1) It was assumed that a change in inlet temperature, dT will 0

produce a change in inlet head, dho, along a constant velocity path, which

will be a function of the velocity and temperature only; it is also assumed

that this function may be approximated by a few t e r m s of a polynomial.

Justification of these assumptions i s evidenced by the good resul ts which

were obtained for both hydrogen and nitrogen (see figures 4.2 and 4.4)

by using the following equation:

dh = [ CIT t CZTo t C3V02 t C4Vo t Cs] dTo. [ lo-11 0 0

Holding V constant and integrating from h to 11 and from T to

T 0 0, 0 9 2 0 , l

there results: 0 . 2

[ 10-21

where the subscript " 1 " refers to the position of a data point before i t is

t ransfer red to a new position identified by the subscript " 2 " .

F o r each of the following steps (two through seven) there is a

corresponding graphical illustration on Figure 10. 1.

( 2 ) h vs Vo experimental data were plotted, a separate graph 0

being used fo r each tes t fluid. The data points were identified with their

individual temperatures so that "best-fit" curves could be drawn through

each group of data points having a common nominal temperature.

nominal temperature is defined a s that temperature which is selected to

A

B-1

Step 2 T" / o

/ 0

0

/'A A. I

/ /

/A

VO

Step 4

I h

v,

t

Step 6 -

Step 3

L TO = To, B

V O

S t e p 5

t

Figure 10. 1 I l l u s t r a t ion of Method Used to C o n s t r u c t Nominal I s o t h e r m s f r o m Exper imen t a1 Da ta

represent a specific group of data points having little temperature variation.

These first-approximation isotherms are shown as dashed lines on step

two of figure 10. 1. I

One of the nominal isotherms i s chosen, on the basis of availability

of sufficient experi-mental h v s V data at o r near that temperature, as a 0 0

reference or "base" isotherm for succeeding computations.

is designated T

This isotherm

in figure 10. 1 while the other isotherms a r e designated 0, B

T ' and To''. 0 ,

( 3 ) The constants in equation [ 10-21 a r e evaluated by selecting

pa i rs of values of h and T f rom the nominal isotherms at identical

velocities as follows: on figure 10. 1 the tail of each a r row indicates a

value of h and T while the a r row head points to h and T The

coordinate points from each a r row a r e then used in equation [ 10-21. Note

that each ar row provides one equation, hence five a r rows a r e needed to

evaluate the constants in [ 10-21. The a r rows always follow a constant

velocity path and mus t be strategically placed in order fo r the five equa-

tions to be independent. The actual data points a r e not shown since they

are not used in this step.

data from one temperature to another within the confines of the bounding

isotherm s.

0 0

0 8 1 0, 1 0 , 2 0 , 2 '

The equation derived from this step will "transfer"

(4) In step four of the illustration, arrows a r e used to indicate the

"transferral" of experimental data points to a new location near the base

isotherm, h and T are known from the experimental data, while

; values of h can OJ 1 0, 1

To, B 0 1 2 is simply the base nominal temperature, To, 2

then be determined, by using equation [ 10-21, and plotted near the base

, To, B Note that the data t ransfer always follows a constant temperature,

velocity path.

B - 3

( 5 ) A new "best f i t " isotherm can then be drawn through - all of the

"transferred" data points a t T This new curve is shown as a solid line 0, B'

in figure 10. 1; the f i r s t approximation isotherms, drawn as dashed lines,

a r e no longer needed and a r e omitted in the illustration of this step. The

curve obtained from this step represents an improved reference isotherm.

(6) The new reference isotherm and equation [ 10-21 may now be

used to reconstruct the other nominal isotherms. T and T I t may be

reconstructed by using equation [ 10;2] and h 0 0

values from the new base 0,

isotherm, Note that T now becomes T and To1 and To" take their 0, €3 O t 1

respective turns as T

plot the two new isotherms shown in the illustration of this step on figure

10.1.

Values of h are then computed in order to 0, 2' 0,2

( 7 ) The original experimental data points were then t ransferred

to their nearest nominal temperature by means of equation [ 10-21.

points having a nominal temperature of T position in step four.

spective isotherms, as shown by the a r rows in the illustration of step

Those

were relocated in their final 0, B

This process brings the data points near their re-

seven. Note that h is again the only unknown in equation [ 10-21. 0, 2

( 8 ) The agreement between the new nominal isotherms and the

t ransferred experimental data points was then observed: If the f i t was

not satisfactory, "best-fit" curves were drawn through the "transferred"

data points and the entire computational procedure---steps ( 3 ) through

( 7 ) --- was repeated.

mathematical expressions for liquid hydrogen and liquid nitrogen: tables

4.3, 4.4, and 4. 5 as well as figures 4. 2 and 4.4 were prepared by using

the following equations.

Several iterations were necessary to obtain suitable

B -4

Hydrogen:

- T ) (0.41 V - 400. 35). + ( T o , 2 0,1 0

[ 10-31

Nitrogen :

)2] t 30. 152 ( T - T ). [ 10-41 0 9 2 0,1

-0.2729 [ (To, 2)2 - ( To,

It should be noted that some of the t e r m s in equation [ 10-21 become

negligible and consequently a r e not included in [ 10-31 and [ 10-41. It is

observed that equation [ 10-31 f o r hydrogen is v e l x i t y dependent, while

equation [ 10-41 for nitrogen i s not.

[ 10-31 and [ 10-41 be used outside the general a r e a of the data points

given.

It is not recommended that equations

B-5

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