NASA-CR-54810 · Large size cryogenic turbine type flowmeter technology

NASA (NTRS) · 1966

Open the PDFPublic domain · NASA (NTRS)Technical Reports

Overview

Procurement, calibration, installation, and use of cryogenic turbine flowmeters for M-1 engine

Pages: 50
Chapters: 4

Key points

The report discusses the procurement, calibration, installation, and use of large turbine flowmeters for liquid oxygen and liquid hydrogen components in the M-1 rocket program.
Calibration of large cryogenic flowmeters is challenging due to the need for cryogenic liquid calibration rather than water calibration, which is not feasible at existing facilities.
The design of large flowmeters incorporates features to minimize repair time and costs, including the use of straightening vanes and pre-loaded ball bearings.
Limited calibration data for several turbine flowmeters is provided, highlighting the relative capabilities of major testing organizations.
The report emphasizes the importance of specialized calibration facilities for large cryogenic flowmeters to ensure accurate performance measurement.

Frequently asked questions

What is the focus of NASA CR-54810?

NASA CR-54810 focuses on the technology and application of large cryogenic turbine flowmeters used in the M-1 rocket program.

Why is calibration of large cryogenic flowmeters difficult?

Calibration is difficult because it requires the use of cryogenic liquids instead of water, and existing facilities are often unable to accommodate the necessary calibration for large flowmeters.

What design features are included in large turbine flowmeters?

Design features include flow straighteners, rugged bearing designs, and multiple sensing coils to enhance performance and minimize repair needs.

What recommendations does the report provide?

The report provides recommendations for calibration facilities and application considerations for large cryogenic turbine flowmeters.

What types of data are included in the report?

The report includes limited calibration data for several turbine flowmeters and discusses the capabilities of major testing organizations.

APPENDIX A

APPENDIX A FLOU DATA FOR & I N . TURBINE FLOWUZEB U N I V E R S I T Y O F C A L I F O R N I A Lcw -0s SCIEKIlpIC LABOUTORY (coN.rucr w-740S-m&36) P . 0. Box 1663 ~ A u H o s , N E I y E x I c o 87544 m LLR.10: CMF-9-1645E February 4, 1966 G . R . Deppe Aerojet General Corporation 4610, Dept. 0830 Bldg.

Sacramento, California Dear Gordon: Flow data on t h e eight inch turbine flowmeter is tabulated below.

C a 1 ibra t ion Flowrate Factor Pressure Uncertainty G R 4 PPG PS IA Percent 36 1105 3.35 33.2 rt 3 . 5 2129 3.48 118 st 2.2 4078 3.51 333 f 1 . 6 6 043 3 . 4 8 663 f 1 . 4 W e would have liked t o run another test t o determine t h e reproduci- is such t h a t it i s doubt- b i l i t y of these points, however, t h e schedule f u l t h a t w e could run again f o r several months. There is a p o s s i b i l i t y t h a t two more points, one each a t 6000 and 7000 GFM, may be retrieved a f t e r a closer look a t the data.

I hope you w i l l find t h i s data useful.

Very t r u l y yours, R. W . Stokes RWS :hp

cc: M a - 2

CMF-9 F i l e Page All

Next: APPENDIX B →

APPENDIX B

APPENDIX B WATER AND LIQUID OXYGXN CALIBRATION DATA

TURBINE FLOwMGlER 14 x 12 - 5498 S/N AJ 12-5

WATER AND LIQUID OXPGE8 CALIBRATION DATA

'I'URBINE FLOVHETEB 14 x 12 - 5498 S/N AJ 12-5

I . WATER DATA - UYLE LABORATORIES, MARa 1965

Flow Rate (GPM) K (FTJL/GAL) 3488 0.6230 4404 0,6228 5929 0.6240 7236 0.6240 9205 0 6239 10276 0,6243 11782 0,6245

15069 0 . 6247

15447 0.6249

L I Q U I D OXYGEN DATA - MARSHAIL SPACE FLIGHT C w

11.

DECEMBER, JANUARY 1965 Flow Rate ( G H ) K (PUI&AL) 109500 0 6293 11,100 0.6297 11,500 0 6289 1 4 9400 0 6301 14,700 0,6309 14,800 0 0 6337 16 9 5 0 0 0 0 6337

Next: APPENDIX c →

APPENDIX c

, APPENDIX c __ LH2 F'LOU DATA COMPARISON FROM TESTS ON TEST STAND H-6, SERIES 102-21-NNP-WM, 1965-1966 LE2 F L O W DATA COMPARIS(24 FROM TESTS ON STAND 11-69 SEBIES 1.2-21-NNP-XXX9 1965-1966 (&bine Meter Data Contains a + 0 . 8 % K Factor Shift) RUN E2.%

- '19%

- - -

78,84 -00% -0.38 -0.09 003 7'7.66 -0.39 -0.6 - 0 . 3 4 77.98 -0.49 -0.11 77.00 78.28 a.48 No07 78.14 n013 007 a 0 5 008 -0.18 78,oi -O 039 -0.20 009 78034 4 0 5 2 010 a.08 -0.09 77.67 +O 27 a009 770 73 -0 002 -0.21 78.09 013 78.40 - 0 . 5 4 - 0 . 5 0

wp = Suction Flow, Pottermeter Model 8=-53709 S/N AJS-8-24

Discharge Flow9 Pottermeter Kodel 8-5369, S/N AJS-22 = WfT = Flow Calculated From Tank VH-11

E, =

P Page c-1

Next: APPENDIX D →

APPENDIX D

APPENDIX D FLOV RATE COMPARISON, TEST STAND E-1, FUEL PUMP PROGRAM .

FLOW DATA COMPARISON, TEST S T A N D E.1 FUEL P U M P PROGRAM I - TEST SERIES 1 , 2 - 0 6 - ~ , 1965 Test No, * ' A wide variance exists in data, depending upon when within each t e s t a f l c w r a t e sample is taken, Where available, steady-state numbers were taken, The duration of steady-state is a matter of 10 sec t o 20 sec i n most cases* The variance is also a function of the t o t a l quantity of I f q u i d &charged, as the percent of v a r i a b i l i t y increases with decreasing Sscharged voiumee Page D-1