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Cold flow testing of the Space Shuttle Main Engine alternate turbopump development high pressure fuel turbine modelNASA's Marshall Space Flight Center has established a cold airflow turbine test program to experimentally determine the performance of liquid rocket engine turbopump drive turbines. Testing of the SSME alternate turbopump development (ATD) fuel turbine was conducted for back-to-back comparisons with the baseline SSME fuel turbine results obtained in the first quarter of 1991. Turbine performance, Reynolds number effects, and turbine diagnostics, such as stage reactions and exit swirl angles, were investigated at the turbine design point and at off-design conditions. The test data showed that the ATD fuel turbine test article was approximately 1.4 percent higher in efficiency and flowed 5.3 percent more than the baseline fuel turbine test article. This paper describes the method and results used to validate the ATD fuel turbine aerodynamic design. The results are being used to determine the ATD high pressure fuel turbopump (HPFTP) turbine performance over its operating range, anchor the SSME ATD steady-state performance model, and validate various prediction and design analyses.
Document ID
19930035475
Document Type
Conference Paper
Authors
Gaddis, Stephen W. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Hudson, Susan T. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Johnson, P. D. (Pratt & Whitney Group West Palm Beach, FL, United States)
Date Acquired
August 15, 2013
Publication Date
June 1, 1992
Subject Category
SPACECRAFT PROPULSION AND POWER
Report/Patent Number
ASME PAPER 92-GT-280
Meeting Information
ASME, International Gas Turbine and Aeroengine Congress and Exposition(Cologne)
Distribution Limits
Public
Copyright
Other