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Space Shuttle Main Engine Low Pressure Oxidizer Turbo-Pump Inducer Dynamic Environment Characterization through Water Model and Hot-Fire TestingThe Low Pressure Oxidizer Turbopump (LPOTP) inducer on the Block II configuration Space Shuttle Main Engine (SSME) experienced blade leading edge ripples during hot firing. This undesirable condition led to a minor redesign of the inducer blades. This resulted in the need to evaluate the performance and the dynamic environment of the redesign, relative to the current configuration, as part of the design acceptance process. Sub-scale water model tests of the two inducer configurations were performed, with emphasis on the dynamic environment due to cavitation induced vibrations. Water model tests were performed over a wide range of inlet flow coefficient and pressure conditions, representative of the scaled operating envelope of the Block II SSME, both in flight and in ground hot-fire tests, including all power levels. The water test hardware, facility set-up, type and placement of instrumentation, the scope of the test program, specific test objectives, data evaluation process and water test results that characterize and compare the two SSME LPOTP inducers are discussed. In addition, dynamic characteristics of the two water models were compared to hot fire data from specially instrumented ground tests. In general, good agreement between the water model and hot fire data was found, which confirms the value of water model testing for dynamic characterization of rocket engine turbomachinery.
Document ID
20070013791
Acquisition Source
Marshall Space Flight Center
Document Type
Conference Paper
Authors
Patrick Arellano
(Pratt & Whitney (United States) Hartford, Connecticut, United States)
Marc Patton
(Pratt & Whitney (United States) Hartford, Connecticut, United States)
Alan Schwartz
(Pratt & Whitney (United States) Hartford, Connecticut, United States)
David Stanton
(Pratt & Whitney (United States) Hartford, Connecticut, United States)
Date Acquired
August 23, 2013
Publication Date
January 9, 2006
Subject Category
Fluid Mechanics And Thermodynamics
Meeting Information
Meeting: 44th AIAA Aerospace Sciences Meeting and Exhibit
Location: Reno, NV
Country: US
Start Date: January 9, 2006
End Date: January 12, 2006
Sponsors: American Institute of Aeronautics and Astronautics
Funding Number(s)
CONTRACT_GRANT: NAS8-01140
Distribution Limits
Public
Copyright
Public Use Permitted.

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