Numerical analyses of a rocket engine turbine and comparison with air test dataThe study presents cold air test data on the Space Shuttle Main Engine High Pressure Fuel Turbopump turbine recently collected at the NASA Marshall Space Flight Center. Overall performance data, static pressures on the first- and second-stage nozzles, and static pressures along with the gas path at the hub and tip are gathered and compared with various (1D, quasi-3D, and 3D viscous) analysis procedures. The results of each level of analysis are compared to test data to demonstrate the range of applicability for each step in the design process of a turbine. One-dimensional performance prediction, quasi-3D loading prediction, 3D wall pressure distribution prediction, and 3D viscous wall pressure distribution prediction are illustrated.
Document ID
19930035287
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Tran, Ken (NASA Marshall Space Flight Center Huntsville, AL, United States)
Chan, Daniel C. (Rockwell International Corp. Rocketdyne Div., Canoga Park, CA, United States)
Hudson, Susan T. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Gaddis, Stephen W. (NASA Marshall Space Flight Center Huntsville, AL, 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-12
Meeting Information
Meeting: ASME, International Gas Turbine and Aeroengine Congress and Exposition