Design of advanced turbopump drive turbines for National Launch System applicationThe aerodynamic design of advanced fuel and oxidizer pump drive turbine systems being developed for application in the main propulsion system of the National Launch System are discussed. The detail design process is presented along with the final baseline fuel and oxidizer turbine configurations. Computed airfoil surface static pressure distributions and flow characteristics are shown. Both turbine configurations employ unconventional high turning blading (approximately 160 deg) and are expected to provide significant cost and performance benefits in comparison with traditional configurations.
Document ID
19920066198
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Huber, F. W. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Johnson, P. D. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Montesdeoca, X. A. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Rowey, R. J. (Pratt & Whitney Group West Palm Beach, FL, United States)
Griffin, L. W. (NASA Marshall Space Flight Center Huntsville, AL, United States)