SSME hot gas manifold flow comparison testAn account is given of the High Pressure Fuel Turbopump (HPFT) component of NASA's Alternate Turbopump Development effort, which is aimed at the proper aerodynamic integration of the current Phase II three-duct SSME Hot Gas Manifold (HGM) and the future 'Phase II-plus' two-duct HGM. Half-scale water flow tests of both HGM geometries were conducted to provide initial design data for the HPFT. The results reveal flowfield results and furnish insight into the performance differences between the two HGM flowpaths. Proper design of the HPFT can potentially secure significant flow improvements in either HGM configuration.
Document ID
19880035221
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Cox, G. B., Jr. (Pratt and Whitney West Palm Beach, FL, United States)
Dill, C. C. (NASA Marshall Space Flight Center Huntsville, AL, United States)