A project has been initiated at the Marshall Space Flight Center to determine if preburner inter- or intra-element mixture ratio maldistributions are the cause of temperature variations in the Space Shuttle Main Engine (SSME) High Pressure Fuel Turbopump (HPFTP) turbine inlet region. Temperature nonuniformity may contribute to the many problems experienced in this region. The project will involve high pressure cold-flow testing and Computational Fluid Dynamics (CFD) modeling.
SSME Fuel Preburner Injector Characterization
1993
4 pages
Report
No indication
English
Space Technology , Rocket Engines & Motors , Fluid Mechanics , Manned Spacecraft , Fuel injection , Injectors , Preburners , Space shuttle main engine , Computational fluid dynamics , Turbine pumps , Cold flow tests , Cracking (Fracturing) , Mixing ratios , Temperature gradients , Temperature measurement , Turbines
SSME fuel preburner injector characterization
NTRS | 1993
|Three-dimensional flow modeling inside SSME preburner
AIAA | 1994
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