Numerical thermal analyses that contributed to the elimination of turbine blade firtree cracks in the Space Shuttle Main Engine High Pressure Fuel Turbopump turbineNASA-Marshall has undertaken analytical and experimental efforts to eliminate all turbine blade cracking and further improve the safety and reliability of the SSME. This work is focused on the elimination of cracks at the blade firtree attachment to the disk, in both the first- and second-stage rotors of the High Pressure Fuel Turbopump. Emphasis is placed on thermal analyses that preceded the overall structural evaluation of the blade firtrees. Thermally-induced contributions to the stresses and strains in the firtrees were quantified by these studies, and feasible design improvement options were identified and tested.
Document ID
19880060808
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Principe, R. S. (Rockwell International Corp. Canoga Park, CA, United States)
Behne, D. S. (Rockwell International Corp. Rocketdyne Div., Canoga Park, CA, United States)