Publication Date:
2019-06-28
Description:
NASA-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.
Keywords:
SPACECRAFT PROPULSION AND POWER
Type:
AIAA PAPER 88-2994
Format:
text
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