Abstract
A HCF life analysis method for 3d printed turbine blades is suggested. This method comprises a stationary thermal 3d Finite Element analysis, a follow-on (one-way coupled) quasi stationary structural 3d Finite Element analysis (including four load steps) of a single and two half turbine blades and the related disk and rotor section and a (modified Goodman equation based) post-processing fatigue life analysis for the highest HCF-loaded point of the 3d printed turbine blade with as-built to machined surface HCF life correction. Finally, this approach is demonstrated by the numerical HCF analysis of a generic Hydrogen turbo pump (1st rotor row) turbine blade of a 1 MN thrust class gas generator LOX-LH2 Liquid Rocket Engine (LRE).
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