HCF, LCF and creep life analysis of a generic LRE turbine blade

Kurzfassung

A numerical turbine blade fatigue life analysis method is suggested. This method comprises: For the HCF analysis, a stationary thermal 3d Finite Element analysis, a followon (one-way coupled) quasi stationary structural 3d Finite Element analysis (including four load steps) of a single and two half turbine blades as well as the related disk and rotor section and a (Haigh based) post-processing fatigue life analysis for the highest HCF-loaded point of the turbine blade. For the LCF analysis, a transient thermal 3d Finite Element analysis, a follow-on (one-way coupled) quasi-stationary structural 3d Finite Element analysis of a single and two half turbine blades as well as the related disk and rotor section and a (Coffin-Manson based) post-processing fatigue life analysis approach for the highest LCF-loaded point of the turbine blade. For the creep analysis, a quasi-stationary 3d Finite Element analysis of a single turbine blade and two half turbine blades for the full hot-run duration under constant maximum loading condition (worst case approach). Finally, this approach is demonstrated by the numerical HCF, LCF and creep 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).