HCF and LCF Analysis of a Generic Full Admission Turbine Blade

A numerical turbine-blade fatigue-life analysis method is suggested. This method comprises a stationary thermal 3D finite element (FE) analysis of the hot run for the combined high-cycle fatigue (HCF) and creep analysis, and a follow-on (one-way coupled) quasi-stationary structural 3D FE analysis (including six 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 turbine blade. For the low-cycle fatigue (LCF) analysis, this includes a transient thermal 3D FE analysis of two full loading cycles, a follow-on (one-way coupled) quasi-stationary structural 3D finite element analysis of a single and two half turbine blades and the related disk and rotor section and a (modified-Langer-equation-based) post-processing fatigue life analysis approach for the highest LCF-loaded point of the turbine blade. Finally, this approach is demonstrated by the numerical HCF, LCF and creep analysis of a generic turbine blade of the first rotor row of a full admission hydrogen turbo pump of a 1 MN thrust class gas generator LOX-LH2 liquid rocket engine (LRE). For this numerical example, the LCF loading turned out to be dominant. Creep turned out to be negligible

HCF analysis of a prospective 3d-printed LRE turbine blade

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)

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

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)