HCF and LCF Analysis of a Generic Full Admission Turbine Blade-Reference-Cited by-同舟云学术

HCF and LCF Analysis of a Generic Full Admission Turbine Blade

Published:2023-02-08 Issue:2 Volume:10 Page:154
ISSN:2226-4310
Container-title:Aerospace
language:en
Short-container-title:Aerospace

Author:

Riccius Jörg R.¹^ORCID,Zametaev Evgeny B.¹

Affiliation:

1. German Aerospace Center, DLR Lampoldshausen, D-74239 Hardthausen, Germany

Abstract

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.

Funder

DLR-Institute of Space Propulsion in Lampoldshausen, Germany

Publisher

MDPI AG

Subject

Aerospace Engineering

Link

https://www.mdpi.com/2226-4310/10/2/154/pdf

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