On the cyclic elastoplastic constitutive model (considering the Chaboche nonlinear kinematic hardening rule), the strain-hardening creep constitutive model and the reasonable expansion of the advanced creep-fatigue damage model. The creep-fatigue damage of a certain type of turbine disk was simulated and predicted. The results show that during the service of 4 h cruise, the most dangerous zone of creep and fatigue damage of the turbine disc mainly at the bottom of the tenon groove, the disc edge close to the tongue and groove and the shape mutation area of the disc. Maximum damage is found at the end of the tenon groove, and the damage dominated by creep. The damage pattern is dominated by fatigue in the core area of the disk with lower temperature. The maximum damage of the turbine disc increases with the cruise time of a single flight, gradually from fatigue dominance condition to creep dominance condition. Research can provide important reference for the long-life and high-reliability design of aero-engine turbine disc.
CHEN Keming
,
TIAN Ruozhou
,
GUO Sujuan
,
WANG Runzi
,
ZHANG Chengcheng
,
CHEN Haofeng
,
ZHANG Xiancheng
,
TU Shandong
. Creep fatigue life prediction of aero-engine turbine disc under cyclic thermal load[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022
, 43(5)
: 225290
-225290
.
DOI: 10.7527/S1000-6893.2021.25290
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