单晶涡轮叶片典型任务循环蠕变分析

Considering the multiple working conditions creep calculation of single crystal turbine blade under the typical mission profile of engine, combined with the creep constitutive model of single crystal super-alloy under varying loading, a ABAQUS/UMAT subroutine for creep calculation of high temperature structure was developed. The creep of a single crystal turbine blade under the typical design load spectrum was calculated, and the working state of negligible creep damage was identified, so as to simplify the load spectrum. The creep deformations of the turbine blade under 10 000 mission cycles of fighter and 40 000 mission cycles of transport aircraft were calculated respectively, and the service life was evaluated. The results showed that, under the typical load states used in the calculation, the creep damage of turbine blade under engine cruise state and below was small, which can be ignored in creep calculation. The creep deformation of turbine blade under the simplified creep load spectrum was basically equal to that under the original load spectrum; turbine blades had different creep life under different aircraft mission profiles. Under the typical mission cycle of fighter used in the calculation, the creep life of the turbine blade was about 1/14 of that of transport aircraft, which was related to the duration of high-power state of the engine.