为提高某型燃气轮机涡轮盘使用寿命，采用弹塑性有限元仿真分析及通用斜率公式方法，预测了轮盘残余变形、应力与转速的关系以及预应力处理前后盘心位置低循环疲劳寿命。根据仿真结果确定超转转速后，通过设计的具有轴向补偿功能的预应力处理试验工装，对涡轮盘开展热态160%超速预应力处理试验研究。研究结果表明：采用的分析模型对涡轮盘残余变形预测精度高，轮缘及轮盘内孔残余变形计算结果与试验测量结果相比，误差分别为4.29%和2.50%，并且预应力处理能够显著提升盘心危险位置的低循环疲劳寿命。

For the purpose of extending the service life of the turbine disc of a certain gas turbine,the relationship of disc residual deformation and stress versus rotation speed,as well as the low cycle fatigue life of the disc bore position before and after prestressing treatment were predicted using elastoplastic finite element simulation analysis and the general slope formula method.After determining the speed of the overspeed,based on the simulation results,160% overspeed prestressing test of the turbine disc was carried out under hot condition by means of a designed test tooling with axial compensation function.The research result shows that the analytical model used in this paper has a high accuracy in predicting the residual deformation of the turbine disc,with a residual deformation calculation error of 4.29% for the rim and 2.50% for the inner bore of the disc compared to the experimental measurement results.Furthermore,the prestressing treatment can improve the low cycle fatigue life at the disc bore position significantly.

TK221

国家重大科技专项（J2019-IV-0015）