为探究高温蠕变对涡轮盘疲劳寿命的影响，以某型燃气轮机高温涡轮盘为研究对象，根据涡轮服役载荷谱，采用有限元仿真技术构建三维数值模型进行多场耦合仿真，确定涡轮盘寿命考核点。基于仿真结果，使用SWT参数修正模型预测涡轮盘疲劳寿命，通过拉森-米勒持久方程以及Miner线性损伤理论预测涡轮盘蠕变寿命，确定了涡轮盘的限寿部位，根据线性损伤累积法得到涡轮盘疲劳/蠕变寿命。研究结果表明：现行载荷谱下，高温涡轮盘引气孔边缘处为限寿部位，涡轮盘的纯疲劳寿命为9720.6小时，纯蠕变寿命为24656.8小时，疲劳/蠕变共同作用下的寿命为6972.2小时，高温蠕变会对涡轮盘的疲劳寿命造成显著影响，相比于涡轮盘的纯疲劳寿命降低幅度达到28.27％。

In order to explore the influence of high temperature creep on the fatigue life of turbine disk, a high temperature turbine disk of a gas turbine was taken as the research object. According to the service load spectrum of the turbine, a three-dimensional numerical model was constructed by finite element simulation technology for multi-field coupling simulation, and the life assessment point of the turbine disk was determined. Based on the simulation results, the SWT parameter correction model is used to predict the fatigue life of the turbine disk. The creep life of the turbine disk is predicted by the Larson-Miller persistence equation and the Miner linear damage theory, and the life limit position of the turbine disk is determined. The fatigue / creep life of the turbine disk is obtained according to the linear damage accumulation method. The results show that under the current load spectrum, the edge of the induced hole of the high temperature turbine disk is the life-limiting part. The pure fatigue life of the turbine disk is 9720.6 hours, the pure creep life is 24656.8 hours, and the life under the combined action of fatigue / creep is 6972.2 hours. The high temperature creep will have a significant impact on the fatigue life of the turbine disk, and the pure fatigue life of the turbine disk is reduced by 28.27 %.