一、前言 航空发动机是在起动-运行-停车的循环状态下工作的,这种循环使其热端部件受到了两种损伤,即由于起动-停车的循环变形而引起的疲劳损伤和在运行过程中,由于持续峰值载荷的作用而引起的蠕变损伤,与单纯疲劳相比,这种疲劳和蠕变交互作用将显著降低构件的寿命。对此,业已提出许多寿命估算方法,其中,虽有些方法较简单,便于工程计算,但其应用还有一定的局限性,而且对交互作用的微观机制尚缺乏深入的研究。 I. INTRODUCTION The aeroengine works in the cycle-start-run-stop mode. This cycle causes two types of damage to its hot-end components: fatigue damage caused by cycle deformation of start-stop and during operation , This fatigue and creep interaction will significantly reduce the life of the component compared to pure fatigue, due to the creep damage caused by the continuous peak load. In this regard, many life estimation methods have been proposed. Although some of the methods are simpler and easier to calculate, their applications have some limitations. However, there is still a lack of in-depth study on the microscopic mechanisms of interaction.