涡轮转子无螺栓挡板过渡态热固耦合响应分析

Transient thermo-mechanical coupling response analysisfor boltless baffle of turbine rotor

采用有限元方法间接耦合方式分析航空发动机涡轮转子过渡态热和变形响应,获取无螺栓挡板过渡态热与机械载荷共同作用下涡轮转子的温度场、变形和应力历程。结果表明,过渡态下的无螺栓挡板与涡轮盘径向配合面受力及挡板自身应力分布均与稳态下的差异明显,且过渡态无螺栓挡板应力峰值大于所有稳态值。为保证涡轮转子无螺栓挡板过渡态下工作安全可靠,应关注其过渡态响应特性。此结论可为航空发动机涡轮转子无螺栓挡板过渡态响应分析与无螺栓挡板设计提供工程参考。

Transient thermal and deformation responses of an aero-engine turbine rotor were calculated by indirect thermo-mechanical coupling method with finite element method(FEM).The transient temperature field,deformation and stress field of the turbine rotor under transient thermal force and mechanical load of the boltless baffle were analyzed.Results show that transient forces on the radial matching surfaces of the boltless baffle and turbine disk are obviously different from the steady conditions,and the peak stress of boltless baffle under the transient load spectrum is greater than any steady condition.In order to make sure that boltless baffle work safely and reliably,the characteristics of boltless baffle's transient thermo-mechan⁃ical responses are quite important.The paper can provide technical reference for analysis of transient ther⁃mal and stress response and design of aero-engine turbine rotor.