微型航空发动机涡轮盘蠕变寿命有限元分析

Finite Element Analysis of Creep Life of Turbine Disk of Micro Aeroengine

为了提高微型航空发动机涡轮盘可靠性,选取蠕变时间、温度和载荷作为蠕变寿命的影响参数,利用应变强化准则对某型微型涡喷航空发动机涡轮盘进行了有限元蠕变分析,计算了特定条件下的涡轮盘蠕变寿命.根据三组不同变量拟合得出的函数关系求解了蠕变寿命与温度、载荷的综合函数关系.通过综合函数关系求解出任意条件下的蠕变寿命.结果表明:涡轮盘的蠕变寿命受离心力载荷、工作温度和蠕变持续时间影响,其中工作温度对蠕变寿命的影响最为明显;涡轮盘工作温度为600℃,离心力载荷为600 MPa时,蠕变寿命为451 072h,与涡轮盘设计寿命相符.

In order to improve the reliability of turbine disk of micro-aeroengine,the creep time,temperature and load are taken as the parameters of creep life,and the finite element creep analysis of a turbine engine disk is carried out by strain-hardening criteria.The creep life of turbine disk is calculated under specified conditions.The connection of creep life,temperature and loads is solved according to fitted function of three different variables.The creep life under any conditions is calculated by comprehensive function.The results show that the creep life of turbine disk is affected by centrifugal force,working temperature and creep duration,the working temperature has the most obvious effect on the creep life.When working temperature of the turbine disk rises to 600 ℃,centrifugal force to 600 MPa,the creep life is 451 072 h,which is consistent with the design life.