机动载荷对弹用涡轮发动机转子动力学特性的影响

The Influence of Maneuvering Load on Rotordynamic Characteristics of Missile Turbine Engine

针对弹用涡轮发动机转子系统特殊的结构及工作特性,从相对运动角度推导了机动飞行转子动力学方程,分析了不同的机动飞行带来的附加载荷,采用有限元方法计算分析了横滚机动和常规机动对转子系统动力特性的影响。结果表明,在现有国军标规定的载荷大小情况下,横滚机动对转子动力特性几乎没有影响,而常规机动会造成与转子工作转速时稳态响应相当的盘心偏移,增大了转子发生碰磨的可能性。

Aiming at the special structure and working characteristics of missile turbine engine rotor system,the equation of maneuvering flight rotor system is derived from the perspective of relative motion,and the additional loads brought by different maneuvering flights are analyzed.Finite element method is used to calculate and analyze the effects of rolling maneuver and conventional maneuver on the dynamic characteristics of the rotor system.The results indicate that under the current load size specified in the national military standard,rolling maneuver has little effect on the dynamic characteristics of the rotor,while the conventional maneuver will cause the disc center shifting.The amplitude of deviation is equivalent to the steady-state response of the rotor at the working speed,which can increase the possibility of rotor collision and wear.