转子叶片撞击瞬态响应分析

以某型航空发动机高压压气机一级转子叶片为模型,采用解析方法,建立了正常工作中的转子叶片受折断叶片撞击时的动力学方程.确定了系统的边界条件,给出了受撞击叶片对冲击载荷响应的解析表达式,从而使得转子叶片受到来自内部折断叶片撞击时的瞬态响应可以被解析地获得.最后,通过一个算例进行了正常工作中的转子叶片受折断叶片撞击时的瞬态响应分析.计算结果表明:当发动机转速为10 000 r/min,撞击位置距叶根0.05 m,撞击时间0.02 s时,该长、宽、厚分别为0.07 m0、.03 m、0.005 m的转子叶片在撞击脉冲力作用下撞击点的最大瞬态位移可达0.002 92 m,不容忽视.

Transient Response Analysis of the Impact on the Rotor Blade

Taking the primary rotor blades of a high pressure compressor of a certain aero-engine as the research object, and by ways of interpretation and analysis, the kinetic equation to describe the impact of a broken blade on the rotor blades was derived, which can analytically describes the transient response of the inside broken blade''s impact on the rotor blades. An example with the length, width and thickness of the rotor blade being 0.07 m, 0.03 m, 0.005m respectively was given to illustrate the transient response when one rotor blade was broken due to impact. The results show that, when the engine speed reaches up to 10000r/min, the impact point is 0.05m far from the root of the blade and the impact time is 0.02s, the maximum transient response displacement can reach up to 0.00 292 m. So, the maximum response under impulsive load should never be neglected.