考虑多叶片-机匣多点变形转静碰摩模型的机匣响应特征与验证

Casing Response Characteristics and Its Verification Considering Multiple Blades-Casing Multiple Point Deformation Rotor-Stator Rubbing Model

针对航空发动机叶片-机匣碰摩故障,提出了一种考虑多叶片-机匣耦合振动下的转静碰摩故障模型,该模型在通用的弹性碰摩模型的基础上,考虑了多个叶片与圆盘之间的耦合作用、叶片与叶片之间的耦合作用、叶片与机匣之间碰摩故障以及叶片与机匣之间转静间隙变化对碰摩力的影响,能够模拟机匣单点、局部及整圈,转子的局部和整圈的碰摩规律。将所提出的碰摩模型运用于转子-支承-机匣耦合动力学模型中,利用数值积分获取碰摩故障下的机匣加速度响应规律。利用带机匣的航空发动机转子试验器,进行了转子叶片-机匣的机匣单点-转子全周的碰摩实验,仿真和实验取得了很好的一致性,验证了所提出的叶片-机匣碰摩新模型的正确有效性。并利用该模型仿真了其他碰摩状态下的碰摩故障特征和碰摩力随时间变化规律。

For the aircraft engine blade-casing rubbing fault,a new aero-engine multiple blades-casing rubbing model which considers multiple blades-casing coupling vibration is put forward,based on the general elastic rubbing model. The new model considers the coupling action between the multiple blades and disk,the blade and blade coupling,blade and casing rubbing fault and the rotor-stator clearance change on rubbing forces,and it can simulate single point,part and whole-cycle rubbing faults on casing,part and whole-cycle rubbing faults on rotor. The new rubbing model is applied to the rotor-support-casing coupling model,and the casing acceleration responses under rubbing faults are obtained by the numerical integration approach. The aero-engine rotor tester with casing is used to carry out the rubbing experiment whose rubbing positions are the single point rubbing fault on casing and whole-cycle rubbing fault on rotor. The simulation results are found to agree well with the experimental results and the new blade-casing rubbing model is fully verified. Finally,the other rubbing faults with various rubbing positions are simulated,and their rubbing characteristics as well as the law of rubbing force variations with time are found out.