基于整机振动响应模型的转子支承阻尼分析与试验

以某型航空发动机为例，建立了该发动机整机振动系统模型，对影响整机振动响应的不同结构挤压油膜阻尼器(SFD）建模方法进行重点分析，并通过多位置-多传感器稳定工况振动响应试验验证了模型的准确性。利用整机振动系统模型计算及对该型发动机的滑油中断试验，讨论了燃气发生器前支点（No.1支点）与自由涡轮后支点（No.3支点）处挤压油膜阻尼值对发动机稳定工况振动响应的影响，得出了该发动机整机振动响应随No.1支点油膜阻尼值增大而先减小后增大，随No.3支点油膜阻尼值增大而减小，并且可以通过适当减小No.1支点处挤压油膜阻尼值，实现发动机在最大连续工况下整机振动总量减小43.4%。 

Analysis and test of rotor support damping based on vibration response model of whole engine

An aviation engine was taken as an example to establish the engine vibration simulation system, and the different structural squeeze film damper (SFD) modeling methods affecting the vibration response of the whole engine were analyzed. Meanwhile, the multi-position and multi-sensor vibration response test of the steady working condition was adopted to verify the accuracy of the model. Based on the calculation of the whole machine vibration system model and the oil interruption test of this engine, the effects of the squeeze oil film damping value at the front fulcrum of the gas generator (No.1 fulcrum) and the rear fulcrum of the free turbine (No.3 fulcrum) on the engine were discussed. Under the stable condition, the result showed that the engine vibration response first decreased and then increased as the No.1 fulcrum oil film damping value increased, and decreased as the No.3 fulcrum oil film damping value increased. By reducing the squeeze oil film damping value at the No.1 fulcrum appropriately, the total vibration response of the engine could be reduced by 43.4% under the maximum continuous working condition.