转静干涉下转子叶片的非定常压力频谱  

Frequency spectrum of unsteady pressure on rotor blade with rotor-stator interaction

作　　者：张小博[1,2] 王延荣[1,2] 黄钟山 王翔鹏[1,2] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191 [2]先进航空发动机协同创新中心,北京100191

出　　处：《航空动力学报》2016年第7期1695-1703,共9页Journal of Aerospace Power

基　　金：国家自然科学基金(51475022)

摘　　要：分别采用多通道模型和相位延迟方法的单通道模型对一压气机转子叶片因转静干涉引起的表面非定常压力进行了分析.对比了转子叶片表面非定常压力的时域和频域信息,并对其高阶主导频率进行了分析.结果表明:相位延迟方法与多通道法计算结果吻合,转子叶片非定常压力的峰值频率为叶片通过频率及其倍频,叶片中部以上区域2倍叶片通过频率的非定常压力幅值约为1倍频的2倍,分析认为这是由尾迹输运和激波振荡导致的,可为深入分析叶片由振动导致高循环疲劳失效的成因提供参考.The unsteady pressure on compressor rotor blade surface clue to rotor-stator interaction was simulated by use of multi-channel model and phase lagged method based on single-channel model. The unsteady pressure on rotor blade surface in both time domain and frequency domain was analysed, and its higher order dominant frequencies were studied. The results show that the results of phase lagged method agree well with those of multi-channel method, the unsteady pressure peak frequencies o{ rotor blade are the BPF （blade passing frequency） and its harmonics, and the unsteady pressure amplitude of 2BPF is approximately 2 times of 1BPF above the middle position of blade height, this can be attributed to the wake transportation and shock oscillation. The results can provide a reference for investigating thoroughly the causes of high cycle fatigue failure of blade due to its vibration.

关 键 词：压气机 转静干涉 非定常压力 频谱特性 高阶主导频率 

分 类 号：V215.3[航空宇航科学与技术—航空宇航推进理论与工程]