某涡轮级转静干涉噪声数值研究  

Numerical investigation of rotor-stator interaction noise in a turbine stage

作　　者：母忠强[1] 乔渭阳[1] 赵磊[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《航空动力学报》2011年第9期2082-2088,共7页Journal of Aerospace Power

摘　　要：通过采用结合相位延迟方法的非定常数值计算,得到真实叶片数下某高压涡轮级叶片通过频率及其倍频下的脉动压力.然后在转子后管道中利用模态匹配方法,摒除了管道末端非物理反射及其非声压脉动的影响,从而获得转子后管道中向下游传播的转静干涉噪声分量.结果分析表明:该涡轮级在叶片通过频率下,周向模态m=3未被截止,且为主要转静干涉噪声源;在2倍叶片通过频率下,周向模态m=6,-64未被截止.By using the unsteady computation which employed phase-lag method to get the fluctuation pressure in a high pressure turbine stage with real blade amount,and also using the mode matching method in the duct of downstream rotor,the non-physic reflection in the duct end and other non-sound pressure fluctuations were extracted.The rotor-stator interaction noise propagating downstream was obtained.The results show that the dominance azimuthal mode m=3 isn＇t cut-off for the blade passing frequency,m=6 and m=-64 aren＇t cut-off for the second blade passing frequency.

关 键 词：涡轮级转静干涉噪声 叶片通过频率 相位延迟方法 模态匹配方法 声压级 声功率级 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]