压气机旋转失速的一个气动声学模型  

AN AEROACOUSTIC MODEL ABOUT THE ROTATING STALL OF A COMPRESSOR

作　　者：孙晓峰[1] 胡宗安[1] 冯毓诚[1] 周盛[1] 

机构地区：[1]北京航空航天大学

出　　处：《航空学报》1991年第9期A467-A473,共7页Acta Aeronautica et Astronautica Sinica

基　　金：国防科技预研基金

摘　　要：根据广义Lighthill方程建立了压气机旋转失速的气动声学模型。提出了一种应用声学方法获取压气机旋转失速特征参数(旋转失速传播速度、数目)的新途径并结合试验结果进行了具体的分析。此外,在简化假设下,用数值法分析了旋转失速特征参数对声音幅值变化的影响。Some experiments show that a kind of special acoustic phenomenon, quite different from that of a normal conditiou of a compreeor, will appear on a compressor test in rotating stall condition. However, little has been known about these problems until now.An aeroacoustic model about the rotating stall of a compressor is described in this paper. The acoustic nature of rotating stall can be preliminarily explained according to this model. Based on the analysis of the nature of frequency and propagation of the sound from rotating stall, an acoustic measuring method for characteristic parameters, such as the number and propagation speed of stall cell, can be obtained. Compared with existing methods, it is an untouched measure without disturbing the flow. The initial experiment results obtained from a transonic axial compressor facility show that this method is feasible. The sound pressure produced by rotating stall is numerically analyed with the change of the width of stall zone, the number and propagation speed of stall cell.

关 键 词：压气机 气动声学 旋转 失速 噪声 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]