低速轴流压气机旋转失速特性试验  

Experimental investigation on characteristic of rotating stall in a low-speed axial compressor

作　　者：屠宝锋[1] 胡骏[1] 王志强[1] 李亮[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2009年第1期143-149,共7页Journal of Aerospace Power

基　　金：国家973项目(2007CB210301)

摘　　要：在一台双级低速轴流压气机上进行了均匀进气时的全流量特性试验研究,重点分析了该压气机旋转失速特性随流量系数的变化情况和失速起始特性.试验结果表明,压气机在失速前出现模态波扰动,其传播频率约等于40%转子旋转频率,范围贯穿整台压气机;压气机第二级在模态波扰动诱导下率先进入旋转失速,初始失速团旋转速度为83.3%转子转速;失速团在向第一级扩散传播过程中,其旋转速度逐步降低,最后稳定在41.9%转子转速;失速团旋转频率随着流量系数的降低而减小;失速团范围随着流量系数的减小而逐渐增加.The full flow characteristic of a 2-stage low-speed axial compressor was investigated with uniform inlet flow. The emphasis of this work was put on the characteristic of rotating stall at different flow coefficient and the stall inception. The results indicate that the modal wave will appear before stall about 30 rotor revolutions, and the rotary speed of modal wave is about 40 % rotor speed. The modal wave can be detected across the compressor. The second stage comes into rotating stall first under the effects of the disturbance of the modal wave. The rotary speed of the early stall cell is about 83.3% rotor speed, and the speed will decrease as the stall cell spreads to the first stage, at last about 41.9% rotor speed. As the flow coefficient reduces, the frequency of the stall cell will decrease, and the scope of the stall cell will extend accordingly.

关 键 词：压气机 旋转失速 失速起始 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]