压气机静子通道内的流场测量  

Measurement of flow field in compressor stator passages

作　　者：罗钜[1] 胡骏[1] 严伟[1] 张晨凯[1] 尹超[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》2013年第11期2510-2516,共7页Journal of Aerospace Power

基　　金：中央高校基本科研业务费专项资金;江苏省普通高校研究生科研创新计划(CXZZ11_0224)

摘　　要：为了研究根部间隙对压气机静子通道内流场的影响,设计了4根不同长度的"L"型五孔探针和1根四孔探针.通过位移机构带动上述探针,在最大流量和近失速两种工况下,对某双级低速轴流压气机的第1级静子通道内5个不同轴向位置截面进行了流场测量.实验结果表明:静子通道内总压损失主要是由叶尖附近角区分离以及根部泄漏流与主流的相互掺混引起的.静子通道内主要存在着上/下通道涡、叶尖角涡和泄漏涡等旋涡结构.In order to study the effect of stator hub gap on performance and flow field of compressor, four ＂L＂ type fivehole probes with different lengths and a fourhole probe were designed. The threedimensional flow field at five sections in the firststage stator passage of a twostage axial compressor was measured with those probes, which were driven by dis placement mechanism under the maximum flow and near stall conditions. Results show that mixing of main stream with hub leakage flow and tip corner separation are the main causes of total pressure loss in stator passages. There are four main vortexes in stator passage, which are upper/lower passage vortex, tip corner vortex and leakage vortex.

关 键 词：压气机 流场测量 根部间隙 泄漏流 五孔探针 四孔探针 

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]