45°周向压力畸变对轴流压气机影响的实验研究和机理分析  

Experimental investigation and analysis of an axial compressor stage with 45° circumferential inlet pressure distortion

作　　者：黄健[1] 吴虎[1] 杜文海[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》2007年第3期460-464,共5页Journal of Aerospace Power

基　　金：国家自然科学基金资助(10377013)

摘　　要：设计了一种45°周向压力畸变模拟发生器,并在某高速轴流压气机实验台进行了实验研究.在中等转速下,详细研究了45°周向压力畸变对该轴流压气机级的转子的性能影响,以及整个轴流压气机级(转子进口、转子出口和静子出口)的压力周向分布.研究结果表明,在中等转速下,畸变区的范围在转子出口转移和扩大并不明显,但是在静子出口扩大了近100%;在转子出口畸变强度明显增强,而在静子出口强度衰减;与均匀进气的情况相比,压气机转子压比提高了1.8%,近失速点换算质量流量减小了2.5%.A 45° circumferential inlet pressure distortion screen was designed and the effects of screen-induced circumferential inlet pressure distortion on axial flow compressor stage were investigated at a high speed subsonic compressor test rig. The performance characteristics for the rotor with circumferential inlet pressure distortion and clean inlet flow were compared at middle-speed. The circumferential pressure distributions at three axial locations （rotor inlet, rotor outlet and stator outlet） were measured. The results show that the inlet flow distortion has weak effects on the compressor stage at middle-speed. In addition, the enlarging and moving of the distortion-section are not obvious at rotor outlet, but it is enlarged about 100 percent at stator outlet; the distortion is enhanced at rotor outlet and decayed at stator outlet. However, with inlet distortion the pressure ratio of this compressor rotor is improved 1.8 percent and the equivalent mass flow reduced 2.5 percent at near-stall condition in comparing with clean inlet flow.

关 键 词：航空 航天推进系统 轴流压气机 实验研究 压力畸变 性能 

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]