轴流压气机对周向总压畸变非定常响应的数值模拟  

Numerical investigation of the response of axial flow compressor to circumferential total pressure distortion

作　　者：黄健[1] 吴虎[1] 张晓东[1] 党春宁[2] 

机构地区：[1]西北工业大学动力与能源学院,西安710072 [2]第二炮兵工程学院,西安710025

出　　处：《航空动力学报》2008年第9期1701-1706,共6页Journal of Aerospace Power

基　　金：国家自然科学基金(10377013)

摘　　要：基于给定的进气周向总压畸变谱,应用非定常三维时间精确数值计算的方法,研究了NWPU-1轴流压气机转子对周向总压畸变的响应,初步揭示了其在进气周向总压畸变条件下的失速机理.结果表明,在84%设计转速,进气周向总压畸变使转子性能明显下降,其失速点流量增加了4.1%,效率下降了0.5%.进气周向总压畸变引起侧流,导致叶片负荷的变化,部分叶片的负荷过重,叶顶间隙泄漏涡几乎堵塞了整个通道,某些叶片的前缘出现溢流,最终导致压气机转子失速.Based on the given circumferential total pressure distortion of steady inlet flow, the response of an axial flow compressor rotor to the circumferential total pressure distortion of steady inlet flow was investigated numerically using 3-D time-accurate unsteady algorithm with the help of NWPU-1 axial flow compressor rig. The results show that, at 84 percent of design speed, the overall performance of compressor rotor is reduced due to distortion, with inlet flow circumferential distortion, the efficiency of compressor rotor is decreased by 0.5 percent and the equivalent weight flow increases by 4.1 percent at near-stall condition if compared with clean inlet flow. Circumferential flow redistribution due to distortion tends to make the load of several blades too high, the blockage zone caused by tip leakage vortex is full of the whole passage, leading to the occurrence of stall.

关 键 词：周向压力畸变 非定常响应 数值计算 轴流压气机 气动稳定性 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]