周向槽机匣对轴流压气机转子畸变响应特性的影响  

Effect of circumferential groove casing on the response to distortion of an axial flow compressor rotor

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,陕西西安710072 [2]第二炮兵工程学院,陕西西安710025

出　　处：《推进技术》2008年第3期334-338,366,共6页Journal of Propulsion Technology

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,应用全三维数值计算方法,研究了周向槽处理机匣对NWPU-1轴流压气机转子容畸变特性的影响,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,在均匀进气条件下,周向槽处理机匣对叶尖间隙泄漏涡形成和发展的抑制是其扩稳的主要原因;在进气周向总压畸变条件下,该轴流压气机转子失速的主要原因是畸变引起的攻角变化,造成部分叶片的负荷过重,由于周向槽处理机匣的作用主要在叶尖部分,所以并不能有效的扩大该压气机转子的稳定工作范围。Based on an assumed steady inlet circumferential total pressure distortion, the effects of circumferential groove casing treatment on the response to steady inlet circumferential total pressure distortion of an axial flow compressor rotor are investigated numerically for the NWPU axial flow compressor. The results show that, with clean inlet flow,the tip leakage vortex is weakened or even destroyed due to the effects of circumferential groove casing treatment, thus the stall margin of compressor is improved. In addition, with inlet circumferential total pressure distortion, the changes of attack angle due to distortion make the load of several blades too high and then stall happens. The main influence zone of circumferential groove casing treatment is in the tip of blade. Circumferential groove casing treatment cannot improve the stall margin of this compressor rotor under inlet circumferential total pressure distortion.

关 键 词：轴流式压缩机 压力 畸变 周向槽处理机匣^+ 稳定性 

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]