带导流叶排的轴流压气机级叶尖处理机匣容畸变特性  

Effect of Casing Treatment on the Response to Steady Circumferential Pressure Distortions of an Axial Flow Compressor with Inlet Guide Vanes

作　　者：吴虎[1] 斯日古楞[1] 高双林[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《航空动力学报》2005年第4期619-624,共6页Journal of Aerospace Power

基　　金：国家自然科学基金资助(10377013);航空科学基金资助(02C53022)

摘　　要：基于叶尖处理机匣轴流压气机叶排实验特性,应用畸变传递的矩阵分析模型,分析了进口导流叶排对叶尖处理机匣结构容总压畸变特性影响,初步建立了在进口导流叶排下几种处理机匣结构对总压畸变及其沿轴流压气机叶排衰减特性影响规律。计算结果表明,叶尖处理机匣虽均能有效提高压气机级的稳定工作范围,但削弱了转子叶排和静子叶排的抗总压畸变能力,这对设计合理的扩大轴流压气机稳定裕度处理机匣结构尤为重要。An efficient calculation procedure was established which allowed the rapid computation of the total pressure distortion development through any combination of rotors, stators and clearances. The predictions of the response to steady circumferential pressure distortion of an axial flow compressor inlet guide vanes,rotor,stator and axial clearance were presented with four casing configurations： solid casing, circumferential groove casing, axial skewed slot casing, and blade angle slot casing. The affects of inlet guide vanes on response to steady circumferential pressure distortion of an axial flow compressor with four casing configurations were obtained. In comparison with solid casing ,greatest attenuation of total pressure distortion and static pressure distortion through the rotor and stator of three casing treatment configurations were obtained. It is obvious that effective improvement in stall margin can be achieved with three casing treatment configurations under conditions of inlet circumferential pressure distortions. Appropriate design of casing treatment configurations for multistage axial flow compressors would be able to make axial compressors have high tolerant to inlet pressure distortions.

关 键 词：航空 航天推进系统 轴流压气机 压力畸变 导流叶片 机匣处理 

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]