进口导流叶排对轴流压气机级畸变响应特性影响  

Effect of inlet guide vanes on response of an axial flow compressor to steady circumferential pressure distortions

作　　者：吴虎[1] 黄健[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：《推进技术》2006年第1期40-43,共4页Journal of Propulsion Technology

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

摘　　要：基于轴流压气机叶片排实验特性,应用畸变传递的矩阵分析模型,对带有进口导流叶片排的轴流压气机级容总压畸变特性进行了详细分析,初步建立了进口导流叶片排对总压畸变及其沿轴流压气机叶片排衰减特性影响规律。计算结果表明,与无导流叶片排相比,带有进口导流叶片排的轴流压气机级具有更强的总压畸变、总温畸变和静压畸变衰减能力,有利于提高轴流压气机稳定工作范围。An efficient calculation procedure was established which allows the rapid computation of the total pressure distortion development through any combination of rotors, stators and clearances. The predictions of response of an axial flow compressor rotor , stator and axial clearance to steady circumferential pressure distortion were presented with and without inlet guide vanes. The effects of inlet guide vanes on response of an axial flow compressor to steady circumferential pressure distortion were found. By using inlet guide vanes, great attenuation of total pressure distortion and static pressure distortion, weak incidence angle changes and low total temperature distortion production through the rotor were obtained. It is apparent that the effective improvement in stall margin can be achieved with inlet guide vanes under conditions of inlet circumferential pressure distortions. Appropriate design of inlet guide vanes for multistage axial flow compressors should ensure that the axial compressors have high tolerant to inlet pressure distortions.

关 键 词：轴流压气机 压力畸变 导流叶片 响应特性 气动稳定性 

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]