径向进气总压畸变对压气机气动稳定性的影响  

Effect of Total Pressure Distortion on Aerodynamic Stability of Compressor

作　　者：屠宝锋[1] 胡骏[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《推进技术》2012年第2期167-173,共7页Journal of Propulsion Technology

基　　金：国家"九七三"项目(2007CB210301)

摘　　要：为揭示径向进气总压畸变对压气机气动稳定性影响的物理机制,分别开展了尖部和根部进气总压畸变对压气机稳定边界以及动态失速过程影响的试验研究。结果表明,均匀进气时,压气机在叶尖区域首先形成失速团;径向总压畸变会引起气流参数的径向分布发生变化,其中尖部进气总压畸变会增加叶尖区域的攻角,导致压气机失速提前,而根部进气总压畸变则会改善叶尖区域的流场,降低攻角,使压气机失速延迟;气流参数径向分布变化也会影响动态失速过程中模态波扰动和失速团的三维扩散过程。An experimental investigation was performed to study the effect of tip and hub total pressure distortion on aerodynamic stability of axial compressor. The results show that stall cell appears at tip region first with uniform inlet flow. Compressor will stall earlier with tip total pressure distortion as a result of increasing the attack angle at tip region. On the other hand, hub total pressure distortion will reduce the attack angle at tip region, so will enhance the stability. Meanwhile, the three-dimensional diffusion characteristic of modal wave and stall cell will also be affected by the change of radial flow varia- bles distribution.

关 键 词：压气机 径向总压畸变 稳定边界 动态失速 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]