叶尖泄漏流对压气机稳定性影响的数值分析  

Numerical analysis of tip leakage flow effect on compressor stability

作　　者：王昊 屠宝锋[1] WANG Hao;TU Baofeng(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2021年第2期320-328,共9页Journal of Aerospace Power

基　　金：国家科技重大专项(2017-Ⅱ-0004-0017)。

摘　　要：为研究叶尖泄漏流对稳定性的影响,发展了一种叶尖泄漏涡模型,并且在由课题组开发的TUSIAC(three dimensional and unsteady stall inception analysis code)程序中实现。该程序将转/静子叶排模化为三维激盘,并在无叶区求解三维非定常欧拉方程,黏性的影响通过特性曲线体现,因此对计算资源的要求较低。数值模拟的结果表明:在叶尖间隙的影响下,压气机的性能和稳定裕度均有所下降。叶尖间隙不改变失速先兆的类型,但使得失速团旋转速度加快,周向尺寸减小。所发展的叶尖涡模型能够预测叶尖间隙尺寸对压气机稳定边界与失速起始过程的影响,从而为在设计初期考虑压气机的气动稳定性、并且优化压气机设计,提供了一种较为实用的方法。To study the effect of tip leakage flow on the compressor stability, a tip leakage vortex model was developed, and implemented in the TUSIAC(three dimensional and unsteady stall inception analysis code) program. The program modeled rotors/stators as three dimensional actuator disks, where the viscous effect was reflected by the characteristic curve, and the three-dimensional unsteady Euler equations in the flow passages between them were solved, thus lower computational resources were required. The numerical simulation showed that the performance and stable margin of the compressor were degraded under the effect of tip clearance.The tip clearance did not change the type of the stall precursor, but shrinked the circumferential size of the stall cell, and made it rotate faster.The newly developed tip vortex model could predict the tip clearance effect on the compressor stability and the stall inception process, thus providing a practical approach to investigate the compressor stability and optimize the compressor design during the preliminary design phase.

关 键 词：压气机稳定性 叶尖泄漏流 激盘模型 计算流体力学 旋转失速 

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]