端区流动对跨声速压气机失速影响的数值研究

Numerical Study for Effects of End Wall Behavior on

关键词:  压气机  失速  端区  泄漏涡  角区分离  数值模拟

Key words:  Compressor  Stall  End wall  Leakage vortex  Corner separation  Numerical simulation

摘要:

为了揭示近失速工况下动叶间隙和静叶角区的复杂流动结构，探索诱发压气机失速的主要因素，对高负荷跨声速压气机开展数值研究，获得了整级压气机和单转子的特性曲线，进而对压气机的流场进行了详细分析。结果表明:对于研究对象，失速最先起始于静叶上角区。上角区完成由开式分离到闭式分离的转变过程，可以认为是静叶发生失速的标志。在近失速工况下，动叶叶尖泄漏涡发生“泡式破裂”堵塞流道，泄漏涡破裂引起的堵塞作用一直从叶顶延伸至70%叶高左右。

Abstract:

In order to study the complex flow structure in rotor clearance and stator corner at near stall condition and explore the main factors inducing compressor stall，a highly loaded compressor was simulated. Characteristics of the compressor and single rotor were obtained. The compressor flow fields were analyzed in detail. Results show，for the compressor in this paper，stall incept in the stator top corner. The completion of transition from open separation to closed separation can be regarded as the signal of stall inception in stator. At near stall point，tip leakage vortex breaks down in bubble type in rotor. The separation bubble plugs the rotor flow field. The plugging effect caused by leakage vortex breakdown has been extended from the tip to about 70% of the blade height.