带自适应流通处理机匣的轴流压气机全通道数值研究  

Full-Annulus Numerical Investigation of Axial Flow Compressor with Self Recirculation Casing Treatment

作　　者：张皓光[1] 吴俊[1] 楚武利[1] 吴艳辉[1] 李相君[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》2013年第7期918-924,931,共8页Journal of Propulsion Technology

基　　金：国家自然科学基金(51006084);国家自然科学基金重点项目(51236006);陕西省自然科学基金(2011JQ7018);西北工业大学基础研究基金(JC201116)

摘　　要：采用全通道数值模拟方法研究了两种自适应流通装置数目的处理机匣对亚声速轴流压气机性能及流场的影响,非定常数值计算结果表明两种自适应流通处理机匣分别获得了6.3%,9%的失速裕度改进量,通过详细地分析压气机叶顶流场表明,高速喷射气流能抑制前缘溢流现象的产生,有效地改善了叶顶通道的流动状况。随着自适应流通装置数目从10增加到15,喷射气流对转子叶顶间隙泄漏流的影响频率也随着提高,因此增强了处理机匣抑制叶顶间隙泄漏流负面影响的能力。Effects on the performance and flow-field of subsonic axial-flow compressor are investigated with full-annulus numerical method with two kinds of self recirculation casing treatment,which are different in the number of self recirculation setting.The unsteady numerical calculative results show that stall margin improvement from 6.3% to 9% is achieved with two kinds of self recirculation casing treatment.The fundamental flow mechanism is obtained by detailed analyzing the flow-filed at the blade tip and the underlying mechanism consists of：（1） Leading edge spilling flow can be restrained by the high speed injecting flow coming from self recirculation casing treatment and consequently the flow-filed of blade tip passage is improved effectively.（2） When increasing the number of self recirculation setting from 10 to 15,the frequency of injecting flow affecting tip leakage flow is improved.As the result,the ability of casing treatment to restrain the negative effects of tip leakage flow is enhanced.

关 键 词：处理机匣 轴流压气机 全通道 裕度改进量 前缘溢流 

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]