来流气流角变化对冲压叶栅性能的影响  

INFLUENCE OF FLOW ANGLE ON THE SUPERSONIC CASCADE PERFORMANCE

作　　者：孙小磊[1,2] 扈延林[1,2] 杜建一[1] 徐建中[1] 

机构地区：[1]中国科学院工程热物理研究所,北京100190 [2]中国科学院研究生院,北京100190

出　　处：《工程热物理学报》2010年第9期1484-1487,共4页Journal of Engineering Thermophysics

基　　金：国家重点基础研究发展计划(973计划)(No.2010CB227302);国家自然科学基金资助项目(No.50806074)

摘　　要：本文研究的冲压叶栅基于激波增压这一思想,在冲压叶栅内组织了多道斜激波及一道结尾正激波,来实现叶栅的增压效应。采用雷诺平均N-S方程和Menter-SST湍流模型,对冲压叶栅的流场进行数值模拟。数值模拟结果表明,来流气流角在37°与49°之间变化时,冲压叶栅波系可以稳定存在,并且随着来流气流角增大,叶片通道内分离趋于严重,且有竹节波产生,使得叶栅流动分离损失及激波损失加剧,等熵效率降低。A shock-in type supersonic compressor is designed based on the concept of shock compression. In order to obtain the pressure rise, several oblique shocks and one terminal normal shock are organized in the flow passage. In this paper, the influence of inlet flow angle on the rotor performance is analysed by numerical method. The Menter-SST turbulence model is applied to solve the RANS equations to simulate the flow field of this supersonic compressor. The simulation results indicate that the shock wave system can remain steady in the flow passage when the inlet flow angle is changed from 37 degree to 49 degree. As the inlet flow angle increases, the separation of boundary layer, which is induced by the terminal normal shock, gradually deteriorates, and causes intersection of the shock wave system. As a result, the separation and shock loss is increased and the isentropic efficiency is decreased.

关 键 词：冲压叶栅 气流角 激波 数值模拟 

分 类 号：TK121[动力工程及工程热物理—工程热物理]