一种预压缩型超音压气机叶栅的性能研究  

Investigation on the Performance of a Supersonic Compressor Cascade With Precompression

作　　者：刘纯杰[1,2] 崔伟伟[1,3] 赵庆军[1,3] 

机构地区：[1]中国科学院工程热物理研究所,北京100190 [2]中国科学院大学,北京100190 [3]中国科学院轻型动力重点实验室,北京100190

出　　处：《工程热物理学报》2013年第9期1630-1634,共5页Journal of Engineering Thermophysics

基　　金：国家重点基础研究发展计划(973计划)资助(No.2010CB227302);国家自然科学基金资助项目(No.51206161)

摘　　要：本文采用理论分析和数值模拟的方法对预压缩型超音压气机叶栅的气动性能进行了分析研究。结果表明,叶栅通道中的预压缩波可以有效地降低叶栅自起动所需的最小喉口/进口面积比,改善起动性能;随进口马赫数的降低,预压缩波由与前缘弓形激波压力面分支相交将变为与吸力面分支相交;当预压缩波与前缘弓形激波吸力面分支相交后,前缘驻点流线与叶片吸力面之间的流道宽度将随进口马赫数的降低而变窄,使得进口气流角增大。In this paper, the aerodynamic performance of a supersonic compressor cascade with precompression is investigated by means of theoratical and numerical tools. The results show that the precompression wave in the cascade passage tends to decrease the minimum area ratio of the throat to the inlet of the cascade, which can maintain the self-starting condition. The introduction of the precom- pression wave can improve the started performance of the cascade. The numerical results also indicate that the intersection point between the precompression wave and the bow shock will migrate from the pressure side to the suction side with the decrease of the Math number at the inlet of the cascade. And the width of the flow passage between the stagnation streamline and the suction side becomes smaller with the decrease of the inlet Mach number when the intersection point of the precompression wave and the bow shock moves towards the suction side. It will results in the increase of the inlet flow angle.

关 键 词：预压缩 自起动 超音叶栅 激波结构 

分 类 号：TK124[动力工程及工程热物理—工程热物理]