掠型设计调控跨声速离心压气机内部流动机理  

Mechanism of swept controlling internal flow of transonic centrifugal compressor

作　　者：李子良 韩戈[1,2,3] 朱俊强 卢新根[1,2,3] LI Ziliang;HAN Ge;ZHU Junqiang;LU Xingen(Laboratory of Light-duty Gas-turbine,Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China;School of Engineering Science,University of Chinese Academy of Sciences,Beijing 100049,China;Innovation Academy for Light-duty Gas Turbine,Chinese Academy of Sciences,Beijing 100190,China)

机构地区：[1]中国科学院工程热物理研究所轻型动力实验室,北京100190 [2]中国科学院大学工程科学学院,北京100049 [3]中国科学院轻型动力创新研究院,北京100190

出　　处：《航空动力学报》2022年第4期826-835,共10页Journal of Aerospace Power

基　　金：航空发动机及燃气轮机重大专项基础研究(2017-Ⅱ-0002-0014)。

摘　　要：跨声速离心压气机面临进口激波控制的难题,探索前缘掠型对跨声离心压气机影响机理对于进一步提升离心压气机性能具有重要意义。以两台跨声速离心压气机为研究对象,利用经过校核的数值模拟手段探究了不同前缘掠型下压气机的性能及流场变化。结果表明:设计工况下叶轮入口的激波位置直接决定了前缘掠型设计的作用效果。掠型设计通过改变导风轮叶顶载荷分布,进而影响其通流能力,同时改变了其入口激波结构和流动损失。当叶轮入口叶顶激波呈吞入状态时,采用前缘后掠会减弱槽道激波强度,从而减小导风轮叶顶附近损失;当叶轮入口叶顶激波呈脱体状态时,采用前缘前掠会减弱前缘激波强度,使得激波更加附体,从而减小导风轮叶顶附近损失。Transonic centrifugal compressors face the problem of shock wave controlling.Therefore,the knowledge of the flow mechanism under leading edge swept effect plays an important role in improving the transonic centrifugal compressors performance.Two different transonic centrifugal compressors were investigated by numerical simulations after verified.The results show that,the inducer inlet shock position directly determines the effect of the leading edge swept under the design point.The change of leading edge swept can affect the flow-through capacity by changing the load distribution on the tip of inducer,and furthermore change the shock structure and flow loss on the tip of the inducer.For the impellers whose passage shock wave was swallowed in the blade passages,the backward swept weakened the strength of the passage shock wave and thus reduced the loss near the blade tip of the inducer.However,for the impellers whose leading edge shock wave was detached from leading edge,the forward swept weakened the strength of the leading edge shock wave and made the shock wave more attached,thus reducing the loss near the tip of inducers.

关 键 词：跨声速离心压气机 流动控制 前缘掠型 载荷分布 激波结构 

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]