高压比离心压气机扩压器自循环扩稳机理研究  

Stability Enhancement Mechanism Study of Vaned Diffuser Recirculation Technique in a Highly Loaded Centrifugal Compressor

作　　者：吴云峰 韩戈[1,2,3] 李子良 卢新根 WU Yunfeng;HAN Ge;LI Ziliang;LU Xingen(Key Laboratory of Light-duty Gas-turbine/Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China;School of Aeronautics and Astronautics,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重点实验室,北京100190 [2]中国科学院大学航空宇航学院,北京100049 [3]中国科学院轻型动力创新研究院,北京100190

出　　处：《工程热物理学报》2024年第10期3022-3031,共10页Journal of Engineering Thermophysics

基　　金：国家科技重大项目(No.2017-II-0002-0014);国家自然科学基金(No.52106065)。

摘　　要：随着离心压气机压比的不断提高,径向扩压器逐渐成为制约高压比离心压气机稳定性的关键因素之一,以某高压比离心压气机为研究对象,利用数值方法开展了扩压器自循环流动控制研究,详细讨论了扩压器自循环流动控制对离心压气机性能和内部流动的影响机理。结果表明,在不同转速下,自循环流动控制的效果不同,100%转速时该流动控制方法能够使其流量裕度提高3.5%;而在非设计转速下,该流动控制方法无法带来稳定裕度的提升。通过对流场的分析发现,100%转速近失速工况下,该流动控制方法通过引入一股与主流方向垂直的射流,减小了扩压器入口马赫数,使发生分离的临界攻角增大,抑制扩压器吸力面流动分离,从而提高离心压气机稳定工作裕度。Radial diffuser is the key component of high pressure ratio centrifugal compressor.A centrifugal compressor with high pressure ratio was taken as the research object.The self-circulating flow control of the diffuser was studied by using the validated numerical method.Mechanism of the recirculation technique of the diffuser on the performance and internal flow of the centrifugal compressor was discussed in detail.The results showed that the self-circulating flow control has different effects at different rotational speeds.At 100%rotational speed,the stall margin of the centrifugal compressor could be increased by 3.5%.However,the flow control method could not improve the stall margin at off-design speeds.Detailed flow field shows that the flow control method reduces the inlet Mach number of the diffuser,increases the critical angle of attack for separation,and prevents flow separation on the suction side of the diffuser under the near-stall condition of 100%rotational speed by introducing a jet perpendicular to the main flow direction,thus effectively improving the stable operating margin of the centrifugal compressor.

关 键 词：高压比离心压气机 扩压器自循环 流动控制 稳定裕度 损失机理 

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]