高负荷离心压气机扩压器叶片前缘开槽流动机理研究  

Numerical Investigation on Flow Mechanisms of Diffuser Leading Edge Slot in a Highly Loaded Centrifugal Compressor

作　　者：张英杰 韩戈[1] 李紫良 阳诚武[1] 张燕峰[1,2] 卢新根 ZHANG Ying-jie;HAN Ge;LI Zi-liang;YANG Cheng-wu;ZHANG Yan-feng;LU Xin-gen(Key Laboratory of Light-Duty Gas-Turbine,Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China;University of Chinese Academy of Sciences,Beijing 100049,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,北京100049

出　　处：《推进技术》2020年第3期559-565,共7页Journal of Propulsion Technology

基　　金：国家自然科学基金(51606187)。

摘　　要：扩压器前缘几何结构直接决定着扩压器的性能和内部流场特性,为进一步拓宽离心压气机的稳定工作范围,以高负荷离心压气机为研究对象,利用经过校核的数值模拟方法开展扩压器叶片前缘开槽流动机理研究,详细讨论了扩压器开槽对压气机性能及内部流动影响的机理。研究结果表明,扩压器叶片前缘开槽能够在保证离心压气机性能基本不变的前提下,使其失速裕度提高13.5%,与原型扩压器相比,扩压器叶片前缘开槽所诱导的间隙泄漏流能有效抑制扩压器通道内的流动分离,从而提高了离心压气机的稳定裕度。The leading edge structure of diffuser has an important effect on its performance and flow field.To extend the stable operating range of centrifugal compressors,a series of numerical simulations was performed in a highly loaded centrifugal compressor to investigate the flow mechanisms of slotted diffuser,and discuss its influences on the stage performance and stall margin.The results indicate that the stall margin of centrifugal compressor was enhanced by 13.5%without performance deterioration.It is because that the leakage flow passing through the slotted portion suppresses the flow separations in the diffuser passages effectively.As the result of this,it enhances the stall margin without stage performance deterioration.

关 键 词：离心压气机 扩压器开槽 数值模拟 失速裕度 流动分离 

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]