扩压器叶片前缘开槽结构对高负荷离心压气机性能影响研究  

Numerical Investigation of Effects of Slotted Diffuser Structures on a Highly Loaded Centrifugal Compressor

作　　者：张英杰 韩戈[1] 李紫良 张燕峰[1,2] 卢新根 ZHANG Ying-Jie;HAN Ge;LI Zi-Liang;ZHANG Yan-Feng;LU Xin-Gen(Key Laboratory of Light-duty Gas-turbine/Institute of Engineering Therniophysics,Chinese Academy of Sciences,Beijing 100190,China;University of 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,北京100049

出　　处：《工程热物理学报》2020年第7期1617-1626,共10页Journal of Engineering Thermophysics

基　　金：国家自然科学基金资助项目(No.51606187)。

摘　　要：离心压气机在小流量工况下,扩压器叶片进口气流为正攻角,其吸力面产生流动分离,恶化压气机性能从而诱发失速。为改善近失速点扩压器内部的流场,拓宽离心压气机的稳定工作范围,本文对扩压器叶片前缘进行开槽处理,采用经过校核的RANS方法探究不同开槽结构对高负荷离心压气机的性能影响及内部流动机理。研究发现:近失速点原型扩压器的压力面和吸力面两侧同时存在大范围的流动分离,本文研究的直槽和斜劈型2种开槽结构均能有效地抑制扩压器通道内的流动分离并提高压气机的失速裕度。但随着开槽深度和长度的增加,斜劈型开槽结构会恶化扩压器通道内的流场,致使压气机性能急剧降低。When centrifugal compressors operate at low flow rates,flow separations will occur on the suction surface of vaned diffuser due to the positive incidence angle at diffuser inlet,which deteriorates compressor performance and leads to compressor stall.To improve the flow field of diffuser at near stall point and extend stable operating range of centrifugal compressor,a series of numerical simulations was performed in a highly loaded centrifugal compressor to investigate the influence of slotted diffuser structures on the stage performance and the flow mechanism inside diffuser passages.The results indicate that both straight and oblique slot structures suppress flow separations effectively which exist on the pressure and suction surfaces of vaned diffuser simultaneously,resulting in a stall margin enhancement.However,the oblique slot structure deteriorates the flow field inside diffuser passages and compressor performance severely,with increasing the slot depth and length.

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]