叶根通槽对跨声速压气机静叶叶栅性能影响的数值仿真  

Numerical simulation of the influence of root slot on the static cascade performance of transonic compressor

作　　者：徐文峰 米瀚沁 孙丹 邹世龙[1] 鲁文昕 XU Wenfenga;MI Hansqin;SUN Dan;ZOU Shilong;LU Wenxin(College of Aero-engine,Shenyang Aerospace University,Shenyang 110136,China;Key Laboratory of Advanced Test Technology for Aeronautical Propulsion System of Liaoning Province,Shenyang Aerospace University,Shenyang 110136,China)

机构地区：[1]沈阳航空航天大学航空发动机学院,沈阳110136 [2]沈阳航空航天大学辽宁省航空推进系统先进测试技术重点实验室,沈阳110136

出　　处：《沈阳航空航天大学学报》2024年第6期11-19,共9页Journal of Shenyang Aerospace University

基　　金：国家自然科学基金(项目编号:52075346,51675351);辽宁省大学生创新创业训练计划支持项目(项目编号:S202310143038);沈阳航空航天大学引进人才科研启动基金(项目编号:23YB20)。

摘　　要：为了探究叶根通槽对跨声速压气机静叶叶栅性能的影响,以高负荷扩压叶栅NACA65-K48模型为基础,通过数值仿真比较不同宽度和高度叶根通槽对压气机叶栅气动性能和流场结构的影响。结果表明,叶根通槽能够有效地削弱吸力面壁面涡强度,抑制沿节距和叶高方向范围的角区分离,减少叶栅的流动损失。其抑制效果随叶根通槽宽度和高度增加均呈现先增强后减弱趋势。当通槽宽度为12%弦长、高度为5%叶高时,叶根通槽对通道内流动改善效果最明显,叶栅流动损失减少11.19%。In order to investigate the influence of root slot on the static cascade performance of transonic compressor,the high-load diffusion cascade model NACA65-K48 was used as the basis and the influences of root slot with different width and height on the aerodynamic performance and flow structure of the compressor cascade were studied through numerical simulation.The results show that the root slot can effectively weaken the vortex strength on the suction surface,suppress the corner separation along both the pitch and blade height directions,and reduce the flow loss of the cascade.The inhibitory effect firstly increases and then decreases with the increase of the slot width,and it shows a similar trend with the rise in the height.When the width is 12%chord and the height is 5%blade height,the root slot structure of the blade has the most significant effect on improving the flow within the slot,reducing the cascade flow loss by 11.19%.

关 键 词：叶根通槽 跨声速压气机 静叶叶栅 角区分离 流场结构 数值仿真 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]