进口气流角对跨音速压气机气动性能的影响研究  

Influence Research of Inlet Flow Angle on the Aerodynamic Performance of a Transonic Compressor

作　　者：党芳 张春梅 DANG Fang;ZHANG Chunmei(VMI(Yantai)Machinery Co.,Ltd.,Yantai 265503,China;Harbin Electric Power Generation Equipment National Engineering Research Center Co.,Ltd.,Harbin 150000,China)

机构地区：[1]飞迈(烟台)机械有限公司,山东烟台265503 [2]哈电发电设备国家工程研究中心有限公司,哈尔滨150000

出　　处：《机械工程师》2020年第8期54-56,共3页Mechanical Engineer

摘　　要：以某燃气轮机1.5级跨音速压气机为研究对象,利用NUMECA软件计算了该压气机在不同进口可转导叶摆放角度情况下跨音速压气机的气动性能。研究结果表明:随着进口气流角的增大,流量-效率曲线和流量-压比曲线均向流量减小的方向平移,相同流量下,进口气流角增加,效率增大,但压比减小;在设计流量工况下,随着进口气流角的增大,来流相对马赫数减小,激波强度减弱,并向尾缘迁移,激波后附面层分离流动改善,压气机损失减小。This paper takes a 1.5-stage transonic compressor in gas turbine as the research object,NUMECA software is used to analyze the aerodynamic performance of transonic compressor at four different angles of inlet vanes.The results show that with the increase of the inlet flow angle,both the flow-efficiency curve and the flow-pressure ratio curve are shifted to the direction of flow reduction,under the same flow,the inlet flow angle increases,the efficiency increases,but the pressure ratio decreases.Under the design flow condition,as the inlet airflow angle increases,the relative Mach number of incoming flow decreases,the intensity of the shock wave weakens,and migrates towards the trailing edge.After the shock wave,the separation flow of the boundary layer is improved,and the compressor loss is reduced.

关 键 词：跨音速压气机 湍流模型 相对马赫数 数值分析 

分 类 号：O345.2[理学—固体力学]