基于安装角优化的吸附式压气机气动性能数值分析  

Numerical Analysis of Aerodynamic Performance of Adsorption Compressor Based on Installation Angle Optimization

作　　者：王爽 贺星[2] WANG Shuang;HE Xing(Huludao Regional Representative of The Navy,Huludao 125003,China;College of Power Engineering,Naval University of Engineering,Wuhan 430033,China)

机构地区：[1]海军驻葫芦岛地区代表室,葫芦岛125003 [2]海军工程大学动力工程学院,武汉430033

出　　处：《汽轮机技术》2020年第5期359-362,共4页Turbine Technology

摘　　要：以海军工程大学压气机试验台第一级转子为研究对象。首先分别对初始叶型和改变叶片安装角的叶型运用NUMECA软件进行数值模拟研究,得出改变叶片安装角对叶片稳定工作范围的影响,并确定叶片最佳安装角为+4°。接下来以最佳的叶片安装角叶片为原型,对该叶型进行附面层抽吸处理,并在气动性能方面与抽吸前的叶型进行对比,得出对叶片进行附面层抽吸处理后,叶片分离尾迹区宽度明显减小,流动分离明显减弱,叶片负荷增加的结论。The first-stage rotor of the compressor test bed of Naval University of Engineering was taken as the research object.Firstly,the initial blade shape and the blade shape changing the blade installation angle were numerically simulated by NUMECA software.The effect of changing the blade installation angle on the stable working range of the blade was obtained,and the optimal installation angle of the blade was determined to be+4°.Next,the best blade-mounted angle blade is used as the prototype,and the blade is subjected to the boundary layer suction treatment,and the aerodynamic performance is compared with the leaf shape before suction,It is concluded that the width of the blade separation wake zone is significantly reduced,the flow separation is obviously weakened,and the blade load is increased after the blade is subjected to the suction layer treatment.

关 键 词：安装角 压气机 附面层抽吸 数值模拟 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]