具有叶顶间隙扩压叶栅附面层抽吸研究  

Investigation of Boundary Layer Suction on Compressor Cascade With Tip Clearance

作　　者：陆华伟[1] 张永超[1] 康达[1] 刘斌[1] 

机构地区：[1]大连海事大学轮机工程学院,大连116026

出　　处：《工程热物理学报》2016年第2期277-284,共8页Journal of Engineering Thermophysics

基　　金：国家自然科学基金资助项目(No.5120613);高等学校博士学科点专项科研基金(No.20112125120009);中央高校基本科研业务费专项资金(No.3132014049)

摘　　要：借助实验校核CFD方法对具有叶顶间隙扩压叶栅进行了数值模拟,分别探究了叶顶开槽、吸力面端部开槽及叶顶-吸力面端部组合开槽进行附面层抽吸对其性能的影响,并从旋涡结构角度阐述其控制机理。结果表明,叶顶抽吸可以推迟泄漏涡的生成,有效抑制泄漏流的发展,降低其损失,端部抽吸则可以吸除角区低能流体团,减小端部损失,通过二者的组合,叶栅总压损失显著降低,气流折转能力加强。The numerical simulation that was verified by an experiment was conducted to study the high-load compressor cascade with tip clearance.In this paper,the influence of the boundary layer suction on its performance is respectively explored where suction slot is separated located in tip,suction side end and tip-suction side end combination.And its control mechanism is explained from the perspective of vortex system.Results show that slot in tip location can postpone the generation of leakage vortex,restrain the development of it effectively and reduce leakage losses.While slot located in suction side end can remove low-energy fluid gathering in corner which better decrease the corner separation.Total pressure loss in cascade reduced significantly by the combination of both of them.In the meantime,flow deflection ability is strengthened.

关 键 词：扩压叶栅 叶顶间隙 附面层抽吸 泄漏流 旋涡结构 

分 类 号：V235.11[航空宇航科学与技术—航空宇航推进理论与工程]