叶型附面层分离流动控制技术研究进展  

Advances in Flow Control Technology of Boundary Layer Separation on the Blade

作　　者：周敏[1] 李航航[1] 唐侃平[1] 

机构地区：[1]北京航空工程技术研究中心,北京100076

出　　处：《航空工程进展》2011年第3期298-304,共7页Advances in Aeronautical Science and Engineering

摘　　要：叶型附面层分离流动控制技术,通过流动控制方法减小和控制叶片吸力面附面层的分离气流和低能流团,提高压气机或涡轮的效率和工作稳定性。主要介绍了国外研发的涡流发生器、射流注入、附面层抽吸、叶片附面层转捩控制和等离子体气动激励等流动控制技术的特点、作用机理和实验验证结果,以及国内在叶型附面层分离流动控制技术方面的研究进展。The flow control technology of boundary layer separation on the blade is applied to minish and control boundary layer separation and low energy flow on the blade suction surface to improve the efficiency and stability of compressor and turbine.The characteristic and effect mechanism of several kinds of flow control technology are presented in this paper,such as vortex generator jets,jet injection,boundary layer suction,boundary layer transition control and plasma assisted flow control.The domestic development of flow control technology of boundary layer separation on the blade is introduced.

关 键 词：附面层分离 涡流发生器 射流注入 附面层抽吸 叶片附面层转捩控制 等离子体气动激励 

分 类 号：V233[航空宇航科学与技术—航空宇航推进理论与工程]