Study on the transition mechanism of vibrating low-pressure turbine blades based on large Eddy simulation

被引:0
作者
Zhang, Yingqiang [1 ,2 ]
Xu, Dong [2 ]
Xuan, Wu [1 ,4 ]
Zhang, Yanfeng [2 ,3 ]
Lu, Xingen [2 ,3 ]
Zhu, Junqiang [2 ,3 ]
机构
[1] North China Elect Power Univ, Sch Energy Power & Mech Engn, Beijing 102206, Peoples R China
[2] Chinese Acad Sci, Key Lab Light Duty Gas Turbine, Inst Engn Thermophys, Beijing 100190, Peoples R China
[3] Univ Chinese Acad Sci, Beijing 100049, Peoples R China
[4] Univ Sci & Technol China, Hefei 230026, Peoples R China
关键词
Blade vibration; Low-pressure turbine blade; Separate; Transition; Aerodynamic losses;
D O I
10.1016/j.ast.2024.109695
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
The low-pressure turbine blades are susceptible to vibration issues due to their thin profiles and large aspect ratios. Blade vibration will significantly affect the evolution of the boundary layer and the flow state. This paper utilizes large eddy simulation to predict the development of the boundary layer on the suction side of lowpressure turbine blades at low Reynolds numbers (Re = 25,000). It introduces different vibration cases to elucidate the mechanisms by which blade vibrations influence boundary layer separation and transition. The study demonstrates that the introduction of vibration cases significantly reduces both the size of the overall spanwise vortices and their roll-up height. A staggered distribution of spanwise vortices, characterized by alternating high and low regions, is observed near the trailing edge of the vibrating blades. The shorter spanwise vortices develop rapidly, nearly traversing the process of hairpin vortices (Lambda vortex) generation and development, and directly breaking down into smaller-scale vortices. This accelerates the transition process. Blade vibration primarily promotes turbulence reattachment by facilitating the transition process dominated by the K-H instability mechanism within the separating shear layer. Consequently, it effectively restricts the growth of the separation bubble on the suction side of the blades, significantly reducing aerodynamic losses. Moreover, increasing the vibration frequency within a certain range can amplify these effects, achieving up to a 23% reduction in total pressure loss compared to stationary blades.
引用
收藏
页数:10
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