Influence of cooling intensity on shock wave boundary layer interaction region in turbine cascade

22nd Fluid Mechanics Conference

物理学;力学

Kaczyski, P.^1 ; Szwaba, R.^1

Institute of Fluid-Flow Machinery, Polish Academy of Sciences (IMP PAN), Fiszera 14, Gdansk

80-231, Poland^1

关键词: Blade cooling systems;    Cooling intensity;    Experimental investigations;    Interaction region;    Normal shock waves;    Shock wave boundary layer interactions;    Transonic turbine;    Transonic wind tunnels;   

Others  :  https://iopscience.iop.org/article/10.1088/1742-6596/760/1/012007/pdf
DOI  :  10.1088/1742-6596/760/1/012007

学科分类：力学，机械学

来源: IOP

【 摘 要 】

The shock wave boundary layer interaction on the suction side of a transonic turbine blade was one of the main objectives of the TFAST project. For this purpose a model of a turbine passage was designed, manufactured and assembled in a transonic wind tunnel. The paper presents the experimental investigations concerning the flow structure on the transonic turbine blade. A clean case (without a cooling system) with a normal shock wave interacting with a laminar boundary layer and also the influence of the blade cooling system with three different coolant blowing intensities on the laminar interaction region were investigated.