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

[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.

[发布机构] Institute of Fluid-Flow Machinery, Polish Academy of Sciences (IMP PAN), Fiszera 14, Gdansk; 80-231, Poland^1

[效力级别] 力学 [学科分类] 力学，机械学

[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