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

被引：2
|
作者：
Kaczynski, P. [1 ]
Szwaba, R. [1 ]
机构：
[1] Polish Acad Sci IMP PAN, Inst Fluid Flow Machinery, Fiszera 14, PL-80231 Gdansk, Poland
来源：
XXII FLUID MECHANICS CONFERENCE (KKMP2016) | 2016年 / 760卷
关键词：
D O I：
10.1088/1742-6596/760/1/012007
中图分类号：
O3 [力学];
学科分类号：
08 ; 0801 ;
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.
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页数：9
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