Influence of cooling intensity on shock wave boundary layer interaction region in turbine cascade
2016; IOP Publishing; Volume: 760; Linguagem: Inglês
10.1088/1742-6596/760/1/012007
ISSN1742-6596
AutoresPiotr Kaczyński, Ryszard Szwaba,
Tópico(s)Computational Fluid Dynamics and Aerodynamics
ResumoThe 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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