Investigations of shock wave boundary layer interaction on suction side of compressor profile

21st Fluid Mechanics Conference

物理学;力学

Piotrowicz, M.^1 ; Flaszyn´ski, P.^1 ; Doerffer, P.^1

Transonic Flows and Numerical Methods Department, Szewalski Institute of Fluid-Flow Machinery (IMP PAN), 14 Fiszera Street, Gdan´sk 80-231, Poland^1

关键词: Boundary layer development;    Shock wave boundary layer interactions;    Suction side;    Test sections;    Transition locations;    Transonic compressor blades;    Transonic wind tunnels;   

Others  :  https://iopscience.iop.org/article/10.1088/1742-6596/530/1/012068/pdf
DOI  :  10.1088/1742-6596/530/1/012068

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 transonic compressor blade is one of main objectives of TFAST project (Transition Location Effect on Shock Wave Boundary Layer Interaction). In order to look more closely into the flow structure on the suction side of a blade, a design of a generic test section in linear transonic wind tunnel was proposed. The test section which could reproduce flow structure, shock wave location, pressure distribution and boundary layer development similar to the obtained on a cascade profile is the main objective of the presented here design. The design of the proposed test section is very challenging, because of shock wave existence, its interaction with boundary layer and its influence on the 3-D flow structure in the test section.