Shock Wave Boundary Layer Interaction on Suction Side of Compressor Profile in Single Passage Test Section  

作　　者：Pawel Flaszynski Piotr Doerffer Ryszard Szwaba Piotr Kaczynski Michal Piotrowicz 

机构地区：[1]The Szewalski Institute of Fluid-Flow Machinery Polish Academy of Sciences (IMP PAN)

出　　处：《Journal of Thermal Science》2015年第6期510-515,共6页热科学学报（英文版）

基　　金：supported by 7 EU framework project;project of acronym TFAST(Transition Location Effect on Shock Wave Boundary Layer Interaction);supported in part by PL-Grid Infrastructure;Numerical simulations are carried out in Academic Computer Centre(TASK)in Gdansk

摘　　要：The shock wave boundary layer interaction on the suction side of transonic compressor blade is one of the main objectives of TFAST project(Transition Location Effect on Shock Wave Boundary Layer Interaction).In order to investigate the flow structure on the suction side of a profile,a design of a generic test section in linear transonic wind tunnel was proposed.The experimental and numerical results for the flow structure investigations are shown for the flow conditions as the existing ones on the suction side of the compressor profile.Near the sidewalls the suction slots are applied for the corner flow structure control.It allows to control the Axial Velocity Density Ratio(AVDR),important parameter for compressor cascade investigations.Numerical results for Explicit Algebraic Reynolds Stress Model with transition modeling are compared with oil flow visualization,schlieren and Pressure Sensitive Paint.Boundary layer transition location is detected by Temperature Sensitive Paint.

关 键 词：transonic flow shock wave laminar-turbulent transition compressor profile 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]