Surface roughness effect on shock wave boundary layer interaction on transonic compressor profile
Identyfikator grantu: PT01122
Kierownik projektu: Paweł Flaszyński
Realizatorzy:
- Ahmed Hanfy
Instytut Maszyn Przepływowych PAN w Gdańsku
Gdańsk
Data otwarcia: 2024-02-22
Streszczenie projektu
The research focuses on investigating the interaction between a shock wave and the boundary layer on an aircraft compressor rotor profile. Experimentally, the impact of surface roughness on the boundary layer on the suction side of the blade and its interaction with the shock wave. This study is conducted as part of the European project H2020-MSCA-ITN TEAMAero, in collaboration with other partners dedicated to research in the field of aircraft compressors. The specialized test section has been designed and installed at the Institute of Fluid-Flow Machinery (IMP PAN) transonic wind tunnel to replicate shock waves within a compressor rotor passage.
For the purpose of test planning, as well as modeling and analysis, Siemens NX CAD software is employed. Additionally, Ansys Fluent is utilized for CFD simulation on a limited scale, strategically integrated into the test planning process. This simulation aims to assess potential interference and evaluate the impact of various devices on flow conditions. Finally, the acquired experimental data will be analyzed using MATLAB.
For the purpose of test planning, as well as modeling and analysis, Siemens NX CAD software is employed. Additionally, Ansys Fluent is utilized for CFD simulation on a limited scale, strategically integrated into the test planning process. This simulation aims to assess potential interference and evaluate the impact of various devices on flow conditions. Finally, the acquired experimental data will be analyzed using MATLAB.