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INFLUENCE OF LIMITING WALLS ON SHOCK WAVE STRUCTURE IN SINGLE PASSAGE TEST SECTION WITH COMPRESSOR PROFILE

Abstract

The shock wave boundary layer interaction on the suction side of a transonic compressor blade is one of the main objectives of the 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 the blade, a design of a turbine passage model in a rectilinear transonic wind tunnel was proposed. The model which could reproduce the flow structure, the shock wave location, the pressure distribution and the boundary layer development similar to the obtained in a reference cascade profile is the main objective of the design presented here. The design of the proposed test section is very challenging, because of the existence of a shock wave, its interaction with the boundary layer and its influence on the 3-D flow structure in the test section. The paper presents the influence of the test section geometry configuration on the flow structure as an effect of the shock wave boundary layer interaction.

Keywords:

shock wave, laminar-turbulent transition, transonic compressor

Details

Issue
Vol. 19 No. 2 (2015)
Section
Research article
Published
2015-06-30
DOI:
https://doi.org/10.17466/TQ2015/19.2/H
Licencja:
Creative Commons License

This work is licensed under a Creative Commons Attribution 4.0 International License.

Author Biography

RYSZARD SZWABA,
Szewalski Institute of Fluid-Flow Machinery (IMP PAN), Experimental Aerodynamics Department



Authors

  • MICHAŁ PIOTROWICZ

    Szewalski Institute of Fluid-Flow Machinery (IMP PAN), Aerodynamics Department
  • PAWEŁ FLASZYŃSKI

    Szewalski Institute of Fluid-Flow Machinery (IMP PAN), Aerodynamics Department
  • RYSZARD SZWABA

    Szewalski Institute of Fluid-Flow Machinery (IMP PAN), Experimental Aerodynamics Department

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