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Aero EnginesSFB 1029 (TurbIn), B05 Eng

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SFB 1029 (TurbIn), B01

Low-Speed annular compressor cascade in the TurboLab at the chair of aero engines.
Lupe


Active flow control in a compressor stator under highly unsteady inflow and outflow conditions

This project is part of the research cluster SFB1029 TurbIn - Substantial efficiency increase in gas turbines through direct use of coupled unsteady combustion and flow dynamics.

At the annular cascade strongly three-dimensional secondary flow develop at the blade-wall-intersection, which is pronounced stronger at the hub than the tip, due to higher loading. To further develop the active flow and closed loop control approaches of the first funding period, this asymmetric flow pattern is simulated in the 2D cascade using a contoured wall while for the annular cascade a 3D blade design is developed to relieve the hub region. In addition to the periodic throttling due to the CVC, the influence of rotor-stator interaction is investigated for active flow control. In addition, trailing edge blowing developed in TP B06 is transferred to the annular cascade and tested in combination with the side wall blowing. Furthermore, experimental and numerical investigations of different concepts of adaptive blade using piezo actuators are validated and verified on the modified 2D-cascade. The results from the 2D-cascade are used to development a design concept of a measuring section for the 3D-test rig to investigate the suitable piezoelectric adaptive blade.

Poster_SFB_B01

Person of contact: Dipl.-Ing. Jan Mihalyovics
Person of contact: Dipl.-Ing. Christian Brück

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References

  • Experimental Investigations on Highly Loaded Compressor Airfoils with Active Flow Control under Non-Steady Flow Conditions in a 3D-Annular Low-Speed Cascade
    C. Brück, C. Tiedemann, D. Peitsch
    ASME Turbo Expo 2016,
    Seoul, South Korea, June 13-17, 2016, GT2016-56891,
    https://doi.org/10.1115/GT2016-56891 .



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