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Publikationen am Fachgebiet Luftfahrtantriebe

Experimental Investigations on Highly Loaded Compressor Airfoils With Active Flow Control Under Non-Steady Flow Conditions in a 3D-Annular Low-Speed Cascade
Zitatschlüssel 2016_brueck_asme
Autor Brück, C. and Tiedemann, C. and Peitsch, D.
Seiten GT2016-56891
Jahr 2016
ISBN 978-0-7918-4969-9
DOI 10.1115/GT2016-56891
Ort Seoul, South Korea
Journal ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition
Jahrgang Volume 2A: Turbomachinery
Monat 06
Notiz V02AT37A027,
Technische Universität Berlin:
C. Brück, C. Tiedemann, D. Peitsch
Herausgeber ASME
Serie Turbo Expo: Power for Land, Sea, and Air
Zusammenfassung This investigation discusses the impact of a non-steady outflow condition on the compressor stator flow in an annular cascade which is periodically chocked through a rotating disc in the wake, to simulate the expected conditions for a pulsed detonation engine (PDE). A 2D controlled diffusion airfoil of the highly loaded linear stator cascade by [1] has been transferred to the annular compressor test rig to compare results under non-steady conditions via multi-colored oil flow visualization on the suction side and pressure measurements in the wake of the blades. Three different Strouhal numbers of the choking device are investigated and analyzed by phase averaged pressure measurements downstream of the stator to visualize the unsteady flow characteristics. Triggered by the changed incidence angle due to the choking, separation on the suction side and in the hub region form a periodic event depending on the position of the blockage device. Active flow control (AFC) is implemented by means of side wall actuation at the hub to improve flow conditions. Pressure measurements show that the turning of the blades can be raised and a static pressure rise is gained by the AFC while periodic choking is active.
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