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A New Linear High Speed Compressor Stator Cascade for Active Flow Control Investigations
Citation key 2012_tiedemann_6aiaafcc
Author Tiedemann, C. and Heinrich, A. and Peitsch, D.
Title of Book AIAA - 6th Flow Control Conference
Year 2012
ISBN 978-1-62410-188-5
DOI 10.2514/6.2012-3251
Location New Orleans, Louisiana, USA
Month 06
Note Technische Universität Berlin:
C. Tiedemann, A. Heinrich, D. Peitsch
Publisher American Institute of Aeronautics and Astronautics
Chapter AIAA-2012-3251
Abstract At the Institute of Aeronautics and Astronautics of the Technical University of Berlin, a linear stator cascade test facility for active flow control investigations has been developed and tested at high speed flow conditions. The compressor blades were designed as critically loaded controlled diffusion airfoils (CDA) for an upstream Mach number of M = 0.75 and a Reynolds number of Re = 1.1 · 10^6 based on the axial chord. An analysis of the baseline cascade flow reveals complex three-dimensional secondary flow phenomena. The paper will show how these can be supressed by active flow control (AFC) methods to receive a higher stage pressure ratio or a lower total pressure loss respectively and where limits can be found. For this purpose, actuators for steady and pulsed blowing through a side wall slit have been developed. A detailed investigation of the base flow and first tests of the actuation method in the cascade test rig have been carried out to investigate the effect of AFC.
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