M.W. Leitner, M. Zippel, S. Staudacher

In axial compressors tip leakage flow is disadvantageous to efficiency and mass flow stability. The interaction of tip leakage flow with incoming flow in a compressor cascade is investigated on a water channel at various tip clearance width and angles of incidence. To study the flow, we considered the movement of inked fluid elements in space and time. By increasing the angle of incidence the flow rate is decreased and the stability limit is exceeded. The arising instability phenomena are described under various conditions. The temporal evolution of a tip leakage vortex breakdown is visualized in detail. A sudden expansion of the vortex with the formation of a recirculation region is observed. This causes a large blockage effect with significant impact on the incoming flow. The stability limit is found. It depends on the tip clearance width. A strong tip leakage vortex supports the beginning of instability.

Deutscher Luft- und Raumfahrtkongress 2017, München

Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2017

Conference Paper

englisch

21,0 x 29,7 cm, 10 Seiten

urn:nbn:de:101:1-201709294932

compressor cascade, tip leakage flow

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29.09.2017