TU Berlin

Aero EnginesPublications

Logo Fachgebiet Luftfahrtantriebe

Page Content

to Navigation

Publications at Chair of Aero Engines

Impact of Hub Clearance on Endwall Flow in a Highly Loaded Axial Compressor Stator
Citation key 2013_beselt_asme
Author Beselt, C. and van Rennings, R. and Peitsch, D. and Thiele, F.
Pages GT2013-95463
Year 2013
ISBN 978-0-7918-5524-9
DOI 10.1115/GT2013-95463
Location San Antonio, Texas, USA
Journal ASME Turbo Expo 2013: Turbine Technical Conference and Exposition
Volume Volume 6C: Turbomachinery
Month 06
Note V06CT42A034,
Technische Universit├Ąt Berlin:
C. Beselt, R. van Rennings, D. Peitsch, F. Thiele
Editor ASME
Series Turbo Expo: Power for Land, Sea, and Air
Abstract Within the present paper the development and interaction of secondary flow structures at different hub clearance gaps at high blade loadings are investigated. Three-dimensional numerical computations were carried out at three levels of hub clearance, ranging from zero to 3% of blade chord. Experimental results at 1% and 3% chord hub clearance were obtained to asses the validity of the numerical predictions. The experimentally and numerically obtained results provide a detailed picture of the development, the interaction of secondary flow structures and the influence of clearance flow for high blade loading. Therefore the time averaged flow features obtained from the experimental test rig and from numerical simulations are compared. In addition this investigation tends to explain the phenomenon of rotating instability for this compressor stator at a specific operating point and different hub clearance gaps by analyzing the secondary flow structures in the leading edge region at the hub.
Link to publication Download Bibtex entry

To top


Quick Access

Schnellnavigation zur Seite über Nummerneingabe