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International Journal of Rotating Machinery
Volume 2008 (2008), Article ID 657202, 10 pages
Research Article

Simulation of Casing Treatments of a Transonic Compressor Stage

1Institute for Flight Propulsion, Technische Universität München, Boltzmannstraße 15, 85747 Garching, Germany
2Compressor Aerodynamics, Rolls-Royce Deutschland, Eschenweg 11, 15827 Dahlewitz Berlin, Germany

Received 31 March 2008; Accepted 1 October 2008

Academic Editor: Chunill Hah

Copyright © 2008 M. Hembera et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.


This article presents the study of casing treatments on an axial compressor stage for improving stability and enhancing stall margin. So far, many simulations of casing treatments on single rotor or rotor-stator configurations were performed. But as the application of casing treatments in engines will be in a multistage compressor, in this study, the axial slots are applied to a typical transonic first stage of a high-pressure 4.5-stage compressor including an upstream IGV, rotor, and stator. The unsteady simulations are performed with a three-dimensional time accurate Favre-averaged Navier-stokes flow solver. In order to resolve all important flow mechanisms appearing through the use of casing treatments, a computational multiblock grid consisting of approximately 2.4 million nodes was used for the simulations. The configurations include axial slots in 4 different variations with an axial extension ranging into the blade passage of the IGV. Their shape is semicircular with no inclination in circumferential direction. The simulations proved the effectiveness of casing treatments with an upstream stator. However, the results also showed that the slots have to be carefully positioned relative to the stator location.