The experimental investigation of the unsteady flow field in a single stage low pressure axial compressor designed for a counter-rotating turbofan engine architecture is presented in this paper. The rotor casing was instrumented with fast response pressure transducers to perform a detailed survey of the tip flow features during stable operation, near stall and during stall. Tests were performed at two different Reynolds numbers representative of cruise and take-off conditions in the VKI-R4 closed loop compressor test rig. Simultaneous time-resolved measurements with a miniature fast response total pressure probe were performed by radial traverses at the rotor exit to support the tip flow field investigation. The casing measurements allow to map the direction and extension of the tip leakage vortex. The flow path measurements show its extension at the exit of the rotor blade passage and its evolution as throttling is increased towards the compressor stability limit. These experimental results are discussed and compared to CFD simulations, showing good agreement. Stall inception and rotating stall patterns are investigated as well and described in this paper. They are based both on hot wire measurements and on the casing unsteady pressure measurements.
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ASME Turbo Expo 2009: Power for Land, Sea, and Air
June 8–12, 2009
Orlando, Florida, USA
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-4888-3
PROCEEDINGS PAPER
Unsteady Pressure Measurements in a Single Stage Low Pressure Axial Compressor: Tip Vortex Flow and Stall Inception
J. F. Brouckaert,
J. F. Brouckaert
Von Karman Institute for Fluid Dynamics, Rhode-Saint-Gene`se, Belgium
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N. Van de Wyer,
N. Van de Wyer
Von Karman Institute for Fluid Dynamics, Rhode-Saint-Gene`se, Belgium
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B. Farkas,
B. Farkas
Von Karman Institute for Fluid Dynamics, Rhode-Saint-Gene`se, Belgium
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F. Ullmann,
F. Ullmann
Von Karman Institute for Fluid Dynamics, Rhode-Saint-Gene`se, Belgium
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J. Desset,
J. Desset
Von Karman Institute for Fluid Dynamics, Rhode-Saint-Gene`se, Belgium
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J. de Laborderie,
J. de Laborderie
Von Karman Institute for Fluid Dynamics, Rhode-Saint-Gene`se, Belgium
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M. Chome´,
M. Chome´
Von Karman Institute for Fluid Dynamics, Rhode-Saint-Gene`se, Belgium
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S. Hiernaux
S. Hiernaux
Techspace Aero, Milmort, Belgium
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J. F. Brouckaert
Von Karman Institute for Fluid Dynamics, Rhode-Saint-Gene`se, Belgium
N. Van de Wyer
Von Karman Institute for Fluid Dynamics, Rhode-Saint-Gene`se, Belgium
B. Farkas
Von Karman Institute for Fluid Dynamics, Rhode-Saint-Gene`se, Belgium
F. Ullmann
Von Karman Institute for Fluid Dynamics, Rhode-Saint-Gene`se, Belgium
J. Desset
Von Karman Institute for Fluid Dynamics, Rhode-Saint-Gene`se, Belgium
J. de Laborderie
Von Karman Institute for Fluid Dynamics, Rhode-Saint-Gene`se, Belgium
M. Chome´
Von Karman Institute for Fluid Dynamics, Rhode-Saint-Gene`se, Belgium
S. Hiernaux
Techspace Aero, Milmort, Belgium
Paper No:
GT2009-59771, pp. 249-262; 14 pages
Published Online:
February 16, 2010
Citation
Brouckaert, JF, Van de Wyer, N, Farkas, B, Ullmann, F, Desset, J, de Laborderie, J, Chome´, M, & Hiernaux, S. "Unsteady Pressure Measurements in a Single Stage Low Pressure Axial Compressor: Tip Vortex Flow and Stall Inception." Proceedings of the ASME Turbo Expo 2009: Power for Land, Sea, and Air. Volume 7: Turbomachinery, Parts A and B. Orlando, Florida, USA. June 8–12, 2009. pp. 249-262. ASME. https://doi.org/10.1115/GT2009-59771
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