In order to gain a better knowledge of the mechanisms of corner stall and to calibrate computational-fluid-dynamics (CFD) tools including both Reynolds-averaged Navier-stokes and large eddy simulation, a detailed and accurate experiment of three-dimensional flow field through a linear compressor cascade has been set up. Experimental data were acquired for a Reynolds number of 3.82 × 105 based on blade chord and inlet flow conditions. First, inlet flow conditions were surveyed by hot-wire anemometry in boundary layers. Second, in order to investigate the effects of incidence, measurements then were acquired at five incidences from −2° to 6°. The results included the outlet flow variables of the cascade, measured by a five-hole pressure probe, and static pressures on both blade and endwall surfaces, measured by pressure taps. Third, the flow field details were measured at an incidence angle of 4°. In this configuration the corner stall region was large enough to be investigated, and without two-dimensional (2D) separation at mid-span on the blade suction side near the trailing edge. The velocity field was then measured by 2D Particle Image Velocimetry in cross-sections parallel to the endwall. And the velocity field in the vicinity of the blade suction side was measured with 2D Laser Dropper Anemometry. In order to test the performance of CFD and also to validate the experimental results, a series of numerical simulations were carried out and compared with the experimental results. We thus obtained a set of detailed measurements which constitute an original and complete data base and in good agreement with the published experimental results in literature. These data were also compared with CFD results and showed that the improvements needed in turbulence modeling in order to accurately simulate the three-dimensional separation configuration of corner stall.
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ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition
June 6–10, 2011
Vancouver, British Columbia, Canada
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-5467-9
PROCEEDINGS PAPER
Experimental Investigations of Corner Stall in a Linear Compressor Cascade Available to Purchase
Wei Ma,
Wei Ma
Ecole Centrale de Lyon, Lyon, France; Beijing University of Aeronautics and Astronautics, Beijing, China
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Xavier Ottavy,
Xavier Ottavy
Ecole Centrale de Lyon, Lyon, France
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Lipeng Lu,
Lipeng Lu
Beijing University of Aeronautics and Astronautics, Beijing, China
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Francis Leboeuf,
Francis Leboeuf
Ecole Centrale de Lyon, Lyon, France
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Feng Gao
Feng Gao
Ecole Centrale de Lyon, Lyon, France; Beijing University of Aeronautics and Astronautics, Beijing, China
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Wei Ma
Ecole Centrale de Lyon, Lyon, France; Beijing University of Aeronautics and Astronautics, Beijing, China
Xavier Ottavy
Ecole Centrale de Lyon, Lyon, France
Lipeng Lu
Beijing University of Aeronautics and Astronautics, Beijing, China
Francis Leboeuf
Ecole Centrale de Lyon, Lyon, France
Feng Gao
Ecole Centrale de Lyon, Lyon, France; Beijing University of Aeronautics and Astronautics, Beijing, China
Paper No:
GT2011-45236, pp. 39-51; 13 pages
Published Online:
May 3, 2012
Citation
Ma, W, Ottavy, X, Lu, L, Leboeuf, F, & Gao, F. "Experimental Investigations of Corner Stall in a Linear Compressor Cascade." Proceedings of the ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition. Volume 7: Turbomachinery, Parts A, B, and C. Vancouver, British Columbia, Canada. June 6–10, 2011. pp. 39-51. ASME. https://doi.org/10.1115/GT2011-45236
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