This paper investigates numerically the effects of shrouded stator seal cavity flows on a high-speed, six-stage, advanced axial-flow compressor performance. Two cases of fully three-dimensional unsteady Reynolds-averaged Navier-Stokes simulations are performed. The first case includes only the main flow path without cavities, while the second case takes into account the effect of cavities by fully meshing and solving the seal cavity flows under each of the stator vanes. Both simulations included rotor blade tip clearances. The latter case showed 1.7 point degradation in efficiency from the first case. Contributors to the overall performance degradation, such as windage heating, mixing loss due to seal leakage flow with the main flow, and additional loss of the rotors and stators due to alteration in velocity triangles, are identified by comparing the two simulation results. Compared to theoretical or semi-empirical leakage and windage models, higher loss production and temperature rise are found especially in mid to rear stages. Unsteady effects for such differences are discussed.
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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
The Influence of Shrouded Stator Cavity Flows on the Aerodynamic Performance of a High-Speed Multistage Axial-Flow Compressor
Mai Yamagami,
Mai Yamagami
IHI Corporation, Mizuho, Tokyo, Japan
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Naoki Tsuchiya,
Naoki Tsuchiya
IHI Corporation, Mizuho, Tokyo, Japan
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Hidekazu Kodama
Hidekazu Kodama
IHI Corporation, Mizuho, Tokyo, Japan
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Dai Kato
IHI Corporation, Mizuho, Tokyo, Japan
Mai Yamagami
IHI Corporation, Mizuho, Tokyo, Japan
Naoki Tsuchiya
IHI Corporation, Mizuho, Tokyo, Japan
Hidekazu Kodama
IHI Corporation, Mizuho, Tokyo, Japan
Paper No:
GT2011-46300, pp. 297-307; 11 pages
Published Online:
May 3, 2012
Citation
Kato, D, Yamagami, M, Tsuchiya, N, & Kodama, H. "The Influence of Shrouded Stator Cavity Flows on the Aerodynamic Performance of a High-Speed Multistage Axial-Flow Compressor." 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. 297-307. ASME. https://doi.org/10.1115/GT2011-46300
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