The large secondary flow area in the compressor hub-corner region usually leads to three-dimensional separation in the passage with large amounts of total pressure loss. In this paper numerical simulations of a linear high-speed compressor cascade, consisting of five NACA 65-K48 stator profiles, were performed to analyze the flow mechanism of hub-corner separation for the base flow. Experimental validation is used to verify the numerical results. Active control of the hub-corner separation was investigated by using boundary layer suction. The influence of the selected locations of the endwall suction slot was investigated in an effort to quantify the gains of the compressor cascade performance. The results show that the optimal chordwise location should contain the development section of the three-dimensional corner separation downstream of the 3D corner separation onset. The best pitchwise location should be close enough to the vanes’ suction surface. Therefore the optimal endwall suction location is the MTE slot, the one from 50% to 75% chord at the hub, close to the blade suction surface. By use of the MTE slot with 1% suction flow ratio, the total-pressure loss is substantially decreased by about 15.2% in the CFD calculations and 9.7% in the measurement at the design operating condition.
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ASME Turbo Expo 2014: Turbine Technical Conference and Exposition
June 16–20, 2014
Düsseldorf, Germany
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-4560-8
PROCEEDINGS PAPER
Location Effect of Boundary Layer Suction on Compressor Hub-Corner Separation
Ping-Ping Chen,
Ping-Ping Chen
Northwestern Polytechnical University, Xi’an, China
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Wei-Yang Qiao,
Wei-Yang Qiao
Northwestern Polytechnical University, Xi’an, China
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Karsten Liesner,
Karsten Liesner
German Aerospace Center (DLR), Berlin, Germany
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Robert Meyer
Robert Meyer
German Aerospace Center (DLR), Berlin, Germany
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Ping-Ping Chen
Northwestern Polytechnical University, Xi’an, China
Wei-Yang Qiao
Northwestern Polytechnical University, Xi’an, China
Karsten Liesner
German Aerospace Center (DLR), Berlin, Germany
Robert Meyer
German Aerospace Center (DLR), Berlin, Germany
Paper No:
GT2014-25043, V02AT37A003; 15 pages
Published Online:
September 18, 2014
Citation
Chen, P, Qiao, W, Liesner, K, & Meyer, R. "Location Effect of Boundary Layer Suction on Compressor Hub-Corner Separation." Proceedings of the ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. Volume 2A: Turbomachinery. Düsseldorf, Germany. June 16–20, 2014. V02AT37A003. ASME. https://doi.org/10.1115/GT2014-25043
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