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Effect of Boundary Layer Suction on Compressor Hub-Corner Separation, Part I: Chord-wise and Pitch-wise Location

Chen, Pingping and Qiao, Weiyang and Liesner, Karsten and Meyer, Robert (2014) Effect of Boundary Layer Suction on Compressor Hub-Corner Separation, Part I: Chord-wise and Pitch-wise Location. In: ASME Turbo Expo 2014, GT2014 (25043). ASME Turbo Expo 2014: Turbine Technical Conference and Exposition, 16.-20. Juni 2014, Düsseldorf, Germany.

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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.

Item URL in elib:https://elib.dlr.de/94510/
Document Type:Conference or Workshop Item (Speech)
Title:Effect of Boundary Layer Suction on Compressor Hub-Corner Separation, Part I: Chord-wise and Pitch-wise Location
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Chen, PingpingNorthwestern Polytechnical University, ChinaUNSPECIFIED
Qiao, WeiyangNorthwestern Polytechnical University, ChinaUNSPECIFIED
Date:16 June 2014
Journal or Publication Title:ASME Turbo Expo 2014
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Keywords:compressor cascade, activ flow-control, suction
Event Title:ASME Turbo Expo 2014: Turbine Technical Conference and Exposition
Event Location:Düsseldorf, Germany
Event Type:international Conference
Event Dates:16.-20. Juni 2014
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:propulsion systems
DLR - Research area:Aeronautics
DLR - Program:L ER - Engine Research
DLR - Research theme (Project):L - Fan and Compressor Technologies
Location: Berlin-Adlershof
Institutes and Institutions:Institute of Propulsion Technology > Engine Acoustic
Deposited By: Meyer, Dr.-Ing. Robert
Deposited On:15 Jan 2015 15:58
Last Modified:15 Jan 2015 15:58

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