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Effect of segment end wall boundary layer suction on compressor 3D corner separation

Chen, P. and Qiao, W. and Liesner, Karsten and Meyer, Robert (2015) Effect of segment end wall boundary layer suction on compressor 3D corner separation. In: Proceedings of ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. ASME Turbo Expo 2015: Turbine Technical Conference and Exposition, 15.-19.06.2015, Montréal, Canada.

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Item URL in elib:https://elib.dlr.de/102021/
Document Type:Conference or Workshop Item (Speech)
Title:Effect of segment end wall boundary layer suction on compressor 3D corner separation
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Chen, P.Northwestern Ploytechnical University, Xi'an, ChinaUNSPECIFIED
Qiao, W.Northwestern Polytechnical University, Xian, ChinaUNSPECIFIED
Liesner, Karstenkarsten.liesner (at) dlr.deUNSPECIFIED
Meyer, Robertrobert.meyer (at) dlr.deUNSPECIFIED
Date:June 2015
Journal or Publication Title:Proceedings of ASME Turbo Expo 2015: Turbine Technical Conference and Exposition
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Status:Published
Keywords:comressor, Verdichter, Corner Separation, Eckenablösung, flow control, Strömungsbeeinflussung, boundary layer suction, Grenzschichtabsaugung
Event Title:ASME Turbo Expo 2015: Turbine Technical Conference and Exposition
Event Location:Montréal, Canada
Event Type:international Conference
Event Dates:15.-19.06.2015
Organizer:ASME - International Gas Turbine Institute
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-Charlottenburg
Institutes and Institutions:Institute of Propulsion Technology > Engine Acoustic
Deposited By: Meyer, Dr.-Ing. Robert
Deposited On:12 Jan 2016 15:26
Last Modified:10 May 2016 23:41

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