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Investigation of Unsteady Flow Effects in an Axial Compressor Based on Whole Annulus Computations

Röber, Thomas and Kügeler, Edmund and Weber, Anton (2010) Investigation of Unsteady Flow Effects in an Axial Compressor Based on Whole Annulus Computations. ASME TurboExpo 2010, 14-18 Jun 2010, Glasgow, UK. (In Press)

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Flows in the first stages of axial compressors are subject to a number of unsteady effects which are not generally taken into account in standard investigations, e.g. transition under the influence of impinging wakes as well as that of downstream potential effects, or the influence of unsteady blade row interactions. For numerical studies of these phenomena, usually, simplifications are made to the test case in question. These simplifications include domain scaling, quasi-unsteady modeling, or modeling assumptions regarding boundary layer development, like wall functions; and their impact on the final result can be quite high. This paper is concerned with the investigation of unsteady blade row interactions in a 4.5 stage research compressor without any of these simplifications. To this end, the whole annulus of the first two stages of the compressor was meshed and unsteady RANS simulations were carried out at two different operating points. Spatial and temporal resolutions were fine enough to allow the investigation of transitional phenomena on the blade surface using an integral multi-mode transition model. For each operating point, one revolution was recorded after computations reached a periodic state. Examination of the boundary layer parameters shows that transition plays a considerable role for the first two compressor stages which were investigated in more detail. It was evident that the development of the blade boundary layer depends not only on incoming wakes from upstream blade rows; the precise transition location is also highly dependent on the potential effect of downstream blade rows.

Item URL in elib:https://elib.dlr.de/64208/
Document Type:Conference or Workshop Item (Paper)
Title:Investigation of Unsteady Flow Effects in an Axial Compressor Based on Whole Annulus Computations
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Status:In Press
Keywords:Compressor Flow, Transition, Unsteady, CFD, Whole-Annulus Computation
Event Title:ASME TurboExpo 2010
Event Location:Glasgow, UK
Event Type:international Conference
Event Dates:14-18 Jun 2010
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Aeronautics
HGF - Program Themes:Propulsion Systems (old)
DLR - Research area:Aeronautics
DLR - Program:L ER - Engine Research
DLR - Research theme (Project):L - Fan and Compressor Technologies (old), L - Virtual Engine and Validation Methods (old)
Location: Köln-Porz
Institutes and Institutions:Institute of Propulsion Technology > Numerical Methodes > Numerical Simulation
Institute of Propulsion Technology > Numerical Methodes
Deposited By: Röber, Thomas
Deposited On:31 May 2010 10:15
Last Modified:31 May 2010 10:15

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