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Investigations of the Unsteady Shock-Boundary Layer Interaction in a Transonic Compressor Cascade

Munoz Lopez, Edwin Joseph and Hergt, Alexander and Klinner, Joachim and Grund, Sebastian and Karboujian, Jirair and Flamm, Jasmin and Gümmer, Volker (2023) Investigations of the Unsteady Shock-Boundary Layer Interaction in a Transonic Compressor Cascade. In: ASME Turbo Expo 2023: Turbomachinery Technical Conference and Exposition, GT 2023, 13D, V13DT36A015. The American Society of Mechanical Engineers. ASME Turbo Expo 2023, 16-30 June 2023, Boston, USA. doi: 10.1115/GT2023-102622. ISBN 978-0-7918-8711-0. (In Press)

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Official URL: https://asmedigitalcollection.asme.org/GT/proceedings-abstract/GT2023/87110/V13DT36A015/1168672


The performance of compressor blades in transonic flow conditions is heavily hampered by unsteady flow effects caused by the Shock-Boundary Layer Interaction (SBLI). Even though these effects have been subject to research for a long period of time, very little is still known about the physical mechanisms driving the unsteadiness. In order to help elucidate the nature of these interactions in turbomachines, the recently designed Transonic Cascade TEAMAero was tested at the DLR's Transonic Cascade Wind Tunnel facility in Cologne. The cascade flow was measured with a unique high-speed Schlieren configuration capturing three adjacent passages simultaneously, along with unsteady total pressure measurements at the outlet, and unsteady acceleration measurements on the tunnel sidewalls. The results indicate that the main oscillation of the shocks is broadband at relatively low frequencies around 550 Hz for the aerodynamic design point, and 180 Hz for the off-design point. A further high-frequency tone is observed around 1140 Hz throughout. These frequencies were also observed with the different measurement devices employed. Cross-correlations between the signals indicate that there are different mechanisms at play between the passages that cause both upstream and downstream transmission of information. Because of this, the shock oscillations were not always in-phase between adjacent passages. The results help characterize the SBLI behavior of the cascade in the wind tunnel, aiding future numerical and experimental efforts aiming to decipher the inherent mechanisms causing it.

Item URL in elib:https://elib.dlr.de/196730/
Document Type:Conference or Workshop Item (Lecture)
Title:Investigations of the Unsteady Shock-Boundary Layer Interaction in a Transonic Compressor Cascade
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Munoz Lopez, Edwin JosephUNSPECIFIEDhttps://orcid.org/0000-0003-4511-037XUNSPECIFIED
Hergt, AlexanderUNSPECIFIEDhttps://orcid.org/0009-0008-1643-7326UNSPECIFIED
Klinner, JoachimUNSPECIFIEDhttps://orcid.org/0000-0003-2709-9664UNSPECIFIED
Journal or Publication Title:ASME Turbo Expo 2023: Turbomachinery Technical Conference and Exposition, GT 2023
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Page Range:V13DT36A015
Publisher:The American Society of Mechanical Engineers
Series Name:Turbo Expo: Power for Land, Sea, and Air
Status:In Press
Keywords:Compressors, SBLI, Experimental, Unsteady, Schlieren
Event Title:ASME Turbo Expo 2023
Event Location:Boston, USA
Event Type:international Conference
Event Dates:16-30 June 2023
Organizer:The American Society of Mechanical Engineers
HGF - Research field:Energy
HGF - Program:Materials and Technologies for the Energy Transition
HGF - Program Themes:High-Temperature Thermal Technologies
DLR - Research area:Energy
DLR - Program:E VS - Combustion Systems
DLR - Research theme (Project):E - Gas Turbine
Location: Köln-Porz
Institutes and Institutions:Institute of Propulsion Technology > Fan and Compressor
Deposited By: Munoz Lopez, Edwin Joseph
Deposited On:29 Aug 2023 08:54
Last Modified:13 Nov 2023 08:42

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