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The unsteady shock-boundary layer interaction in a compressor cascade - part 3: mechanisms of shock oscillation

Munoz Lopez, Edwin Joseph and Hergt, Alexander and Klinner, Joachim and Klose, Björn and Willert, Christian and Gümmer, Volker (2024) The unsteady shock-boundary layer interaction in a compressor cascade - part 3: mechanisms of shock oscillation. ASME Journal of Turbomachinery. American Society of Mechanical Engineers (ASME). doi: 10.1115/1.4066186. ISSN 0889-504X. (In Press)

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Official URL: https://asmedigitalcollection.asme.org/turbomachinery/article/doi/10.1115/1.4066186/1202063/The-Unsteady-Shock-Boundary-Layer-Interaction-in-a

Abstract

The shock-boundary layer interaction in transonic flows is known to cause strong unsteady flow effects that negatively affect the performance and operability of blade and cascade designs. Despite decades of research on the subject, little is still known about the physical mechanisms that drive the different oscillation frequencies observed with different designs. In the conclusion of this three-part series, the experimental and numerical data obtained with the Transonic Cascade TEAMAero are analyzed together in detail in order to test the main theories of continuous shock oscillation. This analysis exposes a main mechanism of shock oscillation, where pressure waves generated inside the passage of the cascade propagate upstream and interact strongly with the main shock when the latter is also in the passage. The interaction of these features causes a breakdown of the flow that is shown to propagate upstream, inevitably causing strong variations in the inflow angle and therefore on the operating conditions of the cascade. The high frequency content of these pressure waves is also shown to be responsible for weaker high-frequency variations of the shock movement throughout the cycle. Parallels are also drawn with previous experimental campaigns in order to search for a global understanding of the different observations made. Although various parts of the described interaction are not fully understood yet, and the dataset of experimental measurements compiled is still rather small, a good basis is provided on which to further study the underlying mechanisms of unsteady flows in transonic cascades.

Item URL in elib:https://elib.dlr.de/206389/
Document Type:Article
Additional Information:Simulations were performed on the national supercomputer HPE Apollo Hawk at the High-Performance Computing Center Stuttgart (HLRS) under the grant number TCTA-SBLI/44238.
Title:The unsteady shock-boundary layer interaction in a compressor cascade - part 3: mechanisms of shock oscillation
Authors:
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
Klose, BjörnUNSPECIFIEDhttps://orcid.org/0000-0002-8069-7885UNSPECIFIED
Willert, ChristianUNSPECIFIEDhttps://orcid.org/0000-0002-1668-0181UNSPECIFIED
Gümmer, VolkerUNSPECIFIEDUNSPECIFIEDUNSPECIFIED
Date:7 August 2024
Journal or Publication Title:ASME Journal of Turbomachinery
Refereed publication:Yes
Open Access:Yes
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:Yes
DOI:10.1115/1.4066186
Publisher:American Society of Mechanical Engineers (ASME)
ISSN:0889-504X
Status:In Press
Keywords:compressors, SBLI, unsteady, experimental, PIV, CFD, LES
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, L - Future Engines and Engine Integration
Location: Köln-Porz
Institutes and Institutions:Institute of Propulsion Technology > Fan and Compressor
Deposited By: Munoz Lopez, Edwin Joseph
Deposited On:17 Sep 2024 15:09
Last Modified:17 Sep 2024 15:09

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