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AEROELASTIC INVESTIGATION OF AN ANNULAR TRANSONIC COMPRESSOR CASCADE: NUMERICAL SENSITIVITY STUDY FOR VALIDATION PURPOSES

Chenaux, Virginie Anne and Grueber, Bjoern (2015) AEROELASTIC INVESTIGATION OF AN ANNULAR TRANSONIC COMPRESSOR CASCADE: NUMERICAL SENSITIVITY STUDY FOR VALIDATION PURPOSES. In: Proceedings of the ASME Turbo Expo. ASME. ASME Turbo Expo Konferenz 2015, 15.-19. Juni 2015, Montreal, Kanada.

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Abstract

The accuracy of flutter or forced response analyses of turbomachinery blade assemblies strongly depends on the correct prediction of the unsteady aerodynamic loads acting on the vibrating blades. This paper presents the aeroelastic numerical results of an annular transonic compressor cascade subjected to harmonic oscillation conditions. The measurements associated were performed in an annular test facility for non-rotating cascades. The aim of this investigation is to get a deeper understanding of the specific characteristics of this test facility as well as improving the flutter prediction procedure and accuracy. For a subsonic and a transonic flow condition, the steady-state blade surface pressure distributions were predicted with two mesh configurations and results were compared to the experimental results. The first configuration omits the geometrical complexity of the experimental model and only models the blade passage. The second mesh configuration includes the cascade’s detailed geometry and cavities. The presence of leakage flows arisen due to the cascade’s slits and cavities are identified and their impact on the main flow field is analyzed and discussed. For the flutter computations, two mesh resolutions were investigated. The global damping predicted with a fine and a coarse mesh was compared, as well as the local pressure amplitudes and phases predicted with both configurations. Results show that even though similar global damping curves are predicted with both mesh resolution, for some IBPAs, local differences exist on the pressure amplitudes and phases. This highlights that only comparing the global damping coefficient, is not sufficient for code validation.

Item URL in elib:https://elib.dlr.de/97925/
Document Type:Conference or Workshop Item (Speech)
Title:AEROELASTIC INVESTIGATION OF AN ANNULAR TRANSONIC COMPRESSOR CASCADE: NUMERICAL SENSITIVITY STUDY FOR VALIDATION PURPOSES
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Chenaux, Virginie Annevirginie.chenaux (at) dlr.deUNSPECIFIED
Grueber, Bjoernbjoern.grueber (at) mtu.deUNSPECIFIED
Date:15 June 2015
Journal or Publication Title:Proceedings of the ASME Turbo Expo
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:No
Publisher:ASME
Status:Published
Keywords:numerical flutter predictions, secondary flows, aerodynamic damping, unsteady pressures, sensitivity study, validation.
Event Title:ASME Turbo Expo Konferenz 2015
Event Location:Montreal, Kanada
Event Type:international Conference
Event Dates:15.-19. Juni 2015
Organizer:ASME
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 - Virtual Engine and Validation methods
Location: Göttingen
Institutes and Institutions:Institute of Aeroelasticity > Aeroelastic Experiments
Deposited By: Chenaux, Virginie
Deposited On:13 Oct 2015 09:28
Last Modified:09 Feb 2018 13:02

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