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The Impact of Viscous Effects on the Aerodynamic Damping of Vibrating Transonic Compressor Blades

Grüber, B. and Carstens, V. (2001) The Impact of Viscous Effects on the Aerodynamic Damping of Vibrating Transonic Compressor Blades. Journal of Turbomachinery, 123 (2), pp. 409-417.

Full text not available from this repository.

Abstract

A parametric study which investigates the influence of viscous effects on the damping behavior of vibrating compressor cascades is presented here. To demonstrate the dependence of unsteady aerodynamic forces on the flow viscosity, a computational study was performed for a transonic compressor cascade of which the blades underwent tuned pitching oscillations while the flow conditions extended from fully subsonic to highly transonic flow. Additionally, the reduced frequency and Reynolds number were varied. In order to check the linear behavior of the aerodynamic forces, all calculations were carried out for three different oscillation amplitudes. Comparisons with inviscid Euler results helped identify the influence of viscous effects. The computations were performed with a Navier-Stokes code, the basic features of which are the use of an AUSM upwind scheme, an implicit time integration, and the implementation of the Baldwin-Lomax turbulence model. In order to demonstrate the possibility of this code to correctly predict the unsteady behavior of strong shock-boundary layer interactions, the experiment of Yamamoto and Tanida on a self-induced shock oscillation due to shock-boundary layer interaction was calculated. A significant improvement in the prediction of the shock amplitude was achieved by a slight modification of the Baldwin Lomax turbulence model. An important result of the presented compressor cascade investigations is that viscous effects may cause a significant change in the aerodynamic damping. This behavior is demonstrated by two cases in which an Euler calculation predicts a damped oscillation whereas a Navier-Stokes computation leads to an excited vibration. It was found that the reason for these contrary results are shock-boundary-layer interactions which dramatically change the aerodynamic damping.

Item URL in elib:https://elib.dlr.de/14404/
Document Type:Article
Additional Information: LIDO-Berichtsjahr=2003,
Title:The Impact of Viscous Effects on the Aerodynamic Damping of Vibrating Transonic Compressor Blades
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Grüber, B.Daimler Chrysler Aerospace, MTU Munich, Munich, GermanyUNSPECIFIED
Carstens, V.UNSPECIFIEDUNSPECIFIED
Date:2001
Journal or Publication Title:Journal of Turbomachinery
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:Yes
Volume:123
Page Range:pp. 409-417
Status:Published
Keywords:Aeroelasticity of Turbomachines, Unsteady Aerodynamics, Oscillating Cascades, Navier-Stokes Method
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Aeronautics
HGF - Program Themes:other
DLR - Research area:Aeronautics
DLR - Program:L ST - Starrflüglertechnologien
DLR - Research theme (Project):UNSPECIFIED
Location: Göttingen
Institutes and Institutions:Institute of Aeroelasticity
Deposited By: DLR-Beauftragter, elib
Deposited On:16 Sep 2005
Last Modified:14 Jan 2010 21:48

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