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Numerical Investigation of Nonlinear Fluid-Structure Interaction in Vibrating Compressor Blades

Carstens, V. and Belz, J. (2000) Numerical Investigation of Nonlinear Fluid-Structure Interaction in Vibrating Compressor Blades. 45th International Gas Turbine and Aeroengine Congress and Exhibition, Munich, Germany, May 8-11 2000.

Full text not available from this repository.

Abstract

The aeroelastic behavior of vibrating blade assemblies is usually investigated in the frequency domain where the determination of aeroelastic stability boundaries is separated from the computation of linearized unsteady aerodynamic forces. However, nonlinear fluid-structure interaction caused by oscillating shocks or strong flow separation may significantly influence the aerodynamic damping and hence effect a shift of stability boundaries. In order to investigate such aeroelastic phenomena, the governing equations of structural and fluid motion have to be simultanesously integrated in time. In this paper a technique is presented which analyzes the aeroelastic behavior of an oscillating compressor cascade in the time domain. The structural part of the governing aeroelastic equations is time-integrated according to the algorithm of Newmark, while the unsteady airloads are computed at every time step by an Euler upwind code. The link between the two time integrations is an automatic grid generation in which the used mesh is dynamically deformed as such that it conforms with the deflected blades at every time step. The computed time series of the aeroelastic simulation of an assembly of twenty compressor blades performing torsional vibrations in transonic flow are presented. For subsonic flow, the differences between time domain and frequency domain results are of negligible order. For transonic flow, however, where vibrating shocks and a temporarily choked flow in the blade channel dominate the unsteady fflow, the energy transfer between fluid and structure is no longer comparable to that of a linear system. It is demonstrated that the application of the time domain method leads to a significantly different aeroelastic behaviour of the blade assembly including a shift of the stability boundary.

Item URL in elib:https://elib.dlr.de/14413/
Document Type:Conference or Workshop Item (Paper)
Additional Information: LIDO-Berichtsjahr=2003, monograph_id=2000-GT-381,
Title:Numerical Investigation of Nonlinear Fluid-Structure Interaction in Vibrating Compressor Blades
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Carstens, V.UNSPECIFIEDUNSPECIFIED
Belz, J.UNSPECIFIEDUNSPECIFIED
Date:2000
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Editors:
EditorsEmail
ASME, UNSPECIFIED
Series Name:ASME Paper
Status:Published
Keywords:Aeroelasticity of Turbomachines, Unsteady Aerodynamics, Fluid-Structure Coupling,Cascade Flutter, Tíme Domain Method
Event Title:45th International Gas Turbine and Aeroengine Congress and Exhibition, Munich, Germany, May 8-11 2000
Organizer:International Gas Turbine Institute
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Aeronautics
HGF - Program Themes:other
DLR - Research area:Aeronautics
DLR - Program:L TT - Triebwerkstechnologien
DLR - Research theme (Project):UNSPECIFIED
Location: Göttingen
Institutes and Institutions:Institute of Aeroelasticity
Deposited By: Erdmann, Daniela
Deposited On:16 Sep 2005
Last Modified:14 Jan 2010 21:49

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