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Implementation of an Aeroelastic Tool to Deduce Influence Coefficients

May, Markus (2011) Implementation of an Aeroelastic Tool to Deduce Influence Coefficients. DLR-Interner Bericht. DLR IB 232-2011 C 05, 20 S.

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This technical report presents the implementation of an aeroelastic tool for turbomachinery applications facilitating the deduction of influence coefficients from unsteady CFD results generated by traveling wave simulations. Based on the equation of motion for a bladed disk assembly and the aerodynamic interaction between adjacent blades the flutter stability equation for a rotor or cascade is derived. The transformation between traveling wave and blade coordinates is illustrated as well as the relationship between aerodynamic work and generalized aerodynamic force. The implementation of the algorithm in the form of a Python script is followed by its application to a generic test case. Aerodynamic damping diagrams showing the logarithmic decrement for all inter-blade phase angles of the considered configuration are opposed to influence coefficient representations in the complex plane. Two different operating conditions are compared, each of them with respect to the first three eigenmode families.

Item URL in elib:https://elib.dlr.de/70243/
Document Type:Monograph (DLR-Interner Bericht)
Title:Implementation of an Aeroelastic Tool to Deduce Influence Coefficients
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
May, Markusmarkus.may (at) dlr.deUNSPECIFIED
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Number of Pages:20
Keywords:aeroelasticity, turbomachinery, aerodynamic work, influence coefficients
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:other
DLR - Research area:Aeronautics
DLR - Program:L - no assignment
DLR - Research theme (Project):L - no assignment (old)
Location: Göttingen
Institutes and Institutions:Institute of Aeroelasticity
Deposited By: Erdmann, Daniela
Deposited On:09 Nov 2011 14:47
Last Modified:09 Nov 2011 14:47

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