Flutter and forced response of mistuned rotors using standing wave analysis
Name
916503824.pdf
Size
4.05 MB
Format
Adobe PDF
Checksum (MD5)
d87710a57698b6a7c5d215a77e759f1e
Author(s)
Bundas, David J.
Dugundji, John
Date Issued
1983
Publisher
Cambridge, Mass. : Gas Turbine & Plasma Dynamics Laboraotry, [1983]
Series/Report no.
N 84-24586
NASA contractor report ; NASA CR-173555
GT & PDL report ; no. 170
Abstract
The torsion flutter and forced response of tuned and mistuned cascades is examined using a standing wave approach, as opposed to the traditional traveling wave approach used in cascades aerodynamic models. The motion of the blades and the corresponding cascade aerodynamic loads are expressed in terms of standing wave modes and arbitrary transient motion, by fitting the sinusoidal force coefficients in terms of ratios of polynomials in the Laplace transform variable, sometimes referred to as Pade approximants. Whitehead's two dimensional, incompressible aerodynamic model is expressed in this transient form and is used to solve the flutter and forced response problems. Results obtained with the transient, standing wave analysis for the flutter and forced response are similar to those obtained by traveling wave analyses, but they yield the transient decay rate associated with vibrations of the blades, as opposed to the structural damping required for flutter obtained by the traveling method.
The standing wave analysis presented here may prove to be more versatile for dealing with certain applications such as mistuned rotors, "localized" blade flutter, low engine order excitation, transient impulses on the rotor, and coupling in with forced response and dynamic shaft problems.
Description
First published as the author's thesis (M.S.) in the M.I.T. Dept. of Aeronautics and Astronautics, 1983
Massachusetts Inst. of Tech. --Microfiche header
March 1983
N84-24586 --Microfiche header
NASA Grant no. NAG3-214
Includes bibliographical references
Persistent DSpace Link
