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Prediction of Modal Damping of Jet Engine Stator Vanes Using Finite Element Techniques FREE

[+] Author Affiliations
P. Trompette, M. Paulard, M. Lalanne

Institut National des Sciences Appliquées, Villeurbanne, France

D. I. G. Jones, M. L. Parin

Air Force Materials Laboratory, Wright-Patterson Air Force Base, OH

Paper No. 76-GT-60, pp. V01AT01A060; 12 pages
doi:10.1115/76-GT-60
From:
  • ASME 1976 International Gas Turbine and Fluids Engineering Conference
  • Volume 1A: General
  • New Orleans, Louisiana, USA, March 21–25, 1976
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7974-0
  • Copyright © 1976 by ASME

abstract

A finite-element analysis utilizing isoparametric elements is used to predict the modal damping and resonant frequencies of a jet engine high pressure compressor stator vane with a damping treatment in the form of an enamel coating applied to the surface. The results of the finite-element analysis are shown to agree well with experimentally measured data. The ultimate advantage of this particular finite-element approach is that it can be applied at very low cost to predicting the effect of many types of damping treatment on modal damping and resonant frequencies of practically any structural component, as well as stress levels if the excitation forces are known.

Copyright © 1976 by ASME
This article is only available in the PDF format.

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