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Parametric Study of Turbine Blade Platform Friction Damping Using the Lumped Parameter Analysis FREE

[+] Author Affiliations
Robert J. Dominic

University of Dayton Research Institute, Dayton, OH

Paper No. 84-GT-109, pp. V005T13A012; 8 pages
doi:10.1115/84-GT-109
From:
  • ASME 1984 International Gas Turbine Conference and Exhibit
  • Volume 5: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation; Education; Process Industries; Technology Resources
  • Amsterdam, The Netherlands, June 4–7, 1984
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7950-4
  • Copyright © 1984 by ASME

abstract

A parametric study of turbine blade platform friction damping has been performed using the lumped parameter analysis. The hardware configuration used in the analysis is the first stage turbine of the High Pressure Fuel Turbopump of the Space Shuttle Main Engine. The analysis procedure, developed over the last few years by A. Muszynska, now of Bently Nevada Corporation, and D.I.G. Jones, of AFWAL/MLLN, solves the nonlinear equations of motion of a turbine blade acted on by a platform friction damper by an iterative matrix method. The parametric study considers the effects on the blade deflection response of variations in: the coefficient of friction; the normal force on the friction surface interface; the blade hysteretic damping; the blade to blade phase angle of the harmonic forcing function; and the amplitude of the forcing function. The results of the study are applicable to any blade-damper system similar to the one used in the study. [Work sponsored by Marshall Space Flight Center of NASA.]

Copyright © 1984 by ASME
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