Vibrating Beam Dampers for Reducing Vibrations in Gas Turbine Blades

[+] Author and Article Information
D. I. G. Jones

Vibrations and Damping, Air Force Materials Laboratory, Wright-Patterson Air Force Base, Ohio

A. D. Nashif

University of Dayton, Dayton, Ohio

H. Stargardter

Aeroelasticity Group, Pratt and Whitney Aircraft, E. Hartford, Conn.

J. Eng. Power 97(1), 111-116 (Jan 01, 1975) (6 pages) doi:10.1115/1.3445888 History: Received November 27, 1973; Online July 14, 2010


This paper reports the results of a preliminary investigation of the feasibility of reducing vibratory response levels in jet engine turbine blades by means of tuned damping devices incorporating high temperature vitreous enamels for energy dissipation. It is shown that an externally coated cantilever beam damper can be very effective in reducing vibration amplitudes, provided that it is properly tuned. Further efforts are needed to develop and verify an engineering design which will satisfy all operational requirements. The first step in that direction, which should be the next phase of the investigation, is to verify that the enamels and dampers considered in this paper will withstand the centrifugal loads imposed by rotation of the blades.

Copyright © 1975 by ASME
Your Session has timed out. Please sign back in to continue.






Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In