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Composite Inlays Increase Flutter Resistance of Turbine Engine Fan Blades FREE

[+] Author Affiliations
W. Troha

Air Force Aero Propulsion Laboratory, Wright Patterson AFB, OH

K. Swain

General Motors Corporation, Indianapolis, IN

Paper No. 76-GT-29, pp. V01AT01A029; 8 pages
doi:10.1115/76-GT-29
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 method for improving turbine engine blade flutter stability was recently demonstrated on a TF41 fan rig and engine. The concept uses the high strength and stiffness properties of B/SiC-titanium composite, bonded into the leading edge tip section of a titanium fan blade, to control the blade vibrational characteristics. Comparisons are made between the blade response characteristics with and without the composite inlay for blade natural frequency, untwist due to rotational speed, and shift in flutter boundary. Engine performance improvements due to shroud removal are also shown.

Copyright © 1976 by ASME
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