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Review of Probabilistic Damage Tolerance Methodology for Hard Alpha Anomalies

[+] Author Affiliations
R. S. J. Corran

Rolls-Royce plc, Derby, UK

M. Gorelik

Honeywell, Phoenix, AZ

D. Chawla

Pratt & Whitney Canada, Mississanga, ON, Canada

S. Mosset

Snecma, Corbeil, France

M. B. Joinson

Rolls-Royce plc, Bristol, UK

D. Harmon, D. Nissley

Pratt & Whitney, East Hartford, CT

A. J. Murphy, K. W. Jacques

GE Aircraft Engines, Cincinnati, OH

J. Stillinger

Rolls-Royce Corporation, Indianapolis, IN

Paper No. GT2012-68987, pp. 397-406; 10 pages
doi:10.1115/GT2012-68987
From:
  • ASME Turbo Expo 2012: Turbine Technical Conference and Exposition
  • Volume 7: Structures and Dynamics, Parts A and B
  • Copenhagen, Denmark, June 11–15, 2012
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4473-1
  • Copyright © 2012 by ASME

abstract

Following the Sioux City event in 1989, the aero gas turbine industry has collaborated with the FAA to develop a probabilistic damage tolerance approach to Hard Alpha melt anomalies in Titanium alloys used for life limited parts, mainly discs. The FAA has published a methodology in AC 33.14-1 by which Engine Manufacturers can determine if the combination of controls in the supply and inspection of the disc and the duty in the engine that the disc must sustain remain consistent with a committed reduction to the expected rate of Hard Alpha related events for all future engines. This methodology was based on the best understanding of the behavior of Hard Alpha anomalies current around 1996. Since that date, the knowledge surrounding melt anomalies in titanium has increased significantly, primarily due to research programs funded by the FAA but also by the collection of field and supply data on production parts in the intervening years. This report reviews the method of assessment described in the FAA AC33.14-1 in the light of later knowledge and over a decade of further supply and field experience. The main conclusions and recommendations from this study are discussed.

Copyright © 2012 by ASME
Topics: Damage

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