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Damage Tolerant Design of Turbine Engine Disks PUBLIC ACCESS

[+] Author Affiliations
C. H. Cook, C. E. Spaeth, D. T. Hunter

United Technologies Corporation, West Palm Beach, FL

R. J. Hill

Air Force Wright Aeronautical Laboratories, Wright-Patterson AFB, OH

Paper No. 82-GT-311, pp. V005T13A029; 8 pages
doi:10.1115/82-GT-311
From:
  • ASME 1982 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; General
  • London, England, April 18–22, 1982
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7960-3
  • Copyright © 1982 by ASME

abstract

This paper describes a USAF sponsored effort to develop, apply, test, and evaluate Pratt & Whitney’s Damage Tolerant Design System for cold-section gas turbine engine disks. The design system includes a Damage Tolerance Specification proposed for new USAF engine programs, material characterization for crack-growth behavior, design procedures, and analytical life prediction methodology for consideration of large flaws. To evaluate and refine the design system, a current engine fan disk was redesigned to operate safely for a specified time after the occurrence of 0.030-inch (0.76 mm) surface length fatigue cracks. The redesigned disk was tested to failure while monitoring crack growth and correlating observed measurements with analytical prediction. Test results were used to refine the design system. Current work involves extending Damage Tolerant Design capability to hot-section powder-metallurgy disks. The impact of these efforts is twofold; current designs will benefit from improved life prediction capability in applying Retirement-for-Cause philosophy, and future designs can take advantage of the Life-Cycle-Cost benefit of designing for damage tolerance.

Copyright © 1982 by ASME
This article is only available in the PDF format.

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