Fatigue-Crack-Growth Analysis of Titanium Gas-Turbine Fan Blades.

Abstract

First stage forged titanium gas turbine fan blades from a military aircraft were removed from service, cut into specimens and tested for fatigue crack growth properties. A method for determining stress intensity based on change in compliance with increasing crack length was applied. Results of testing in air and salt water environments are presented. A model, based on stress-strain curve behavior, is developed and applied to simulate the data. The data is compared to that taken from rolled baseplate forms of the same material and the applicability of the data to fan blade design and life-time estimates is discussed. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1976
Accession Number
ADA031836

Entities

People

  • F. R. Stonesifer
  • W. H. Cullen

Organizations

  • United States Naval Research Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Ground and Sea Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Alloys
  • Chemistry
  • Corrosion
  • Cracks
  • Fan Blades
  • Frequency
  • Gas Turbines
  • Geometry
  • Hydrogen Embrittlement
  • Materials
  • Mechanics
  • Military Aircraft
  • Salt Water
  • Stress Corrosion Cracking
  • Titanium Alloys
  • Turbines

Readers

  • Aerodynamics.
  • Materials Science (Mechanical Engineering).
  • Systems Analysis and Design