Fatigue Crack Growth Retardation After Single-Cycle Peak Overload in Ti-6 Al-4V Titanium Alloy

Abstract

Fatigue crack growth after single-cycle peak overload was investigated in Ti-6Al-4V sheet. Strain hardening was determined not to be the major controlling mechanism retarding crack growth after peak overload, but instead, strain hardening slightly accelerated crack growth for the case when strain hardening was induced prior to crack initiation. Crack growth after peak overload was characterized by: (1) no effect after 20 percent overload (a 20 percent increase in maximum stress intensity); (2) crack arrest immediately following 70 and 100 percent overloads; (3) subsequent retarded crack growth rates after 70 and 100 percent overloads; and (4) retardation but no arrest following 50 percent overload.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1972
Accession Number
AD0753899

Entities

People

  • Raymond E. Jones

Organizations

  • University of Dayton

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Chemical Analysis
  • Cold Working
  • Contracts
  • Crack Tips
  • Cracks
  • Equations
  • Governments
  • Hardening
  • Materials
  • Materials Engineering
  • Materials Laboratories
  • Mechanical Working
  • Recovery
  • Strain Hardening
  • Tensile Properties
  • Titanium Alloys

Readers

  • Materials Science (Mechanical Engineering).
  • Mathematics or Statistics