Crack Growth Modeling in an Advanced Powder Metallurgy Alloy

Abstract

An interpolative model has been developed to calculate the cyclic crack growth rate of an advanced aircraft engine disk alloy (AF115). The test variables included within the model consists of stress ratio, temperature, frequency, and hold time. The model was based on experimental results conducted within a statistically designed test program. A nonsymmetric Sigmoidal equation consisting of six independent coefficients was used to equate stress intensity range to cyclic growth rate. Two verification tests were conducted at two conditions other than those used during the development of the model to evaluate the model.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1980
Accession Number
ADA093992

Entities

People

  • David A. Utah

Organizations

  • General Electric

Tags

Communities of Interest

  • Air Platforms
  • Ground and Sea Platforms

DTIC Thesaurus Topics

  • Air Force
  • Air Force Facilities
  • Aircraft Engines
  • Aircrafts
  • Data Analysis
  • Engines
  • Fabrication
  • Materials
  • Materials Laboratories
  • Mechanics
  • Operating Systems
  • Plastic Explosives
  • Regression Analysis
  • Test And Evaluation
  • Test Equipment
  • Test Facilities
  • Verification Tests

Readers

  • Mechanical Engineering/Mechanics of Materials.
  • Regression Analysis.
  • Structural Health Monitoring of Composite Structures.