Accession Number:

ADA031836

Title:

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

Descriptive Note:

Memorandum rept.,

Corporate Author:

NAVAL RESEARCH LAB WASHINGTON D C

Personal Author(s):

Report Date:

1976-10-01

Pagination or Media Count:

30.0

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

Subject Categories:

  • Properties of Metals and Alloys
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE