Accession Number:

ADA061801

Title:

Failure Studies of a Third Stage Fan Disk from a TF-30 Turbine Engine.

Descriptive Note:

Final rept.,

Corporate Author:

NAVAL RESEARCH LAB WASHINGTON D C

Report Date:

1978-11-13

Pagination or Media Count:

29.0

Abstract:

A detailed failure analysis was made of a fan disk from the third stage of the Navys turbo-jet engine in order to gain a better understanding of the origing and growth kinetics of the cracks that had developed in service. The in service stress that had caused the cracks to originate was determined by a two dimensional photoelastic and holographic stress analysis. A further experimental stress analysis was made to determine the stress intensity factor, after the crack had formed, as a function of crack length. These results were compared with a fractographic study of the bearing surface and the fracture surface. It was found that the striation spacings were in good agreement with the calculated values of the stress intensity factor. Some conclusions were drawn concerning the origin and growth mechanism of these cracks. Author

Subject Categories:

  • Metallurgy and Metallography
  • Mechanics
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE