Improved Damage Tolerance of Ti-6Al-4V Aero Engine Blades and Vanes Using Residual Compression by Design

Abstract

The deep stable layer of compressive residual stress produced by low plasticity burnishing (LPB) has been demonstrated in laboratory testing to improve damage tolerance in engine alloys IN718, Ti-6Al-4V, Ti-6-2-4-6, and 17-4PH. This paper describes the fatigue and FOD tolerance benefits afforded by LPB treatment of a Ti-6Al-4V first stage fan blade and vane. FOD sensitive blades and vanes removed from fielded engines were LPB processed to protect the leading edge of the blade and the trailing edge of the vane. Both components were fatigue tested in cantilever bending mode at R>0 using specially designed test fixtures. FOD was simulated with machined notches for the blade and electrical discharge machined (EDM) notches for the vane. Residual stress and cold work distributions were measured using x-ray diffraction mapping techniques.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Jan 01, 2005
Accession Number
ADA444511

Entities

People

  • N. Jayaraman
  • P. S> Prevey
  • R. Ravindranath

Tags

Communities of Interest

  • Air Platforms
  • Space

DTIC Thesaurus Topics

  • Aircrafts
  • Compression
  • Damage Tolerance
  • Fan Blades
  • Foreign Object Damage
  • Fracture (Mechanics)
  • Geometry
  • Leading Edges
  • Maintenance
  • Materials
  • Mechanics
  • Military Aircraft
  • Residual Stress
  • Simulations
  • Stresses
  • Thickness
  • Trailing Edges

Fields of Study

  • Materials science

Readers

  • Combustion and Flow Dynamics.
  • Manufacturing Engineering.
  • Mechanical Engineering/Mechanics of Materials.