Evaluation and Improvement of Coatings for Columbium Alloy Gas Turbine Engine Components

Abstract

Data generated using laboratory tests such as oxidation-erosion, thermal fatigue, ballistic impact, and wear-galling to simulate turbine engine environments are reported for eight coated columbium alloy composites. Applications considered were turbine vane and turbine blade airfoils operating in the 1800-2500 deg F temperature range and turbine blade roots at 1300-1600 deg F.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1966
Accession Number
AD0801396

Entities

People

  • H. A. Hauser
  • J. F. Jr Holloway

Organizations

  • Pratt & Whitney

Tags

Communities of Interest

  • Advanced Electronics
  • Weapons Technologies

DTIC Thesaurus Topics

  • Chemical Synthesis
  • Chemistry
  • Crystal Structure
  • Engine Components
  • Failure Mode And Effect Analysis
  • Fatigue Tests (Mechanics)
  • Gas Turbines
  • High Temperature
  • Materials
  • Materials Laboratories
  • Mechanical Working
  • Refractory Metals
  • Sheet Metal
  • Solid Solutions
  • Tensile Strength
  • Test And Evaluation
  • Turbines

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Surface Engineering/Surface Coating Technology.