Experimental Study of Ceramic-Coated Tip Seals for Turbojet Engines.

Abstract

Ceramic turbine tip shrouds were experimentally evaluated in the operating environment of a small turboshaft engine under steady and transient conditions. Ceramic gas-path seals were fabricated and successfully operated over 1000 cycles from flight idle to maximum power in a small turboshaft engine. The seals were fabricated by plasma spraying zirconia over a NiCoCrAlX bond coat on the Haynes 25 substrate. Coolant-side substrate temperatures and related engine parameters were recorded. Post-test inspection revealed 'mud-flat' surface cracking with penetration to the ceramic - bond-coat interface.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1985
Accession Number
ADA165882

Entities

People

  • E. S. Lassow
  • G. A. Klann
  • G. Mcdonald
  • M. Mchenry
  • T. J. Biesiadny

Organizations

  • National Aeronautics and Space Administration

Tags

DTIC Thesaurus Topics

  • Army Aviation
  • Ceramic Coatings
  • Ceramic Materials
  • Coatings
  • Engines
  • Failure Mode And Effect Analysis
  • Flow
  • Heat Transfer
  • Materials
  • Plasma Spraying
  • Substrates
  • Thermal Spraying
  • Trailing Edges
  • Turbine Components
  • Turbines
  • Turbojet Engines
  • Turboshaft Engines

Readers

  • Aerospace Engineering
  • Surface Engineering/Surface Coating Technology.