Accession Number:

ADA165882

Title:

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

Descriptive Note:

Technical memo.,

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH LEWIS RESEARCH CENTER

Report Date:

1985-01-01

Pagination or Media Count:

21.0

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.

Subject Categories:

  • Adhesives, Seals and Binders
  • Ceramics, Refractories and Glass
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE