Experimental study of ceramic-coated tip seals for turbojet engines. Technical memo

Technical Report · Tue Jan 01 00:00:00 EST 1985

OSTI ID:5632952

Biesiadny, T J; Klann, G A; Lassow, E S; McHenry, M; McDonald, G

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.

• Research Organization: National Aeronautics and Space Administration, Cleveland, OH (USA). Lewis Research Center
• OSTI ID: 5632952
• Report Number(s): AD-A-165882/2/XAB
• Country of Publication: United States
• Language: English

Related Subjects

36 MATERIALS SCIENCE
TURBINE BLADES
SPRAYED COATINGS
TURBOJET ENGINES
ZIRCONIUM OXIDES
PLASMA ARC SPRAYING
BONDING
CRACKS
GAS FLOW
INTERFACES
SEALS
TRANSIENTS
CHALCOGENIDES
COATINGS
DEPOSITION
ENGINES
FABRICATION
FLUID FLOW
JOINING
OXIDES
OXYGEN COMPOUNDS
SPRAY COATING
SURFACE COATING
TRANSITION ELEMENT COMPOUNDS
ZIRCONIUM COMPOUNDS
360201* - Ceramics
Cermets
& Refractories- Preparation & Fabrication