DTIC ADA165882: Experimental Study of Ceramic Coated pdf

DTIC ADA165882: Experimental Study of Ceramic Coated

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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

• Creator/s: Defense Technical Information Center
• Date: 1/1/1985
• Year: 1985
• Book Topics/Themes: DTIC Archive, Biesiadny, T J, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH LEWIS RESEARCH CENTER, *CERAMIC COATINGS, *SEALS(STOPPERS), STEADY STATE, TRANSIENTS, TURBOSHAFT ENGINES, INTERFACES, PARAMETERS, CRACKS, CERAMIC MATERIALS, TURBINE BLADES, ENGINES, BONDING, PLASMA SPRAYING, ZIRCONIUM OXIDES, GAS FLOW, TURBOJET ENGINES

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