GAS TURBINE ENGINE COATING WITH THERMAL PROTECTION

A section of a gas turbine engine includes a ceramic component (104) and a metallic component (102) situated adjacent the ceramic component (104). The ceramic component (104) and the metallic component (102) are situated outside of a core flow path of the gas turbine engine. The section of a gas tur...

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Bibliographische Detailangaben
Hauptverfasser:	LITTON, David A, ROGERS, Daniel S, WHITE III, Robert A, ABDI, Ahmed Abdillahi
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING CYLINDERS ENGINE PLANTS IN GENERAL ENGINEERING ELEMENTS AND UNITS GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PISTONS SEALINGS STEAM ENGINES THERMAL INSULATION IN GENERAL WEAPONS
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Beschreibung
Zusammenfassung:	A section of a gas turbine engine includes a ceramic component (104) and a metallic component (102) situated adjacent the ceramic component (104). The ceramic component (104) and the metallic component (102) are situated outside of a core flow path of the gas turbine engine. The section of a gas turbine engine also includes an interface (106) between the ceramic component (104) and the metallic component (102) and a mullite-based coating (200) disposed at the interface (106). The coating (200) provides thermal protection to the ceramic component (104) and the metallic component (102), and provides thermochemical protection against interaction between the ceramic component (104) and the metallic component (102). A gas turbine engine and a method of protecting components (102, 104) in a gas turbine engine are also disclosed.