METHODS AND MATERIALS FOR REPAIRING A THERMAL BARRIER COATING OF A GAS TURBINE COMPONENT
A sprayable thermal barrier coating powder mixture (208) for a gas turbine engine (10) includes: a dry composition having a low surface area ceramic powder (214) having a median particle size distribution greater than 5 microns and less than 50 microns, and a high surface area ceramic powder (216) h...
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Format | Patent |
Language | English French German |
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12.01.2022
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Abstract | A sprayable thermal barrier coating powder mixture (208) for a gas turbine engine (10) includes: a dry composition having a low surface area ceramic powder (214) having a median particle size distribution greater than 5 microns and less than 50 microns, and a high surface area ceramic powder (216) having a median particle size distribution smaller than 5 microns, wherein the low surface area ceramic powder (214) makes up at least 50% by weight of the dry composition of the sprayable thermal barrier coating powder mixture (208). The low surface area ceramic powder (214) has less than 10 meters squared of surface area per gram, and wherein the high surface area ceramic powder (216) has greater than 10 meters squared of surface area per gram and less than 4,000 meters squared of surface area per gram.A method (300) for repairing a thermal barrier coating (146) of a component (252) of a gas turbine engine (10) in situ comprising:spraying a thermal barrier coating powder mixture (208) onto the component (252) of the gas turbine engine (10) in situ, the thermal barrier coating powder mixture (208) comprising a low surface area ceramic powder (214), a low surface area ceramic powder (214) precursor, or both, the thermal barrier coating powder mixture (208) further comprising a high surface area ceramic powder (216), the thermal barrier coating powder mixture (208) defining an activation temperature range from 300 degrees Celsius to 1200 degrees Celsius; andoperating the gas turbine engine (10) to cure the thermal barrier coating powder mixture (208) on the component (252). |
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AbstractList | A sprayable thermal barrier coating powder mixture (208) for a gas turbine engine (10) includes: a dry composition having a low surface area ceramic powder (214) having a median particle size distribution greater than 5 microns and less than 50 microns, and a high surface area ceramic powder (216) having a median particle size distribution smaller than 5 microns, wherein the low surface area ceramic powder (214) makes up at least 50% by weight of the dry composition of the sprayable thermal barrier coating powder mixture (208). The low surface area ceramic powder (214) has less than 10 meters squared of surface area per gram, and wherein the high surface area ceramic powder (216) has greater than 10 meters squared of surface area per gram and less than 4,000 meters squared of surface area per gram.A method (300) for repairing a thermal barrier coating (146) of a component (252) of a gas turbine engine (10) in situ comprising:spraying a thermal barrier coating powder mixture (208) onto the component (252) of the gas turbine engine (10) in situ, the thermal barrier coating powder mixture (208) comprising a low surface area ceramic powder (214), a low surface area ceramic powder (214) precursor, or both, the thermal barrier coating powder mixture (208) further comprising a high surface area ceramic powder (216), the thermal barrier coating powder mixture (208) defining an activation temperature range from 300 degrees Celsius to 1200 degrees Celsius; andoperating the gas turbine engine (10) to cure the thermal barrier coating powder mixture (208) on the component (252). |
Author | BEWLAY, Bernard Patrick KESHAVAN, Hrishikesh SAHA, Atanu NAGESH, Mamatha WALLACE, Margeaux KULKARNI, Ambarish Jayant |
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DocumentTitleAlternate | VERFAHREN UND MATERIALIEN ZUR REPARATUR EINER WÄRMEDÄMMSCHICHT EINER GASTURBINENKOMPONENTE PROCÉDÉS ET MATÉRIAUX DE RÉPARATION D'UN REVÊTEMENT BARRIÈRE THERMIQUE D'UN COMPOSANT DE TURBINE À GAZ |
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Snippet | A sprayable thermal barrier coating powder mixture (208) for a gas turbine engine (10) includes: a dry composition having a low surface area ceramic powder... |
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SubjectTerms | ARTIFICIAL STONE BLASTING CEMENTS CERAMICS CHEMICAL SURFACE TREATMENT CHEMISTRY COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATIONOR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY IONIMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL COATING MATERIAL WITH METALLIC MATERIAL COATING METALLIC MATERIAL COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDINGMATERIALS CONCRETE DIFFUSION TREATMENT OF METALLIC MATERIAL ENGINE PLANTS IN GENERAL HEATING INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION INGENERAL LIGHTING LIME, MAGNESIA MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING METALLURGY NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES REFRACTORIES SLAG STEAM ENGINES SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THESURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION TREATMENT OF NATURAL STONE WEAPONS |
Title | METHODS AND MATERIALS FOR REPAIRING A THERMAL BARRIER COATING OF A GAS TURBINE COMPONENT |
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