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公开(公告)号：EP3819399A1
公开(公告)日：2021-05-12
申请号：EP20205023.3
申请日：2020-10-30
发明人： BEWLAY, Bernard , HRISHIKESH, Keshavan , KULKARNI, Ambarish , WALLACE, Margeaux , PRITCHARD, Byron , ELKADY, Almed , SAHA, Atanu , NAGESH, Mamatha
IPC分类号： C23C28/00 , C23C28/04 , C23C4/02 , C23C4/11 , C23C4/12 , C23C4/134 , C23C4/18 , C23C14/02 , C23C14/08 , C23C16/02 , C23C16/40 , B23P6/00
摘要： A coated component of a gas turbine engine includes a substrate defining a surface, a thermal barrier coating deposited on the surface of the substrate, a region of the component where the thermal barrier coating has spalled from the substrate, a layer of environmental contaminant compositions formed on one or more of the thermal barrier coating or the region of the component where the thermal barrier coating has spalled from the substrate in response to an initial exposure of the component to high operating temperatures of the gas turbine engine, and a thermal barrier coating (TBC) restoration coating deposited at least on the region of the component where there thermal barrier coating has spalled from the substrate.
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2.发明公开
公开(公告)号：EP4008701A1
公开(公告)日：2022-06-08
申请号：EP22152828.4
申请日：2021-05-25
发明人： KESHAVAN, Hrishikesh , SAHA, Atanu , WALLACE, Margeaux , NAGESH, Mamatha , KULKARNI, Ambarish Jayant , BEWLAY, Bernard Patrick
IPC分类号： C04B35/626 , F01D5/28 , C23C4/11 , C23C18/06 , C23C18/12 , C04B35/486 , C23C24/04 , F01D5/00
摘要： 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).
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公开(公告)号：EP4008704A1
公开(公告)日：2022-06-08
申请号：EP21200371.9
申请日：2021-09-30
摘要： Methods for forming a sintered patch on a silicon-based substrate are disclosed. The methods include applying a patch slurry on the silicon-based substrate, drying the patch slurry on the silicon-based substrate to form a dried patch material, and sintering the dried patch material in an oxidizing atmosphere to form a sintered patch on the silicon-based substrate. The patch slurry includes a patch material containing silicates in a fluid carrier.
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4.发明公开
公开(公告)号：EP3936491A3
公开(公告)日：2022-03-16
申请号：EP21175663.0
申请日：2021-05-25
发明人： KESHAVAN, Hrishikesh , SAHA, Atanu , WALLACE, Margeaux , NAGESH, Mamatha , KULKARNI, Ambarish Jayant , BEWLAY, Bernard Patrick
IPC分类号： C04B35/626 , F01D5/28 , C23C4/11 , C23C18/06 , C23C18/12 , C04B35/486
摘要： 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; and
operating the gas turbine engine (10) to cure the thermal barrier coating powder mixture (208) on the component (252).-
公开(公告)号：EP4261322A1
公开(公告)日：2023-10-18
申请号：EP23167529.9
申请日：2023-04-12
发明人： WALLACE, Margeaux , NAGESH, Mamatha , NAYAK, Mohandas , KUMAR, Sundeep , BEWLAY, Bernard Patrick , KUHN, Julie Marie
IPC分类号： C23C4/067 , C04B35/00 , C23C4/11 , C23C4/134 , F01D5/28 , C04B41/00 , C04B41/52 , C04B41/89 , C04B111/00
摘要： Coated components (100), along with methods of their formation, are provided. The coated component (100) may include a substrate (120) having a surface (115) and a thermal barrier coating (110) on the surface (115) of the substrate (120). The thermal barrier coating (110) includes a plurality of elongated surface connected voids (130) therein, and wherein the thermal barrier coating (110) comprises a plurality of nonspherical particles (112) within a ceramic thermal barrier material (114).
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公开(公告)号：EP4155351A1
公开(公告)日：2023-03-29
申请号：EP22193784.0
申请日：2022-09-02
IPC分类号： C09D5/08 , C09D7/61 , C09D183/00 , C08K3/10 , C08K3/22
摘要： A corrosion resistant coating (64), including a matrix (63); corrosion resistant particles (65) dispersed throughout the matrix (63); and a glass-forming additive is disclosed. The glass-forming additive and one or more materials in the matrix (63) form a glassy-phase when cured.
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公开(公告)号：EP4335833A3
公开(公告)日：2024-04-03
申请号：EP23195249.0
申请日：2023-09-04
摘要： Methods for repairing a thermal barrier coating (140) deposited on a component (100) with localized spallation (150) of the thermal barrier coating (140) includes depositing a primer slurry on a thermally grown oxide (132) of the component (100) exposed by the localized spallation (150), depositing a ceramic slurry on the primer slurry, and heating the primer slurry and the ceramic slurry. The primer slurry includes a primer that includes a metal or a metal oxide. The ceramic slurry includes a ceramic material, a ceramic slurry binder material, and a ceramic slurry fluid carrier. Heating the primer slurry and the ceramic slurry forms a first chemical bond (210) between the primer and the thermally grown oxide (132) and a second chemical bond (230) between the primer and the ceramic material.
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公开(公告)号：EP4335833A2
公开(公告)日：2024-03-13
申请号：EP23195249.0
申请日：2023-09-04
摘要： Methods for repairing a thermal barrier coating (140) deposited on a component (100) with localized spallation (150) of the thermal barrier coating (140) includes depositing a primer slurry on a thermally grown oxide (132) of the component (100) exposed by the localized spallation (150), depositing a ceramic slurry on the primer slurry, and heating the primer slurry and the ceramic slurry. The primer slurry includes a primer that includes a metal or a metal oxide. The ceramic slurry includes a ceramic material, a ceramic slurry binder material, and a ceramic slurry fluid carrier. Heating the primer slurry and the ceramic slurry forms a first chemical bond (210) between the primer and the thermally grown oxide (132) and a second chemical bond (230) between the primer and the ceramic material.
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9.发明公开
公开(公告)号：EP3936491A2
公开(公告)日：2022-01-12
申请号：EP21175663.0
申请日：2021-05-25
发明人： KESHAVAN, Hrishikesh , SAHA, Atanu , WALLACE, Margeaux , NAGESH, Mamatha , KULKARNI, Ambarish Jayant , BEWLAY, Bernard Patrick
IPC分类号： C04B35/626 , F01D5/28 , C23C4/11 , C23C18/06 , C23C18/12 , C04B35/486
摘要： 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; and
operating the gas turbine engine (10) to cure the thermal barrier coating powder mixture (208) on the component (252).
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