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1.发明公开公开(公告)号：US20240353343A1
公开(公告)日：2024-10-24
申请号：US18303965
申请日：2023-04-20
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Thomas J. BATZINGER , Thomas E. MOLDENHAUER , Keith C. BELSOM
CPC classification number: G01N21/8422 , F01D5/288 , F05D2230/10 , F05D2230/90 , G01N2021/8433
Abstract: The present application provides a cooling hole location system for locating a cooling hole in a gas turbine component, wherein the cooling hole is covered by a thermal barrier coating. The cooling hole location system may include a light source positioned on a first side of the gas turbine component and an optical detector positioned on a second side of the gas turbine component. The optical detector detects light from the light source visible through the thermal barrier coating covering the cooling hole.
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公开(公告)号：US12084988B2
公开(公告)日：2024-09-10
申请号：US17593226
申请日：2020-03-06
Applicant: NUOVO PIGNONE TECNOLOGIE—S.r.l.
Inventor： Michelangelo Bellacci , Gianfranco Maffulli , Lorenzo Cosi , Nicola Ciarla
CPC classification number: F01D5/288 , C10G11/18 , C10G75/00 , F01D5/20 , F01D11/122 , F05D2220/62 , F05D2230/90 , F05D2240/307 , F05D2300/6111
Abstract: A blade for fluid catalytic cracking (FCC) flue hot gas expander with a layer of hard abrasive material localized on the blade tip that contributes to reducing the accumulation of FCC catalyst residuals in the expander.
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3.发明授权公开(公告)号：US12071382B2
公开(公告)日：2024-08-27
申请号：US16726553
申请日：2019-12-24
Applicant: Rolls-Royce Corporation
Inventor： Jun Shi , Li Li , Gregory John Kenneth Harrington
CPC classification number: C04B41/009 , C04B41/0072 , C04B41/5024 , C04B41/89 , C23C4/18 , F01D5/282 , F01D5/288 , F05D2230/31 , F05D2230/40 , F05D2230/90 , F05D2300/15 , F05D2300/6033 , F05D2300/611
Abstract: In one example, a method for forming a coating system including an environmental barrier coating (EBC) and abradable coating on a substrate. The method may include depositing the EBC on a ceramic or ceramic matrix composite (CMC) substrate to form an as-deposited EBC; heat treating the as-deposited EBC following the deposition of the as-deposited EBC on the substrate to form a heat treated EBC; and subsequently depositing an abradable coating on the heat treated EBC to form an as-deposited abradable coating. The as-deposited abradable coating may be heat treated to form a heat treated abradable coating.
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公开(公告)号：US12037924B2
公开(公告)日：2024-07-16
申请号：US17784932
申请日：2020-12-14
Applicant: SAFRAN AIRCRAFT ENGINES
CPC classification number: F01D5/288 , F01D5/147 , F05D2220/32 , F05D2230/20 , F05D2230/31 , F05D2240/30
Abstract: A method for manufacturing a blade from composite material having an added metal leading edge for a gas turbine aeroengine includes producing a blade body from composite material including a blade root part, a shank part and an airfoil body part; manufacturing, via additive manufacturing, a leading edge extending in a longitudinal direction between a lower end present at the shank part of the composite material and an upper end present at the tip; bonding the manufactured leading edge onto the foremost edge portion of the airfoil body of the blade body.
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公开(公告)号：US12012869B2
公开(公告)日：2024-06-18
申请号：US16958422
申请日：2018-12-26
Applicant: SAFRAN
Inventor： Luc Bianchi , Aurélien Joulia , André Hubert Louis Malie , Benjamin Dominique Roger Joseph Bernard
CPC classification number: F01D5/288 , C04B41/009 , C04B41/5024 , C04B41/5042 , C04B41/5072 , C04B41/522 , C04B41/89 , F01D25/00 , F05D2220/30 , F05D2230/31 , F05D2230/90
Abstract: The invention relates to a turbomachine part comprising a substrate consisting of a metal material, or a composite material, and also comprising a layer of a coating for protection against the infiltration of CMAS-type compounds, at least partially covering the surface of the substrate, the protective coating layer comprising a plurality of elementary layers including elementary layers of a first assembly of elementary layers inserted between elementary layers of a second assembly of elementary layers, each elementary layer of the first assembly and each elementary layer of the second assembly comprising an anti-CMAS compound, and each contact zone between an elementary layer of the first assembly and an elementary layer of the second assembly forming an interface conducive to the spreading of cracks along said interface.
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Patent Agency Ranking
公开(公告)号：US12006837B2
公开(公告)日：2024-06-11
申请号：US17587764
申请日：2022-01-28
Applicant: Raytheon Technologies Corporation
Inventor： Bryan P. Dube , David A. Litton
CPC classification number: F01D5/186 , F01D5/284 , F01D5/288 , F05D2230/90 , F05D2260/202 , F05D2260/232 , F05D2300/6033 , F05D2300/611
Abstract: A ceramic matrix composite component includes a ceramic matrix composite wall; a coating disposed on the wall; and a cooling hole formed in the wall. The cooling hole has a metering section defined along a first axis and a diffuser section defined along a second axis that is offset from the first axis. The cooling hole has a total length defined along the first axis, the total length being the sum of a length of the metering portion and a length of the diffuser portion. The length of the metering portion is between about 40 percent and about 85 percent of the total length. A ceramic matrix composite airfoil and a method of applying a coating to a ceramic matrix composite component are also disclosed.
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7.发明公开公开(公告)号：US20240117479A1
公开(公告)日：2024-04-11
申请号：US18364875
申请日：2023-08-03
Applicant: General Electric Company
Inventor： Lawrence Bernard Kool , Bangalore Aswatha Nagaraj , Thomas George Holland , Alfred Albert Mancini , Michael Anthony Benjamin
IPC: C23C2/04 , B05D1/12 , B05D1/18 , B05D5/00 , B32B15/04 , B32B15/18 , C09D1/00 , C23C2/26 , C23C4/04 , C23C4/06 , C23C4/10 , C23C4/18 , C23C14/08 , C23C20/00 , C23C20/06 , C23C20/08 , C23C24/00 , C23C26/00 , F01D5/28 , F02C7/30
CPC classification number: C23C2/04 , B05D1/12 , B05D1/18 , B05D5/00 , B32B15/04 , B32B15/043 , B32B15/18 , C09D1/00 , C23C2/26 , C23C4/04 , C23C4/06 , C23C4/10 , C23C4/18 , C23C14/087 , C23C20/00 , C23C20/06 , C23C20/08 , C23C24/00 , C23C26/00 , F01D5/28 , F01D5/286 , F01D5/288 , F02C7/30 , F05D2220/323 , F05D2230/30 , F05D2230/31 , F05D2230/90 , Y02T50/60 , Y10T428/12847 , Y10T428/12944 , Y10T428/12951 , Y10T428/12979 , Y10T428/2495 , Y10T428/24967 , Y10T428/26 , Y10T428/265
Abstract: A hydrocarbon fluid containment article having a wall with a surface that is wetted by hydrocarbon fluid. The surface includes an anti-coking coating. The anti-coking coating includes a copper salt, a silver salt, or a combination thereof. A gas turbine engine component including a wall having a first surface and an anti-coking coating on the first surface of the wall that is wetted by hydrocarbon fluid. The anti-coking coating including a copper salt, a silver salt, or a combination thereof that prevents the formation of gum or coke on a surface thereon. Methods for reducing the deposition of thermal decomposition products on a wall of an article are also provided.
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公开(公告)号：US11946147B2
公开(公告)日：2024-04-02
申请号：US16979971
申请日：2019-02-06
Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.
Inventor： Taiji Torigoe , Yoshifumi Okajima , Daisuke Kudo , Masahiko Mega , Shuji Tanigawa
IPC: F01D5/28 , B32B15/04 , C23C4/02 , C23C4/04 , C23C4/134 , C23C28/00 , F01D1/00 , F01D25/00 , F02C7/00
CPC classification number: C23C4/04 , B32B15/04 , C23C4/02 , C23C4/134 , C23C28/30 , C23C28/32 , C23C28/3215 , F01D1/00 , F01D5/28 , F01D5/288 , F01D25/00 , F02C7/00 , B32B2315/02 , C04B2235/3246
Abstract: A thermal barrier coating includes a bond coat layer deposited on a substrate, and a ceramic layer deposited on the bond coat layer. The ceramic layer includes a first layer having a porosity of 10% or more and 15% or less, and a second layer having a porosity of 0.5% or more and 9.0% or less and deposited on the first layer.
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9.发明授权公开(公告)号：US11946146B2
公开(公告)日：2024-04-02
申请号：US17329326
申请日：2021-05-25
Applicant: General Electric Company
Inventor： Hrishikesh Keshavan , Bernard Patrick Bewlay , Jose Sanchez , Margeaux Wallace , Byron Pritchard , Ambarish Kulkarni
CPC classification number: C23C28/042 , C23C18/1216 , C23C18/1295 , F01D5/288 , F05B2220/30 , F05B2280/6011 , F05D2230/90
Abstract: A coating system configured to be applied to a thermal barrier coating of an article includes an infiltration coating configured to be applied to the thermal barrier coating. The infiltration coating infiltrates at least some pores of the thermal barrier coating. The infiltration coating decomposes within the at least some pores of the thermal barrier coating to coat a portion of the at least some pores of the thermal barrier coating. The infiltration coating reduces a porosity of the thermal barrier coating. The coating system also includes a reactive phase spray formulation coat configured to be applied to the thermal barrier coating. The reactive phase spray formulation coating reacts with dust deposits on the thermal barrier coating.
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公开(公告)号：US11920245B2
公开(公告)日：2024-03-05
申请号：US17687901
申请日：2022-03-07
Applicant: RTX CORPORATION
Inventor： Christopher W. Strock , Paul M. Lutjen
CPC classification number: C23C4/08 , C23C4/06 , C23C4/12 , C23C4/123 , C23C4/134 , C23C4/18 , F01D5/288 , F01D11/122 , F05D2230/312 , F05D2300/121 , Y02T50/60
Abstract: A novel method of depositing grit particles onto a fan blade tip coating is provided. The method enhances grit capture by presenting a softened coating surface for the impinging particles. The softened surface is achieved without high substrate temperatures that could degrade the base metal properties in the fan blade. An auxiliary heat source is used to establish a locally heated and softened surface where the grit deposition takes place. The softened surface greatly increases the probability of grit capture.
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