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公开(公告)号：US20170292703A1
公开(公告)日：2017-10-12
申请号：US15627843
申请日：2017-06-20
CPC分类号： F23R3/002 , F23R3/005 , F23R3/06 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043 , F23R2900/03044 , Y02T50/675 , Y10T29/49229
摘要： A gas turbine engine variable porosity combustor liner has a laminated alloy structure. The laminated alloy structure has combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side. The combustion chamber facing holes are in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal alloy sheets of the laminated alloy structure. Porous zones having respective different cooling flow amounts are formed in the laminated alloy structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages.
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公开(公告)号：US20240352872A1
公开(公告)日：2024-10-24
申请号：US18304037
申请日：2023-04-20
摘要： An example system includes one or more heaters configured and positioned to add thermal energy to one or more portions of a gas turbine engine after the gas turbine engine was in operation, wherein the thermal energy minimizes or prevents undesired contact or seizing of a rotor of the gas turbine engine with another component of the gas turbine engine due to warping of the rotor due to uneven cooling of the gas turbine engine after the operation. The system further includes a controller configured to control operation of the one or more heaters.
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公开(公告)号：US12091368B2
公开(公告)日：2024-09-17
申请号：US16694486
申请日：2019-11-25
发明人： Taylor K. Blair
CPC分类号： C04B41/5059 , C04B41/4556 , C04B41/4558 , C04B41/522 , C04B41/524 , C04B41/87 , F02C7/30 , F05D2220/32 , F05D2230/90 , F05D2300/30
摘要： A method may include applying a layer comprising a carbon source on a surface of a substrate including silicon; applying a layer comprising silicon on the layer comprising elemental carbon; and heat treating at least the layer comprising the carbon source to cause carbon from the layer comprising the carbon source to react with at least one of silicon from the substrate or silicon from the layer comprising silicon to form silicon carbide.
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公开(公告)号：US12077479B2
公开(公告)日：2024-09-03
申请号：US16788917
申请日：2020-02-12
CPC分类号： C04B41/4584 , C04B41/4505 , C04B41/5024 , C04B41/5059 , C04B41/5066 , C04B41/52 , C04B41/87 , B32B3/08 , B32B5/06 , B32B18/00 , B32B2260/021 , B32B2262/105 , B32B2305/026 , B32B2305/80 , B32B2603/00 , C04B2235/5252 , C04B2235/6025 , C04B2235/6027 , C04B2235/614 , C04B2235/616 , C04B2235/96
摘要： A ceramic matrix composite (CMC) component is provided that includes: a CMC body in which an environmental protection layer is completely embedded within a CMC material of the CMC body, the environmental protection layer comprising a ceramic that has a higher impact and/or environmental resistance than the CMC material. Methods for manufacturing the CMC component are also provided.
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5.发明公开公开(公告)号：US20240287915A1
公开(公告)日：2024-08-29
申请号：US18113386
申请日：2023-02-23
发明人： Aaron D. Sippel
CPC分类号： F01D25/005 , F01D11/005 , F01D11/08 , F01D11/12 , F01D11/122 , F01D25/243 , F05D2220/32 , F05D2240/55 , F05D2300/6033
摘要： Turbine shroud structures and a method of assembling a turbine shroud into a turbine are disclosed. The method includes arranging turbine shroud segments into a full ring and inserting the full ring into a turbine case as a single unit.
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6.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
发明人： Jun Shi , Li Li , Gregory John Kenneth Harrington
CPC分类号： 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
摘要： 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：US12065258B2
公开(公告)日：2024-08-20
申请号：US18101567
申请日：2023-01-25
IPC分类号： B64D33/02
CPC分类号： B64D33/02 , B64D2033/0226 , B64D2033/0286
摘要： An aircraft includes a duct system configured to receive a flow of air therethrough and a gas turbine engine. The duct system includes a main duct and inlet ducts arranged fluidly upstream of the main duct so as to conduct the flow of air from the inlet ducts into the main duct. The gas turbine engine in downstream fluid communication with the main duct.
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公开(公告)号：US12025059B1
公开(公告)日：2024-07-02
申请号：US18088994
申请日：2022-12-27
CPC分类号： F02C9/20 , F02C3/04 , F02C6/00 , F05D2220/32 , F05D2220/70 , F05D2270/05 , F05D2270/101
摘要： A gas turbine engine comprises a primary fan and an engine core. The primary fan is mounted for rotation about an axis of the gas turbine engine to provide thrust. The engine core is coupled to the primary fan and configured to drive the primary fan about the axis to cause the fan to push air to provide thrust for the gas turbine engine.
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9.发明授权公开(公告)号：US12018621B1
公开(公告)日：2024-06-25
申请号：US18234657
申请日：2023-08-16
CPC分类号： F02C9/22 , F01D17/141 , F02K3/06 , F04D29/542 , F05D2220/36 , F05D2240/12 , F05D2240/14
摘要： A fan case assembly adapted for use with a gas turbine engine includes a case at extends circumferentially at least partway about an axis of the gas turbine engine and a plurality of vanes. The case is formed to define a channel that extends circumferentially at least partway about the axis. The plurality of vanes are arranged in the channel and spaced apart circumferentially about the axis.
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公开(公告)号：US12012997B2
公开(公告)日：2024-06-18
申请号：US17930192
申请日：2022-09-07
发明人： Joseph D. Black
摘要： In some examples, a cone clutch assembly includes an inner cone member rotationally coupled to a first shaft, the inner cone member defining a first friction surface, and an outer cone member rotationally coupled to a second shaft, the outer cone member defining a second friction surface opposing the first friction surface. The inner cone member and outer cone member are configured to be selectively engage and disengaged from each other. When the inner cone member is engaged with the outer cone member, the first friction surface of the inner cone member frictionally engages the second friction surface of the outer cone member such that rotational motion is transferred between the inner cone member and the outer cone member. The inner surface of the inner cone member opposing the first friction surface includes at least one groove configured to receive a cooling fluid during operation of the cone clutch assembly.
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