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公开(公告)号:US12078081B1
公开(公告)日:2024-09-03
申请号:US18195149
申请日:2023-05-09
发明人: Jonas Banhos , Russell Kim , James T. Roach
CPC分类号: F01D5/284 , F01D5/187 , F01D5/282 , C04B35/80 , F05D2300/6033
摘要: An airfoil includes an airfoil wall that circumscribes a main cavity and defines radially inner and outer ends, leading and trailing edges, and pressure and suction sides. The airfoil wall includes a lay-up of ceramic matrix composite (CMC) plies that span the radially inner and outer ends and have an inner-most CMC ply bounding at least a portion of the main cavity, an exterior skin CMC ply, and intermediate CMC plies between the inner-most CMC ply and the exterior skin CMC ply. At least one of the intermediate CMC plies has cutout voids that define cooling channels in the airfoil wall. The cooling channels are bound on lateral sides by the at least one of the intermediate CMC plies, bound on an inner side by a first adjacent one of the CMC plies, and bound on an outer side by a second, different adjacent one of the CMC plies.
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公开(公告)号:US12006842B1
公开(公告)日:2024-06-11
申请号:US18328177
申请日:2023-06-02
发明人: Russell Kim , Raymond Surace , James T. Roach , Jonas Banhos
CPC分类号: F01D5/282 , F01D5/147 , F01D5/284 , F05D2240/80 , F05D2250/283 , F05D2300/6033 , F05D2300/612
摘要: An airfoil for a gas turbine engine includes an airfoil section and a platform that has a non-gaspath side and a gaspath side from which the airfoil section extends. The platform is comprised of a sandwich composite that has first and second ceramic matrix composite (CMC) skins that each include at least one 2-D ceramic fiber ply. The first and second CMC skins are disposed, respectively, on the gaspath side and the non-gaspath side, and there is a cellular core disposed radially between the first and second CMC skins.
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公开(公告)号:US11788419B1
公开(公告)日:2023-10-17
申请号:US17887870
申请日:2022-08-15
发明人: Jonas Banhos , Ravon Venters , Russell Kim , Raymond Surace , James T. Roach
CPC分类号: F01D5/187 , F01D5/282 , F01D5/284 , F05D2240/121 , F05D2240/303 , F05D2300/6033
摘要: A ceramic matrix composite airfoil includes a high-pressure surface and a low-pressure surface connected at a leading edge and a trailing edge. The high-pressure surface and the low-pressure surface extend from a first end to a second end. A leading edge cooling passage includes an inlet portion, a midspan portion and an outlet portion. A cross-sectional flow area of the midspan portion is less than a cross-sectional flow area of either the inlet portion or the outlet portion.
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公开(公告)号:US12044132B1
公开(公告)日:2024-07-23
申请号:US18195159
申请日:2023-05-09
发明人: Jonas Banhos , James T. Roach , Russell Kim
CPC分类号: F01D11/08 , F01D25/14 , F05D2240/55 , F05D2260/2214 , F05D2300/6033
摘要: A seal arc segment includes a wall that defines radially inner and outer sides, forward and aft ends, and first and second circumferential sides. The wall includes a CMC ply lay-up of a radially inner-most CMC ply on the inner side, a radially outer-most CMC ply on the radially outer side, and radially intermediate CMC plies therebetween. At least one of the radially intermediate CMC plies has cutout voids that define cooling channels in the wall. The cooling channels are bound on lateral channel sides by the at least one of the radially intermediate CMC plies, bound on a radially inner channel side by a first adjacent one of the CMC plies, and bound on a radially outer channel side by a second, different adjacent one of the CMC plies. The radially outer-most CMC ply includes at least one inlet hole connected to the cooling channels for providing cooling air.
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公开(公告)号:US20240175373A1
公开(公告)日:2024-05-30
申请号:US18071121
申请日:2022-11-29
发明人: James T. Roach , Jonas Banhos , Russell Kim
CPC分类号: F01D25/12 , F01D5/18 , F01D9/02 , F05D2220/323 , F05D2240/126 , F05D2240/30 , F05D2260/20
摘要: A gas turbine engine component includes an airfoil body extending between a leading edge and a trailing edge and having a suction wall and a pressure wall. An outer surface of the airfoil body is formed by an outer coat defining around the pressure and suction sides, a leading edge and a trailing edge. An internal cross-rib is formed within a cavity in the airfoil body. The internal cross-rib extends to be secured to the outer coat adjacent the leading edge and the trailing edge, and extending across the internal cavity to form a junction such that the cross-rib is x-shaped. The outer coat and the cross-rib are formed of ceramic matrix composites. A gas turbine engine is also disclosed.
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公开(公告)号:US12084982B2
公开(公告)日:2024-09-10
申请号:US17958946
申请日:2022-10-03
IPC分类号: F01D25/24
CPC分类号: F01D25/243 , F05D2220/323 , F05D2230/60 , F05D2240/12 , F05D2240/14
摘要: A flange stiffener support for a duct in a gas turbine engine includes a circumferential flange segment that has a plurality of flange fastener openings. An axial body segment extends from a radially inner side of the circumferential segment and has at least one body fastener opening. The axial body segment extends at least partially along a circumferential distance of the circumferential flange segment.
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公开(公告)号:US20240110492A1
公开(公告)日:2024-04-04
申请号:US17958946
申请日:2022-10-03
IPC分类号: F01D25/24
CPC分类号: F01D25/243 , F05D2220/323 , F05D2230/60 , F05D2240/12 , F05D2240/14
摘要: A flange stiffener support for a duct in a gas turbine engine includes a circumferential flange segment that has a plurality of flange fastener openings. An axial body segment extends from a radially inner side of the circumferential segment and has at least one body fastener opening. The axial body segment extends at least partially along a circumferential distance of the circumferential flange segment.
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公开(公告)号:US11913348B1
公开(公告)日:2024-02-27
申请号:US17964355
申请日:2022-10-12
发明人: Jonas Banhos , James T. Roach
CPC分类号: F01D25/12 , F01D5/186 , F01D5/187 , F01D5/188 , F01D5/189 , F01D9/041 , F05D2220/32 , F05D2240/12 , F05D2260/20
摘要: A gas turbine engine stator vane combination includes a stator vane body having an airfoil with a leading edge, a trailing edge, a suction side and a pressure side, and having at least one internal cooling channel. The stator vane body is formed of ceramic matrix composite materials. A spar is received within the at least one cooling air channel and formed of a metal. The spar has an outer peripheral surface spaced from an inner peripheral surface of the cooling air channel to define a cooling air path, with the cooling air path having a varying cross-sectional area through the cooling air channel. A gas turbine engine is also disclosed.
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公开(公告)号:US11905851B2
公开(公告)日:2024-02-20
申请号:US18126556
申请日:2023-03-27
发明人: Russell Kim , James T. Roach , Jonas Banhos
CPC分类号: F01D5/282 , F01D5/147 , F01D5/284 , F05D2230/31 , F05D2240/122 , F05D2250/75 , F05D2300/2261 , F05D2300/6012 , F05D2300/6033 , F05D2300/6034
摘要: A method of forming a ceramic matrix composite airfoil includes forming a fibrous ceramic preform by laying up a plurality of plies to form a hollow core cavity, overwrapping the plurality of plies of the core cavity with a first overwrap layer, weaving together a tows of first free portion and tows of a second free portion of the first overwrap layer to form a cross brace, overwrapping the plurality of plies of the core cavity and the first overwrap layer with a second overwrap layer, and consolidating the first free portion and the second free portion of the first overwrap layer and a third free portion and a fourth free portion of the second overwrap layer to form a trailing edge.
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公开(公告)号:US11905847B1
公开(公告)日:2024-02-20
申请号:US17970917
申请日:2022-10-21
发明人: Jonas Banhos , James T. Roach , Cheng Gao
CPC分类号: F01D5/147 , F01D5/18 , F01D5/282 , F01D9/041 , F05D2220/32 , F05D2230/20 , F05D2240/12 , F05D2240/30 , F05D2300/603
摘要: An airfoil includes an airfoil wall that has a span between first and second radial ends and that defines leading and trailing edges, pressure and suction sides each joining the leading and trailing edges, and an internal cavity. The internal cavity is divided into at least first and second sub-cavities extending over the span. The first sub-cavity defines a venturi tube.
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