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公开(公告)号：US11933223B2
公开(公告)日：2024-03-19
申请号：US16388206
申请日：2019-04-18
摘要： An attritable engine includes an engine case, which includes an outer wall and a fuel rail integral with the outer wall. The fuel rail includes a fuel line integral with the outer wall, a fuel ring configured to receive fuel from the fuel line, and an injector throat configured to receive aerated fuel from the fuel ring. The engine case includes counter distortion webbing defining the injector throat and is integral with the fuel rail and the outer wall. The engine case includes a combustion chamber configured to receive fuel from the injector throat.
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2.发明授权公开(公告)号：US11806939B2
公开(公告)日：2023-11-07
申请号：US17503880
申请日：2021-10-18
发明人： Lawrence Binek , Matthew B. Kennedy , Evan Butcher , Jesse R. Boyer , Vijay Narayan Jagdale , Dmytro Mykolayovych Voytovych
CPC分类号： B29C64/40 , B29C64/153 , F01D5/02 , F01D21/045 , B33Y10/00 , B33Y30/00 , B33Y80/00 , F05D2230/22 , F05D2230/233
摘要： A rotary component may comprise a first structure configured to rotate about an axis and a second structure configured to rotate about the axis. A support structure may be coupled to the first structure at a first attachment location and to the second structure at a second attachment location. The support structure may be configured to separate from the first structure and the second structure in response to a centrifugal force generated by the first structure and the second structure rotating about the axis.
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公开(公告)号：US11612938B2
公开(公告)日：2023-03-28
申请号：US17591054
申请日：2022-02-02
摘要： A core engine article includes a combustor liner defining a combustion chamber therein and a turbine nozzle. The combustor liner includes a plurality of injector ports, and the plurality of injector ports have a shape that tapers to a corner on a forward side of the injector ports. The turbine nozzle includes a plurality of airfoils. The combustor liner and turbine nozzle are integral with one another. A method of making a core engine article is also disclosed.
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公开(公告)号：US11578614B2
公开(公告)日：2023-02-14
申请号：US17465244
申请日：2021-09-02
IPC分类号： F01D25/00
摘要： A monolithic combustor apparatus comprises an outer casing comprising a forward flange, a fuel manifold disposed on the outer casing and defining an annular chamber extending perimetrically around the outer casing, a combustor liner disposed within the outer casing, the combustor liner defining an annular combustion chamber, a first annular plenum disposed between the outer casing and the combustor liner, an inner liner disposed radially from the combustor liner, a first inner flange extending forward from the combustor liner, and a second inner flange extending radially inward from the first inner flange.
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公开(公告)号：US20210396151A1
公开(公告)日：2021-12-23
申请号：US17465244
申请日：2021-09-02
IPC分类号： F01D25/00
摘要： A monolithic combustor apparatus comprises an outer casing comprising a forward flange, a fuel manifold disposed on the outer casing and defining an annular chamber extending perimetrically around the outer casing, a combustor liner disposed within the outer casing, the combustor liner defining an annular combustion chamber, a first annular plenum disposed between the outer casing and the combustor liner, an inner liner disposed radially from the combustor liner, a first inner flange extending forward from the combustor liner, and a second inner flange extending radially inward from the first inner flange.
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公开(公告)号：US12053821B2
公开(公告)日：2024-08-06
申请号：US18122207
申请日：2023-03-16
摘要： A core engine article includes a combustor liner defining a combustion chamber therein and a turbine nozzle. The combustor liner includes a plurality of injector ports, and the plurality of injector ports have a shape that tapers to a corner on a forward side of the injector ports. The turbine nozzle includes a plurality of airfoils. The combustor liner and turbine nozzle are integral with one another. A method of making a core engine article is also disclosed.
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公开(公告)号：US20230241681A1
公开(公告)日：2023-08-03
申请号：US18122207
申请日：2023-03-16
摘要： A core engine article includes a combustor liner defining a combustion chamber therein and a turbine nozzle. The combustor liner includes a plurality of injector ports, and the plurality of injector ports have a shape that tapers to a corner on a forward side of the injector ports. The turbine nozzle includes a plurality of airfoils. The combustor liner and turbine nozzle are integral with one another. A method of making a core engine article is also disclosed.
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8.发明申请公开(公告)号：US20220032554A1
公开(公告)日：2022-02-03
申请号：US17503880
申请日：2021-10-18
发明人： Lawrence Binek , Matthew B. Kennedy , Evan Butcher , Jesse R. Boyer , Vijay Narayan Jagdale , Dmytro Mykolayovych Voytovych
IPC分类号： B29C64/40 , B29C64/153 , F01D5/02 , F01D21/04
摘要： A rotary component may comprise a first structure configured to rotate about an axis and a second structure configured to rotate about the axis. A support structure may be coupled to the first structure at a first attachment location and to the second structure at a second attachment location. The support structure may be configured to separate from the first structure and the second structure in response to a centrifugal force generated by the first structure and the second structure rotating about the axis.
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公开(公告)号：US11904405B2
公开(公告)日：2024-02-20
申请号：US17665788
申请日：2022-02-07
发明人： Vijay Narayan Jagdale , Jesse R. Boyer , Om P. Sharma , Evan J. Butcher , Lawrence Binek , Bryan G. Dods
CPC分类号： B23K26/0006 , B22F10/25 , B22F10/38 , F01D25/24 , B22F10/366 , B33Y10/00 , B33Y80/00 , F05D2230/22 , F05D2230/30 , F05D2250/181 , F05D2250/63
摘要： A process for additively controlled surface features of a gas turbine engine casing. The process comprises forming the casing having an inner surface and an outer surface opposite the inner surface; forming a surface feature on the casing proximate the inner surface, wherein the surface feature comprises a structure on the inner surface configured to align or misalign with respect to a flow direction of a working fluid in a flow path of the casing.
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公开(公告)号：US20220221151A1
公开(公告)日：2022-07-14
申请号：US17591054
申请日：2022-02-02
摘要： A core engine article includes a combustor liner defining a combustion chamber therein and a turbine nozzle. The combustor liner includes a plurality of injector ports, and the plurality of injector ports have a shape that tapers to a corner on a forward side of the injector ports. The turbine nozzle includes a plurality of airfoils. The combustor liner and turbine nozzle are integral with one another. A method of making a core engine article is also disclosed.
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