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公开(公告)号：US20230119008A1
公开(公告)日：2023-04-20
申请号：US17451102
申请日：2021-10-15
Applicant: General Electric Company
Inventor： Ryan Christopher Jones , Shai Birmaher , Nicholas John Bloom , Daniel J. Kirtley , Gerardo Antonio Salazar Lois , Anquan Wang , Trevor James Hahm
Abstract: A combustor for a turbomachine engine includes a dome made of a ceramic matrix composite (CMC) material, the dome being secured within a support structure. The combustor includes an outer liner made of the CMC material, the outer liner being secured to the dome within the support structure. The combustor also includes an inner liner made of the CMC material, the inner liner being secured to the dome within the support structure.
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公开(公告)号：US11092076B2
公开(公告)日：2021-08-17
申请号：US15823732
申请日：2017-11-28
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Anquan Wang , Hojjat Nasr , Craig Alan Gonyou , Michael Anthony Benjamin
Abstract: A combustor assembly for a turbine engine and method for cooling a portion of the combustor assembly, the combustor assembly comprising a combustor liner defining a combustion chamber with an inlet and an outlet, a fuel dome located in the inlet and having a wall adjacent at least a portion of the combustor liner, and a deflector overlying and spaced from at least a portion of the wall.
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公开(公告)号：US20240102392A1
公开(公告)日：2024-03-28
申请号：US18536428
申请日：2023-12-12
Applicant: General Electric Company
Inventor： Anquan Wang , Ryan Christopher Jones , Paul Christopher Schilling , Craig Alan Gonyou
IPC: F01D5/18
CPC classification number: F01D5/186
Abstract: An apparatus relating to a component for a turbine engine which generates a hot gas fluid flow, and provides a cooling fluid flow. The component having a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow. At least one cooling hole including a connecting passage extending from a first inlet located at the cooled surface, to a first outlet located at the heated surface, the connecting passage defining a downstream flow direction from the first inlet to the first outlet, the connecting passage comprising a metering section fluidly coupled to the first inlet and defining a metered centerline and a diffusing section, downstream of the metering section, defining a diffused centerline, and fluidly coupling the metering section to the first outlet.
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公开(公告)号：US20210199296A1
公开(公告)日：2021-07-01
申请号：US17187040
申请日：2021-02-26
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Anquan Wang , Eric John Ruggiero
Abstract: An apparatus, system, and method of reducing film cooling scrubbing in a combustor are provided. The apparatus includes a combustor liner that includes a field of a plurality of sparsely-spaced film holes that extend through the combustor liner wherein the field includes a boundary. The combustor liner also includes a patch of relatively more densely-spaced shield holes that extend through the combustor liner at specific predetermined locations within the boundary of the field.
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公开(公告)号：US10822958B2
公开(公告)日：2020-11-03
申请号：US16249285
申请日：2019-01-16
Applicant: General Electric Company
Inventor： Anquan Wang , Ryan Christopher Jones , Paul Christopher Schilling , Craig Alan Gonyou
IPC: F01D5/18
Abstract: An apparatus and method relating to a cooling hole of a component of a turbine engine. The component can include a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow and at least one cooling hole comprising at least one inlet at the cooled surface, at least one outlet at the heated surface, with the outlet having a modified outlet shape.
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Patent Agency Ranking
公开(公告)号：US10662786B2
公开(公告)日：2020-05-26
申请号：US14993366
申请日：2016-01-12
Applicant: General Electric Company
Inventor： Anquan Wang , Wilbur Douglas Scheidt , Jeffrey Lehmkuhl
Abstract: An engine component is generally provided for a gas turbine engine generating hot combustion gas flow. In one embodiment, the engine the engine component includes a substrate having a hot surface facing the hot combustion gas flow and a cooling surface facing a cooling fluid flow. The substrate defines a film hole extending through the substrate and having an inlet provided on the cooling surface, an outlet provided on the hot surface, and a passage connecting the inlet and the outlet. The passage defines a diffusion section having a pair of side passage walls extending to the outlet on the hot surface, with each of the side passage walls within the diffusion section having a surface roughness (Ra) of about 4 mils to about 7 mils. Methods are also provided for forming a film hole in a CMC substrate.
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公开(公告)号：US11859819B2
公开(公告)日：2024-01-02
申请号：US17451102
申请日：2021-10-15
Applicant: General Electric Company
Inventor： Ryan Christopher Jones , Shai Birmaher , Nicholas John Bloom , Daniel J. Kirtley , Gerardo Antonio Salazar Lois , Anquan Wang , Trevor James Hahm
CPC classification number: F23R3/002 , F02C3/04 , F23R3/007 , F23R3/60 , F05D2220/32 , F05D2240/35
Abstract: A combustor for a turbomachine engine includes a dome made of a ceramic matrix composite (CMC) material, the dome being secured within a support structure. The combustor includes an outer liner made of the CMC material, the outer liner being secured to the dome within the support structure. The combustor also includes an inner liner made of the CMC material, the inner liner being secured to the dome within the support structure.
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公开(公告)号：US20210317745A1
公开(公告)日：2021-10-14
申请号：US17068235
申请日：2020-10-12
Applicant: General Electric Company
Inventor： Anquan Wang , Ryan Christopher Jones , Paul Christopher Schilling , Craig Alan Gonyou
IPC: F01D5/18
Abstract: An apparatus and method relating to a cooling hole of a component of a turbine engine. The component can include a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow and at least one cooling hole comprising at least one inlet at the cooled surface, at least one outlet at the heated surface, with the outlet having a modified outlet shape.
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公开(公告)号：US20180283689A1
公开(公告)日：2018-10-04
申请号：US15477818
申请日：2017-04-03
Applicant: General Electric Company
Inventor： Shanwu Wang , Anquan Wang
Abstract: A combustor liner, a combustor, and a gas turbine engine are provided. The combustor liner includes a liner portion having a plurality of dilution holes extending through the liner portion. Each dilution hole includes a downstream edge in a direction of a flow of a first fluid through the combustion liner. The downstream edge includes a film cooling starter device. The film cooling starter device includes a plurality of cooling holes extending through the liner portion and spaced apart from the downstream edge in a downstream direction. The film cooling starter device also includes a support flange extending from the downstream edge into the combustion zone, and a lip extending away from the support flange in the downstream direction and spaced a predetermined distance from a surface of the liner portion.
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公开(公告)号：US10041676B2
公开(公告)日：2018-08-07
申请号：US14794016
申请日：2015-07-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nayan Vinodbhai Patel , Kwanwoo Kim , Chad Holden Sutton , Duane Douglas Thomsen , Craig Alan Gonyou , Harris Daniel Abramson , James A. Russo , Robert Andrew Stowers , Shanwu Wang , Anquan Wang
Abstract: A combustor assembly for a gas turbine engine defining an axial direction is provided. The combustor assembly generally includes a liner, an annular dome, and a deflector plate. The liner at least partially defines a combustion chamber. The annular dome defines a first cavity and has a plurality of impingement holes, and the deflector plate defines a conical surface and a flat surface, wherein a plurality of cooling holes are defined through the deflector plate. The annular dome and the deflector plate are positioned together to define a second cavity that is in fluid communication with the first cavity through the plurality of impingement holes. In addition, the second cavity is in fluid communication with the combustion chamber through the plurality of cooling holes.
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