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公开(公告)号：US20240175364A1
公开(公告)日：2024-05-30
申请号：US18432818
申请日：2024-02-05
Applicant: GENERAL ELECTRIC COMPANY
CPC classification number: F01D5/147 , F01D25/12 , F01D25/14 , F23C7/02 , F05D2300/60 , F05D2300/70
Abstract: A method of forming a gas turbine engine component, the method including forming a plurality of cooling apertures in a preform structure of the component, the plurality of cooling apertures of the preform structure comprising a first cooling aperture and a second cooling aperture, wherein cross-sectional shapes of the first and second cooling apertures of the preform structure are different from one another, as measured in a same relative plane; and applying a coating to at least a portion of the preform structure to form the component, wherein a cross-sectional shape of the first and second cooling apertures of the component are approximately the same as one another, as measured in the same relative plane.
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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：US11828466B2
公开(公告)日：2023-11-28
申请号：US17499085
申请日：2021-10-12
Applicant: General Electric Company
Inventor： Gerardo Antonio Salazar Lois , Daniel J. Kirtley , Nicholas John Bloom , Shai Birmaher , Ryan Christopher Jones
CPC classification number: F23R3/16 , F23R3/007 , F23R3/60 , F23R2900/00017
Abstract: A combustor for a gas turbine includes a ceramic matrix composite (CMC) dome with a swirler mounting wall formed integral with the CMC dome, and a swirler assembly including a plurality of clevis dome attachment members for connecting the swirler assembly to the CMC dome. Bushings are arranged within a plurality of dome-side swirler assembly mounting openings of the swirler mounting wall, and the CMC dome is arranged within respective ones of the plurality of clevis dome attachment members of the swirler assembly. A swirler-dome connecting member is disposed through each of the clevis dome attachment members so as to mount the swirler assembly to the CMC dome.
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公开(公告)号：US20230112757A1
公开(公告)日：2023-04-13
申请号：US17499083
申请日：2021-10-12
Applicant: General Electric Company
Inventor： Gerardo Antonio Salazar Lois , Nicholas John Bloom , Daniel J. Kirtley , Shai Birmaher , Ryan Christopher Jones
Abstract: A combustor for a gas turbine includes a ceramic matrix composite (CMC) dome including a swirler opening therethrough with a flare interface surface surrounding the swirler opening, a swirler assembly including (a) a secondary swirler having a threaded flare attachment portion, and (b) a flare having (i) a threaded secondary swirler attachment portion, and (ii) a dome interface wall that interfaces with the flare interface surface of the CMC dome, and a swirler-dome attachment member. The flare is connected to the secondary swirler via the threaded flare attachment portion and the threaded secondary swirler attachment portion, and the swirler-dome attachment member applies a force to the CMC dome to engage the dome interface wall and the flare interface surface so as to connect the CMC dome and the swirler assembly.
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公开(公告)号：US20210220904A1
公开(公告)日：2021-07-22
申请号：US17221911
申请日：2021-04-05
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Daniel Endecott Osgood , Tingfan Pang , Gregory Terrence Garay , Zachary Daniel Webster , Ryan Christopher Jones
Abstract: A leachable casting core and method of manufacture may include a plurality of legs configured to establish a plurality of internal flow channels of a cast component. Tie bars, with a first tie bar end and a second tie bar end opposite thereof, may couple to at least two of the plurality of legs. At least one of the tie bars may be oriented to form a linking cavity within the cast component between the internal flow channels. The linking cavity may serve as an obstruction to fluid communication through the linking cavity.
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Patent Agency Ranking
公开(公告)号：US20210148242A1
公开(公告)日：2021-05-20
申请号：US17158670
申请日：2021-01-26
Applicant: General Electric Company
Inventor： Ryan Christopher Jones , Daniel Endecott Osgood , Zachary Daniel Webster , Gregory Terrence Garay , Tingfan Pang
Abstract: A turbomachinery sealing apparatus including a first turbomachinery component having a first end face, and a seal extending away from the first end face, the seal being connected to a wall of the component by a tab extending between the wall and the seal.
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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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公开(公告)号：US20200040753A1
公开(公告)日：2020-02-06
申请号：US16055987
申请日：2018-08-06
Applicant: General Electric Company
Inventor： Ryan Christopher Jones , Daniel Endecott Osgood , Zachary Daniel Webster , Gregory T. Garay , Tingfan Pang
Abstract: A turbomachinery sealing apparatus including a first turbomachinery component having a first end face, and a seal extending away from the first end face, the seal being connected to a wall of the component by a tab extending between the wall and the seal.
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公开(公告)号：US11873734B2
公开(公告)日：2024-01-16
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
CPC classification number: F01D5/186
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：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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