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公开(公告)号：US20190162117A1
公开(公告)日：2019-05-30
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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22.发明申请公开(公告)号：US20170167728A1
公开(公告)日：2017-06-15
申请号：US14969372
申请日：2015-12-15
Applicant: General Electric Company
Inventor： Craig Alan Gonyou , William Thomas Bennett
CPC classification number: F23R3/002 , F23R3/06 , F23R3/16 , F23R3/283 , F23R3/60 , F23R2900/00012 , F23R2900/00017 , Y02T50/675
Abstract: A combustor for a gas turbine engine comprising a combustion liner defining a combustion chamber, wherein the combustion liner has at least one opening into which a combustor liner mount is received. The combustor liner mount can have at least one cooling passage defined therein having an inlet defining an inlet axis and an outlet defining an outlet axis, wherein the inlet axis is not collinear with the outlet axis for providing enhanced cooling to at least one of the combustor liner mount and an adjacent combustion component, such as an igniter or a borescope plug.
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公开(公告)号：US12291997B1
公开(公告)日：2025-05-06
申请号：US18650626
申请日：2024-04-30
Applicant: General Electric Company
Inventor： Steven Douglas Johnson , Scott Alan Schimmels , Craig Alan Gonyou , Paul Hadley Vitt
IPC: F02C7/042
Abstract: A variable area turbine nozzle assembly includes a guide vane including an outer centering pin defining a tab. An inner support ring is spaced radially outward from the guide vane and defines an opening and a protrusion. The protrusion is configured to engage with the tab of the outer centering pin. An outer support ring extends circumferentially around the inner support ring and defines an aperture. The outer support ring has a second coefficient of thermal expansion that is greater than or less than the first coefficient of thermal expansion. At least one linkage joins the inner support ring to the outer support ring and is configured to rotate the inner support ring circumferentially about an axial centerline of the variable area turbine nozzle assembly in response to a change in operational temperature of a combustion gas thus causing the guide vane to rotate.
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公开(公告)号：US20240066588A1
公开(公告)日：2024-02-29
申请号：US17898751
申请日：2022-08-30
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Daniel Endecott Osgood , Zachary Daniel Webster , Craig Alan Gonyou , Daniel Lee Durstock , Kevin R. Feldmann , Kirk Douglas Gallier , William C. Herman , Nicholas Charles Gentilli
IPC: B22C9/10
CPC classification number: B22C9/10
Abstract: A casting core used in the manufacture of a cast engine component for a turbine engine, the cast engine component having a first area, a second area, a fluid passage wall separating the first area and the second area, and a connecting fluid passage extending through the fluid passage wall and interconnecting the first area and the second area. The connecting fluid passage having a turn with a radius (R). The casting core having a first core and a second core. The first core and the second core being defined by a set of geometric characteristics having a first minimum equivalent diameter (D1eqmin) of the first core and a second minimum equivalent diameter (D2eqmin) of the second core. A first flexible geometry factor (FGF1) being equal to:
(
D
1
eq
min
D
2
eq
min
)
(
R
D
2
eq
min
)
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公开(公告)号：US11492972B2
公开(公告)日：2022-11-08
申请号：US16730570
申请日：2019-12-30
Applicant: General Electric Company
Inventor： Craig Alan Gonyou , Robert Proctor , Christopher Michael Thompson , Scott Alan Schimmels , Steven Douglas Johnson
Abstract: An annular fluid flow control or metering device comprises: first and second annular plates disposed in an annular flow path, the first annular plate and second annular plates being made of different first and second materials, the first annular plate having a lower first coefficient of thermal expansion than a second coefficient of thermal expansion of the second annular plate, the first annular plate abutting or in contact with the second annular plate, the first annular plate including at least one first metering aperture, and the second annular plate being more thermally responsive than the first annular plate wherein the second annular plate being configured to radially grow and shrink to at least partly obstruct the at least one first metering aperture for metering or controlling a flow of fluid through the at least one first metering aperture.
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Patent Agency Ranking
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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27.发明授权公开(公告)号：US10995954B2
公开(公告)日：2021-05-04
申请号：US16170981
申请日：2018-10-25
Applicant: General Electric Company
Inventor： Craig Alan Gonyou , William Thomas Bennett
Abstract: A combustor for a gas turbine engine comprising a combustion liner defining a combustion chamber, wherein the combustion liner has at least one opening into which a combustor liner mount is received. The combustor liner mount can have at least one cooling passage defined therein having an inlet defining an inlet axis and an outlet defining an outlet axis, wherein the inlet axis is not collinear with the outlet axis for providing enhanced cooling to at least one of the combustor liner mount and an adjacent combustion component, such as an igniter or a borescope plug.
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公开(公告)号：US20200182059A1
公开(公告)日：2020-06-11
申请号：US16210314
申请日：2018-12-05
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo , Kirk Douglas Gallier , Brandon Wayne Miller , Craig Alan Gonyou , Kevin Robert Feldmann , Justin Paul Smith
Abstract: An aspect of the present disclosure is directed to a rotor assembly for a turbine engine. The rotor assembly includes an airfoil assembly and a hub to which the airfoil assembly is attached. A wall assembly defines a first cavity and a second cavity between the airfoil assembly and the hub. The first cavity and the second cavity are at least partially fluidly separated by the wall assembly. The first cavity is in fluid communication with a flow of first cooling fluid and the second cavity is in fluid communication with a flow of second cooling fluid different from the first cooling fluid.
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公开(公告)号：US20200063583A1
公开(公告)日：2020-02-27
申请号：US16107227
申请日：2018-08-21
Applicant: General Electric Company
Inventor： Andrew Scott Bilse , Donald Lee Gardner , Craig Alan Gonyou , Paul Christopher Schilling , Hojjat Nasr , Ryan Christopher Jones
Abstract: A combustor assembly for a heat engine is generally provided. The combustor assembly includes a liner wall defining a combustion chamber, and a deflector assembly. The deflector assembly includes a radially extended first wall disposed adjacent to the combustion chamber, and further an axially extended second wall disposed forward of the first wall and adjacent thereto. The second wall is coupled to the liner wall.
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30.发明申请公开(公告)号：US20190154260A1
公开(公告)日：2019-05-23
申请号：US16170981
申请日：2018-10-25
Applicant: General Electric Company
Inventor： Craig Alan Gonyou , William Thomas Bennett
Abstract: A combustor for a gas turbine engine comprising a combustion liner defining a combustion chamber, wherein the combustion liner has at least one opening into which a combustor liner mount is received. The combustor liner mount can have at least one cooling passage defined therein having an inlet defining an inlet axis and an outlet defining an outlet axis, wherein the inlet axis is not collinear with the outlet axis for providing enhanced cooling to at least one of the combustor liner mount and an adjacent combustion component, such as an igniter or a borescope plug.
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