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公开(公告)号：US20170284303A1
公开(公告)日：2017-10-05
申请号：US15083392
申请日：2016-03-29
Applicant: General Electric Company
Inventor： Steven Douglas Johnson , Brandon Wayne Miller , Craig Alan Gonyou
CPC classification number: F02C9/18 , B64D13/08 , F01D17/105 , F01D25/14 , F02C3/04 , F02C7/18 , F02K3/06 , F02K3/075 , F05D2220/323 , F05D2250/411 , F05D2260/213 , F05D2270/101 , F05D2270/112
Abstract: Axially adjacent annular booster bleed aft and forward plenums with annular common wall therebetween extend radially outwardly from transition duct. Variable bleed valve includes bleed valve door in bleed inlet in transition duct, attached to rotatable valve body rotatable about axis of rotation, operable to open and close bleed inlet to aft plenum. Rotatable plenum door clocked or circumferentially spaced apart from variable bleed valve door and attached to rotatable valve body, operable to close and open up and control flow through an inter plenum aperture in common wall. Aft and forward bleed exhaust ducts extend from booster bleed aft and forward plenums to bypass flow path. One or more heat exchanger, such as from thermal management system, may be disposed in the bleed exhaust ducts. Heat exchangers may be used for cooling oil for power gear box and/or engine bearings, air conditioning, or variable frequency generator.
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公开(公告)号：US20170130651A1
公开(公告)日：2017-05-11
申请号：US14934867
申请日：2015-11-06
Applicant: General Electric Company
Inventor： Hojjat Nasr , Juntao Zhang , Jessica Erin Schladt , Craig Alan Gonyou
CPC classification number: F02C7/18 , F23M5/085 , F23R3/002 , F23R3/04 , F23R3/06 , F23R2900/03042 , Y02T50/675
Abstract: A combustor for a gas turbine engine comprises a combustion liner to define a combustion chamber for burning fuel to drive to turbine. The combustion liner comprises a plurality of nugget holes for providing cooling fluid to create a cooling film over the surface of the combustion liner adjacent the combustion chamber. The nugget holes can be circumferentially angled relative to the engine centerline to provide the flow of cooling fluid in an angled manner to align with a local streamline for the flow of fluid from the combustor.
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公开(公告)号：US20170009986A1
公开(公告)日：2017-01-12
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 Andrews Stowers , Shanwu Wang , Anquan Wang
CPC classification number: F23R3/002 , F02C3/04 , F23R3/50 , F23R3/60 , F23R2900/03041 , F23R2900/03044 , Y02T50/675
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.
Abstract translation: 提供了一种用于限定轴向方向的燃气涡轮发动机的燃烧器组件。 燃烧器组件通常包括衬套，环形圆顶和偏转板。 衬垫至少部分地限定燃烧室。 环形拱顶限定第一腔并且具有多个冲击孔，并且偏转板限定锥形表面和平坦表面，其中多个冷却孔限定穿过偏转板。 环形圆顶和偏转板被定位在一起以限定通过多个冲击孔与第一空腔流体连通的第二腔。 此外，第二空腔通过多个冷却孔与燃烧室流体连通。
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公开(公告)号：US20250093032A1
公开(公告)日：2025-03-20
申请号：US18469187
申请日：2023-09-18
Applicant: GENERAL ELECTRIC COMPANY , GE Marmara Technology Center Muhendislik Hizmetleri Ltd , GE Aerospace Poland sp. z o.o.
Inventor： Emrah Deniz , Fatih Yasar , Katarzyna Anna Mikolajczyk , Michael T. Bucaro , Ahmet Kacar , Anquan Wang , Hejie Li , Craig Alan Gonyou , Aaron C. Brady
Abstract: A gas turbine engine comprises a compressor section, a combustion section, and a turbine section in a serial flow arrangement and enshrouded by a casing, the combustion section comprising: an annular combustion chamber defined by at least a dome wall and an annular liner; a plurality of combustor cups circumferentially arranged on the dome wall; a fuel supply connected to the casing; and a fuel nozzle passing through the casing and having a nozzle tube and a distribution manifold fluidly coupling the nozzle tube to at least two combustor cups of the plurality of combustor cups; wherein the fuel nozzle is fixed to the at least two combustor cups.
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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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Patent Agency Ranking
公开(公告)号：US11821324B2
公开(公告)日：2023-11-21
申请号：US17845213
申请日：2022-06-21
Applicant: General Electric Company
Inventor： Mehmet Cem Apaydin , Craig Alan Gonyou , Scott Alan Schimmels , Christopher Michael Thompson
CPC classification number: F01D21/003 , F02C3/04 , G01M15/14 , F05D2270/3015
Abstract: A turbine engine includes a pressurized fluid source, a duct system comprising a plurality of ducts in fluid communication with the pressurized fluid source, and a duct failure detection system. The duct failure detection system includes a plurality of pressure sensors. Each of the plurality of pressure sensors is in operable communication with two ducts of the plurality of ducts. Each of the plurality of ducts has at least two pressure sensors of the plurality of pressure sensors in operable communication therewith.
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公开(公告)号：US11339966B2
公开(公告)日：2022-05-24
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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公开(公告)号：US11187412B2
公开(公告)日：2021-11-30
申请号：US16108674
申请日：2018-08-22
Applicant: General Electric Company
Inventor： Andrew Scott Bilse , Craig Alan Gonyou , Ryan Christopher Jones
Abstract: A heat engine including a wall assembly is generally provided. The wall assembly includes a plurality of radial walls coupled together via a connecting member. The radial wall defines a flow opening therethrough. A flow cavity is defined between the plurality of radial walls and the connecting member.
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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：US11021961B2
公开(公告)日：2021-06-01
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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