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公开(公告)号：US20160369633A1
公开(公告)日：2016-12-22
申请号：US14901450
申请日：2014-07-03
Applicant: GENERAL ELECTRIC COMPANY
Inventor： George Joe-Kueng CHAN , Ronald Scott Bunker , Victor Hugo Silva CORREIA , Christopher Kanoa HOFFMAN
CPC classification number: F01D5/187 , F01D5/143 , F01D5/18 , F01D5/186 , F01D9/041 , F01D25/12 , F04D29/324 , F04D29/542 , F04D29/5846 , F05D2220/32 , F05D2260/202 , Y02T50/673 , Y02T50/676
Abstract: An airfoil comprises at least one wall defining a leading edge, a trailing edge, a pressure side extending between the leading edge and the trailing edge, and a suction side extending between the leading edge and the trailing edge. The airfoil is curved in three dimensions and has one or more cavities defined by an interior surface of the at least one wall. A plurality of cooling film holes extending between the cavity and at least one cooling trench located on at least one of the pressure side and the suction side, spaced from the leading edge. The at least one trench has a floor spaced from an outer surface of the airfoil. The plurality of cooling film holes extend through the floor at an angle other than perpendicular.
Abstract translation: 翼型件包括限定前缘，后缘，在前缘和后缘之间延伸的压力侧的至少一个壁和在前缘和后缘之间延伸的吸力侧。 翼型件在三维中弯曲并具有由至少一个壁的内表面限定的一个或多个空腔。 多个冷却膜孔，其在所述空腔和位于所述压力侧和所述吸入侧中的至少一个上的至少一个冷却沟槽之间延伸，与所述前缘间隔开。 至少一个沟槽具有与翼型件的外表面间隔开的底板。 多个冷却膜孔以与垂直不同的角度延伸穿过地板。
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公开(公告)号：US20160208700A1
公开(公告)日：2016-07-21
申请号：US15012173
申请日：2016-02-01
Applicant: GENERAL ELECTRIC COMPANY
Inventor： William Paul Minnear , Ronald Scott Bunker , Narendra Digamber Joshi , Andrei Tristan Evulet
CPC classification number: F02C7/16 , C04B41/0072 , C04B41/009 , C04B41/80 , F01D15/10 , F01D25/12 , F02C7/12 , F05D2260/232 , Y02T50/672 , Y02T50/676 , C04B35/56 , C04B35/565 , C04B35/806 , C04B41/4529
Abstract: A turbine power generation system with enhanced stabilization of refractory carbides provided by hydrocarbon from high carbon activity gases is disclosed. The disclosure also includes a method of using high carbon activity gases to stabilize hot gas path components.
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公开(公告)号：US20140352319A1
公开(公告)日：2014-12-04
申请号：US13906144
申请日：2013-05-30
Applicant: General Electric Company
Inventor： Ronald Scott Bunker
IPC: F02C3/04
CPC classification number: F02C7/08 , F02C3/10 , F05D2240/35 , F23R3/18 , F23R3/26 , F23R3/50 , F23R2900/00015 , F23R2900/03341
Abstract: A gas turbine engine and method for operating a gas turbine engine includes compressing an air stream in a compressor and generating a post combustion gas by combusting a compressed air stream exiting from the compressor in a combustor. The post combustion gas is expanded in a first turbine. The expanded combustion gas exiting from the first turbine is split into a first stream, a second stream and a third stream. The first stream of the expanded combustion gas is combusted in a reheat combustor. An outer liner and flame stabilizer of the reheat combustor are cooled using the second stream of the expanded combustion gas. An inner liner of the reheat combustor is cooled using the third stream of the expanded combustion gas and a portion of the second stream of the expanded combustion gas passing through the one or more flame stabilizers.
Abstract translation: 用于操作燃气涡轮发动机的燃气涡轮发动机和方法包括压缩压缩机中的空气流并且通过在燃烧器中燃烧从压缩机排出的压缩空气流而产生后燃气体。 后燃烧气体在第一涡轮机中膨胀。 从第一涡轮机排出的膨胀的燃烧气体被分成第一流，第二流和第三流。 膨胀燃烧气体的第一流在再热燃烧器中燃烧。 使用扩展燃烧气体的第二流冷却再热燃烧器的外衬和火焰稳定器。 再加热燃烧器的内衬层使用膨胀燃烧气体的第三流冷却，并且膨胀的燃烧气体的第二流的一部分通过一个或多个火焰稳定器。
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公开(公告)号：US11313235B2
公开(公告)日：2022-04-26
申请号：US14659640
申请日：2015-03-17
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Frederick Alan Buck , Robert David Briggs , Gulcharan Singh Brainch , Kevin Robert Feldmann
Abstract: An engine component for a gas turbine engine includes a film-cooled substrate having a hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow. The substrate includes one or more film holes that have a metering section defining a metering diameter and a diffusing section that defines a hooded length.
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公开(公告)号：US10731472B2
公开(公告)日：2020-08-04
申请号：US15150647
申请日：2016-05-10
Applicant: General Electric Company
Inventor： Ronald Scott Bunker
Abstract: An airfoil for a turbine engine having an engine component including an air supply circuit coupled to a plurality of passages within the outer wall of the engine component where cooling air moves from the air supply circuit to an outer surface of the engine component through the passages.
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Patent Agency Ranking
公开(公告)号：US10577949B2
公开(公告)日：2020-03-03
申请号：US15182651
申请日：2016-06-15
Applicant: General Electric Company
Inventor： Shawn Michael Pearson , Kirk Douglas Gallier , Ronald Scott Bunker
IPC: F01D5/28
Abstract: A component for a gas turbine engine includes a first region formed substantially of a first CMC material, wherein first region defines a first thermal conductivity. The component further includes a second region formed substantially of a second CMC material, wherein the second region defines a second thermal conductivity. Further, the component defines a thickness and the first region is positioned adjacent to the second region along the thickness, wherein the first thermal conductivity is different than the second thermal conductivity to alert a thermal profile of the component.
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公开(公告)号：US10570767B2
公开(公告)日：2020-02-25
申请号：US15016645
申请日：2016-02-05
Applicant: General Electric Company
Inventor： Jonathan Russell Ratzlaff , Ronald Scott Bunker
Abstract: An apparatus and method of a gas turbine engine comprising a rotor having at least one disk with a rotor defining an axial face and a stator having at least one ring with a stator axial face confronting the rotor axial face, with terminal portions of the axial faces forming a fluid outlet there between. A recess formed in one of the axial faces defines a buffer cavity into which a wing extends from the other of the axial faces and having a surface confronting the fluid outlet. A flow reverser is further provided within at least one of the surface or the terminal portion of the other of the axial faces.
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公开(公告)号：US10472972B2
公开(公告)日：2019-11-12
申请号：US14955261
申请日：2015-12-01
Applicant: General Electric Company
Abstract: Engine components are provided for a gas turbine engines that generate a hot combustion gas flow. The engine component can include a substrate constructed from a CMC material and having a hot surface facing the hot combustion gas flow and a cooling surface facing a cooling fluid flow. The substrate generally 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 engine component can also include a coating on at least a portion of the hot surface and on at least a portion of an inner surface defined within the passage.
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公开(公告)号：US20190338651A1
公开(公告)日：2019-11-07
申请号：US16458567
申请日：2019-07-01
Applicant: General Electric Company
Inventor： Ronald Scott Bunker
Abstract: An apparatus and method for providing a cooling fluid flow having a wall separating the hot air flow from the cooling fluid flow and having a first surface along which the hot air flows in a hot flow path and a second surface facing the cooling fluid flow, first and second supply circuits for providing the cooling fluid flow, at least one skin cooling circuit with at least one channel formed in the first surface, the at least one channel fluidly coupled with the first supply circuit.
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公开(公告)号：US10458259B2
公开(公告)日：2019-10-29
申请号：US15152887
申请日：2016-05-12
Applicant: General Electric Company
Inventor： Jason Randolph Allen , Ronald Scott Bunker
Abstract: An apparatus and method for flowing cooling air through an outer wall of an engine component such as an airfoil. The airfoil having the outer wall can include an opening. A framework can be disposed in the opening adapted to reduce the required flow through the opening to increase the efficiency of the engine and improve cooling.
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