公开(公告)号：US20170145831A1

公开(公告)日：2017-05-25

申请号：US14950627

申请日：2015-11-24

Applicant: General Electric Company

Inventor： Ronald Scott Bunker

IPC: F01D5/18 ,  F23R3/06 ,  F04D29/58 ,  F01D25/12 ,  F04D29/32 ,  F04D29/54 ,  F23R3/00 ,  F01D9/02

CPC classification number: F01D5/186 ,  F01D9/02 ,  F01D9/065 ,  F01D25/12 ,  F04D29/324 ,  F04D29/542 ,  F04D29/545 ,  F04D29/582 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/35 ,  F05D2240/81 ,  F05D2250/312 ,  F05D2250/314 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/06 ,  F23R2900/03042 ,  Y02T50/672 ,  Y02T50/676

Abstract: An engine component for a gas turbine engine can generate a hot combustion gas flow and provide a cooling fluid flow. A wall can separate the hot combustion gas flow from the cooling fluid flow. Multiple film holes can be disposed in the wall, having an inlet adjacent the cooling fluid flow and an outlet at the hot combustion gas flow such that the cooling fluid flow can be provided to the hot combustion gas flow. The film holes further comprise inlets, such that the inlets can be arranged with the inlets having at least one of a different orientation relative to one another or are non-aligned with each other relative to the cooling fluid flow.

公开(公告)号：US20170122109A1

公开(公告)日：2017-05-04

申请号：US14926294

申请日：2015-10-29

Applicant: General Electric Company

Inventor： Ronald Scott Bunker ,  Kirk D. Gallier ,  David Alan Frey

IPC: F01D5/18 ,  F01D9/04 ,  F04D29/54 ,  F01D5/28 ,  F04D29/38 ,  F01D5/14 ,  F01D25/12

CPC classification number: F01D5/18 ,  F01D5/147 ,  F01D5/282 ,  F01D5/284 ,  F01D9/023 ,  F01D9/041 ,  F01D25/12 ,  F01D25/14 ,  F04D29/384 ,  F04D29/544 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2240/35 ,  F05D2260/20 ,  F05D2300/6033 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676

Abstract: A component for a gas turbine engine includes a first surface and a second surface. The component additionally includes one or more layers of ceramic matrix composite material extending between the first and second surfaces. A thermal void extends between a first end and a second end. The second end of the thermal void is a terminal end embedded in the component between the first and second surfaces.

公开(公告)号：US09598963B2

公开(公告)日：2017-03-21

申请号：US15171270

申请日：2016-06-02

Applicant: General Electric Company

Inventor： Ronald Scott Bunker

IPC: F01D5/18 ,  F01D5/14 ,  B23P15/04

CPC classification number: F01D5/147 ,  B23P15/04 ,  F01D5/186 ,  F01D5/189 ,  F05D2230/30 ,  F05D2230/90 ,  F05D2260/204 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676 ,  Y10T29/49229

Abstract: A component includes a substrate having an outer surface and an inner surface, where the inner surface defines at least one hollow, interior space. The outer surface of the substrate defines a pressure side wall and a suction side wall. The pressure and suction side walls are joined together at a leading edge and at a trailing edge of the component. The outer surface defines one or more grooves that extend at least partially along the pressure or suction side walls in a vicinity of the trailing edge of the component. Each groove is in fluid communication with a respective hollow, interior space. The component further includes a coating disposed over at least a portion of the outer surface of the substrate. The coating comprises at least a structural coating, where the structural coating extends over the groove(s), such that the groove(s) and the structural coating together define one or more channels for cooling the trailing edge of the component. A method of forming cooling channels in the vicinity of the trailing edge of a component is also provided.

公开(公告)号：US20170051674A1

公开(公告)日：2017-02-23

申请号：US14829678

申请日：2015-08-19

Applicant: General Electric Company

Inventor： Robert Francis Manning ,  Ronald Scott Bunker ,  Robert Frederick Bergholz ,  Robert David Briggs

IPC: F02C7/18

CPC classification number: F02C7/18 ,  F01D5/186 ,  F05D2250/294 ,  F05D2260/202 ,  F23R2900/03042 ,  Y02T50/672 ,  Y02T50/676

Abstract: An engine component for a gas turbine engine includes a film-cooled recess comprising a contoured portion defining a step. A hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow are fluidly coupled by a passage through the engine component. The passage further comprises an inlet in the cooling surface and an outlet in the step. The inlet, passage and outlet are oriented such that the cooling fluid flowing through the passage and exiting the outlet diffuses within the contoured portion prevents premature mixing out with the hot fluid flow.

Abstract translation: 用于燃气涡轮发动机的发动机部件包括膜冷却凹部，其包括限定步骤的轮廓部分。 面向热燃烧气体的热表面和面向冷却流体流的冷却表面通过通过发动机部件的通道流体耦合。 通道还包括冷却表面中的入口和台阶中的出口。 入口，通道和出口被定向成使得流过通道并离开出口的冷却流体在轮廓部分内扩散以防止与热流体流过度混合。

公开(公告)号：US20150202683A1

公开(公告)日：2015-07-23

申请号：US13650320

申请日：2012-10-12

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Ronald Scott Bunker

IPC: B22D25/02 ,  B22C9/10 ,  B22D21/00 ,  B22C7/00 ,  B22D29/00 ,  B22C9/02 ,  B22C9/24

CPC classification number: B22D25/02 ,  B22C7/00 ,  B22C9/02 ,  B22C9/10 ,  B22C9/103 ,  B22C9/24 ,  B22D21/007 ,  B22D29/00 ,  B28B7/346 ,  B28B7/348

Abstract: Methods of casting a component including one or more surface cooling channels. The method including casting a ceramic core into a flexible mold of a core section and casting a ceramic shell in at least two sections into respective flexible molds of a first shell section and a second shell section. A ceramic casting vessel is subsequently formed by assembling the ceramic core within the ceramic shell sections. A metal substrate material is cast into the ceramic casting vessel. Removal of the ceramic casting vessel reveals a substrate of the component having defined therein the interior passageway, the one or more cooling passages in fluidic communication with the interior passageway and one or more surface grooves in fluidic communication with the one or more cooling passages.

Abstract translation: 铸造包括一个或多个表面冷却通道的部件的方法。 该方法包括将陶瓷芯铸造到芯部分的柔性模具中并将至少两个部分中的陶瓷壳体铸造到第一壳部分和第二壳部分的相应的柔性模具中。 随后通过将陶瓷芯组装在陶瓷壳体部分内而形成陶瓷铸造容器。 将金属基材材料浇注到陶瓷铸造容器中。 去除陶瓷铸造容器显示了其中限定有内部通道的部件的基板，与内部通道流体连通的一个或多个冷却通道和与一个或多个冷却通道流体连通的一个或多个表面槽。

公开(公告)号：US20150135512A1

公开(公告)日：2015-05-21

申请号：US14084655

申请日：2013-11-20

Applicant: General Electric Company

Inventor： Robert R. Niblock ,  Paul H. Tacheron ,  Steven J. Craigen ,  Mohamed A. Hashish ,  Ronald Scott Bunker ,  Andrew Lee Trimmer

IPC: B26F1/26

CPC classification number: B26F1/26 ,  B23K26/00 ,  B23P15/02 ,  B23P2700/06 ,  B24C1/045 ,  F01D5/18 ,  F01D5/181 ,  Y10T29/49341 ,  Y10T29/49885 ,  Y10T29/49982 ,  Y10T29/49986 ,  Y10T29/49995

Abstract: A method of machining a component including a substrate having an outer surface and an inner surface defining at least one interior space includes: disposing a distributed medium having a plurality of irregularly shaped particles in the interior space and forming at least one hole in the substrate, while the distributed medium is disposed within the interior space, such that the distributed medium provides backstrike protection for an opposing wall during the formation of the hole(s). Each hole extends through the substrate to provide fluid communication with the respective interior space; and the method further includes removing the distributed medium from the interior space.

Abstract translation: 一种加工包括具有限定至少一个内部空间的外表面和内表面的基板的部件的方法包括：在所述内部空间中设置具有多个不规则形状的颗粒的分布介质，并在所述基板中形成至少一个孔， 而分布式介质设置在内部空间内，使得分布介质在孔的形成期间为相对的壁提供反冲击保护。 每个孔延伸穿过衬底以提供与相应内部空间的流体连通; 并且该方法还包括从内部空间移除分布式介质。

公开(公告)号：US09003657B2

公开(公告)日：2015-04-14

申请号：US13718256

申请日：2012-12-18

Applicant: General Electric Company

Inventor： Ronald Scott Bunker ,  Scott Andrew Weaver ,  Wayne Charles Hasz

IPC: B21D53/78 ,  B21K3/04 ,  B23P15/02 ,  F02C7/12 ,  C23C4/02 ,  F01D5/18

CPC classification number: F02C7/12 ,  B23P2700/06 ,  C23C4/02 ,  F01D5/183 ,  F05D2260/203 ,  Y02T50/672 ,  Y02T50/676 ,  Y10T29/49336 ,  Y10T29/49339 ,  Y10T29/49341 ,  Y10T29/49986

Abstract: A manufacturing method includes providing a substrate with an outer surface and at least one interior space and machining the substrate to selectively remove a portion of the substrate and define one or more cooling supply holes therein. Each of the one or more cooling supply holes is in fluid communication with the at least one interior space. The method further includes disposing an open cell porous metallic layer on at least a portion of the substrate. The open cell porous metallic layer is in fluid communication with the one or more cooling supply holes. A coating layer is disposed on the open cell porous metallic layer. The coating layer having formed therein one or more cooling exit holes in fluid communication with the open cell porous metallic layer. The substrate, the one or more cooling supply holes, the open cell porous metallic layer and the cooling exit holes providing a cooling network for a component.

Abstract translation: 一种制造方法包括：提供具有外表面和至少一个内部空间的基板，并加工所述基板以选择性地移除所述基板的一部分并在其中限定一个或多个冷却供应孔。 所述一个或多个冷却供应孔中的每一个与所述至少一个内部空间流体连通。 该方法还包括在基底的至少一部分上设置开孔多孔金属层。 开孔多孔金属层与一个或多个冷却供给孔流体连通。 在开孔多孔金属层上设置涂层。 涂层在其中形成有与开孔多孔金属层流体连通的一个或多个冷却出口孔。 衬底，一个或多个冷却供应孔，开孔多孔金属层和冷却出口孔为组件提供冷却网络。

公开(公告)号：US20140366550A1

公开(公告)日：2014-12-18

申请号：US13920244

申请日：2013-06-18

Applicant: General Electric Company

Inventor： Ronald Scott Bunker ,  Andrei Tristan Evulet

IPC: F02C3/04

CPC classification number: F02C7/141 ,  F02C3/10 ,  F23R3/18 ,  F23R3/26 ,  F23R2900/03341

Abstract: A gas turbine engine and method for operating a gas turbine engine includes compressing an air stream in a compressor and combusting the compressed air stream to generate a post combustion gas. The post combustion gas is expanded in a first turbine. The expanded combustion gas exiting the first turbine is split into a first stream, a second stream and a third stream in a splitting zone including one or more aerodynamically shaped flow diverters. 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燃烧压缩空气流以产生后燃烧气体。 后燃烧气体在第一涡轮机中膨胀。 离开第一涡轮机的膨胀的燃烧气体被分裂成包括一个或多个空气动力学形状的分流器的分流区中的第一流，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。

公开(公告)号：US20140157792A1

公开(公告)日：2014-06-12

申请号：US13709306

申请日：2012-12-10

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Gary Michael Itzel ,  Kevin R. Kirtley ,  Christian Lee Vandervort ,  Ronald Scott Bunker

IPC: F01D9/04

CPC classification number: F01D9/041 ,  F01D5/187 ,  F01D5/288 ,  F05D2260/204 ,  F05D2260/205

Abstract: A system for removing heat from a turbine includes a component in the turbine having a supply plenum and a return plenum therein. A substrate that defines a shape of the component has an inner surface and an outer surface. A coating applied to the outer surface of the substrate has an interior surface facing the outer surface of the substrate and an exterior surface opposed to the interior surface. A first fluid channel is between the outer surface of the substrate and the exterior surface of the coating. A first fluid path is from the supply plenum, through the substrate, and into the first fluid channel, and a second fluid path is from the first fluid channel, through the substrate, and into the return plenum.

Abstract translation: 用于从涡轮机去除热量的系统包括涡轮机中的部件，其中具有供应气室和回流室。 限定部件形状的基板具有内表面和外表面。 施加到基板的外表面的涂层具有面向基板的外表面的内表面和与内表面相对的外表面。 第一流体通道位于基底的外表面和涂层的外表面之间。 第一流体路径来自供应气室，通过基底，并进入第一流体通道，第二流体路径来自第一流体通道，穿过基底，并进入回流通气室。

公开(公告)号：US08741420B2

公开(公告)日：2014-06-03

申请号：US14097939

申请日：2013-12-05

Applicant: General Electric Company

Inventor： Ronald Scott Bunker ,  Dennis Michael Gray ,  Don Mark Lipkin

IPC: B32B3/00

CPC classification number: F01D25/12 ,  C23C4/02 ,  C23C4/18 ,  C23C24/04 ,  F01D5/187 ,  F01D5/288 ,  F05B2280/6011 ,  F05D2260/204 ,  Y02T50/67 ,  Y02T50/672 ,  Y02T50/676 ,  Y10T428/13 ,  Y10T428/2462

Abstract: A component is disclosed. The component comprises a substrate comprising an outer surface and an inner surface, where the inner surface defines at least one hollow, interior space, where the outer surface defines one or more grooves, and where each of the one or more grooves extends at least partially along the surface of the substrate and has a base. One or more access holes extend through the base of a respective groove to place the groove in fluid communication with respective ones of the at least one hollow interior space. The component further comprises a coating disposed over at least a portion of the substrate surface, where the coating comprises one or more layers. At least one of the layers defines one or more permeable slots, such that the respective layer does not completely bridge each of the one or more grooves. The grooves and the coating together define one or more channels for cooling the component.

Abstract translation: 公开了一个组件。 该组件包括一个包括一个外表面和一个内表面的基底，其中内表面限定了至少一个中空的内部空间，其中外表面限定了一个或多个凹槽，并且其中每个凹槽至少部分地延伸 沿着基板的表面并具有基部。 一个或多个进入孔延伸穿过相应凹槽的基部，以使凹槽与至少一个中空内部空间中的相应凹槽流体连通。 该组件还包括设置在衬底表面的至少一部分上的涂层，其中涂层包括一层或多层。 层中的至少一个限定一个或多个可渗透狭缝，使得相应的层不完全桥接一个或多个凹槽中的每一个。 凹槽和涂层一起限定一个或多个通道用于冷却部件。