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公开(公告)号：US20160061044A1
公开(公告)日：2016-03-03
申请号：US14784857
申请日：2014-04-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： John McBrien , Lea Kennard Castle , Brandon W. Spangler , JinQuan Xu
IPC: F01D5/28 , B32B9/00 , B32B1/08 , B32B3/08 , B22C9/22 , B22F3/105 , B23K26/342 , B23K15/00 , B22C9/02 , B22C9/10 , B32B3/26 , B32B5/16
CPC classification number: F01D5/28 , B22C7/02 , B22C9/02 , B22C9/043 , B22C9/061 , B22C9/10 , B22C9/101 , B22C9/108 , B22C9/22 , B22C9/24 , B22D23/06 , B22D25/02 , B22D27/04 , B22D27/045 , B22F3/1055 , B22F3/11 , B22F3/24 , B22F5/04 , B22F2003/248 , B22F2998/00 , B22F2998/10 , B23K15/0006 , B23K15/0086 , B23K26/342 , B32B1/08 , B32B3/08 , B32B3/26 , B32B5/16 , B32B9/005 , B32B2250/03 , B32B2264/105 , B32B2603/00 , B33Y10/00 , B33Y80/00 , C30B11/00 , C30B29/52 , F01D5/147 , F01D5/18 , F01D5/187 , F01D5/282 , F01D9/02 , F01D9/041 , F01D9/065 , F01D25/12 , F05D2220/32 , F05D2230/31 , F05D2300/175 , F05D2300/211 , F05D2300/607 , F23R3/28 , Y02P10/292 , Y02P10/295 , B22F2003/242 , C30B11/14
Abstract: One embodiment includes a method to regenerate a component (10). The method includes additively manufacturing a component (10) to have voids greater than 0 percent but less than approximately 15 percent in a near finished shape. The component (10) is encased in a shell mold (22). The shell mold (22) is cured. The encased component (10) is placed in a furnace and the component (10) is melted. The component (10) is solidified in the shell mold (22). The shell mold (22) is removed from the solidified component (10).
Abstract translation: 一个实施例包括重新生成组件（10）的方法。 该方法包括在接近完成的形状中相加地制造具有大于0％但小于约15％的空隙的部件（10）。 组件（10）被封装在壳模（22）中。 壳模（22）固化。 被封装的部件（10）被放置在炉中并且部件（10）熔化。 组分（10）在壳模（22）中固化。 从凝固组分（10）中除去壳模（22）。
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公开(公告)号：US11168571B2
公开(公告)日：2021-11-09
申请号：US16745930
申请日：2020-01-17
Applicant: United Technologies Corporation
Inventor： David A. Niezelski , Timothy J. Jennings , Bret M. Teller , John McBrien , Thomas N. Slavens
Abstract: Airfoils for gas turbine engines are described. The airfoils include an airfoil body extending between a platform and a tip, the airfoil body having a leading edge, a trailing edge, a pressure side, and a suction side, a serpentine cavity formed within the airfoil body and having an up-pass serpentine cavity, a down-pass serpentine cavity, and a trailing edge cavity, and a dead-end tip flag cavity extending in a direction between the leading edge and the trailing edge, the dead-end tip flag cavity arrange between the serpentine cavity and the tip, wherein the dead-end tip flag cavity ends at a dead-end wall located at a position between the leading edge and the trailing edge of the airfoil body.
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公开(公告)号：US09375782B2
公开(公告)日：2016-06-28
申请号：US14784857
申请日：2014-04-17
Applicant: United Technologies Corporation
Inventor： John McBrien , Lea Kennard Castle , Brandon W. Spangler , JinQuan Xu
IPC: B22C7/02 , B22D23/06 , F01D5/28 , F01D5/18 , B22F3/105 , B22F5/04 , C30B11/00 , C30B29/52 , B22C9/04 , B22C9/02 , B22C9/10 , B22C9/22 , B23K15/00 , B32B1/08 , B32B3/08 , B32B3/26 , B32B5/16 , B32B9/00 , B33Y10/00 , B33Y80/00
CPC classification number: F01D5/28 , B22C7/02 , B22C9/02 , B22C9/043 , B22C9/061 , B22C9/10 , B22C9/101 , B22C9/108 , B22C9/22 , B22C9/24 , B22D23/06 , B22D25/02 , B22D27/04 , B22D27/045 , B22F3/1055 , B22F3/11 , B22F3/24 , B22F5/04 , B22F2003/248 , B22F2998/00 , B22F2998/10 , B23K15/0006 , B23K15/0086 , B23K26/342 , B32B1/08 , B32B3/08 , B32B3/26 , B32B5/16 , B32B9/005 , B32B2250/03 , B32B2264/105 , B32B2603/00 , B33Y10/00 , B33Y80/00 , C30B11/00 , C30B29/52 , F01D5/147 , F01D5/18 , F01D5/187 , F01D5/282 , F01D9/02 , F01D9/041 , F01D9/065 , F01D25/12 , F05D2220/32 , F05D2230/31 , F05D2300/175 , F05D2300/211 , F05D2300/607 , F23R3/28 , Y02P10/292 , Y02P10/295 , B22F2003/242 , C30B11/14
Abstract: One embodiment includes a method to regenerate a component (10). The method includes additively manufacturing a component (10) to have voids greater than 0 percent but less than approximately 15 percent in a near finished shape. The component (10) is encased in a shell mold (22). The shell mold (22) is cured. The encased component (10) is placed in a furnace and the component (10) is melted. The component (10) is solidified in the shell mold (22). The shell mold (22) is removed from the solidified component (10).
Abstract translation: 一个实施例包括重新生成组件（10）的方法。 该方法包括在接近完成的形状中相加地制造具有大于0％但小于约15％的空隙的部件（10）。 组件（10）被封装在壳模（22）中。 壳模（22）固化。 被封装的部件（10）被放置在炉中并且部件（10）熔化。 组分（10）在壳模（22）中固化。 从凝固组分（10）中除去壳模（22）。
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公开(公告)号：US20200256196A1
公开(公告)日：2020-08-13
申请号：US16745930
申请日：2020-01-17
Applicant: United Technologies Corporation
Inventor： David A. Niezelski , Timothy J. Jennings , Bret M. Teller , John McBrien , Thomas N. Slavens
Abstract: Airfoils for gas turbine engines are described. The airfoils include an airfoil body extending between a platform and a tip, the airfoil body having a leading edge, a trailing edge, a pressure side, and a suction side, a serpentine cavity formed within the airfoil body and having an up-pass serpentine cavity, a down-pass serpentine cavity, and a trailing edge cavity, and a dead-end tip flag cavity extending in a direction between the leading edge and the trailing edge, the dead-end tip flag cavity arrange between the serpentine cavity and the tip, wherein the dead-end tip flag cavity ends at a dead-end wall located at a position between the leading edge and the trailing edge of the airfoil body.
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公开(公告)号：US20160201475A1
公开(公告)日：2016-07-14
申请号：US14854606
申请日：2015-09-15
Applicant: United Technologies Corporation
Inventor： Sasha M. Moore , Timothy J. Jennings , Thomas N. Slavens , Clifford J. Musto , Nicholas M. LoRicco , Carey Clum , John McBrien , Christopher Whitfield , San Quach
CPC classification number: F01D5/187 , F01D5/186 , F01D9/041 , F01D9/065 , F01D25/12 , F04D29/321 , F05D2220/32 , F05D2240/12 , F05D2240/127 , F05D2240/30 , F05D2240/81 , F05D2260/202 , F23R2900/03041 , F23R2900/03042 , Y02T50/676
Abstract: A gas turbine engine component includes a body with a wall surrounding an interior cavity. The wall has opposed interior and exterior surfaces. The interior surface has a plurality of coolant inlets and the exterior surface has a coolant outlet defined therein. A coolant conduit extends between the coolant inlets and the coolant outlet and is configured and adapted to induce secondary flow vortices in coolant traversing the coolant conduit and in an adherent coolant film over a portion of the exterior surface of component body.
Abstract translation: 燃气涡轮发动机部件包括具有围绕内部空腔的壁的主体。 墙壁与内部和外部表面相对。 内表面具有多个冷却剂入口，并且外表面具有限定在其中的冷却剂出口。 冷却剂导管在冷却剂入口和冷却剂出口之间延伸，并且被构造和适于在冷却剂中引导二次流动涡流，所述冷却剂穿过冷却剂管道以及在组件主体的外表面的一部分上的粘附冷却剂膜中。
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Patent Agency Ranking
公开(公告)号：US20160177738A1
公开(公告)日：2016-06-23
申请号：US14831997
申请日：2015-08-21
Applicant: United Technologies Corporation
Inventor： Sasha M. Moore , Clifford J. Musto , Timothy J. Jennings , Thomas N. Slavens , San Quach , Nicholas M LoRicco , John McBrien , Carey Clum , Christopher Whitfield
IPC: F01D5/18 , F01D11/08 , F01D25/12 , F02C7/18 , F04D29/54 , F04D29/58 , F02C3/04 , F01D9/04 , F04D29/32
Abstract: A gas turbine engine component includes a wall that provides an exterior surface and an interior flow path surface. The wall has a wall thickness. A protrusion is arranged on the wall that extends a height beyond the wall thickness and provides a portion of the interior flow path surface. A film cooling hole that has an inlet is provided on the protrusion and extends to an exit on the exterior surface.
Abstract translation: 燃气涡轮发动机部件包括提供外表面和内部流路表面的壁。 墙壁有壁厚。 突出部设置在壁上，其高度超过壁厚，并提供内部流路表面的一部分。 具有入口的薄膜冷却孔设置在突起上并延伸到外表面上的出口。
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公开(公告)号：US20140090384A1
公开(公告)日：2014-04-03
申请号：US13629705
申请日：2012-09-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： John McBrien , Brandon W. Spangler , Matthew A. Devore
CPC classification number: F01D5/186 , F05D2250/14 , F05D2250/141 , F05D2250/314 , F23R3/002 , F23R3/06 , F23R2900/00018 , F23R2900/03042 , Y02T50/676
Abstract: A gas turbine engine component includes a structure having an exterior surface. A cooling hole extends from a cooling passage to the exterior surface to provide an exit area on the exterior surface that is substantially circular in shape. A gas turbine engine includes a compressor section and a turbine section. A combustor is provided between the compressor and turbine sections. A component in at least one of the compressor and turbine sections has an exterior surface. A film cooling hole extends from a cooling passage to the exterior surface to provide an exit area that is substantially circular in shape. A method of machining a film cooling hole includes providing a component having an internal cooling passage and an exterior surface, machining a film cooling hole from the exterior surface to the internal cooling passage to provide a substantially circular exit area on the exterior surface.
Abstract translation: 燃气涡轮发动机部件包括具有外表面的结构。 冷却孔从冷却通道延伸到外表面，以在外表面上形成大致圆形形状的出口区域。 燃气涡轮发动机包括压缩机部和涡轮部。 在压缩机和涡轮机部分之间提供燃烧器。 压缩机和涡轮机部分中的至少一个中的部件具有外表面。 薄膜冷却孔从冷却通道延伸到外表面以提供基本上圆形的出口区域。 一种加工薄膜冷却孔的方法包括提供具有内部冷却通道和外部表面的部件，从外表面到内部冷却通道加工薄膜冷却孔，以在外部表面上提供基本上圆形的出口区域。
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公开(公告)号：US10196902B2
公开(公告)日：2019-02-05
申请号：US14854606
申请日：2015-09-15
Applicant: United Technologies Corporation
Inventor： Sasha M. Moore , Timothy J. Jennings , Thomas N. Slavens , Clifford J. Musto , Nicholas M. LoRicco , Carey Clum , John McBrien , Christopher Whitfield , San Quach
Abstract: A gas turbine engine component includes a body with a wall surrounding an interior cavity. The wall has opposed interior and exterior surfaces. The interior surface has a plurality of coolant inlets and the exterior surface has a coolant outlet defined therein. A coolant conduit extends between the coolant inlets and the coolant outlet and is configured and adapted to induce secondary flow vortices in coolant traversing the coolant conduit and in an adherent coolant film over a portion of the exterior surface of component body.
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公开(公告)号：US10006371B2
公开(公告)日：2018-06-26
申请号：US14827050
申请日：2015-08-14
Applicant: United Technologies Corporation
Inventor： John McBrien , Thomas N. Slavens , Clifford J. Musto , Timothy J. Jennings , Nicholas M. LoRicco , Sasha M. Moore
CPC classification number: F02C7/18 , F01D5/186 , F01D9/023 , F01D9/065 , F02C3/04 , F05D2220/32 , F05D2240/81 , F05D2260/202 , F23R3/002 , F23R3/005 , F23R2900/03042 , Y02T50/672 , Y02T50/673 , Y02T50/676
Abstract: A gas turbine engine component is described. The component includes a component wall having an internal surface that is adjacent a flow of coolant and an external surface that is adjacent a flow of gas. The component wall includes a cooling hole that has an inlet defined by the internal surface and an outlet defined by the external surface. The cooling holes also has a metering location having the smallest cross-section area of the cooling hole, an internal diffuser positioned between the inlet and the metering location, an accumulation diverter portion of the internal diffuser and an accumulator portion of the internal diffuser.
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公开(公告)号：US20160319677A1
公开(公告)日：2016-11-03
申请号：US15211913
申请日：2016-07-15
Applicant: United Technologies Corporation
Inventor： John McBrien , Lea Kennard Castle , Brandon W. Spangler
IPC: F01D5/28 , B22C9/02 , B22C9/04 , B22C9/10 , B22C9/24 , B22D23/06 , B22F3/105 , B22F5/04 , B23K26/342 , B33Y10/00 , B33Y80/00 , B22D27/04 , C30B29/52 , F01D5/18 , F01D5/14 , F01D9/04 , F01D25/12 , B22C7/02
CPC classification number: F01D5/28 , B22C7/02 , B22C9/02 , B22C9/043 , B22C9/061 , B22C9/10 , B22C9/101 , B22C9/108 , B22C9/22 , B22C9/24 , B22D23/06 , B22D25/02 , B22D27/04 , B22D27/045 , B22F3/1055 , B22F3/11 , B22F3/24 , B22F5/04 , B22F2003/248 , B22F2998/00 , B22F2998/10 , B23K15/0006 , B23K15/0086 , B23K26/342 , B23P6/00 , B32B1/08 , B32B3/08 , B32B3/26 , B32B5/16 , B32B9/005 , B32B2250/03 , B32B2264/105 , B32B2603/00 , B33Y10/00 , B33Y80/00 , C30B11/00 , C30B29/52 , F01D5/147 , F01D5/18 , F01D5/187 , F01D5/282 , F01D9/02 , F01D9/041 , F01D9/065 , F01D25/12 , F05D2220/32 , F05D2230/31 , F05D2300/175 , F05D2300/211 , F05D2300/607 , F23R3/28 , Y02P10/292 , Y02P10/295 , B22F2003/242 , C30B11/14
Abstract: A metal single crystal turbine component with internal passageways includes a polycrystalline turbine blade formed by additive manufacturing. The turbine component is remelted and directionally solidified to form the single crystal turbine component with internal passageways.
Abstract translation: 具有内部通道的金属单晶涡轮机部件包括通过附加制造形成的多晶涡轮机叶片。 涡轮机部件被重熔并定向凝固以形成具有内部通道的单晶涡轮机部件。
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