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公开(公告)号：US20160208705A1
公开(公告)日：2016-07-21
申请号：US15022990
申请日：2014-10-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas N. Slavens , Brooks E. Snyder
CPC classification number: F02C7/18 , F01D5/186 , F01D5/187 , F01D11/08 , F01D25/30 , F05D2240/305 , F05D2260/202 , F05D2260/204 , F23R3/002 , F23R3/005 , F23R3/04 , F23R3/06 , F23R2900/03042 , F23R2900/03044 , Y02T50/676
Abstract: A cooling circuit for a gas turbine engine comprises a first wall having a first surface facing a first cavity and a second surface facing away from the first cavity. A second wall is spaced outwardly of the second surface of the first wall to provide at least one second cavity. Cooling fluid is configured to flow from the first cavity and exit to an external surface of the second wall via at least one hole to provide cooling to the external surface. A gas turbine engine and a method of forming a cooling circuit for a gas turbine engine are also disclosed.
Abstract translation: 用于燃气涡轮发动机的冷却回路包括具有面向第一腔的第一表面和背离第一腔的第二表面的第一壁。 第二壁与第一壁的第二表面向外间隔开以提供至少一个第二腔。 冷却流体构造成从第一腔流出并经由至少一个孔离开第二壁的外表面，以向外表面提供冷却。 还公开了一种燃气涡轮发动机和形成燃气涡轮发动机的冷却回路的方法。
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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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公开(公告)号：US20160201474A1
公开(公告)日：2016-07-14
申请号：US14854253
申请日：2015-09-15
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Timothy J. Jennings , Roberto J. Perez
IPC: F01D5/18 , F01D11/08 , F01D25/12 , F04D29/08 , F04D29/54 , F02C3/04 , F02C7/18 , F04D29/58 , F01D9/04 , F04D29/32
CPC classification number: F01D5/187 , F01D5/186 , F01D9/041 , F01D11/08 , F01D25/12 , F02C3/04 , F02C7/18 , F04D29/083 , F04D29/324 , F04D29/542 , F04D29/582 , F05D2220/32 , F05D2240/127 , F05D2240/35 , F05D2240/81 , F05D2260/202 , F05D2260/2212 , Y02T50/676
Abstract: A gas turbine engine component includes a wall that provides an exterior surface and an interior flow path surface. A film cooling hole extends through the wall and is configured to fluidly connect the interior flow path surface to the exterior surface. The film cooling hole has a diffuser that is arranged downstream from a metering hole. The diffuser includes inner and outer diffuser surfaces opposite one another and respectively arranged on sides near the interior flow path surface and the exterior surface. A protrusion is arranged in the diffuser on the outer diffuser 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。 薄膜冷却孔延伸穿过壁并构造成将内部流动通道表面流体连接到外部表面。 薄膜冷却孔具有布置在计量孔下游的扩散器。 扩散器包括彼此相对的内部和外部扩散器表面，并且分别布置在靠近内部流动路径表面和外部表面的侧面上。 在外扩散器表面上的扩散器中布置有突起。
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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：US20160024938A1
公开(公告)日：2016-01-28
申请号：US14804865
申请日：2015-07-21
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Brooks E. Snyder , Andrew D. Burdick
IPC: F01D5/18
CPC classification number: F01D5/187 , F05D2220/32 , F05D2240/303 , F05D2250/322 , F05D2260/2212 , Y02T50/676
Abstract: An airfoil for a gas turbine engine, the airfoil includes a wall that has a leading edge and a trailing edge and at least partially defining a boundary of a leading edge cavity radially along the leading edge. A cooling jet structure is operatively associated with a portion of the wall proximate the leading edge and is configured to direct a cooling fluid tangent to the portion of the wall.
Abstract translation: 用于燃气涡轮发动机的翼型件，翼型件包括具有前缘和后缘的壁，并且沿着前缘至少部分地限定前缘腔的边界径向地限定。 冷却射流结构与靠近前缘的壁的一部分可操作地相关联，并且构造成引导与壁的该部分相切的冷却流体。
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Patent Agency Ranking
公开(公告)号：US20150003997A1
公开(公告)日：2015-01-01
申请号：US14320727
申请日：2014-07-01
Applicant: United Technologies Corporation
Inventor： Sergey Mironets , Alexander Staroselsky , Thomas J. Martin , Thomas N. Slavens
IPC: F01D5/14
CPC classification number: B22F5/009 , B22F3/1055 , B22F5/04 , B22F7/06 , B22F2207/01 , F01D5/28 , F01D25/005 , F05D2230/22 , F05D2300/2261 , F05D2300/6033 , Y02P10/295 , Y10T29/49337
Abstract: A monolithic composite turbine component includes at least one first region of a first material and one second region of a second material formed by solid freeform fabrication (SFF). The first material may be a metal and the second material may be a ceramic or a ceramic matrix composite. Transition regions between the metal region and ceramic region are functionally graded regions to minimize internal stress during temperature fluctuations.
Abstract translation: 单片复合涡轮机部件包括通过固体自由形状制造（SFF）形成的第一材料的至少一个第一区域和第二材料的一个第二区域。 第一材料可以是金属，第二材料可以是陶瓷或陶瓷基复合材料。 金属区域和陶瓷区域之间的过渡区域是功能梯度区域，以在温度波动期间最小化内部应力。
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公开(公告)号：US10954800B2
公开(公告)日：2021-03-23
申请号：US16100257
申请日：2018-08-10
Applicant: United Technologies Corporation
Inventor： Sasha M. Moore , Thomas N. Slavens , Nicholas M. Loricco , Timothy J. Jennings
Abstract: One exemplary embodiment of this disclosure relates to a method of forming an engine component. The method includes forming an engine component having an internal passageway, the internal passageway formed with an initial dimension. The method further includes establishing a flow of machining fluid within the internal passageway, the machining fluid changing the initial dimension.
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公开(公告)号：US10683768B2
公开(公告)日：2020-06-16
申请号：US15113298
申请日：2014-11-14
Applicant: United Technologies Corporation
Inventor： Brooks E. Snyder , Thomas N. Slavens
Abstract: A seal for sealing a space defined by first and second components, the seal including at least one first seal and at least one second seal wherein at least a portion of the at least one first seal is disposed in the at least one second seal.
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公开(公告)号：US10549338B2
公开(公告)日：2020-02-04
申请号：US16214651
申请日：2018-12-10
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , James T. Auxier
Abstract: A core for use in casting an internal cooling circuit within a gas turbine engine component, the core including a core body with an outer skin in which a core body additively manufacturing binder is locally eliminated. A method of manufacturing a core for casting a component, including casting a core body for at least partially forming an internal passage architecture of a component; and forming an outer skin on the core body in which a core body binder is locally eliminated.
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公开(公告)号：US20200025085A1
公开(公告)日：2020-01-23
申请号：US16574580
申请日：2019-09-18
Applicant: United Technologies Corporation
Inventor： Kevin L. Zacchera , Thomas N. Slavens
Abstract: A method for applying a coating to a substrate having a plurality of holes. The method comprises: applying a braze material to a substrate having a plurality of holes; heating the substrate to melt the braze material to form a melt; cooling the substrate to solidify the melt to form plugs in the respective holes; applying a coating to the substrate; and further heating the substrate to melt the plugs.
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