公开(公告)号：US20170022822A1

公开(公告)日：2017-01-26

申请号：US15039918

申请日：2014-11-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Steven Taffet ,  Brandon S. Donnell ,  Daniel C. Nadeau ,  Russell Deibel ,  San Quach

IPC: F01D5/18 ,  F01D25/12 ,  B22C9/04 ,  F01D9/04 ,  B22C7/02 ,  B22C9/24

CPC classification number: F01D5/187 ,  B22C7/02 ,  B22C9/04 ,  B22C9/10 ,  B22C9/24 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/323 ,  F05D2230/21 ,  F05D2230/211 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2260/202 ,  Y02T50/676

Abstract: A lost core mold component comprises a first leg and a second leg with a plurality of crossover members connecting the first and second legs. The plurality of crossover members includes outermost crossover members spaced from each other. Adjacent ends of each of the first and second legs, and second crossover members are spaced closer to each other than are the outermost crossover members. Central crossover members extend between the first and second leg and between the second crossover members. The outermost crossover members extend for a first cross-sectional area. The second crossover members extend for a second cross-sectional area and the central crossover members extend for a third cross-sectional area. The first cross-sectional area is greater than the second cross-sectional area. The second cross-sectional area is greater than the third cross-sectional area. A gas turbine engine and component are also disclosed.

Abstract translation: 失去的芯模组件包括第一腿部和第二腿部，其具有连接第一和第二腿部的多个交叉构件。 多个交叉构件包括彼此间隔开的最外侧交叉构件。 第一和第二腿部和第二交叉构件中的每一个的相邻端部比最外面的交叉构件彼此更靠近地间隔开。 中央交叉构件在第一和第二腿之间以及第二交叉构件之间延伸。 最外面的交叉构件延伸到第一横截面积。 第二交叉构件延伸到第二横截面积，并且中心交叉构件延伸第三横截面积。 第一截面积大于第二横截面积。 第二横截面积大于第三横截面积。 还公开了一种燃气涡轮发动机和部件。

公开(公告)号：US20160230566A1

公开(公告)日：2016-08-11

申请号：US14619582

申请日：2015-02-11

Applicant: United Technologies Corporation

Inventor： Christopher King ,  San Quach

IPC: F01D5/18 ,  F01D11/08 ,  B23H9/10 ,  F02C7/18 ,  F23R3/00 ,  F01D9/04 ,  F01D25/12

CPC classification number: F01D5/187 ,  B23H9/10 ,  B23K2101/001 ,  F01D9/041 ,  F01D9/065 ,  F01D11/08 ,  F01D25/12 ,  F02C7/18 ,  F05D2220/30 ,  F05D2230/12 ,  F05D2230/22 ,  F05D2230/30 ,  F05D2240/11 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2240/35 ,  F05D2240/55 ,  F05D2250/121 ,  F05D2250/14 ,  F05D2250/141 ,  F05D2250/38 ,  F05D2260/2214 ,  F05D2260/22141 ,  F23R3/002 ,  Y02T50/676

Abstract: A turbomachine component includes a body defining a cooling inlet and a cooling outlet in fluid communication with each other through a cooling channel that defines a longitudinal axis, and at least one pedestal disposed within the cooling channel. The pedestal is angled within the cooling channel relative to the longitudinal axis. The turbomachine component can be a vane, a blade, a blade outer air seal, or a combustor panel.

Abstract translation: 涡轮机组件包括限定冷却入口的主体和通过限定纵向轴线的冷却通道彼此流体连通的冷却出口，以及设置在冷却通道内的至少一个基座。 基座相对于纵向轴线在冷却通道内成角度。 涡轮机组件可以是叶片，叶片，叶片外部空气密封件或燃烧器面板。

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

IPC: F01D5/18 ,  F01D9/04 ,  F04D29/32 ,  F01D25/12

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。

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。

公开(公告)号：US20160177734A1

公开(公告)日：2016-06-23

申请号：US14862422

申请日：2015-09-23

Applicant: United Technologies Corporation

Inventor： San Quach ,  Christopher King ,  Steven Bruce Gautschi ,  David J. Candelori

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F01D5/141 ,  F05D2240/303 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2250/324 ,  F05D2260/202 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

Abstract: The systems and methods described herein adapt the orientation, position and/or diffusion angles of showerhead cooling holes depending on the external gas/streamline flow direction. In regions, for example, where the stagnation line is on the pressure side, the breakouts of the showerhead holes substantially face aft (e.g., primarily towards the suction side). The location and positioning of the holes may be oriented according to the direction of incoming gas flows.

Abstract translation: 本文所述的系统和方法根据外部气体/流线流动方向适应喷头冷却孔的取向，位置和/或扩散角。 例如，在停滞线处于压力侧的区域中，喷头孔的突破基本上向后（例如主要朝向吸力侧）。 孔的位置和定位可以根据进入的气流的方向定向。

公开(公告)号：US20160169004A1

公开(公告)日：2016-06-16

申请号：US14949047

申请日：2015-11-23

Applicant: United Technologies Corporation

Inventor： San Quach ,  Christopher King ,  Tracy A. Propheter-Hinckley

IPC: F01D5/18 ,  F01D11/08 ,  F04D29/32 ,  F02C7/18 ,  F23R3/00 ,  F01D9/04 ,  F01D25/12

CPC classification number: F01D5/186 ,  F01D9/041 ,  F01D11/08 ,  F01D25/12 ,  F02C7/18 ,  F04D29/324 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2240/35 ,  F05D2250/13 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2250/184 ,  F05D2250/185 ,  F05D2260/202 ,  F05D2260/204 ,  F23R3/002 ,  F23R2900/03042 ,  Y02T50/676

Abstract: A gas turbine engine component includes a wall having an inner surface and an outer surface. At least one non-rectangular slot extends through the outer wall surface and is in communication with a passage. The passages extend through the wall and include an inlet portion located at the inner surface and an outlet portion located at the outer surface. An intermediate portion fluidly connects the inlet portion and the outlet portion.

Abstract translation: 燃气涡轮发动机部件包括具有内表面和外表面的壁。 至少一个非矩形槽延伸穿过外壁表面并且与通道连通。 通道延伸穿过壁并且包括位于内表面处的入口部分和位于外表面处的出口部分。 中间部分流体地连接入口部分和出口部分。

公开(公告)号：US20150300258A1

公开(公告)日：2015-10-22

申请号：US14689168

申请日：2015-04-17

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Dominic J. Mongillo ,  San Quach ,  Steven Bruce Gautschi ,  Brandon S. Donnell ,  Anita L. Tracy ,  Yafet Girma

IPC: F02C7/18 ,  F01D25/12 ,  F02C3/04

CPC classification number: F01D5/186 ,  F05D2250/18 ,  F05D2250/31 ,  F05D2250/32 ,  F05D2260/202 ,  Y02T50/676

Abstract: A component for a gas turbine engine according to an exemplary aspect of this disclosure includes a surface having a plurality of cooling holes. The surface includes a first region and a second region each having a plurality of cooling holes. The cooling holes within the first region are arranged differently than the cooling holes in the second region.

Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的部件包括具有多个冷却孔的表面。 表面包括第一区域和第二区域，每个具有多个冷却孔。 第一区域内的冷却孔的布置与第二区域中的冷却孔不同。

公开(公告)号：US11143038B2

公开(公告)日：2021-10-12

申请号：US14767768

申请日：2014-02-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： San Quach ,  Matthew A. Devore

IPC: F01D5/18 ,  F02C3/04 ,  F02C7/18

Abstract: An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges. A stagnation line is located on the pressure side wall aft of the leading edge. A cooling passage is provided between the pressure and suction side walls. Forward-facing cooling holes are provided adjacent to the stagnation line on the pressure side wall and oriented toward the leading edge.

公开(公告)号：US11098595B2

公开(公告)日：2021-08-24

申请号：US15584846

申请日：2017-05-02

Applicant: United Technologies Corporation

Inventor： San Quach ,  Tracy A. Propheter-Hinckley

IPC: F01D5/18 ,  B22C9/10 ,  B22F10/10 ,  B33Y80/00 ,  F01D25/12 ,  B33Y10/00

Abstract: An airfoil includes a leading edge and a trailing edge. A first exterior wall extends between the leading edge and the trailing edge. A second exterior wall opposite the first exterior wall extends between the leading edge and the trailing edge. A first cavity is adjacent the first exterior wall and includes a central portion and at least one forward extending slot passage and at least one aft extending slot passage.

公开(公告)号：US11002153B2

公开(公告)日：2021-05-11

申请号：US16031057

申请日：2018-07-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Alberto A. Mateo ,  Tracy A. Propheter-Hinckley ,  San Quach

IPC: F01D9/06 ,  F01D25/26 ,  F04D29/54 ,  F16M13/02

Abstract: A balance bracket for a diffuser case of gas turbine engine is disclosed. In various embodiments, the balance bracket includes a first portion configured for mounting to a first boss on the diffuser case, a second portion configured for mounting to a second boss on the diffuser case, the second portion spaced a distance from the first portion, and a first undulating portion positioned intermediate the first portion and the second portion.