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公开(公告)号：US20160177736A1
公开(公告)日：2016-06-23
申请号：US14804424
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 , F05D2240/306 , F05D2250/314 , F05D2260/201 , Y02T50/676
Abstract: An airfoil structure for a gas turbine engine includes an airfoil that includes a suction side cooling circuit with at least two segments that are connected by at least one impingement passage.
Abstract translation: 用于燃气涡轮发动机的翼型结构包括一个翼型件，其包括具有至少两个段的吸入侧冷却回路，所述至少两个段由至少一个冲击通道连接。
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公开(公告)号：US20160084164A1
公开(公告)日：2016-03-24
申请号：US14816125
申请日：2015-08-03
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas N. Slavens , Dominic J. Mongillo , Steven Bruce Gautschi , Jaime G. Ghigliotty
CPC classification number: F02C7/18 , F01D5/081 , F01D5/145 , F01D5/18 , F01D5/181 , F01D5/182 , F01D5/183 , F01D5/184 , F01D5/185 , F01D5/186 , F01D5/187 , F01D5/188 , F01D5/189 , F01D5/30 , F01D9/06 , F01D9/065 , F02C3/04 , F02C9/16 , F05D2220/32 , F05D2250/51 , F05D2250/71 , F05D2250/72 , F05D2250/73 , F05D2260/232 , Y02T50/676
Abstract: A cooling device for a gas turbine engine component comprises a gas turbine engine component having an upstream channel and a downstream channel that define a cooling flow path. A meter feature includes at least one hole to meter flow from the upstream channel to the downstream channel, and has an upstream side and a downstream side. An exit diffuser extends outwardly from the downstream side of the meter feature to control flow in a desired direction into the downstream channel. A gas turbine engine is also disclosed.
Abstract translation: 用于燃气涡轮发动机部件的冷却装置包括具有限定冷却流路的上游通道和下游通道的燃气涡轮发动机部件。 仪表特征包括至少一个孔，用于测量从上游通道到下游通道的流量，并具有上游侧和下游侧。 出口扩散器从仪表特征的下游侧向外延伸以控制在所需方向上的流向下游通道。 还公开了一种燃气涡轮发动机。
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公开(公告)号：US09116051B2
公开(公告)日：2015-08-25
申请号：US14134603
申请日：2013-12-19
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Charles W. Haldeman
CPC classification number: G01K1/12 , G01D11/245 , G01K13/02 , G01K2013/024
Abstract: An actively cooled turbine sensor assembly is designed to withstand post-combustion gas-path conditions of gas turbine engines. The housing forms part of a cooling system and includes an elongated tubular structure that may be inserted into the hot flow path. The distal end portion of the sensor assembly is contoured to minimize heat transfer. The housing also includes leading and trailing plenums for flowing cooling air through the housing and out through the distal end portion. Additional side cavities may also be provided for active cooling of the sensor and reducing possible heat conduction paths to the sensor.
Abstract translation: 主动冷却的涡轮传感器组件被设计成能够承受燃气涡轮发动机的燃烧后气体路径状况。 壳体形成冷却系统的一部分并且包括可以插入到热流路中的细长管状结构。 传感器组件的远端部分的轮廓是使热传递最小化。 壳体还包括用于使冷却空气流过壳体并通过远端部分流出的前部和后部气室。 还可以提供附加的侧腔，用于主动冷却传感器并减少可能的传导通路。
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公开(公告)号：US20140254631A1
公开(公告)日：2014-09-11
申请号：US14134603
申请日：2013-12-19
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Charles W. Haldeman
CPC classification number: G01K1/12 , G01D11/245 , G01K13/02 , G01K2013/024
Abstract: An actively cooled turbine sensor assembly is designed to withstand post-combustion gas-path conditions of gas turbine engines. The housing forms part of a cooling system and includes an elongated tubular structure that may be inserted into the hot flow path. The distal end portion of the sensor assembly is contoured to minimize heat transfer. The housing also includes leading and trailing plenums for flowing cooling air through the housing and out through the distal end portion. Additional side cavities may also be provided for active cooling of the sensor and reducing possible heat conduction paths to the sensor.
Abstract translation: 主动冷却的涡轮传感器组件被设计成能够承受燃气涡轮发动机的燃烧后气体路径状况。 壳体形成冷却系统的一部分并且包括可以插入到热流路中的细长管状结构。 传感器组件的远端部分的轮廓是使热传递最小化。 壳体还包括用于使冷却空气流过壳体并通过远端部分流出的前部和后部气室。 还可以提供附加的侧腔，用于主动冷却传感器并减少可能的传导通路。
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公开(公告)号：US11022039B2
公开(公告)日：2021-06-01
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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Patent Agency Ranking
公开(公告)号：US10982552B2
公开(公告)日：2021-04-20
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 , F01D9/04 , F01D11/08 , F01D25/12 , F02C3/04 , F02C7/18 , F04D29/32 , F04D29/54 , F04D29/58
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.
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公开(公告)号：US10662781B2
公开(公告)日：2020-05-26
申请号：US16048466
申请日：2018-07-30
Applicant: United Technologies Corporation
Inventor： Dominic J. Mongillo , Tracy A. Propheter-Hinckley , Mark F. Zelesky , Joel H. Wagner , Thomas N. Slavens
IPC: F01D5/18 , F01D11/08 , F01D25/24 , F02C7/18 , F01D25/12 , B22F3/105 , B23P15/26 , F01D5/14 , F01D9/02 , F01D25/08 , B33Y10/00 , B33Y70/00 , B33Y80/00
Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure defines a hollow vascular structure configured to communicate a fluid through the vascular engineered lattice structure. The vascular engineered lattice structure has at least one inlet hole and at least one outlet hole that communicates the fluid into and out of the hollow vascular structure. A method for producing a component is also disclosed.
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公开(公告)号：US10563583B2
公开(公告)日：2020-02-18
申请号：US15022990
申请日：2014-10-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas N. Slavens , Brooks E. Snyder
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.
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公开(公告)号：US20200011187A1
公开(公告)日：2020-01-09
申请号：US16571724
申请日：2019-09-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Nicholas M. LoRicco , James Tilsley Auxier , Brooks E. Snyder , Thomas N. Slavens
Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a body, a wall extending inside of the body and a plurality of vortex promoting features arranged in a helical pattern along the wall.
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公开(公告)号：US10385728B2
公开(公告)日：2019-08-20
申请号：US15034951
申请日：2014-11-03
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Eric A. Grover , John D. Teixeira
IPC: F01D25/12 , F01D17/16 , F01D5/14 , F01D9/04 , F01D9/06 , F01D5/02 , F01D5/12 , F01D17/14 , F02C3/04
Abstract: A turbine stator vane assembly for a gas turbine engine is disclosed and includes an airfoil rotatable about an axis transverse to an engine longitudinal axis. The airfoil includes outer walls defining an inner chamber between a pressure side and a suction side of the airfoil. At least one spindle supports rotation of the airfoil and includes a feed opening for communicating cooling air into the inner chamber. An inlet defines a passage between the feed opening and the inner chamber and includes a protrusion of the outer wall on at least one of the pressure side and suction side of the airfoil.
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