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公开(公告)号：US20160177767A1
公开(公告)日：2016-06-23
申请号：US14907461
申请日：2014-07-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas N. Slavens , Sasha M. Moore , Nicholas M. LoRicco
CPC classification number: F01D11/008 , F01D11/006 , F04D29/083 , F04D29/542 , F05D2220/32 , F05D2240/55 , F05D2250/75 , F16J15/06 , F16J15/062 , F16J15/0887
Abstract: This disclosure relates to a gas turbine engine including a first engine component and a second engine component. The first engine component has a mate face adjacent a mate face of the second engine component. The engine further includes a seal provided between the mate face of the first engine component and the mate face of the second engine component. The seal includes least one trough.
Abstract translation: 本公开涉及一种包括第一发动机部件和第二发动机部件的燃气涡轮发动机。 第一发动机部件具有与第二发动机部件的配合面相邻的配合面。 发动机还包括设置在第一发动机部件的配合面与第二发动机部件的配合面之间的密封件。 密封件包括至少一个槽。
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公开(公告)号：US20160177740A1
公开(公告)日：2016-06-23
申请号：US14923511
申请日：2015-10-27
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Brooks E. Snyder
CPC classification number: F01D5/187 , F01D5/143 , F05D2200/263 , F05D2230/21 , F05D2240/81 , F05D2250/322 , F05D2250/71 , F05D2260/202 , F23R3/002 , Y02T50/673 , Y02T50/676
Abstract: A cooling circuit for a gas turbine engine comprises a gas turbine engine component having a first portion connected to a second portion via a curved surface. An inlet is formed in or near one of the first and second portions to receive a cooling air flow. An outlet is formed in or near the other of the first and second portions to direct cooling flow along a surface of the gas turbine engine component. At least one cooling path extends between the inlet and the outlet and has at least one cooling path portion that conforms in shape to the curved 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燃气涡轮发动机部件，其具有通过弯曲表面连接到第二部分的第一部分。 入口形成在第一和第二部分中的一个中或其附近，以接收冷却空气流。 出口形成在第一和第二部分中的另一个中或其附近，以沿着燃气涡轮发动机部件的表面引导冷却流。 至少一个冷却通道在入口和出口之间延伸，并且具有至少一个冷却通道部分，其形状与弯曲表面一致。 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：US20160010465A1
公开(公告)日：2016-01-14
申请号：US14633677
申请日：2015-02-27
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Dominic J. Mongillo, JR. , Matthew A. Devore
CPC classification number: F01D5/187 , F01D5/08 , F01D5/186 , F01D5/188 , F01D9/041 , F01D17/16 , F05D2220/32 , F05D2220/3212 , F05D2240/12 , F05D2240/303 , F05D2260/202 , Y02T50/673 , Y02T50/676
Abstract: An example gas turbine engine component includes an airfoil having a leading edge area, a first circuit to cool a first section of the leading edge area, and a second circuit to cool a second section of the leading edge area. The first circuit separate and distinct from the second circuit within the airfoil.
Abstract translation: 示例性燃气涡轮发动机部件包括具有前缘区域的翼型件，用于冷却前缘区域的第一部分的第一电路和用于冷却前缘区域的第二部分的第二电路。 第一回路与翼型内的第二回路分开且不同。
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24.发明申请公开(公告)号：US20150375297A1
公开(公告)日：2015-12-31
申请号：US14766061
申请日：2014-01-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas N. Slavens , Lane Thornton , Sasha M. Moore , Nicholas M. LoRicco
CPC classification number: B22D19/0072 , B22C9/04 , B22C9/103 , F01D5/187 , F01D9/023 , F05D2230/211 , F05D2250/185 , F23R3/002 , Y02T50/676
Abstract: A method of manufacturing a component that includes providing a core structure, casting a component about the core structure, removing a first portion of the core structure from the cast component, and leaving a second portion of the core structure in the cast component to provide a reduced cross-section in the cast component.
Abstract translation: 一种制造组件的方法，所述方法包括提供芯结构，围绕所述芯结构铸造部件，从所述铸造部件移除所述芯结构的第一部分，以及将所述芯结构的第二部分留在所述铸造部件中，以提供 减少铸件中的横截面积。
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公开(公告)号：US20150322801A1
公开(公告)日：2015-11-12
申请号：US14687974
申请日：2015-04-16
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Matthew A. Devore
CPC classification number: F01D5/18 , F01D5/186 , F01D5/187 , F01D9/02 , F01D25/12 , F01D25/24 , F05D2220/32 , F05D2260/202 , Y02T50/676
Abstract: An airfoil according to an exemplary aspect of the present disclosure includes, among other things, a first cooling hole with a first cooling passage arranged at a first angle relative to a chordwise axis and a second cooling hole with a second cooling passage arranged at a second different angle relative to the chordwise axis. A radial projection of the first cooling passage intersects a radial projection of the second cooling passage.
Abstract translation: 根据本公开的示例性方面的翼型件包括第一冷却孔，第一冷却孔具有相对于弦向轴线以第一角度布置的第一冷却通道和第二冷却孔，第二冷却通道布置在第二冷却通道的第二冷却通道 不同的角度相对于和弦轴。 第一冷却通道的径向突起与第二冷却通道的径向突出部相交。
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Patent Agency Ranking
公开(公告)号：US20140212298A1
公开(公告)日：2014-07-31
申请号：US13729110
申请日：2012-12-28
Applicant: United Technologies Corporation
Inventor： James T. Auxier , Jason L. O'Hearn , Thomas N. Slavens , Yafet Girma
IPC: F01D5/18
CPC classification number: F01D5/186 , F01D5/20 , F01D11/08 , F05D2240/307 , Y02T50/676
Abstract: An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil having an exterior surface that extends in a radial direction to a tip. A camber line at the tip extends from the leading edge to the trailing edge. Pressure and suction side shelves are arranged in the exterior surface on opposing sides of the camber line respectively in the pressure and suction side walls. A plateau is proud of and separates the pressure and suction side shelves. The plateau is arranged along the camber line and extends to the leading edge.
Abstract translation: 用于燃气涡轮发动机的翼型件包括彼此间隔开并在前缘和后缘连接的压力和吸力壁，以提供具有沿径向方向延伸到尖端的外表面的翼型件。 尖端处的弧形线从前缘延伸到后缘。 压力和吸力侧搁板分别设置在压力侧和吸力侧壁的外倾线的相对侧的外表面上。 高原是为压力和吸力侧货架感到自豪和分离。 平台沿着弧形线布置并延伸到前缘。
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公开(公告)号：US10465530B2
公开(公告)日：2019-11-05
申请号：US15102335
申请日：2014-11-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Nicholas M. LoRicco , James T. 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：US10436113B2
公开(公告)日：2019-10-08
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
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.
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公开(公告)号：US10434545B2
公开(公告)日：2019-10-08
申请号：US15109020
申请日：2015-01-15
Applicant: United Technologies Corporation
Inventor： Thomas J. Martin , Alexander Staroselsky , Sergey Mironets , Thomas N. Slavens , Brooks E. Snyder
IPC: B07B7/08 , B07B7/083 , B07B13/04 , B22F3/105 , B33Y40/00 , B23K26/342 , B23K15/00 , B07B4/02 , B29C64/153 , B29C64/20 , B29C64/35 , B33Y10/00 , B33Y30/00 , B29K105/00
Abstract: A aerodynamic particle separator for an Additive Manufacturing System (AMS) has an air supply device to entrain a mixed powder in an airstream flowing through a housing. Each particle in the mixed powder is imparted with a momentum dependent upon the particle weight and size. Utilizing this momentum characteristic, the heavier particles are capable of crossing streamlines of the airstream at a bend portion of the housing and the lighter particles generally stay within the streamlines. Utilizing this dynamic characteristic, the particles of specific weight ranges are collected through respective offtake holes in the housing and controllably fed to a spreader of the AMS.
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公开(公告)号：US20190176228A1
公开(公告)日：2019-06-13
申请号：US16275468
申请日：2019-02-14
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Lane Thornton , Sasha M. Moore , Nicholas M. LoRicco
Abstract: A gas turbine engine includes a structure that has walls that provide a cooling passage and a cooling surface. A non-ferrous obstruction is relative to the walls. The obstruction includes a portion spaced from the cooling surface to provide a gap which is configured to receive a cooling fluid.
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