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公开(公告)号：US20140165593A1
公开(公告)日：2014-06-19
申请号：US13713371
申请日：2012-12-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： San Quach , Lane Thornton
IPC: F01D5/12
CPC classification number: F01D5/186 , F01D5/20 , F05D2240/303 , F05D2240/307 , Y02T50/673 , 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 tip trench is provided in the tip and wrapping at least a portion of the airfoil from the pressure side wall around the leading edge to the suction side wall. The tip trench is provided by a recess.
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。 尖端沟槽设置在尖端中，并且将翼型件的至少一部分从前缘的压力侧壁包裹到吸力侧壁。 尖端沟槽由凹槽提供。
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公开(公告)号：US20140075947A1
公开(公告)日：2014-03-20
申请号：US13621968
申请日：2012-09-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Steven Bruce Gautschi , Lane Thornton
CPC classification number: F01D5/189 , F05D2240/126 , Y02T50/676
Abstract: A component for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, a body portion and a cooling circuit disposed inside of the body portion. The cooling circuit includes a first baffle received within a first core cavity that extends inside of the body portion, a second baffle received within a second core cavity that extends inside of the body portion, and a first rib disposed between the first core cavity and the second core cavity. The first baffle is in fluid communication with the second baffle through the first rib.
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设置在主体部分内部的主体部分和冷却回路。 冷却回路包括容纳在主体部分内部延伸的第一芯腔内的第一挡板，容纳在主体部分内延伸的第二芯腔内的第二挡板，以及设置在第一芯腔和第二芯腔之间的第一肋 第二核心腔。 第一挡板通过第一肋与第二挡板流体连通。
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公开(公告)号：US10738619B2
公开(公告)日：2020-08-11
申请号：US15107493
申请日：2015-01-02
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Lane Thornton , Matthew A. Devore , Dominic J. Mongillo , Steven Bruce Gautschi
IPC: F01D5/18
Abstract: A gas turbine engine component comprises an airfoil with a suction side and pressure side extending from a leading edge to a trailing edge. There are a plurality of cooling holes adjacent the leading edge, with the cooling holes having a non-circular shape, with a longer dimension and a smaller dimension. The airfoil defines a radial direction from a radially outer end to a radially inner end, and radially outer of the cooling holes spaced toward the radially outer end, which have the longer dimension extending closer to parallel to the radial direction. Radially inner cooling holes closer to the radially inner end having the longer dimension extend to be closer to perpendicular relative to the radial direction compared to the radially outer cooling holes.
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公开(公告)号：US10400607B2
公开(公告)日：2019-09-03
申请号：US14627587
申请日：2015-02-20
Applicant: United Technologies Corporation
Inventor： Lane Thornton , Scott D. Lewis , Matthew A. Devore
Abstract: A cooling hole for a component includes a meter section and a diffuser section. The diffuser section has a footprint region defined by five sides, a first side of the five sides extending along substantially an entire height of the diffuser section and second and third sides of the five sides meeting in an obtuse angle opposite the first side. A component having the cooling hole and a method of forming the cooling hole are also disclosed.
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公开(公告)号：US20170145833A1
公开(公告)日：2017-05-25
申请号：US14948511
申请日：2015-11-23
Applicant: United Technologies Corporation
Inventor： Lane Thornton
CPC classification number: F01D5/187 , F01D5/189 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2230/80 , F05D2240/12 , F05D2240/122 , F05D2240/126 , F05D2240/301 , F05D2240/304 , F05D2260/202 , Y02T50/671 , Y02T50/673 , Y02T50/676
Abstract: An airfoil according to an example of the present disclosure includes, among other things, an airfoil body defining a cavity, and a baffle including a baffle body including sidewalls and defining an internal passage for conveying coolant. The baffle body is situated in the cavity such that a majority of external surfaces of the sidewalls abut the cavity.
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Patent Agency Ranking
公开(公告)号：US20160326898A1
公开(公告)日：2016-11-10
申请号：US14704278
申请日：2015-05-05
Applicant: United Technologies Corporation
Inventor： Dominic J. Mongillo, JR. , Brandon W. Spangler , Lane Thornton
IPC: F01D11/00
CPC classification number: F01D11/006 , F01D11/005 , F01D25/246 , F05D2240/11 , F05D2240/57 , F05D2250/182 , Y02T50/672
Abstract: A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a body including a cold side surface adjacent to a mate face. A plurality of ridges extends from the cold side surface. A seal member abuts the plurality of ridges to define a plurality of cooling passages. The seal member is configured to move between a first position and a second position relative to the plurality of ridges. Each of the plurality of cooling passages includes a first inlet defined at the first position and a second, different inlet defined at the second position. A method of sealing between adjacent components of a gas turbine engine is also disclosed.
Abstract translation: 根据本公开的示例的用于燃气涡轮发动机的部件包括包括邻近配合面的冷侧表面的主体。 多个脊从冷侧表面延伸。 密封构件邻接多个脊以限定多个冷却通道。 密封构件被构造成相对于多个脊在第一位置和第二位置之间移动。 多个冷却通道中的每一个包括限定在第一位置处的第一入口和限定在第二位置处的第二不同入口。 还公开了一种在燃气涡轮发动机的相邻部件之间的密封方法。
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公开(公告)号：US20160186576A1
公开(公告)日：2016-06-30
申请号：US14627587
申请日：2015-02-20
Applicant: United Technologies Corporation
Inventor： Lane Thornton , Scott D. Lewis , Matthew A. Devore
CPC classification number: F01D5/186 , F01D9/041 , F01D25/12 , F05D2220/30 , F05D2230/12 , F05D2230/13 , F05D2260/202 , Y02T50/673 , Y02T50/676
Abstract: A cooling hole for a component includes a meter section and a diffuser section. The diffuser section has a footprint region defined by five sides, a first side of the five sides extending along substantially an entire height of the diffuser section and second and third sides of the five sides meeting in an obtuse angle opposite the first side. A component having the cooling hole and a method of forming the cooling hole are also disclosed.
Abstract translation: 用于组件的冷却孔包括仪表部分和扩散器部分。 扩散器部分具有由五个侧面限定的覆盖区域，五个侧面的第一侧沿着扩散器部分的大致整个高度延伸，五边的第二和第三侧以与第一侧相对的钝角相交。 还公开了具有冷却孔的部件和形成冷却孔的方法。
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公开(公告)号：US20160169001A1
公开(公告)日：2016-06-16
申请号：US14908573
申请日：2014-08-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Lane Thornton , Matthew Andrew Hough
IPC: F01D5/18
CPC classification number: F01D5/186 , F01D5/187 , F05D2220/32 , F05D2240/11 , F05D2240/81 , F05D2250/292 , F05D2250/324 , Y02T50/676
Abstract: A gas turbine engine component has first and second components each having a platform with an upper surface and a lower surface and with a plurality of side faces extending between the upper and lower surfaces. The platforms are arranged adjacent to one another such that one side face of the platform faces a mating side face of an adjacent platform. At least one cooling hole is formed within the platform and has an inlet to receive a cooling flow and an outlet at least at one of the side faces. The at least one cooling hole increases in size in a direction toward the outlet. A method of cooling a gas turbine engine is also disclosed.
Abstract translation: 燃气涡轮发动机部件具有第一和第二部件，每个部件具有一个具有上表面和下表面的平台，并且多个侧面在上表面和下表面之间延伸。 平台彼此相邻设置，使得平台的一个侧面面向相邻平台的配合侧面。 在平台内形成至少一个冷却孔，并且至少在一个侧面具有用于接收冷却流的入口和出口。 至少一个冷却孔在朝向出口的方向上尺寸增大。 还公开了一种冷却燃气涡轮发动机的方法。
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19.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：US10655473B2
公开(公告)日：2020-05-19
申请号：US13713371
申请日：2012-12-13
Applicant: United Technologies Corporation
Inventor： San Quach , Lane Thornton
IPC: F01D5/18
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 tip trench is provided in the tip and wrapping at least a portion of the airfoil from the pressure side wall around the leading edge to the suction side wall. The tip trench is provided by a recess.
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