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公开(公告)号：US10196917B2
公开(公告)日：2019-02-05
申请号：US14789232
申请日：2015-07-01
Applicant: United Technologies Corporation
Inventor： Paul M. Lutjen , Shawn J. Gregg , Thurman Carlo Dabbs , Ken F. Blaney , Russell E. Keene , Bruce E. Chick
Abstract: A blade outer air seal for a gas turbine engine includes a wall, a forward hook, and an aft hook. The wall extends between the forward hook and the aft hook, which are adapted to mount the blade outer air seal to a casing of the gas turbine engine. The wall includes a cored passage extending along at least a portion of the wall. The cored passage extends radially and axially through a portion of the aft hook to communicate with one or more apertures along a trailing edge of the aft hook.
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公开(公告)号：US09334755B2
公开(公告)日：2016-05-10
申请号：US13630107
申请日：2012-09-28
Applicant: United Technologies Corporation
Inventor： Sarah Riley , Mark A. Boeke , Jeffrey J. DeGray , Shawn J. Gregg
CPC classification number: F01D25/12 , F01D5/187 , F01D9/02 , F05D2240/12 , F05D2240/126 , F05D2240/127 , F05D2240/81 , F05D2250/183 , F05D2260/2212 , F05D2260/22141 , Y02T50/672 , Y02T50/676
Abstract: An airfoil component for a gas turbine engine includes an airfoil extending from a platform. At least one of the airfoil and the platform includes a cooling passage defined by a surface. A chevron-shaped trip strip extends from the surface into the cooling passage at a trip strip height along a length. The trip strip height varies along the length. A turbine vane for a gas turbine engine includes inner and outer platforms. A cooling passage is provided in the inner platform. The cooling passage is provided by first and second radially extending legs spaced circumferentially apart from one another and joined to one another by a circumferential passage. A pair of airfoils extend radially from the same inner platform. A trip strip extends from the surface into the circumferential passage at a trip strip height along a length. The trip strip height varying along the length.
Abstract translation: 用于燃气涡轮发动机的翼型件包括从平台延伸的翼型件。 翼型件和平台中的至少一个包括由表面限定的冷却通道。 一个V形形状的跳闸条从一个长度的跳闸带高度从表面延伸到冷却通道中。 跳闸条高度沿长度变化。 用于燃气涡轮发动机的涡轮叶片包括内平台和外平台。 在内平台上设有冷却通道。 冷却通道由第一和第二径向延伸的腿部彼此周向间隔开并且通过周向通道彼此连接而设置。 一对翼型件从相同的内平台径向延伸。 跳闸条沿着一段长度以一个跳闸带高度从表面延伸到圆周通道中。 行程长度沿长度变化。
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公开(公告)号：US20160251969A1
公开(公告)日：2016-09-01
申请号：US14634006
申请日：2015-02-27
Applicant: United Technologies Corporation
Inventor： Mark A. Boeke , Richard M. Salzillo , Jeffrey J. DeGray , Shawn J. Gregg
CPC classification number: F01D5/189 , F01D5/141 , F01D5/147 , F01D9/041 , F01D9/065 , F01D25/12 , F05D2220/32 , F05D2230/20 , F05D2230/60 , F05D2240/126 , F05D2240/301 , F05D2240/81 , F05D2260/221 , Y02T50/676
Abstract: An airfoil includes an airfoil wall including an exterior airfoil surface and at least partially defines an airfoil cavity. A fillet is on the exterior airfoil surface. A recess is in an interior surface of the airfoil wall adjacent the fillet. A baffle tube is located in the airfoil cavity spaced from the recess.
Abstract translation: 翼型件包括包括外部翼型件表面的翼型件壁，并且至少部分地限定翼型腔。 一个圆角在外部翼面上。 凹槽位于靠近圆角的翼型壁的内表面。 挡板管位于与凹槽间隔开的翼型腔中。
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公开(公告)号：US20140219778A1
公开(公告)日：2014-08-07
申请号：US13630419
申请日：2012-09-28
Applicant: United Technologies Corporation
Inventor： Mark A. Boeke , Shawn J. Gregg , Sarah Riley , Jeffrey J. DeGray , Richard M. Salzillo
CPC classification number: F01D5/186 , F01D5/187 , F01D9/02 , F01D25/12 , F01D25/246 , F05D2240/12 , F05D2240/81 , F05D2260/204 , Y02T50/672 , Y02T50/676
Abstract: A stator vane for a gas turbine engine includes an airfoil extending in a radial direction and supported by a platform having a gas flowpath surface. A cooling passage is arranged in the platform and includes a circumferential passage that is fluidly connected to an inlet passage extending through and edge of the platform, and film cooling holes extending from the gas flowpath surface to the circumferential passage, radial extending passage through the edge of the platform. A void is interconnected to at least one of the radially extending passage and the inlet passage.
Abstract translation: 用于燃气涡轮发动机的定子叶片包括沿径向延伸并由具有气体流路表面的平台支撑的翼型件。 冷却通道布置在平台中，并且包括流体连接到延伸通过平台的边缘的入口通道的圆周通道，以及从气体流路表面延伸到周向通道的膜冷却孔，通过边缘的径向延伸通道 的平台。 空隙与径向延伸通道和入口通道中的至少一个相互连接。
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公开(公告)号：US20160214211A1
公开(公告)日：2016-07-28
申请号：US15026474
申请日：2014-09-25
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Shawn J. Gregg , Alexander Staroselsky , Gajawalli V. Srinivasan
IPC: B23K26/342 , F01D5/18 , B23K26/00 , B23K26/12 , B23K26/144
CPC classification number: B23K26/342 , B22F3/1055 , B22F3/11 , B22F5/04 , B22F2207/13 , B22F2207/17 , B23K26/0006 , B23K26/12 , B23K26/144 , B23K2103/02 , B23K2103/08 , B23K2103/14 , B33Y10/00 , B33Y80/00 , F01D5/18 , F01D5/28 , Y02P10/295
Abstract: A method of forming a metal component having different regions containing different grain sizes and in porosities is by additive manufacturing. The method includes spreading a layer of starting powder on a temperature controlled moveable platform in a heated chamber with atmosphere and temperature control. Selected areas of the powder are melted and solidified with a computer controlled focused energy beam. The cooled platform is then indexed down and the process repeated. The grain size of the melted and solidified region can be controlled by the cooling rate during solidification which, in turn is controlled by the temperature of the chamber and the temperature of the cooled moveable platform.
Abstract translation: 通过添加制造，形成具有不同晶粒尺寸和孔隙度不同区域的金属成分的方法。 该方法包括在加热室中的温度控制的可移动平台上涂覆起始粉末层，其中气氛和温度控制。 粉末的选定区域用计算机控制的聚焦能量束熔化和固化。 然后冷却的平台被索引并重复该过程。 熔化和固化区域的晶粒尺寸可以通过凝固过程中的冷却速度进行控制，而冷却速度又由室内的温度和冷却的可移动平台的温度控制。
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Patent Agency Ranking
公开(公告)号：US20160003152A1
公开(公告)日：2016-01-07
申请号：US14769224
申请日：2014-03-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Sarah Riley , Mark A. Boeke , Shawn J. Gregg
Abstract: A stator for a gas turbine engine has a platform supporting multiple vanes that includes first and second vanes respectively. First and second regions are arranged at the same location on the first and second vanes. The first and second regions respectively include first and second cooling hole configurations that are different than one another.
Abstract translation: 用于燃气涡轮发动机的定子具有分别支撑包括第一和第二叶片的多个叶片的平台。 第一和第二区域布置在第一和第二叶片上的相同位置。 第一和第二区域分别包括彼此不同的第一和第二冷却孔构造。
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公开(公告)号：US09080452B2
公开(公告)日：2015-07-14
申请号：US13630419
申请日：2012-09-28
Applicant: United Technologies Corporation
Inventor： Mark A. Boeke , Shawn J. Gregg , Sarah Riley , Jeffrey J. DeGray , Richard M. Salzillo
CPC classification number: F01D5/186 , F01D5/187 , F01D9/02 , F01D25/12 , F01D25/246 , F05D2240/12 , F05D2240/81 , F05D2260/204 , Y02T50/672 , Y02T50/676
Abstract: A stator vane for a gas turbine engine includes an airfoil extending in a radial direction and supported by a platform having a gas flowpath surface. A cooling passage is arranged in the platform and includes a circumferential passage that is fluidly connected to an inlet passage extending through and edge of the platform, and film cooling holes extending from the gas flowpath surface to the circumferential passage, radial extending passage through the edge of the platform. A void is interconnected to at least one of the radially extending passage and the inlet passage.
Abstract translation: 用于燃气涡轮发动机的定子叶片包括沿径向延伸并由具有气体流路表面的平台支撑的翼型件。 冷却通道布置在平台中，并且包括流体连接到延伸通过平台的边缘的入口通道的圆周通道，以及从气体流路表面延伸到周向通道的膜冷却孔，通过边缘的径向延伸通道 的平台。 空隙与径向延伸通道和入口通道中的至少一个相互连接。
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公开(公告)号：US10239156B2
公开(公告)日：2019-03-26
申请号：US15026474
申请日：2014-09-25
Applicant: United Technologies Corporation
Inventor： Shawn J. Gregg , Alexander Staroselsky , Gajawalli V. Srinivasan
IPC: F01D5/18 , B23K26/342 , B23K26/00 , B23K26/12 , B23K26/144 , B22F3/11 , B22F3/105 , B22F5/04 , B23K103/02 , B23K103/08 , B23K103/14 , F01D5/28 , B33Y10/00 , B33Y80/00
Abstract: A method of forming a metal component having different regions containing different grain sizes and in porosities is by additive manufacturing. The method includes spreading a layer of starting powder on a temperature controlled moveable platform in a heated chamber with atmosphere and temperature control. Selected areas of the powder are melted and solidified with a computer controlled focused energy beam. The cooled platform is then indexed down and the process repeated. The grain size of the melted and solidified region can be controlled by the cooling rate during solidification which, in turn is controlled by the temperature of the chamber and the temperature of the cooled moveable platform.
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公开(公告)号：US10024172B2
公开(公告)日：2018-07-17
申请号：US14634006
申请日：2015-02-27
Applicant: United Technologies Corporation
Inventor： Mark A. Boeke , Richard M. Salzillo , Jeffrey J. DeGray , Shawn J. Gregg
Abstract: An airfoil includes an airfoil wall including an exterior airfoil surface and at least partially defines an airfoil cavity. A fillet is on the exterior airfoil surface. A recess is in an interior surface of the airfoil wall adjacent the fillet. A baffle tube is located in the airfoil cavity spaced from the recess.
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公开(公告)号：US20170175631A1
公开(公告)日：2017-06-22
申请号：US15450087
申请日：2017-03-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Shawn J. Gregg , Dominic J. Mongillo , Michael Leslie Clyde Papple , Russell J. Bergman , Mohammed Ennacer
CPC classification number: F01D5/188 , F01D5/187 , F01D5/189 , F01D9/041 , F01D25/12 , F02C7/12 , F04D29/324 , F04D29/542 , F04D29/582 , F05D2220/32 , F05D2240/126 , F05D2240/30 , F05D2260/201 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
Abstract: A component for a gas turbine engine includes, among other things, an airfoil that extends between a leading edge and a trailing edge and a cooling circuit disposed inside of the airfoil. The cooling circuit includes at least one core cavity that extends inside of the airfoil, a baffle received within the at least one core cavity, a plurality of pedestals positioned adjacent to the at least one core cavity and a first plurality of axial ribs positioned between the plurality of pedestals and the trailing edge of the airfoil.
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