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公开(公告)号：US20190169995A1
公开(公告)日：2019-06-06
申请号：US15832455
申请日：2017-12-05
Applicant: United Technologies Corporation
Inventor： Christopher Whitfield , Carey Clum , Dominic J. Mongillo, Jr.
CPC classification number: F01D5/187 , F02C3/04 , F02C9/18 , F05D2220/32 , F05D2240/35 , F05D2250/185 , F05D2260/201 , F05D2260/202 , F05D2260/204 , F05D2260/2212
Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip. A skin passage is arranged in one of the pressure and suction side walls to form a hot side wall at an outer surface and a cold side wall at an inner surface. The skin passage extends a height in the radial direction, a width in a width direction, and a thickness in a thickness direction. The thickness is less than the width. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage at a core passage surface. The core passage and the skin passage are configured to have a same direction of fluid flow. A resupply hole fluidly interconnects the core and skin passages. A centerline of the resupply hole is arranged at an first angle relative to the direction of fluid flow in the core passage. The first angle lies in a plane parallel to the thickness direction. The centerline of the resupply hole is arranged at a second angle relative to the direction of fluid flow in the core passage. The second angle lies in a plane parallel to the width direction. The second angle is at an acute angle. The first and second angles are configured to provide a low turbulence flow region in the skin passage.
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公开(公告)号：US20190101010A1
公开(公告)日：2019-04-04
申请号：US15723512
申请日：2017-10-03
Applicant: United Technologies Corporation
Inventor： Tracy A. Propheter-Hinckley , Carey Clum , Timothy J. Jennings
Abstract: Airfoil bodies having a first core cavity within the airfoil body and a second core cavity located within the airfoil body and adjacent the first core cavity, wherein the second core cavity is defined by a first cavity wall, a second cavity wall, a first exterior wall, and a second exterior wall, wherein the first cavity wall is located between the second core cavity. The first cavity wall includes a first surface angled toward the first exterior wall and a second surface angled toward the second exterior wall and at least one first cavity impingement hole is formed within the first surface. A funneling feature extends the second core cavity along the first exterior wall to funnel the first impingement flow along the first exterior wall.
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公开(公告)号：US20190101009A1
公开(公告)日：2019-04-04
申请号：US15723500
申请日：2017-10-03
Applicant: United Technologies Corporation
Inventor： Tracy A. Propheter-Hinckley , Carey Clum , Timothy J. Jennings
Abstract: Airfoil bodies having a first core cavity and a second core cavity located within the airfoil body and adjacent the first core cavity, wherein the second core cavity is defined by a first cavity wall, a second cavity wall, a first exterior wall, and a second exterior wall, wherein the first cavity wall is located between the second core cavity and the first core cavity. The first cavity wall includes a first surface angled toward the first exterior wall and a second surface angled toward the second exterior wall. At least one first cavity impingement hole is formed within the first surface and has an oblong shape with a long axis oriented between 0° and 180° relative to the first exterior side wall.
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公开(公告)号：US20190078441A1
公开(公告)日：2019-03-14
申请号：US15699303
申请日：2017-09-08
Applicant: United Technologies Corporation
Inventor： Carey Clum , Dominic J. Mongillo, JR.
Abstract: Components for gas turbine engines and methods of making the same, the components including a component body having an external side wall and an internal side wall and defining at least a first cooling cavity and a second cooling cavity between the external side wall and the internal side wall, at least one segmented rib extending within the component body and separating the first cooling cavity from the second cooling cavity, wherein the first and second cooling cavities, the at least one segmented rib comprising at least two rib segments separated by a segment gap, and a discharge hole formed in the external side wall fluidly connected the segment gap to an exterior surface of the component body.
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公开(公告)号：US20190072033A1
公开(公告)日：2019-03-07
申请号：US15697219
申请日：2017-09-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Carey Clum , Timothy S. Snyder
Abstract: A combustor may comprise a combustion chamber encapsulated by a combustor casing, wherein the combustor casing comprises a casing forward portion, a casing radially inward portion, a casing radially outward portion, and a casing aft portion. The casing radially inward portion may comprise a dirt collector system comprising a hot panel adjacent to the combustion chamber; a cold shell panel coupled to the hot panel such that the hot panel is between the combustion chamber and the cold shell panel; and a dirt collector panel coupled to the cold shell panel such that the cold shell panel is between the hot panel and the dirt collector panel. The cold shell panel and the dirt collector panel at least partially define a dirt collecting space.
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Patent Agency Ranking
公开(公告)号：US20180347397A1
公开(公告)日：2018-12-06
申请号：US15613686
申请日：2017-06-05
Applicant: United Technologies Corporation
Inventor： Carey Clum , Adam Generale
CPC classification number: F01D25/12 , F01D5/187 , F01D9/041 , F01D17/105 , F02C3/04 , F05D2220/32 , F05D2240/12 , F05D2240/35 , F05D2240/81 , F05D2250/185 , F05D2260/20
Abstract: A turbine assembly may comprise a platform defining a platform cavity cooled by a platform flow with a vane extending from the platform. A platform-fed through cavity is defined by the vane and cooled by a first portion of the platform flow. A direct-fed through flow cavity is defined in the vane and cooled by a direct-fed through flow. The direct-fed through flow cavity and the platform-fed through cavity meet at an outlet to expel an outgoing through flow from the outlet. A platform-fed serpentine cavity may be defined in the vane and separated from the platform-fed through cavity by a divider. The platform-fed serpentine cavity is cooled by a second portion of the platform flow.
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公开(公告)号：US20180283181A1
公开(公告)日：2018-10-04
申请号：US15471731
申请日：2017-03-28
Applicant: United Technologies Corporation
Inventor： Carey Clum , Ricardo Trindade
Abstract: An airfoil has a pressure side wall and a suction side wall circumferentially spaced apart from the pressure side wall. Each radially extends between a root region and a tip region, and each axially extends between a leading edge and a trailing edge. The airfoil also has a gusset, a squealer pocket, and a tip pocket. The gusset extends between the pressure side wall and the suction side wall. The squealer pocket is formed in the tip region and is disposed between the leading edge, the gusset, the pressure side wall, and the suction side wall. The tip pocket is formed in the tip region and is spaced apart from the squealer pocket. The tip pocket is disposed between the trailing edge, the gusset, the pressure side wall, and the suction side wall.
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公开(公告)号：US10077664B2
公开(公告)日：2018-09-18
申请号：US14961221
申请日：2015-12-07
Applicant: United Technologies Corporation
Inventor： Carey Clum , Timothy J. Jennings
IPC: F01D5/14 , F01D9/02 , B22F3/105 , B22D25/02 , B22C9/10 , F01D25/12 , B23K15/00 , F23R3/00 , F02C7/18 , F01D11/08 , F01D25/30 , F01D5/18 , B33Y80/00 , B33Y10/00
CPC classification number: F01D5/147 , B22C9/108 , B22D25/02 , B22F3/1055 , B23K15/0086 , B33Y10/00 , B33Y80/00 , F01D5/186 , F01D5/187 , F01D9/02 , F01D11/08 , F01D25/12 , F01D25/30 , F02C7/18 , F05D2220/32 , F05D2230/21 , F05D2260/202 , F05D2260/204 , F23R3/002 , Y02T50/673 , Y02T50/676
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 includes a plurality of nodes, a plurality of branches that extend between the plurality of nodes, and a plurality of passages extending between the plurality of nodes and the plurality of passages. Further, at least one of the branches is non-circular in cross-section.
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公开(公告)号：US20170051673A1
公开(公告)日：2017-02-23
申请号：US14827773
申请日：2015-08-17
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Carey Clum
IPC: F02C7/18
CPC classification number: F02C7/18 , F01D5/186 , F05D2220/32 , F05D2260/202
Abstract: A film-cooled component for a gas turbine engine includes a first surface of the component located at a gas path of a gas turbine engine, a second surface of the component defining a component passage, and a cooling airflow passage extending from the second surface to the first surface to convey a cooling airflow from the passage and emit the cooling airflow at the first surface. The cooling airflow passage is curvilinearly diffused in at least two directions relative to a local gas flow direction in the gas path. A method of cooling a component includes flowing a cooling airflow into an internal component passage of the turbine component, conveying the cooling airflow through a cooling airflow passage, diffusing the cooling airflow in at least two directions along the airflow passage, and emitting the cooling airflow at a gas path surface to cool the gas path surface of the component.
Abstract translation: 用于燃气涡轮发动机的薄膜冷却部件包括位于燃气涡轮发动机的气体路径处的部件的第一表面，限定部件通道的部件的第二表面和从第二表面延伸到 所述第一表面用于从所述通道传送冷却气流并且在所述第一表面处发出冷却气流。 冷却气流通道相对于气体路径中的局部气体流动方向在至少两个方向上曲线地扩散。 一种冷却部件的方法包括将冷却气流流入涡轮机部件的内部部件通道，将冷却气流传送通过冷却气流通道，沿着气流通道沿至少两个方向扩散冷却气流，并且发射冷却气流 在气体路径表面处，以冷却部件的气体路径表面。
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70.发明授权公开(公告)号：US11415319B2
公开(公告)日：2022-08-16
申请号：US16208993
申请日：2018-12-04
Applicant: United Technologies Corporation
Inventor： Dennis M. Moura , Carey Clum
Abstract: A gas turbine engine component assembly is provided. The gas turbine engine component assembly, comprising: a first component having a first surface, a second surface opposite the first surface, and a cooling hole extending from the second surface to the first surface through the first component; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween in fluid communication with the cooling hole for cooling the second surface of the second component; and a particulate capture device attached to at least one of the first component and the second component, the particulate capture device configured to aerodynamically separate the airflow from the particulate.
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