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公开(公告)号：US20170335722A1
公开(公告)日：2017-11-23
申请号：US15161807
申请日：2016-05-23
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： David J. Candelori , Brandon Spangler
CPC classification number: F01D25/32 , F01D9/041 , F01D11/08 , F01D19/00 , F01D25/005 , F01D25/12 , F05D2220/32 , F05D2260/202 , F05D2260/607 , F05D2300/17 , Y02T50/675
Abstract: A system for circumferentially distributing debris in a gas turbine engine includes a component that defines a component cooling channel that has an opening and is configured to receive a cooling airflow. The system also includes a casing at least partially enclosing the component. The system also includes a debris distribution surface positioned radially between the casing and the opening.
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公开(公告)号：US20170335721A1
公开(公告)日：2017-11-23
申请号：US15161742
申请日：2016-05-23
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brandon Spangler , David J. Candelori
CPC classification number: F01D25/32 , F01D5/187 , F01D9/041 , F01D19/00 , F01D21/003 , F01D25/12 , F01D25/24 , F02C3/04 , F05D2220/32 , F05D2260/202 , F05D2260/607 , F05D2260/85 , Y02T50/675
Abstract: A system for reducing debris in a gas turbine engine includes a component that defines a component cooling channel for receiving a cooling airflow. The system also includes a casing at least partially enclosing the component. The system also includes a debris evacuation door coupled to the casing and having an open state in which the debris can exit the casing and a closed state.
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公开(公告)号：US10316698B2
公开(公告)日：2019-06-11
申请号：US15161807
申请日：2016-05-23
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： David J. Candelori , Brandon Spangler
Abstract: A system for circumferentially distributing debris in a gas turbine engine includes a component that defines a component cooling channel that has an opening and is configured to receive a cooling airflow. The system also includes a casing at least partially enclosing the component. The system also includes a debris distribution surface positioned radially between the casing and the opening.
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公开(公告)号：US09976423B2
公开(公告)日：2018-05-22
申请号：US14862422
申请日：2015-09-23
Applicant: United Technologies Corporation
Inventor： San Quach , Christopher King , Steven Bruce Gautschi , David J. Candelori
CPC classification number: F01D5/186 , F01D5/141 , F05D2240/303 , F05D2240/305 , F05D2240/306 , F05D2250/324 , F05D2260/202 , Y02T50/671 , Y02T50/673 , Y02T50/676
Abstract: The systems and methods described herein adapt the orientation, position and/or diffusion angles of showerhead cooling holes depending on the external gas/streamline flow direction. In regions, for example, where the stagnation line is on the pressure side, the breakouts of the showerhead holes substantially face aft (e.g., primarily towards the suction side). The location and positioning of the holes may be oriented according to the direction of incoming gas flows.
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公开(公告)号：US20160177734A1
公开(公告)日：2016-06-23
申请号：US14862422
申请日：2015-09-23
Applicant: United Technologies Corporation
Inventor： San Quach , Christopher King , Steven Bruce Gautschi , David J. Candelori
IPC: F01D5/18
CPC classification number: F01D5/186 , F01D5/141 , F05D2240/303 , F05D2240/305 , F05D2240/306 , F05D2250/324 , F05D2260/202 , Y02T50/671 , Y02T50/673 , Y02T50/676
Abstract: The systems and methods described herein adapt the orientation, position and/or diffusion angles of showerhead cooling holes depending on the external gas/streamline flow direction. In regions, for example, where the stagnation line is on the pressure side, the breakouts of the showerhead holes substantially face aft (e.g., primarily towards the suction side). The location and positioning of the holes may be oriented according to the direction of incoming gas flows.
Abstract translation: 本文所述的系统和方法根据外部气体/流线流动方向适应喷头冷却孔的取向，位置和/或扩散角。 例如，在停滞线处于压力侧的区域中，喷头孔的突破基本上向后（例如主要朝向吸力侧）。 孔的位置和定位可以根据进入的气流的方向定向。
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Patent Agency Ranking
公开(公告)号：US10480326B2
公开(公告)日：2019-11-19
申请号：US15701008
申请日：2017-09-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： David J. Candelori , Michael F. Blair
Abstract: Disclosed is a vane stage for a variable area turbine, comprising vane platforms comprising a first vane platform and a second vane platform, one of the vane platforms being a radial inner vane platform and another of the vane platforms being a radial outer vane platform, and a space therebetween defining an air flowpath; a primary vane body secured at opposing radial ends to the first vane platform and the second vane platform, a secondary vane body movably secured at the first vane platform, the secondary vane body being movable between a stowed position, wherein the secondary vane body is outside of the air flow path, and a deployed position, wherein the secondary vane body is extended between the plurality of vane platforms to form a vane trailing edge extension.
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公开(公告)号：US10294823B2
公开(公告)日：2019-05-21
申请号：US15161742
申请日：2016-05-23
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brandon Spangler , David J. Candelori
Abstract: A system for reducing debris in a gas turbine engine includes a component that defines a component cooling channel for receiving a cooling airflow. The system also includes a casing at least partially enclosing the component. The system also includes a debris evacuation door coupled to the casing and having an open state in which the debris can exit the casing and a closed state.
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公开(公告)号：US20190078440A1
公开(公告)日：2019-03-14
申请号：US15701008
申请日：2017-09-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： David J. Candelori , Michael F. Blair
CPC classification number: F01D5/148 , F01D5/142 , F01D5/145 , F01D5/186 , F01D9/041 , F01D17/148 , F01D17/16 , F01D17/162 , F04D29/544 , F05D2240/122 , F05D2240/304 , F05D2260/202
Abstract: Disclosed is a vane stage for a variable area turbine, comprising vane platforms comprising a first vane platform and a second vane platform, one of the vane platforms being a radial inner vane platform and another of the vane platforms being a radial outer vane platform, and a space therebetween defining an air flowpath; a primary vane body secured at opposing radial ends to the first vane platform and the second vane platform, a secondary vane body movably secured at the first vane platform, the secondary vane body being movable between a stowed position, wherein the secondary vane body is outside of the air flow path, and a deployed position, wherein the secondary vane body is extended between the plurality of vane platforms to form a vane trailing edge extension.
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公开(公告)号：US20150300180A1
公开(公告)日：2015-10-22
申请号：US14686979
申请日：2015-04-15
Applicant: United Technologies Corporation
Inventor： David J. Candelori , San Quach
CPC classification number: F01D5/288 , C23C28/3215 , C23C28/3455 , F01D1/02 , F01D5/18 , F01D5/20 , F01D25/12 , F05D2230/90 , F05D2240/30 , F05D2240/307 , F05D2260/231 , Y02T50/673 , Y02T50/6765
Abstract: A blade for a gas turbine engine includes an airfoil that has a tip with a terminal end surface. The terminal end surface includes a recess that has a depth of less than 40 mils (1.016 mm). The recess is filled with a thermal barrier coating. The recess is without any cooling holes.
Abstract translation: 一种用于燃气涡轮发动机的叶片包括具有带有末端表面的尖端的翼型件。 终端表面包括具有小于40密耳（1.016mm）的深度的凹部。 凹部填充有热障涂层。 凹槽没有任何冷却孔。
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公开(公告)号：US20160177733A1
公开(公告)日：2016-06-23
申请号：US14639507
申请日：2015-03-05
Applicant: United Technologies Corporation
Inventor： Scott D. Lewis , Gaurav M. Patel , Jeffery Scott Hembree , San Quach , Mark F. Zelesky , David J. Candelori , Dominic J. Mongillo
CPC classification number: F01D5/186 , B23P2700/06 , F01D5/147 , F01D5/288 , F01D9/041 , F01D11/08 , F05D2220/32 , F05D2230/10 , F05D2230/90 , F05D2250/70 , F05D2260/202 , Y02T50/676
Abstract: A method of forming a component for use in a gas turbine engine comprises the steps of determining a desired shape for a cooling hole on a gas turbine engine component, and determining the likely deposition of a coating to be provided on the component into the cooling hole. An intermediate cooling hole is formed that has an enlarged area from the desired shape to account for deposition of the coating. The component is then coated. A component and an intermediate component for use in a gas turbine engine are also disclosed.
Abstract translation: 一种形成用于燃气涡轮发动机的部件的方法包括以下步骤：确定燃气涡轮发动机部件上的冷却孔的期望形状，以及确定要提供到部件上的涂层可能沉积到冷却孔 。 形成中间冷却孔，该中间冷却孔具有从期望形状的放大区域以解决涂层的沉积。 然后将组分涂覆。 还公开了一种用于燃气涡轮发动机的部件和中间部件。
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