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公开(公告)号：US20200141248A1
公开(公告)日：2020-05-07
申请号：US16177933
申请日：2018-11-01
Applicant: United Technologies Corporation
Inventor： Daniel P. Preuss , Brandon W. Spangler
Abstract: An airfoil for a gas turbine engine includes axial flow and radial flow cooling circuits defined within an airfoil body. A baffle disposed in spaced relation to an inner surface of the airfoil has a plurality of impingement cooling holes configured to direct a cooling fluid at an inner surface of the airfoil body and an axial extent from the leading edge defined by an aft wall, with the axial extent being substantially constant between the inner and outer end walls and defined by a plane perpendicular to an engine axis. A first radially-extending rib is angled with respect to the baffle to define a first passage between the first rib and the baffle that tapers in cross-sectional area between the inner end wall and the outer end wall, becoming larger in cross-sectional area in a direction of cooling fluid flow through the first passage.
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公开(公告)号：US10526917B2
公开(公告)日：2020-01-07
申请号：US15884473
申请日：2018-01-31
Applicant: United Technologies Corporation
Inventor： Corey D. Anderson , Brandon W. Spangler
Abstract: An exemplary gas turbine engine includes a turbine section positioned about an engine central longitudinal axis. The turbine section includes a component with a platform providing a lip, a rail extending radially from the platform and at an axial location spaced from an outer axial extension of the lip. An inner face of the rail and a surface of the platform at least partially provide a cavity. At least one opening extends from the inner face to an outer face of the rail opposite the inner face to provide fluid communication from the cavity to the lip.
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公开(公告)号：US10480329B2
公开(公告)日：2019-11-19
申请号：US15496093
申请日：2017-04-25
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Dominic J. Mongillo
Abstract: Turn caps for airfoils of gas turbine engines having exterior side walls, an exterior top wall extending between the exterior side walls, a first turn cap divider extending from the exterior top wall and positioned between the exterior side walls and defining a first turning feature between the first turn cap divider and the exterior side walls, the first turning feature comprising a first suction-side turn passage and a first pressure-side turn passage wherein the first turn cap divider fluidly separates the first pressure-side turn passage from the first suction-side turn passage within the turn cap, and a merging chamber is formed in the turn cap wherein fluid flows passing through the first suction side turn passage and the first pressure side turn passage are merged at the merging chamber.
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公开(公告)号：US20190330987A1
公开(公告)日：2019-10-31
申请号：US15962074
申请日：2018-04-25
Applicant: United Technologies Corporation
Inventor： Corey D. Anderson , Brandon W. Spangler
Abstract: Baffles and airfoils for installation within gas turbine engines are provided. The baffles include a baffle side wall extending between a first end and a second end and a baffle divider within the baffle side wall, wherein the baffle divider and the baffle side wall define a first cavity and a second cavity. The first cavity is located at a first side at the first end and the second cavity is located at a second side at the first end and the baffle divider includes a spiral portion such that the first cavity is transitioned toward the second side and the second cavity is transitioned toward the first side.
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公开(公告)号：US10458291B2
公开(公告)日：2019-10-29
申请号：US15252874
申请日：2016-08-31
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brandon W. Spangler , Russell J. Bergman
Abstract: A component for a gas turbine engine includes a platform having a non-gas path side and a gas path side, an airfoil extending from the gas path side of the platform, and a cover plate positioned adjacent to the non-gas path side of the platform. The cover plate can include a first plurality of openings that communicate a first portion of a cooling air to a first cooling cavity of the platform and a second plurality of openings that can communicate a second portion of the cooling air to the second cooling cavity that is separate from the first cooling cavity. Each of the first cooling cavity and the second cooling cavity can include a plurality of augmentation features.
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Patent Agency Ranking
公开(公告)号：US10458264B2
公开(公告)日：2019-10-29
申请号：US14704278
申请日：2015-05-05
Applicant: United Technologies Corporation
Inventor： Dominic J. Mongillo, Jr. , Brandon W. Spangler , Lane Thornton
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.
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公开(公告)号：US10422233B2
公开(公告)日：2019-09-24
申请号：US14961726
申请日：2015-12-07
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Atul Kohli
Abstract: A component of a gas turbine engine having: an internal cooling cavity; a baffle insert configured to be inserted into the internal cooling cavity; a plurality of trip strips extending upwardly from an exterior surface of the baffle insert; at least one separating feature located between a pair of ends of a pair of the plurality of trip strips, wherein the plurality of trip strips and the at least one separating feature are spaced from an interior surface of the internal cooling cavity; a plurality of trip strips extending upwardly from the interior surface; and at least one separating feature located between a pair of ends of the plurality of trip strips located on the interior surface of the internal cooling cavity, wherein the plurality of trip strips and the at least one separating feature of the interior surface are spaced from the exterior surface of the baffle insert.
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公开(公告)号：US20190234236A1
公开(公告)日：2019-08-01
申请号：US15884500
申请日：2018-01-31
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Corey D. Anderson
CPC classification number: F01D25/12 , F01D5/188 , F01D5/189 , F01D9/041 , F02C3/06 , F05D2220/32 , F05D2240/121 , F05D2240/122 , F05D2260/201 , F05D2260/221
Abstract: A component for a gas turbine engine according to example of the present disclosure includes a body that has an airfoil extending between a radially inner platform and a radially outer platform, and that has an internal cavity within the airfoil. A baffle is disposed within the internal cavity. The baffle defines first and second baffle cavities that are separated by a baffle dividing wall extending between the radially inner platform and the radially outer platform. An impingement plate is spaced apart from one of the radially inner and outer platforms, includes a first opening that provides fluid communication between a first chamber and the first baffle cavity, and includes a plurality of second openings that are smaller than the first opening and provide fluid communication between the first chamber and the second baffle cavity via a second chamber.
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公开(公告)号：US20190234235A1
公开(公告)日：2019-08-01
申请号：US15884494
申请日：2018-01-31
Applicant: United Technologies Corporation
Inventor： Corey D. Anderson , Brandon W. Spangler
CPC classification number: F01D25/12 , F01D5/188 , F01D9/041 , F05D2220/323 , F05D2240/12 , F05D2240/126 , F05D2240/80 , F05D2240/81 , F05D2260/201
Abstract: A vane section of a gas turbine engine according to an example of the present disclosure includes a platform and an airfoil extending outwardly from the platform and having an internal channel communicating with an opening in the platform. A rail extends inwardly from the platform, such that a surface of the platform opposite the airfoil and the rail at least partially define a platform cavity. A flow diverter extends inwardly of the platform within the platform cavity and defines a diverter cavity, an inlet configured to receive fluid flowing in a first direction from the opening in the platform to the diverter cavity, and an outlet configured to expel fluid from the diverter cavity to the platform cavity in a second direction different from the first direction.
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公开(公告)号：US10358978B2
公开(公告)日：2019-07-23
申请号：US14772398
申请日：2014-03-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Dominic J. Mongillo , Brandon W. Spangler
IPC: F01D5/18 , F01D9/04 , F01D9/06 , F02C7/18 , F02C7/25 , F02K1/82 , F23R3/16 , F01D11/08 , F01D25/12 , F01D25/30
Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a first wall, a second wall and at least one row of shaped pedestals extending between the first wall and the second wall. The at least one row of shaped pedestals includes a first set of C-shaped pedestals and a second set of C-shaped pedestals adjacent to the first set of C-shaped pedestals.
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