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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：US10975702B2
公开(公告)日：2021-04-13
申请号：US16008521
申请日：2018-06-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Corey D. Anderson
Abstract: A turbine vane includes a platform, an airfoil, and a cooling arrangement. The platform has a first surface and a second surface. The first surface and the second surface each axially between a first platform end and a second platform end and each circumferentially extend between a first platform side and a second platform side. The airfoil is connected to the platform and defines a passage outlet that extends through the second surface. The cooling arrangement includes a third wall that is connected to the second surface of the platform. The third wall defines a first outlet and a second outlet.
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公开(公告)号：US20200378261A1
公开(公告)日：2020-12-03
申请号：US16430191
申请日：2019-06-03
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Corey D. Anderson , Marianne C. Monastero , Vladimir Skidelsky
Abstract: A vane assembly may comprise a plurality of airfoils each extending between an inner platform and an outer platform, the plurality of airfoils comprising a nominal airfoil, a thickened airfoil, and a first thinned airfoil circumferentially adjacent to the thickened airfoil, wherein, the nominal airfoil has a first chord thickness, the thickened airfoil has a second chord thickness, and the thinned airfoil has a third chord thickness, wherein the second chord thickness is greater than the first chord thickness and the third chord thickness is less than the first chord thickness, and a member disposed within the thickened airfoil.
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公开(公告)号：US20200263563A1
公开(公告)日：2020-08-20
申请号：US16700513
申请日：2019-12-02
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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Patent Agency Ranking
公开(公告)号：US10697309B2
公开(公告)日：2020-06-30
申请号：US15961930
申请日：2018-04-25
Applicant: United Technologies Corporation
Inventor： Corey D. Anderson , Brandon W. Spangler
IPC: F01D5/18
Abstract: Components for gas turbine engines are provided. The components include a platform, a first airfoil extending from the platform, a first cavity located within the first airfoil, the first cavity includes a forward portion and an aft portion separated by a divider, a cover plate attached to the platform on a side opposite the airfoil, wherein a platform cavity is defined between the cover plate and the platform and wherein the first cavity is fluidly connected to the platform cavity through a first cavity inlet, and a first cavity separating rail dividing the platform cavity into a first platform forward cavity and a first platform aft cavity, wherein the first platform forward cavity is fluidly connected to the aft portion of the first cavity and the first platform aft cavity is fluidly connected to the forward portion of the first cavity.
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公开(公告)号：US20200040760A1
公开(公告)日：2020-02-06
申请号：US16055761
申请日：2018-08-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Corey D. Anderson
Abstract: A component for a gas turbine engine is disclosed. In various embodiments, the component includes an airfoil, including therein a first cavity and a second cavity, and an outer spindle extending from the airfoil, the outer spindle including a first channel in fluid communication with the first cavity and a second channel in fluid communication with the second cavity.
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公开(公告)号：US20190330999A1
公开(公告)日：2019-10-31
申请号：US15965130
申请日：2018-04-27
Applicant: United Technologies Corporation
Inventor： Corey D. Anderson
Abstract: A variable vane system for a gas turbine engine includes an airfoil trunnion that extends through a vane platform such that the airfoil is rotatable with respect to the vane platform about an axis, the airfoil trunnion having an inlet configuration into the airfoil and a fixed airflow inlet mask to abut the airfoil trunnion, the fixed airflow inlet mask having a mask inlet configuration that modulates an airflow through the inlet configuration.
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公开(公告)号：US10415428B2
公开(公告)日：2019-09-17
申请号：US15884500
申请日：2018-01-31
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Corey D. Anderson
IPC: F04F5/16 , F04F5/46 , F04D17/16 , F04D25/06 , F04D25/08 , F04D25/16 , F04D29/42 , F04D29/66 , F01D11/00 , F01D5/08 , F01D5/06 , F01D25/12 , F02C3/04 , F16J15/16 , F16J15/447 , F01D9/04 , F02C3/06
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：US20190234234A1
公开(公告)日：2019-08-01
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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