-
公开(公告)号：US11230927B2
公开(公告)日：2022-01-25
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.
-
公开(公告)号：US10995955B2
公开(公告)日：2021-05-04
申请号：US16052242
申请日：2018-08-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Corey D. Anderson
Abstract: A heat shield panel arrangement for use in a combustor of a gas turbine engine is disclosed. In various embodiments, the heat shield panel arrangement includes a first panel having a first rail, the first rail having a first distal tip and a first angled outer wall, the first distal tip having a first distal tip length; and a second panel having a second rail, the second rail having a second distal tip and a second angled outer wall, the second distal tip having a second distal tip length. The first distal tip length is less than the second distal tip length and the first angled outer wall is substantially parallel to the second angled outer wall with a gap formed therebetween.
-
公开(公告)号：US10738620B2
公开(公告)日：2020-08-11
申请号：US15956298
申请日：2018-04-18
Applicant: United Technologies Corporation
Inventor： Corey D. Anderson , Jeremy Styborski
Abstract: A gas turbine engine includes a first vane of a turbine section, a second vane of the turbine section, an impingement plate that includes a first impingement hole and a second impingement hole, and a pipe that supplies a fluid. The first vane includes a first platform. The second vane includes a second platform and a baffle. A first portion of the fluid traverses the first impingement hole and impinges on a first surface of the first platform. A second portion of the fluid traverses the second impingement hole and impinges on a second surface of the second platform. A third portion of the fluid bypasses the impingement plate and enters the baffle.
-
公开(公告)号：US20200063572A1
公开(公告)日：2020-02-27
申请号：US16107160
申请日：2018-08-21
Applicant: United Technologies Corporation
Inventor： Corey D. Anderson
Abstract: Vanes for gas turbine engines are described. The vanes include an airfoil body extending between a first platform and a second platform, the airfoil body having a leading edge, a trailing edge, a pressure side, and a suction side and at least one skin core cavity comprising a first skin core cavity, wherein the first skin core cavity defines a throughflow passage through the vane between the first platform and the second platform, wherein the at least one skin core cavity is defined between an external hot wall of the vane and an internal cold wall of the vane.
-
Patent Agency Ranking
公开(公告)号：US20190383146A1
公开(公告)日：2019-12-19
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.
-
公开(公告)号：US20190353038A1
公开(公告)日：2019-11-21
申请号：US15982163
申请日：2018-05-17
Applicant: United Technologies Corporation
Inventor： Corey D. Anderson , Jeremy Styborski
IPC: F01D5/18
Abstract: Partitioned baffles and components for installation within gas turbine engines are provided. The partitioned baffles include a baffle body defining a first cavity, the baffle body having a first inlet and at least one first impingement hole arranged for flow to pass through the first cavity from the first inlet to the at least one first impingement hole and a partitioned channel installed within the baffle body and defining a second cavity, wherein the partitioned channel has a second inlet and at least one second impingement hole, wherein a flow through the second cavity flows from the second inlet to the at least one second impingement hole. The baffle body is configured to receive cooling air from a first source and the partitioned channel is configured to receive cooling air from a second source, wherein the first source is different from the second source.
-
公开(公告)号：US20190323358A1
公开(公告)日：2019-10-24
申请号：US15956298
申请日：2018-04-18
Applicant: United Technologies Corporation
Inventor： Corey D. Anderson , Jeremy Styborski
Abstract: A gas turbine engine includes a first vane of a turbine section, a second vane of the turbine section, an impingement plate that includes a first impingement hole and a second impingement hole, and a pipe that supplies a fluid. The first vane includes a first platform. The second vane includes a second platform and a baffle. A first portion of the fluid traverses the first impingement hole and impinges on a first surface of the first platform. A second portion of the fluid traverses the second impingement hole and impinges on a second surface of the second platform. A third portion of the fluid bypasses the impingement plate and enters the baffle.
-
公开(公告)号：US20190301286A1
公开(公告)日：2019-10-03
申请号：US15938062
申请日：2018-03-28
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Corey D. Anderson
Abstract: Airfoils for gas turbine engines are provided. The airfoil include an airfoil body, the body extending between a leading edge and a trailing edge in an axial direction and between a pressure side wall and a suction side wall in a circumferential direction, the airfoil body defining an airfoil cavity therein and a baffle located within the airfoil cavity. The airfoil includes increased thickness side walls to form an airfoil cavity to account for the baffle within the cavity and to direct cooling flow through the airfoil.
-
公开(公告)号：US20190242270A1
公开(公告)日：2019-08-08
申请号：US15888237
申请日：2018-02-05
Applicant: United Technologies Corporation
Inventor： Corey D. Anderson , Brandon W. Spangler
CPC classification number: F01D11/001 , F01D11/24 , F05D2240/11 , F05D2240/81 , F05D2260/2214 , F05D2260/22141
Abstract: Components for gas turbine engines are provided. The components include a component body having a hot side and a cold side, an attachment element extending from the cold side of the component body, a component extension extending from the component body at the attachment element to an end surface, the component extension having a cold-side first portion and a cold-side second portion, wherein the cold-side first portion is a portion of the component extension between the attachment element and the cold-side second portion, and the cold-side second portion is a portion of the component extension extending from the cold-side first portion to the end surface of the component extension, and a cold-side heat transfer augmentation feature on the cold-side second portion of the component extension, wherein the cold-side first portion defines a uniform surface.
-
-
-
-
-
-
-
-
Search Results
29
records
(took 0.02 seconds)
