-
公开(公告)号：US20240011399A1
公开(公告)日：2024-01-11
申请号：US18142577
申请日：2023-05-02
Applicant: General Electric Company
Inventor： Thomas Earl Dyson , Nicholas William Rathay , Brendon James Leary , Gregory Terrence Garay , Gustavo Adolfo Ledezma , David Wayne Weber , Aaron Ezekiel Smith
CPC classification number: F01D5/187 , F01D5/20 , F01D5/141 , F05D2260/201 , F05D2260/205 , F01D5/3007
Abstract: An airfoil includes a body, a cooling passage, a first cooling cavity, a second cooling cavity, a cooling conduit, and a connecting conduit. The body defines an interior and includes a tip rail with an exterior surface extending between a first surface, a second surface, and a third surface. The cooling passage is formed within the interior. The first cooling cavity and the second cooling cavity are spaced from each other within the tip rail. The cooling conduit fluidly couples the cooling passage with the first cooling cavity. The connecting conduit fluidly couples the first cooling cavity to the second cooling cavity.
-
公开(公告)号：US11306735B2
公开(公告)日：2022-04-19
申请号：US16654496
申请日：2019-10-16
Applicant: General Electric Company
Inventor： Sylvain Pierre , Brendon James Leary , Jason Adam Neville
Abstract: A turbine nozzle includes an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.
-
公开(公告)号：US20210047718A1
公开(公告)日：2021-02-18
申请号：US16539803
申请日：2019-08-13
Applicant: General Electric Company
Inventor： Thomas Earl Dyson , Lyndsay Marie Kibler , Brendon James Leary , David Vincent Bucci
Abstract: A method of depositing a coating on a component of a turbine engine. The method includes forming a turbine component including at least one cooling flow passage in fluid communication with an aperture on a surface of the turbine component. A protective shield is formed on an inner surface of the at least one cooling flow passage and extending to an exterior of the turbine component via the aperture. During a coating process, the protective shield is configured to block the coating from being deposited in the at least one cooling flow passage via the aperture. Subsequent to coating, at least a portion of the protective shield is removed to provide for passage of a cooling fluid flow in the at least one cooling flow passage. The cooling fluid flow exits the turbine component through the aperture. A turbine component employing user of the protective shield is also disclosed.
-
公开(公告)号：US20200063574A1
公开(公告)日：2020-02-27
申请号：US16669756
申请日：2019-10-31
Applicant: General Electric Company
Abstract: A blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and form a radially extending chamber for receiving a coolant flow. A rib configuration may include: a leading edge transverse rib connecting the pressure side outer wall and the suction side outer wall and partitioning the radially extending chamber into a leading edge passage within the leading edge of the airfoil and a central passage adjacent to the leading edge passage. One or both camber line ribs connect to a corresponding pressure side outer wall and suction side outer wall at a point aft of the leading edge transverse rib causing the central passage to extend towards one or both of the pressure side outer wall and the suction side outer wall, resulting in a flared center cavity aft of the leading edge.
-
公开(公告)号：US10415463B2
公开(公告)日：2019-09-17
申请号：US15271864
申请日：2016-09-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Marc Edward Blohm , Brendon James Leary
Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
-
Patent Agency Ranking
公开(公告)号：US20190017391A1
公开(公告)日：2019-01-17
申请号：US15648541
申请日：2017-07-13
Applicant: General Electric Company
Inventor： Thomas Earl Dyson , Nicholas William Rathay , Brendon James Leary , Gregory Terrence Garay , Gustavo Adolfo Ledezma , David Wayne Weber , Aaron Ezekiel Smith
Abstract: An apparatus and method for cooling a blade tip for a turbine engine can include an blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the blade at the tip. A plurality of film-holes can be provided in the tip rail. A flow of cooling fluid can be provided through the film-holes from the interior of the blade to cool the tip of the blade.
-
公开(公告)号：US10030526B2
公开(公告)日：2018-07-24
申请号：US14977200
申请日：2015-12-21
Applicant: General Electric Company
Inventor： Gregory Thomas Foster , Elisabeth Kraus Black , Michelle Jessica Iduate , Brendon James Leary , Jacob Charles Perry, II , David Wayne Weber
Abstract: A cooling system for a turbine bucket including a multi-wall blade and a platform. A cooling circuit for the multi-wall blade includes: an outer cavity circuit and a central cavity for collecting cooling air from the outer cavity circuit; a platform core air feed for receiving the cooling air from the central cavity; and an air passage for fluidly connecting the platform core air feed to a platform core of the platform.
-
公开(公告)号：US20180163544A1
公开(公告)日：2018-06-14
申请号：US15883498
申请日：2018-01-30
Applicant: General Electric Company
Inventor： Aaron Ezekiel Smith , Gregory Thomas Foster , Michelle Jessica Iduate , Brendon James Leary , David Wayne Weber
IPC: F01D5/18
CPC classification number: F01D5/187 , F05D2240/304 , F05D2260/201 , F05D2260/203 , F05D2260/22141 , Y02T50/676
Abstract: One aspect of the disclosure provides for a turbine airfoil. The turbine airfoil may include a trailing edge having: a set of cooling channels having a first cooling channel fluidly connected to a second cooling channel; a first section having a first pin bank cooling arrangement, the first section fluidly connected to the first cooling channel; a second section having a second pin bank cooling arrangement, the second section fluidly connected to the second cooling channel and being radially inward of the first section; and a pressure side panel having a third pin bank cooling arrangement, the pressure side panel fluidly connected to the first cooling channel.
-
公开(公告)号：US20180080458A1
公开(公告)日：2018-03-22
申请号：US15271864
申请日：2016-09-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Marc Edward Blohm , Brendon James Leary
CPC classification number: F02C3/04 , F01D5/141 , F04D29/324 , F04D29/544 , F05D2220/32 , F05D2240/123 , F05D2240/124 , F05D2240/305 , F05D2240/306 , F05D2250/74 , Y02T50/673
Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
-
公开(公告)号：US20170175550A1
公开(公告)日：2017-06-22
申请号：US14978235
申请日：2015-12-22
Applicant: General Electric Company
Inventor： Aaron Ezekiel Smith , Gregory Thomas Foster , Michelle Jessica Iduate , Brendon James Leary , David Wayne Weber
IPC: F01D5/18
CPC classification number: F01D5/187 , F05D2240/304 , F05D2260/201 , F05D2260/203 , F05D2260/22141 , Y02T50/676
Abstract: One aspect of the disclosure provides for a turbine airfoil. The turbine airfoil may include a trailing edge having: a set of cooling channels having a first cooling channel fluidly connected to a second cooling channel; a first section having a first pin bank cooling arrangement, the first section fluidly connected to the first cooling channel; a second section having a second pin bank cooling arrangement, the second section fluidly connected to the second cooling channel and being radially inward of the first section; and a pressure side panel having a third pin bank cooling arrangement, the pressure side panel fluidly connected to the first cooling channel.
-
-
-
-
-
-
-
-
-
Search Results
62
records
(took 0.024 seconds)
