-
公开(公告)号：US10815789B2
公开(公告)日：2020-10-27
申请号：US15043512
申请日：2016-02-13
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Jason Randolph Allen
Abstract: An apparatus for an impingement hole for an engine component of a gas turbine engine includes an impingement baffle. The impingement baffle is spaced from an impingement surface and includes a plurality of impingement holes for providing an impingement flow to the impingement surface. The impingement holes can have an angled upstream edge such that an inlet has a greater cross-sectional area than an outlet. The walls of the impingement holes can have a hood to provide a higher shear flow content to minimize dust accumulation on the impingement surface.
-
公开(公告)号：US20190127283A1
公开(公告)日：2019-05-02
申请号：US15799709
申请日：2017-10-31
Applicant: General Electric Company
Inventor： Carlos Bonilla Gonzalez , Eric John Ruggiero , Jason Randolph Allen
IPC: C04B35/638 , B22C3/00 , F01D5/18 , F01D5/22 , F01D5/34
CPC classification number: C04B35/638 , B22C3/00 , B33Y10/00 , B33Y80/00 , F01D5/187 , F01D5/225 , F01D5/34 , F01D9/04 , F05D2220/32 , F05D2230/21 , F05D2230/30 , F05D2240/11 , F05D2260/204
Abstract: A turbine system includes a turbine shroud segment. The turbine shroud segment includes a backside, a flow path surface opposite to the back side and configured to be disposed adjacent a hot gas path of the turbine system, and side walls extending between the backside of the turbine shroud segment and the flow path surface of the turbine shroud segment. The turbine shroud segment also includes cooling channels disposed in a thickness of the turbine shroud segment between the backside and the flow path surface, where each cooling channel includes an outlet at one of the side walls of the turbine shroud segment.
-
公开(公告)号：US20170191417A1
公开(公告)日：2017-07-06
申请号：US14989290
申请日：2016-01-06
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Robert Frederick Bergholz , Jason Randolph Allen , Robert David Briggs , Byron Andrew Pritchard, JR. , Kevin Robert Feldmann , Curtis Walton Stover , Zachary Daniel Webster , Fernando Reiter , Michael Alan Meade
CPC classification number: F01D5/187 , F01D9/065 , F01D25/12 , F05D2240/11 , F05D2250/21 , F05D2250/22 , F05D2250/23 , F05D2250/232 , F05D2250/241 , F05D2250/27 , F05D2260/201 , F05D2260/2214 , F23R3/005 , F23R2900/03044 , F23R2900/03045 , Y02T50/672 , Y02T50/676
Abstract: An engine component assembly includes a first engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface, and a second engine component having a first surface in fluid communication with a cooling fluid flow and a second surface spaced from the cooling surface to define a space. A cooling aperture extends through the second engine component. A cooling feature extends from the cooling surface of the first engine component, and is oriented relative to the cooling aperture such that the cooling fluid flow is orthogonal and non-orthogonal to different portions of the cooling feature.
-
公开(公告)号：US20220170383A1
公开(公告)日：2022-06-02
申请号：US17673426
申请日：2022-02-16
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Robert Frederick Bergholz , Jason Randolph Allen , Robert David Briggs , Kevin Robert Feldmann , Curtis Walton Stover , Zachary Daniel Webster , Fernando Reiter
IPC: F01D25/12 , F23R3/00 , F01D5/18 , F23R3/06 , F01D9/04 , F01D11/08 , F02C3/04 , F02C7/18 , F23R3/04
Abstract: An engine component assembly with a first substrate having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface, with the cooling surface being different than the hot surface, a second substrate having a first surface in fluid communication with a cooling fluid supply and a second surface, different from the first surface, facing and spaced from the cooling surface to define at least one interior cavity. At least one cavity is provided within the first substrate defining a cavity surface where at least a portion of the cavity surface is directly opposite the second surface. At least one cooling aperture extending through the second substrate from the first surface to the second surface, and defining a streamline along which a cooling fluid passes from the cooling fluid supply to the at least one interior cavity.
-
公开(公告)号：US20170234139A1
公开(公告)日：2017-08-17
申请号：US15043512
申请日：2016-02-13
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Jason Randolph Allen
Abstract: An apparatus for an impingement hole for an engine component of a gas turbine engine includes an impingement baffle. The impingement baffle is spaced from an impingement surface and includes a plurality of impingement holes for providing an impingement flow to the impingement surface. The impingement holes can have an angled upstream edge such that an inlet has a greater cross-sectional area than an outlet. The walls of the impingement holes can have a hood to provide a higher shear flow content to minimize dust accumulation on the impingement surface.
-
Patent Agency Ranking
公开(公告)号：US10458259B2
公开(公告)日：2019-10-29
申请号：US15152887
申请日：2016-05-12
Applicant: General Electric Company
Inventor： Jason Randolph Allen , Ronald Scott Bunker
Abstract: An apparatus and method for flowing cooling air through an outer wall of an engine component such as an airfoil. The airfoil having the outer wall can include an opening. A framework can be disposed in the opening adapted to reduce the required flow through the opening to increase the efficiency of the engine and improve cooling.
-
公开(公告)号：US20170328221A1
公开(公告)日：2017-11-16
申请号：US15152887
申请日：2016-05-12
Applicant: General Electric Company
Inventor： Jason Randolph Allen , Ronald Scott Bunker
Abstract: An apparatus and method for flowing cooling air through an outer wall of an engine component such as an airfoil. The airfoil having the outer wall can include an opening. A framework can be disposed in the opening adapted to reduce the required flow through the opening to increase the efficiency of the engine and improve cooling.
-
公开(公告)号：US20170234140A1
公开(公告)日：2017-08-17
申请号：US15043513
申请日：2016-02-13
Applicant: General Electric Company
CPC classification number: F01D5/187 , F01D5/188 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2240/30 , F05D2250/185 , F05D2260/2212 , F05D2260/607 , Y02T50/676
Abstract: A method and apparatus for an airfoil in a gas turbine engine can include an outer surface bounding an interior. At least one flow channel can be defined among one or more full-length and partial-length ribs to further define a cooling circuit within the airfoil. The cooling circuit can have at least one tip turn at the partial-length rib, having at least on fastback turbulator disposed at least partially within the tip turn.
-
公开(公告)号：US10450874B2
公开(公告)日：2019-10-22
申请号：US15043513
申请日：2016-02-13
Applicant: General Electric Company
Abstract: A method and apparatus for an airfoil in a gas turbine engine can include an outer surface bounding an interior. At least one flow channel can be defined among one or more full-length and partial-length ribs to further define a cooling circuit within the airfoil. The cooling circuit can have at least one tip turn at the partial-length rib, having at least on fastback turbulator disposed at least partially within the tip turn.
-
公开(公告)号：US10370300B2
公开(公告)日：2019-08-06
申请号：US15799709
申请日：2017-10-31
Applicant: General Electric Company
Inventor： Carlos Bonilla Gonzalez , Eric John Ruggiero , Jason Randolph Allen
Abstract: A turbine system includes a turbine shroud segment. The turbine shroud segment includes a backside, a flow path surface opposite to the back side and configured to be disposed adjacent a hot gas path of the turbine system, and side walls extending between the backside of the turbine shroud segment and the flow path surface of the turbine shroud segment. The turbine shroud segment also includes cooling channels disposed in a thickness of the turbine shroud segment between the backside and the flow path surface, where each cooling channel includes an outlet at one of the side walls of the turbine shroud segment.
-
-
-
-
-
-
-
-
-
Search Results
18
records
(took 0.014 seconds)
