-
公开(公告)号：US20220145764A1
公开(公告)日：2022-05-12
申请号：US17582305
申请日：2022-01-24
Applicant: General Electric Company
Abstract: An apparatus and method relating to a cooling hole of a component of a turbine engine. The cooling hole can extend from an inlet to an outlet to define a connecting passage. The cooling hole can contain a diffusing section. The diffusing section can be defined by an interior surface having variable geometries.
-
公开(公告)号：US11280215B2
公开(公告)日：2022-03-22
申请号：US15522854
申请日：2015-10-28
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 includes a first engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface with at least one cavity. A second engine component is spaced from the cooling surface, and includes at least one cooling aperture. The cooling aperture is arranged such that cooling fluid impinges on the cooling surface at an angle.
-
公开(公告)号：US20210262352A1
公开(公告)日：2021-08-26
申请号：US17314530
申请日：2021-05-07
Applicant: General Electric Company
Inventor： Daniel Endecott Osgood , Tingfan Pang , Gregory Terrence Garay , Zachary Daniel Webster , Ryan Christopher Jones
Abstract: A cast component having reduced cross flow linking cavities and method of casting may include a body. The body may define a plurality of internal flow channels. The plurality of internal flow channels may include a first internal flow channel and a second internal flow channel. The cast component may also include a plurality of linking cavities obstructing unintended fluid communication between the first internal flow channel and the second internal flow channel through the plurality of linking cavities.
-
公开(公告)号：US10968750B2
公开(公告)日：2021-04-06
申请号：US16120758
申请日：2018-09-04
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Zachary Daniel Webster , Gregory Terrence Garay , Xi Yang , Tingfan Pang , Steven Robert Brassfield
IPC: F01D5/18
Abstract: An apparatus and method for cooling a component for a turbine engine which generates a hot gas flow and provides a cooling fluid flow, the component comprising a body having an outer surface, at least a portion of which is exposed to the hot gas flow to define a hot surface, a cooling cavity located within the body and fluidly coupled to the cooling fluid flow and a pin located within the cooling cavity and defining a cooling hole.
-
公开(公告)号：US20210078070A1
公开(公告)日：2021-03-18
申请号：US17108319
申请日：2020-12-01
Applicant: General Electric Company
Inventor： Douglas Ray Smith , Gregory Terrence Garay , Zachary Daniel Webster
Abstract: Aspects of the disclosure generally relate to a casting mold for forming a cast part. The casting mold includes a casting shell having an internal surface bounding an interior, and a casting core positioned within the interior to define a cavity between the casting core and the casting shell, whereby the internal surface of the casting shell defines an outer surface of the cast part.
-
Patent Agency Ranking
公开(公告)号：US10927682B2
公开(公告)日：2021-02-23
申请号：US15814996
申请日：2017-11-16
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Aaron Ezekiel Smith , Fernando Reiter , Zachary Daniel Webster
Abstract: An apparatus and method for a component for a turbine engine, which generates a hot gas flow, and provides a cooling fluid flow, comprising a wall separating the hot gas flow from the cooling fluid flow and having a heated surface along which the hot gas flows and a cooled surface facing the cooling fluid flow and at least one cooling hole comprising a connecting passage extending between an inlet at the cooled surface and an outlet located at the heated surface, with the connecting passage comprising a diffusing section.
-
公开(公告)号：US20210040858A1
公开(公告)日：2021-02-11
申请号：US17082288
申请日：2020-10-28
Applicant: General Electric Company
Inventor： Tingfan Pang , Helen Ogbazion Gabregiorgish , Zachary Daniel Webster , Gregory Terrence Garay , Steven Robert Brassfield , Daniel Endecott Osgood
IPC: F01D5/18
Abstract: An airfoil for a turbine engine can include an outer wall bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip to define a span-wise direction. A plurality of outlets and a plurality of scalloped portions can extend along the outer wall.
-
公开(公告)号：US20200156145A1
公开(公告)日：2020-05-21
申请号：US16195089
申请日：2018-11-19
Applicant: General Electric Company
Inventor： Daniel Endecott Osgood , Tingfan Pang , Gregory Terrence Garay , Zachary Daniel Webster , Ryan Christopher Jones
Abstract: A leachable casting core and method of manufacture may include a plurality of legs configured to establish a plurality of internal flow channels of a cast component. Tie bars, with a first tie bar end and a second tie bar end opposite thereof, may couple to at least two of the plurality of legs. At least one of the tie bars may be oriented to form a linking cavity within the cast component between the internal flow channels. The linking cavity may serve as an obstruction to fluid communication through the linking cavity.
-
公开(公告)号：US20190218917A1
公开(公告)日：2019-07-18
申请号：US15873301
申请日：2018-01-17
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Gregory Terrence Garay , Tingfan Pang , Helen Ogbazion Gabregiorgish , Zachary Daniel Webster , Steven Robert Brassfield
CPC classification number: F01D5/187 , F01D9/02 , F01D25/12 , F01D25/24 , F05D2260/202 , F05D2260/2212
Abstract: An apparatus and method an engine component for a turbine engine comprising an outer wall bounding an interior and defining a pressure side and an opposing suction side, with both sides extending between a leading edge and a trailing edge to define a chord-wise direction, and extending between a root and a tip to define a span-wise direction, at least one cooling passage located within the interior, a set of cooling holes having an inlet fluidly coupled to the cooling passage, an outlet located on one of the pressure side or suction side, with a connecting passage fluidly coupling the inlet to the outlet.
-
公开(公告)号：US10344598B2
公开(公告)日：2019-07-09
申请号：US14958082
申请日：2015-12-03
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Zachary Daniel Webster
Abstract: A component for a gas turbine engine comprises an airfoil having an outer surface. One or more cooling passages can be disposed within the airfoil, having a cooling passage extending along a trailing edge. A plurality of cooling channels can extend from the cooling passage through the trailing edge. At least one flow element and at least one film hole can be disposed in the cooling channel or the trailing edge passage adjacent the cooling channel. The flow element and the film hole can be in a predetermined relationship with one another providing improved flow to the film hole.
-
-
-
-
-
-
-
-
-
Search Results
102
records
(took 0.019 seconds)
