-
公开(公告)号：US20190218925A1
公开(公告)日：2019-07-18
申请号：US15874337
申请日：2018-01-18
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Gregory Terrence Garay , Aaron Ezekiel Smith , Daniel Lee Durstock
CPC classification number: F01D9/065 , F01D25/12 , F01D25/14 , F05D2220/3215 , F05D2240/10 , F05D2260/201
Abstract: A shroud for a turbine engine includes a body having a first surface with an inlet fluidly coupled to a cooling fluid flow, and a second surface facing a heated fluid flow. A cavity within the body can be fluidly coupled to the inlet and include an impingement zone thermally coupled to the second surface.
-
公开(公告)号：US20190186272A1
公开(公告)日：2019-06-20
申请号：US15844684
申请日：2017-12-18
Applicant: GENERAL ELECTRIC COMPANY
CPC classification number: F01D5/186 , F01D5/141 , F05D2260/202 , F23R3/002
Abstract: An apparatus and method an airfoil for a turbine engine, the airfoil comprising an outer wall defining an interior bound by a pressure side and a suction side extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction. The airfoil further includes at least one cooling hole including a diffusing section and fluidly coupling an exterior of the engine component to an exterior of the engine component.
-
公开(公告)号：US20190145267A1
公开(公告)日：2019-05-16
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：US20190071977A1
公开(公告)日：2019-03-07
申请号：US15697916
申请日：2017-09-07
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：US20190003314A1
公开(公告)日：2019-01-03
申请号：US16122536
申请日：2018-09-05
Applicant: General Electric Company
Inventor： Aaron Ezekiel Smith , Metodi Blagoev Zlatinov , Thomas Earl Dyson
IPC: F01D5/18
Abstract: A component is provided and comprises at least one wall comprising a first and a second surface. At least one film cooling hole extends through the wall between the first and second surfaces and has an outlet region at the second surface. The film cooling hole includes a first expansion section being a side diffusion portion and a second expansion section being a layback diffusion portion, wherein the side diffusion portion is upstream and spaced from the layback diffusion portion.
-
Patent Agency Ranking
公开(公告)号：US20180347374A1
公开(公告)日：2018-12-06
申请号：US15609430
申请日：2017-05-31
Applicant: General Electric Company
Inventor： Matthew Thomas Beyer , Gregory Terrence Garay , Aaron Ezekiel Smith
IPC: F01D5/18
Abstract: An apparatus and method for cooling an airfoil tip for a turbine engine can include an airfoil, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the airfoil at the tip. A plurality of cooling holes can be provided in the tip rail. A flow of cooling fluid can be provided through the cooling holes from the interior of the airfoil to cool the tip of the airfoil.
-
公开(公告)号：US20180328192A1
公开(公告)日：2018-11-15
申请号：US16046066
申请日：2018-07-26
Applicant: General Electric Company
Inventor： Aaron Ezekiel Smith , Gregory Thomas Foster
CPC classification number: F01D5/187 , F01D5/186 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2240/35 , F05D2240/81 , F05D2250/185 , F05D2260/201 , F05D2260/202 , F05D2260/204 , Y02T50/676
Abstract: A cooling system according to an embodiment includes: a leading edge cooling circuit including a pressure side serpentine circuit and a suction side serpentine circuit; a first mid-blade cooling circuit including a suction side serpentine circuit; a second mid-blade cooling circuit including a pressure side serpentine circuit; a trailing edge cooling circuit; and at least one air feed for supplying cooling air to the leading edge cooling circuit, the first mid-blade cooling circuit, the second mid-blade cooling circuit, and the trailing edge cooling circuit.
-
公开(公告)号：US10088164B2
公开(公告)日：2018-10-02
申请号：US14631929
申请日：2015-02-26
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Jason Randolph Allen , Robert Charles Groves, II , Aaron Ezekiel Smith
Abstract: A hot gas path component for an engine may generally include a substrate extending between an outer surface and an inner surface opposite the outer surface. The outer surface may be configured to be exposed to a hot gas path of the engine. In addition, the substrate may be formed from a non-metallic composite material. The hot gas path component may also include a thermal coating disposed on the inner surface of the substrate. The thermal coating may be applied to the inner surface so as to have a non-uniform distribution along at least a portion of the inner surface, wherein the non-uniform distribution provides for change in a thermal gradient experienced across the hot gas path component between the outer and inner surfaces of the substrate.
-
公开(公告)号：US09995149B2
公开(公告)日：2018-06-12
申请号：US14143443
申请日：2013-12-30
Applicant: General Electric Company
IPC: F01D5/18
CPC classification number: F01D5/187 , F01D5/188 , F05D2240/305 , F05D2240/306 , F05D2250/71 , F05D2250/711 , F05D2250/712 , F05D2250/713 , F05D2250/75 , F05D2260/22141 , Y02T50/676
Abstract: A turbine blade having an airfoil defined by a concave shaped pressure side outer wall and a convex shaped suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant. The turbine blade may further include a rib configuration that partitions the chamber into radially extending flow passages. The rib configuration may include a camber line rib having a wavy profile. The wavy profile may include at least one back-and-forth “S” shape.
-
公开(公告)号：US20180142559A1
公开(公告)日：2018-05-24
申请号：US15360529
申请日：2016-11-23
Applicant: General Electric Company
CPC classification number: F01D5/187 , F01D5/20 , F01D5/3007 , F05D2220/32 , F05D2240/307 , F05D2250/25 , F05D2250/70 , F05D2260/202 , F05D2260/203 , F05D2260/204
Abstract: A tip cooling apparatus for a turbine airfoil includes: a tip cap; a pair of spaced-apart tip walls connected to, extending around, and projecting outwardly from the tip cap so as to surround a central portion of the tip cap; a pocket defined by the tip walls; at least one feed hole passing through the tip cap or tip walls, communicating with the pocket; and a cooling matrix disposed in the pocket, the cooling matrix being an organized structure including an inlet surface having a plurality of inlets communicating with the pocket, and an outlet surface having a plurality of outlets, and further comprising a plurality of interior passages interconnecting the inlets to the outlets, with no line-of-sight therebetween.
-
-
-
-
-
-
-
-
-
Search Results
107
records
(took 0.025 seconds)
