-
公开(公告)号：US11480061B2
公开(公告)日：2022-10-25
申请号：US17151799
申请日：2021-01-19
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , John McConnell Delvaux , Thomas Raymond Farrell , Markus Feigl
Abstract: A method may include: in a used metal turbomachine blade including a root including a shank, a platform coupled to the shank and an airfoil coupled to the platform, removing the airfoil, leaving a remaining base including the platform, the shank and the root. The method may also form a radially extending opening through the platform into the shank, and insert a ceramic shank nub extending from a ceramic airfoil into the radially extending opening of the remaining base. The ceramic airfoil is fixedly attached to the remaining base. The method allows reuse of the metal shank while providing the lower cooling requirements of a ceramic airfoil.
-
公开(公告)号：US20220098989A1
公开(公告)日：2022-03-31
申请号：US17038601
申请日：2020-09-30
Applicant: General Electric Company
Inventor： Suryarghya Chakrabarti , Jing Li , John McConnell Delvaux
IPC: F01D5/22
Abstract: A rotor blade assembly includes a first rotor blade and a second rotor blade positioned adjacent to one another. The first rotor blade and the second rotor blade each include a platform and an airfoil extending radially outward from a root coupled to the platform to a tip. The airfoil includes a part-span shroud. The part-span shroud extends from the airfoil and is disposed between the root and the tip. The part-span shroud includes a pressure side portion extending from the pressure side surface and a suction side portion extending from the suction side surface. A damper is in contact with both the part span shroud of the first rotor blade and the part span shroud of the second rotor blade at an interference joint. The damper is movable relative to the part span shroud of both the first rotor blade and the second rotor blade.
-
公开(公告)号：US11242756B2
公开(公告)日：2022-02-08
申请号：US16865999
申请日：2020-05-04
Applicant: General Electric Company
Inventor： James Zhang , John McConnell Delvaux
Abstract: A coating is applied to a base material. The coating comprises a viscoelastic layer having a surface in which cavities are formed; and a constraint layer. The viscoelastic layer is disposed on the base material, and the constraint layer is disposed on, and partially bonded, at an interface, to the viscoelastic layer over the surface in which the cavities are formed. The cavities are filled with particles configured for vibration and frictional interaction at the partially bonded interface between the partially bonded viscoelastic layer and the constraint layer. A turbine blade having an airfoil with the subject coating is also provided.
-
公开(公告)号：US11179917B2
公开(公告)日：2021-11-23
申请号：US15401575
申请日：2017-01-09
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Matthew Troy Hafner , John McConnell Delvaux , Glenn Curtis Taxacher , Zachary John Snider
Abstract: A CMC ply assembly is disclosed including at least one matrix ply interspersed amongst a plurality of CMC plies. Each of the plurality of CMC plies includes a first matrix and a plurality of ceramic fibers. The at least one matrix ply includes a second matrix and is essentially free of ceramic fibers. The plurality of CMC plies and the at least one matrix ply are arranged in an undensified ply stack having an article conformation. A CMC article is disclosed including a plurality of densified CMC plies and at least one densified matrix ply interspersed amongst the plurality of densified CMC plies. A method for forming the CMC article is disclosed including forming, carburizing, infusing a melt infiltration agent into, and densifying the CMC ply assembly. The melt infiltration agent infuses more completely through the at least one matrix ply than through the plurality of CMC plies.
-
公开(公告)号：US10822955B2
公开(公告)日：2020-11-03
申请号：US16235114
申请日：2018-12-28
Applicant: General Electric Company
Inventor： John McConnell Delvaux , Markus Feigl , Matthew Troy Hafner , Michael Anthony Wondrasek , James Zhang , Peter de Diego
Abstract: A gas turbine that includes a rotor blade that includes an airfoil. The airfoil may include non-integral base and top portions. The airfoil may include a pin connector connecting the top portion to the base portion. The pin connector may include: a tab extending from the top portion; a complimentary slot for receiving the tab formed in the base portion; an elongated pin cavity formed through an interior region of the airfoil, where the pin cavity intersects the slot to divide the pin cavity into first and second pin cavity segments; a tab aperture formed through the tab, where the tab aperture is positioned so align with the pin cavity upon the tab being received within the slot; and a locking pin that extends continuously through the first segment of the pin cavity, the tab aperture, and the second segment of the pin cavity.
-
Patent Agency Ranking
公开(公告)号：US10808575B2
公开(公告)日：2020-10-20
申请号：US15624070
申请日：2017-06-15
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Glenn Curtis Taxacher , John McConnell Delvaux , Matthew Troy Hafner
Abstract: A turbine component assembly is disclosed, including a first component, a second component, and a circumferentially oriented flat spring. The first component is arranged to be disposed adjacent to a hot gas path, and includes a ceramic matrix composite composition. The second component is adjacent to the first component and arranged to be disposed distal from the hot gas path across the first component. The circumferentially oriented flat spring is disposed on and directly contacting the second component and directly contacting and supporting the first component as a compliant contact interface between the first component and the second component. The circumferentially oriented flat spring provides a radial spring compliance between the first component and the second component.
-
公开(公告)号：US10605100B2
公开(公告)日：2020-03-31
申请号：US15604074
申请日：2017-05-24
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Jacob John Kittleson , John McConnell Delvaux
Abstract: A ceramic matrix composite (CMC) turbine blade assembly includes a rotor, a CMC turbine blade, and at least one dovetail sleeve. The rotor has a blade slot with at least one slot surface. The slot surface is at a slot angle. The CMC turbine blade is received in the blade slot. The CMC turbine blade includes a dovetail root having at least one root surface. The root surface is at a root angle. The root angle is at least 5 degrees greater than the slot angle. The dovetail sleeve is received in the blade slot of the rotor. The dovetail sleeve has at least one inner surface contacting at least one root surface and at least one outer surface contacting at least one slot surface to radially retain the CMC turbine blade in the blade slot. A dovetail sleeve and a method of mounting a CMC turbine blade are also disclosed.
-
公开(公告)号：US10550721B2
公开(公告)日：2020-02-04
申请号：US15080201
申请日：2016-03-24
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Matthew Troy Hafner , Gary Michael Itzel , John McConnell Delvaux , Sandip Dutta
Abstract: An apparatus is disclosed including a first and second article, a first interface volume disposed between and enclosed by the first article and second article, a cooling fluid supply, and at least one cooling fluid channel in fluid communication with the cooling fluid supply and the first interface volume. The first article includes a first material composition. The second article includes a second material composition. The at least one cooling fluid channel includes a heat exchange portion disposed in at least one of the first and second article downstream of the cooling fluid supply and upstream of the first interface volume. A turbine shroud is disclosed wherein the first and second articles are an outer and inner shroud. A turbine nozzle is disclosed wherein the first and second articles are an endwall and fairing.
-
公开(公告)号：US09297265B2
公开(公告)日：2016-03-29
申请号：US13693350
申请日：2012-12-04
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Ronald Ralph Cairo , Jason Robert Parolini , John McConnell Delvaux
CPC classification number: F01D5/282 , F01D5/02 , F01D5/147 , F01D5/284 , F01D5/3007 , F01D5/3084 , F01D5/3092 , F05D2220/32 , F05D2240/24 , F05D2250/711 , F05D2250/712 , F05D2300/6033 , Y02T50/672
Abstract: An apparatus having reduced wear and friction between CMC-to-metal attachment and interface of the apparatus, including a CMC component having a surface. The CMC component surface is configured for sliding contact with a surface of a metal component, the sliding contact resulting in formation of debris along the contacting surfaces. The surface of the CMC component has an engineered surface feature formed therein to substantially prevent an accumulation of debris along the contacting surfaces.
-
30.发明授权公开(公告)号：US11519276B1
公开(公告)日：2022-12-06
申请号：US17574092
申请日：2022-01-12
Applicant: General Electric Company
Inventor： Zachary John Snider , John McConnell Delvaux
IPC: F01D5/16
Abstract: A vibration damping element for a vibration damping system for a turbine nozzle or blade includes an elongated body and a wire mesh member that surrounds the elongated body. The wire mesh member has a first outer dimension in an inoperative state and a second, larger outer dimension in an operative state. In the operative state, the wire mesh member frictionally engages with an inner surface of a body opening in the turbine nozzle or blade to damp vibration. In the inoperative state, the wire mesh member slides freely in the body opening in the turbine nozzle or blade. A retention system includes a retention member on the elongated body that fixes the wire mesh member relative to a length of the elongated body in the operative state in the body opening of the turbine nozzle or blade.
-
-
-
-
-
-
-
-
-
Search Results
60
records
(took 0.016 seconds)
