公开(公告)号：US11085303B1

公开(公告)日：2021-08-10

申请号：US16902343

申请日：2020-06-16

Applicant: General Electric Company

Inventor： John McConnell Delvaux ,  Claire Fridtjof Lang ,  Suryarghya Chakrabarti

IPC: F01D5/22 ,  F01D5/16 ,  F01D25/06

Abstract: A blade vibration damping system impacts a pressurized damping fluid on a surface of at least one of a plurality of blades of a turbine in opposition to a vibratory movement thereof to cause damping of vibration of the blade(s) during operation of the turbine. The system includes a fluid injection nozzle in a stationary component adjacent the plurality of blades. A valve selectively admits the pressurized damping fluid to the fluid injection nozzle from a source of pressurized damping fluid, and a control system controls the valve to operate the fluid injection nozzle in response to an operational parameter exceeding a threshold during operation of the turbine. A related turbine casing and method are also provided.

公开(公告)号：US10907484B2

公开(公告)日：2021-02-02

申请号：US16270071

申请日：2019-02-07

Applicant: General Electric Company

Inventor： Matthew Troy Hafner ,  John McConnell Delvaux ,  Thomas Raymond Farrell ,  Markus Feigl

IPC: F01D5/30 ,  F01D5/00

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：US20200217213A1

公开(公告)日：2020-07-09

申请号：US16243154

申请日：2019-01-09

Applicant: General Electric Company

Inventor： Peter de Diego ,  John McConnell Delvaux ,  John Ellington Greene ,  David Randall Hobart ,  James Joseph Murray, III

IPC: F01D9/04 ,  B28B1/00

Abstract: A method of layering ceramic matrix composite (CMC) plies during a build of a component is disclosed. The method may include creating a plurality of CMC plies for creating the component. At least a first plurality of the plurality of the CMC plies each define both an outer portion and an inner portion of the component, each inner portion being defined within the outer portion by one or more openings in the respective CMC ply. The method may also include layering the plurality of CMC plies, and infiltrating the CMC plies with a binder to form the component. In one example, the component can be a turbine nozzle endwall.

公开(公告)号：US10562210B2

公开(公告)日：2020-02-18

申请号：US15465726

申请日：2017-03-22

Applicant: General Electric Company

Inventor： Jason Robert Parolini ,  Matthew Troy Hafner ,  James Joseph Murray ,  Srikanth Chandrudu Kottilingam ,  Canan Uslu Hardwicke ,  John McConnell Delvaux

IPC: B29C70/00 ,  B29C35/02 ,  C04B35/80 ,  B32B18/00 ,  B29C70/54 ,  B29C33/38 ,  C04B35/626 ,  C04B35/628 ,  C04B35/657 ,  F01D5/28 ,  B29L31/00

Abstract: The present disclosure is directed to a method for forming a passage in a composite component. The method includes forming a cavity in a fiber preform. The cavity forms a portion of the passage. The method also includes inserting a core into the cavity and placing one or more fiber plies onto the fiber preform to form a fiber preform assembly. The method further includes thermally processing the fiber preform assembly and densifying the fiber preform assembly to form the composite component. The method also includes removing the core from the composite component.

公开(公告)号：US20180216469A1

公开(公告)日：2018-08-02

申请号：US15420457

申请日：2017-01-31

Applicant: General Electric Company

Inventor： Robert Frank Hoskin ,  Robert Alan Brittingham ,  Brian Denver Potter ,  Daniel Jason Erno ,  John McConnell Delvaux

IPC: F01D5/16 ,  F02C3/04 ,  F01D5/14 ,  F01D5/22

CPC classification number: F01D5/16 ,  B33Y80/00 ,  F01D5/147 ,  F01D5/225 ,  F01D5/26 ,  F05D2240/307 ,  F05D2260/96

Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil having a leading edge, a trailing edge, a root, and a tip. The airfoil defines a chord extending from the leading edge to the trailing edge and a span extending from the root to the tip. A first particle-filled damper is positioned within the airfoil between fifty percent of the chord and one hundred percent of the chord.

公开(公告)号：US09896945B2

公开(公告)日：2018-02-20

申请号：US14088612

申请日：2013-11-25

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Peter de Diego ,  John McConnell Delvaux ,  Glenn Curtis Taxacher

IPC: C04B35/71 ,  F01D5/28 ,  F01D5/08 ,  F01D5/18 ,  C04B35/573 ,  C04B35/65 ,  C04B35/80 ,  F01D5/30

CPC classification number: F01D5/282 ,  C04B35/573 ,  C04B35/65 ,  C04B35/806 ,  F01D5/081 ,  F01D5/18 ,  F01D5/284 ,  F01D5/3007 ,  F05D2300/6033

Abstract: A process of producing a ceramic matrix composite turbine bucket, an insert for a ceramic matrix composite turbine bucket, and a ceramic matrix composite turbine bucket are disclosed. The process includes providing a bucket preform having a dovetail cavity, the dovetail cavity being enclosed within a dovetail shank of the bucket preform, positioning an insert within the dovetail cavity, then forming the ceramic matrix composite turbine bucket in a furnace. The insert includes a geometry configured to be fit within a dovetail cavity of the ceramic matrix composite turbine bucket, a bucket preform, or both. The insert is foam material or a plurality of ceramic matrix composite plies. The ceramic matrix composite turbine bucket includes a dovetail shank and a dovetail cavity enclosed within the dovetail shank. The dovetail cavity is arranged and disposed for receiving an insert.

公开(公告)号：US09745849B2

公开(公告)日：2017-08-29

申请号：US14752186

申请日：2015-06-26

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Canan Uslu Hardwicke ,  John McConnell Delvaux ,  Jason Robert Parolini ,  Matthew Troy Hafner

IPC: B29C65/54 ,  B29C73/14 ,  B32B37/12 ,  B32B38/10 ,  B32B43/00 ,  C09J5/02 ,  C09J5/06 ,  F01D5/14 ,  B29C65/00 ,  B29C65/02 ,  B23P6/00 ,  F01D5/00 ,  F01D5/18 ,  F01D5/28 ,  F01D9/02 ,  F01D25/24 ,  F01D25/30 ,  F02K1/82 ,  B29L31/00 ,  B29C73/04

CPC classification number: F01D5/14 ,  B23P6/005 ,  B28B1/002 ,  B29C65/002 ,  B29C65/02 ,  B29C73/04 ,  B29L2031/7504 ,  C04B37/005 ,  C04B2235/5252 ,  C04B2235/5268 ,  C04B2235/60 ,  C04B2235/606 ,  C04B2237/083 ,  C04B2237/086 ,  C04B2237/78 ,  C04B2237/84 ,  F01D5/005 ,  F01D5/187 ,  F01D5/282 ,  F01D5/284 ,  F01D5/288 ,  F01D9/02 ,  F01D25/246 ,  F01D25/30 ,  F02K1/82 ,  F02K1/822 ,  F02K1/827 ,  F05D2230/40 ,  F05D2230/60 ,  F05D2230/64 ,  F05D2260/36 ,  F05D2300/224 ,  F05D2300/2261 ,  F05D2300/6012 ,  F05D2300/6033 ,  F05D2300/6034 ,  F05D2300/701 ,  Y02T50/675

Abstract: A method for treating a field operated component is disclosed which includes providing the component including a ceramic matrix composite and removing a first portion of the component, forming a first exposed surface on the component. The method further includes providing a second portion including the composite, the second portion having a second exposed surface including a conformation adapted to mate with the first exposed surface. The second portion is positioned in association with the component so as to replace the first portion, and the second portion and the component are joined to form a treated component. Another method is disclosed wherein the component is a turbine component which further includes removing an environmental barrier coating from the component, arranging and conforming the first exposed surface and the second exposed surface to define a joint, and applying an environmental barrier coating to the treated component.

公开(公告)号：US20240110484A1

公开(公告)日：2024-04-04

申请号：US17937851

申请日：2022-10-04

Applicant: General Electric Company

Inventor： James Zhang ,  John McConnell Delvaux ,  Zachary John Snider

IPC: F01D5/16 ,  F01D9/04 ,  F01D25/06

CPC classification number: F01D5/16 ,  F01D9/041 ,  F01D25/06 ,  F05D2220/30 ,  F05D2230/60 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2260/96

Abstract: A vibration damping system includes a vibration damping element for a turbomachine nozzle or blade. A body opening extends through the turbomachine nozzle or blade between the tip end and the base end thereof. A vibration damping element includes a volute spring vibration damping element configured to be installed within the body opening in the turbomachine nozzle or blade. The volute spring vibration damping element includes a spiral coil of a metal sheet strip with a surface of the metal sheet strip contacting itself in a direction of an axis of the coil. The body opening has an inner dimension, and the volute spring vibration damping element has an outer dimension sized to frictionally engage the inner dimension of the body opening to dampen vibration. In certain embodiments, the body opening and the volute spring vibration damping element each have a conical perspective shape.

公开(公告)号：US20240035384A1

公开(公告)日：2024-02-01

申请号：US17815372

申请日：2022-07-27

Applicant: General Electric Company

Inventor： Zachary John Snider ,  Brad Wilson VanTassel ,  Brian Denver Potter ,  John McConnell Delvaux

IPC: F01D25/04 ,  F01D25/06

CPC classification number: F01D25/04 ,  F01D25/06 ,  F05D2220/32 ,  F05D2260/96

Abstract: A vibration dampening system includes a vibration dampening element for a turbine nozzle or blade. A body opening extends through the turbine nozzle or blade, e.g., through the airfoil among potentially other parts of the nozzle or blade. A vibration dampening element includes a plurality of stacked damper pins within the body opening. The damper pins include an outer body having an inner opening, a first end surface and an opposing second end surface; and an inner body nested and movable within the inner opening of the outer body. The end surfaces frictionally engage to dampen vibration. The inner body has a first central opening including a first portion configured to engage an elongated body therein and an outer surface configured to frictionally engage a portion of the inner opening of the outer body to dampen vibration.

公开(公告)号：US11536144B2

公开(公告)日：2022-12-27

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.