公开(公告)号：US20220307380A1

公开(公告)日：2022-09-29

申请号：US17389945

申请日：2021-07-30

Applicant: General Electric Company ,  General Electric Company Polska Sp. z o.o.

Inventor： Elzbieta Kryj-Kos ,  Piotr Jerzy Kulinski ,  Pawel Adam Lewicki ,  Ruolong Ma ,  Wendy Wenling Lin ,  Patrick Keene Clements

IPC: F01D9/02

Abstract: An airfoil for a gas turbine engine defining a spanwise direction, a root end, a tip end, a leading edge end, and trailing edge end is provided. The airfoil includes: a body extending along the spanwise direction between the root end and the tip end, the body formed of a composite material; and a sculpted leading edge member attached to the body positioned at the leading edge end of the airfoil, the sculped leading edge member formed at least in part of a metal material and defining a non-linear patterned leading edge of the airfoil.

公开(公告)号：US12123324B2

公开(公告)日：2024-10-22

申请号：US18343013

申请日：2023-06-28

Applicant: GENERAL ELECTRIC COMPANY ,  General Electric Company Polska Sp. z o.o.

Inventor： Elzbieta Kryj-Kos ,  Piotr Jerzy Kulinski ,  Pawel Adam Lewicki ,  Ruolong Ma ,  Wendy Wenling Lin ,  Patrick Keene Clements

IPC: F01D9/02

CPC classification number: F01D9/02 ,  F05D2230/31 ,  F05D2240/121 ,  F05D2250/185

Abstract: A method of electroforming an airfoil comprising an airfoil body. The method comprising electroforming a metal edge shell over a filler, located at a leading edge of the airfoil body, and over the airfoil body. The filler can be encapsulated within the metal edge shell and the metal edge shell has a sculpted leading edge defining a non-linear pattern.

公开(公告)号：US20230340885A1

公开(公告)日：2023-10-26

申请号：US18343013

申请日：2023-06-28

Applicant: GENERAL ELECTRIC COMPANY ,  General Electric Company Polska Sp. z o.o.

Inventor： Elzbieta Kryj-Kos ,  Piotr Jerzy Kulinski ,  Pawel Adam Lewicki ,  Ruolong Ma ,  Wendy Wenling Lin ,  Patrick Keene Clements

IPC: F01D9/02

CPC classification number: F01D9/02 ,  F05D2230/31 ,  F05D2240/121 ,  F05D2250/185

Abstract: A method of electroforming an airfoil comprising an airfoil body. The method comprising electroforming a metal edge shell over a filler, located at a leading edge of the airfoil body, and over the airfoil body. The filler can be encapsulated within the metal edge shell and the metal edge shell has a sculpted leading edge defining a non-linear pattern.

公开(公告)号：US11725524B2

公开(公告)日：2023-08-15

申请号：US17389945

申请日：2021-07-30

Applicant: General Electric Company ,  General Electric Company Polska Sp. z o.o.

Inventor： Elzbieta Kryj-Kos ,  Piotr Jerzy Kulinski ,  Pawel Adam Lewicki ,  Ruolong Ma ,  Wendy Wenling Lin ,  Patrick Keene Clements

IPC: F01D9/02

CPC classification number: F01D9/02 ,  F05D2230/31 ,  F05D2240/121 ,  F05D2250/185

Abstract: An airfoil for a gas turbine engine defining a spanwise direction, a root end, a tip end, a leading edge end, and trailing edge end is provided. The airfoil includes: a body extending along the spanwise direction between the root end and the tip end, the body formed of a composite material; and a sculpted leading edge member attached to the body positioned at the leading edge end of the airfoil, the sculped leading edge member formed at least in part of a metal material and defining a non-linear patterned leading edge of the airfoil.

公开(公告)号：US12286903B2

公开(公告)日：2025-04-29

申请号：US18173989

申请日：2023-02-24

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Benjamin Thomas Van Oflen ,  Gary Willard Bryant, Jr. ,  Michael John Franks ,  Elzbieta Kryj-Kos ,  Nicholas Joseph Kray ,  Arthur William Sibbach

IPC: F01D5/30 ,  F01D5/28

Abstract: A turbine engine having a disk and a composite airfoil assembly. The disk having a slot. The composite airfoil assembly having an airfoil portion, a dovetail portion, and a roll snubber. The dovetail portion having a radially inner surface. The roll snubber being provided on the radially inner surface. The radially inner surface spaced from the slot to define a gap therebetween.

公开(公告)号：US12241383B2

公开(公告)日：2025-03-04

申请号：US18173952

申请日：2023-02-24

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Benjamin Thomas Van Oflen ,  Gary Willard Bryant, Jr. ,  Nicholas Joseph Kray ,  Arthur William Sibbach ,  Michael John Franks ,  Elzbieta Kryj-Kos

IPC: F01D11/00 ,  F01D5/14 ,  F01D5/26 ,  F01D5/28 ,  F01D5/32 ,  F01D9/04

Abstract: A turbine engine having a disk, a composite airfoil assembly and a pitch snubber. The disk having a slot. The composite airfoil assembly having an airfoil portion and a dovetail portion. The dovetail portion having a radially inner surface spaced from the slot to define a gap therebetween. The pitch snubber being provided on one of the slot or the radially inner surface of the dovetail portion.

公开(公告)号：US20240352862A1

公开(公告)日：2024-10-24

申请号：US18304784

申请日：2023-04-21

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Nicholas Joseph Kray ,  Tod Winton Davis ,  Nicholas Mark Daggett ,  Arthur William Sibbach ,  Elzbieta Kryj-Kos

IPC: F01D5/30 ,  F01D5/28 ,  F01D5/32

CPC classification number: F01D5/3023 ,  F01D5/282 ,  F01D5/32 ,  F05D2260/37 ,  F05D2300/603

Abstract: An airfoil assembly having a trunnion and a spar. The trunnion having an interior surface defining a flared socket with an open top. The spar extending from the flared socket and through the open top. The spar further having a furcated tail with a set of branches defining an intervening gap between adjacent branches of the set of branches

公开(公告)号：US20250109693A1

公开(公告)日：2025-04-03

申请号：US18480192

申请日：2023-10-03

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Elzbieta Kryj-Kos

IPC: F01D5/28

Abstract: An airfoil assembly and engine component for a turbine engine having an engine core extending along an engine centerline, the airfoil assembly having an airfoil extending between a root and a tip in a radial direction, away from the engine centerline, to define a span length. The airfoil comprising a composite core and a set of skins defining at least a portion of an exterior surface of the airfoil. A shank extending in the radial direction from the root toward the engine centerline and having a flared cross-section.

公开(公告)号：US20240309763A1

公开(公告)日：2024-09-19

申请号：US18182559

申请日：2023-03-13

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Arthur William Sibbach ,  Elzbieta Kryj-Kos ,  Michael John Franks ,  Nicholas Joseph Kray

IPC: F01D5/14 ,  F01D5/28

CPC classification number: F01D5/147 ,  F01D5/288 ,  F05D2220/36 ,  F05D2300/6034

Abstract: A gas turbine engine includes a fan section, a compressor section, combustor section, and turbine section in serial flow arrangement, and defining an engine longitudinal axis. Sets of blades can be rotatably driven about the longitudinal axis in the fan section, the compressor section, and the turbine section. The airfoil structure defining one or more of the blades or vanes can include a structure which includes a woven or foam core, with a laminate skin, and an exterior coating.

公开(公告)号：US20240018683A1

公开(公告)日：2024-01-18

申请号：US18463350

申请日：2023-09-08

Applicant: General Electric Company

Inventor： Sriram Krishnamurthy ,  Lakshmi Krishnan ,  Elzbieta Kryj-Kos ,  Justin M. Welch

IPC: C25D5/56 ,  C25D7/00

CPC classification number: C25D5/56 ,  C25D7/00

Abstract: A method for depositing a metal layer on a component includes applying an electrically conductive coating composition comprising a resin and metal particles on a coating region of the component and partially curing the resin to a gel state to form an electrically conductive coating. The method also includes applying additional metal particles to the partially cured resin in the gel state and depositing, via an electrodeposition process, a metal layer on the electrically conductive coating.