公开(公告)号：US12234745B1

公开(公告)日：2025-02-25

申请号：US18386867

申请日：2023-11-03

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Nicholas Joseph Kray ,  Daniel E. Mollmann ,  Elzbieta Kryj-Kos ,  Arthur William Sibbach ,  Brent Michael Push

IPC: F01D5/30 ,  F01D7/00

Abstract: An airfoil assembly for a turbine engine, the airfoil assembly including a platform defining an inner surface and an outer surface, a variable pitch airfoil extending radially from the outer surface of the platform from a root to a tip to define a span length and a mounting structure connected to the platform.

公开(公告)号：US12228037B1

公开(公告)日：2025-02-18

申请号：US18527567

申请日：2023-12-04

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Brandon Wayne Miller ,  Gary Willard Bryant, Jr. ,  Arthur William Sibbach

IPC: F01D17/16 ,  F01D9/04

Abstract: A guide vane assembly for a nacelle of a gas turbine engine includes a forward vane and an aft vane. The aft vane is located aft of the forward vane and forward of a plurality of fan blades. The forward vane defines a fixed pitch angle and the aft vane is movable between a first pitch angle and a second pitch angle.

公开(公告)号：US20250052172A1

公开(公告)日：2025-02-13

申请号：US18366800

申请日：2023-08-08

Applicant: General Electric Company

Inventor： Abhijeet Jayshingrao Yadav ,  Nicholas Joseph Kray ,  Nitesh Jain

IPC: F01D17/00 ,  F04D29/18 ,  F04D29/20

Abstract: A fan assembly for an engine has a fan blade, a disk having a disk segment, a trunnion mechanism having a trunnion extending at least partially through the disk segment, and first and second attachment systems. The trunnion has a platform and a shaft. The fan blade is adjacent to the platform of the trunnion. The trunnion is attached to the disk segment using the first attachment system along a preload path. The first and second attachment systems further include first and second retention features, respectively, separate from the preload path. During normal operation of the fan assembly, the first attachment system retains the trunnion within the disk along a first load path. Upon a failure in the trunnion, the first and second retention features together retain the trunnion within the disk segment along a second load path, the first load path being different than the second load path.

公开(公告)号：US20240417063A1

公开(公告)日：2024-12-19

申请号：US18333743

申请日：2023-06-13

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Elzbieta Kryj-Kos ,  Nicholas Joseph Kray ,  Tod Winton Davis ,  Gary Willard Bryant, JR.

IPC: B64C11/26 ,  F01D5/28

Abstract: A composite airfoil assembly for a gas turbine engine. The composite airfoil assembly includes a composite airfoil defined by a core and a skin. The composite airfoil assembly further includes cladding. The core defines a core exterior, where the skin is applied to at least a portion of the core exterior. The cladding is prepared before being coupled or adhered to the composite airfoil.

公开(公告)号：US20240401486A1

公开(公告)日：2024-12-05

申请号：US18328856

申请日：2023-06-05

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Nicholas Joseph Kray ,  Tod Winton Davis ,  Elzbieta Kryj-Kos ,  Michael John Franks

IPC: F01D5/28 ,  F02C3/04

Abstract: A composite airfoil assembly for a gas turbine engine, the composite airfoil assembly comprising a composite airfoil, a first cladding, and a second cladding. The composite airfoil having a core comprising a composite structure having a core bulk modulus and a laminate skin applied to at least a portion of an exterior of the core. The first cladding and the second cladding are coupled to an outer surface of the composite airfoil.

公开(公告)号：US20240376828A1

公开(公告)日：2024-11-14

申请号：US18314499

申请日：2023-05-09

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Nicholas Joseph Kray ,  Elzbieta Kryj-Kos

IPC: F01D5/28

Abstract: A composite airfoil with an airfoil core and a wall surrounding the airfoil core. The wall including a first set of stacked plies including a first type of ply having directional fibers extending in a first direction, and defining at least a portion of an exterior surface, the exterior surface extending between a leading edge and a trailing edge to define a chordwise direction and between a root and a tip to define a spanwise direction. At least one stiffener located between the airfoil core and the wall, the at least one stiffener having a second set of stacked plies.

公开(公告)号：US12123321B2

公开(公告)日：2024-10-22

申请号：US18088990

申请日：2022-12-27

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Nicholas Joseph Kray ,  Michael John Franks

IPC: F01D5/28 ,  F01D5/14 ,  F01D5/30

CPC classification number: F01D5/282 ,  F01D5/147 ,  F01D5/30 ,  F05D2300/6034

Abstract: A composite blade assembly for a turbine engine, the composite blade assembly having a core and a laminate skin. The core having a composite structure. The laminate skin having at least one composite ply. The laminate skin having a first portion forming a first angle relative to a horizontal plane, and a second portion forming a second angle relative to the horizontal plane.

公开(公告)号：US20240287911A1

公开(公告)日：2024-08-29

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

CPC classification number: F01D5/3007 ,  F01D5/282 ,  F05D2220/32 ,  F05D2240/24 ,  F05D2240/30

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：US11988103B2

公开(公告)日：2024-05-21

申请号：US17511866

申请日：2021-10-27

Applicant: General Electric Company

Inventor： Li Zheng ,  Nicholas Joseph Kray ,  Changjie Sun

IPC: F01D5/14 ,  F01D5/28 ,  F01D25/00

CPC classification number: F01D25/005 ,  F01D5/14 ,  F01D5/28 ,  F05D2220/32 ,  F05D2230/60

Abstract: An airfoil for a fan section of a turbine engine may include a fan blade or an outlet guide vane formed of a first material, and an edge guard disposed about an edge of the fan blade. The edge guard may include a matrix composite that has a toughness that is greater than a toughness of the first material. The airfoil may include a fan blade or an outlet guide vane. The first material of the airfoil may include a metal alloy and/or a matrix composite. A method of manufacturing an airfoil for a fan section of a turbine engine may include manufacturing an edge guard, attaching the edge guard to the airfoil.

公开(公告)号：US11982205B1

公开(公告)日：2024-05-14

申请号：US18171490

申请日：2023-02-20

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Nitesh Jain ,  Abhijeet Jayshingrao Yadav ,  Balaraju Suresh ,  Nicholas Joseph Kray

IPC: F01D5/14 ,  F01D5/28 ,  F01D9/02 ,  F01D9/04 ,  F01D25/24

CPC classification number: F01D5/147 ,  F01D5/282 ,  F01D9/02 ,  F01D9/04 ,  F01D9/041 ,  F01D9/042 ,  F01D25/243 ,  F01D25/246 ,  F05D2220/323 ,  F05D2300/603

Abstract: An airfoil for a turbine engine having a spar assembly. The spar assembly including a composite spar, a metallic hub, and a composite body. The metallic hub can receive a portion of the composite spar at an interior surface to define an overlapping region. The composite body is located at the overlapping region.