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.

公开(公告)号：US20240068373A1

公开(公告)日：2024-02-29

申请号：US18146511

申请日：2022-12-27

Applicant: General Electric Company

Inventor： Abrhijeet Jayshingrao Yadav ,  Nicholas Joseph Kray ,  Nitesh Jain ,  Ricardo Hernandez Pandeli

IPC: B64C11/32 ,  B64C11/06

CPC classification number: B64C11/32 ,  B64C11/06

Abstract: A gas turbine engine including: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order; a fan defining a fan axis and comprising a plurality of fan blades rotatable about the fan axis; and a pitch change mechanism operable with the plurality of fan blades, the pitch change mechanism including a plurality of linkages, the plurality of linkages including a first linkage coupled to a first fan blade of the plurality of fan blades and a second linkage coupled to a second fan blade of the plurality of fan blades; and a non-uniform blade actuator system operable with one or more of the plurality of linkages to control a pitch of the first fan blade relative to a pitch of the second fan blade.

公开(公告)号：US11879354B2

公开(公告)日：2024-01-23

申请号：US17488836

申请日：2021-09-29

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Nitesh Jain

IPC: F01D5/14 ,  F02K3/06 ,  F01D21/04

CPC classification number: F01D5/147 ,  F02K3/06 ,  F05D2220/323 ,  F05D2240/301 ,  F05D2300/50 ,  F05D2300/60

Abstract: A rotor blade for a gas turbine engine is provided. The rotor blade includes a blade body formed of a first material; and a spar within a portion of the blade body, the spar formed of a second material that is different than the first material, the spar having an elongate body including a notch. The notch, weakened geometric feature, or other reduction in cross-section defines a frangible portion of the spar that is used to control a fracture of a rotor blade.

公开(公告)号：US11821319B2

公开(公告)日：2023-11-21

申请号：US17490401

申请日：2021-09-30

Applicant: General Electric Company

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

IPC: F01D5/14 ,  F03G7/06

CPC classification number: F01D5/148 ,  F03G7/0614 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2240/307

Abstract: An airfoil including a plurality of composite plies extending from a leading edge to a trailing edge and between a tip and a root. The airfoil further includes a frangible airfoil portion at the tip extending between the leading edge and the trailing edge and extending between the tip and a frangible line along a span. The frangible airfoil portion including a plurality of composite plies and one or more shape memory alloy inserts disposed between the plurality of composite plies. A gas turbine engine including a frangible airfoil and methods for forming a frangible airfoil are also disclosed.

公开(公告)号：US11719103B1

公开(公告)日：2023-08-08

申请号：US17715360

申请日：2022-04-07

Applicant: General Electric Company

Inventor： Abhijit Roy ,  Nicholas Joseph Kray

IPC: F01D5/28 ,  B32B5/26 ,  B32B5/02 ,  B29C70/08 ,  F01D5/14 ,  B29C70/34

CPC classification number: F01D5/282 ,  B29C70/081 ,  B32B5/02 ,  B32B5/26 ,  F01D5/147 ,  B29C70/342 ,  B32B2250/20 ,  B32B2250/40 ,  B32B2260/023 ,  B32B2260/046 ,  B32B2262/0261 ,  B32B2262/101 ,  B32B2262/103 ,  B32B2262/105 ,  B32B2262/106 ,  B32B2262/16 ,  B32B2603/00 ,  F05D2220/32 ,  F05D2230/20 ,  F05D2300/6034

Abstract: Composite components, such as gas turbine engine airfoils, and methods of forming composite components are provided. For example, a composite component of a gas turbine engine comprises a plurality of continuous fiber layers, each continuous fiber layer formed from a plurality of continuous fibers disposed in a matrix material, and a chopped fiber layer comprising a plurality of chopped fibers formed as a filmed sheet. The chopped fiber layer is laid up with the plurality of continuous fiber layers to form the composite component. A method for forming a composite component comprises laying up a plurality of continuous fiber layers, each continuous fiber layer comprising continuous fibers disposed in a matrix material; laying up a chopped fiber layer with the plurality of continuous fiber layers, the layup of the plurality of continuous fiber layers and the chopped fiber layer forming a reinforced layup; and curing the reinforced layup.

公开(公告)号：US11702940B2

公开(公告)日：2023-07-18

申请号：US17844578

申请日：2022-06-20

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Viswanadha Gupta Sakala ,  Nicholas Joseph Kray ,  Ambika Shivamurthy ,  Kirti Arvind Petkar

IPC: F01D5/02 ,  F01D5/14 ,  G06F30/17

CPC classification number: F01D5/147 ,  F01D5/02 ,  G06F30/17 ,  F05D2220/32 ,  F05D2230/80 ,  F05D2240/24

Abstract: Methods, apparatus, systems and articles of manufacture corresponding to a fan blade with intrinsic damping characteristics are disclosed. An example fan blade comprises an exterior body including a first side and a second side; a first hairpin structure in contact with (a) the first side of the exterior body and (b) the second side of the exterior body; and a second hairpin structure in contact with (a) the first side and (b) the second side, wherein the first hairpin structure and the second hairpin structure are made from different materials.