公开(公告)号：US11867082B2

公开(公告)日：2024-01-09

申请号：US17236236

申请日：2021-04-21

Applicant: General Electric Company

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

IPC: F01D5/14 ,  F01D5/02 ,  F01D5/28

CPC classification number: F01D5/147 ,  F01D5/02 ,  F01D5/28 ,  F05D2220/32 ,  F05D2230/80 ,  F05D2240/307 ,  F05D2300/17

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 tip component removably connected to the blade body, the tip component formed of a second material that is different than the first material.

公开(公告)号：US11814174B2

公开(公告)日：2023-11-14

申请号：US17071379

申请日：2020-10-15

Applicant: General Electric Company

Inventor： David William Crall ,  Nicholas Joseph Kray ,  Douglas Duane Ward ,  Brandon Wayne Miller

IPC: F01D9/04 ,  F01D5/30 ,  F01D5/14 ,  F01D5/18 ,  F01D7/00 ,  F01D15/10 ,  F01D15/12 ,  F02K5/00 ,  F02K3/06 ,  F02C6/20 ,  F02C9/00 ,  F02C9/22 ,  F02C7/26 ,  F02C7/32 ,  F02C7/36 ,  F02C3/113 ,  B32B7/022 ,  B64C1/38 ,  B64D45/00 ,  F01D17/16 ,  F01D25/12 ,  F02C7/264 ,  F02K1/66 ,  F02K1/76

CPC classification number: B64D45/00 ,  B32B7/022 ,  B64C1/38 ,  F01D5/146 ,  F01D5/187 ,  F01D5/30 ,  F01D5/3007 ,  F01D7/00 ,  F01D9/041 ,  F01D15/10 ,  F01D15/12 ,  F01D17/162 ,  F01D25/12 ,  F02C6/206 ,  F02C7/264 ,  F02C7/32 ,  F02C7/36 ,  F02C9/00 ,  F02C9/22 ,  F02K1/66 ,  F02K1/76 ,  B32B2307/558 ,  B32B2307/72 ,  B32B2307/732 ,  B32B2571/02 ,  B32B2605/18 ,  F02C3/113 ,  F05D2220/323 ,  F05D2220/325 ,  F05D2230/60 ,  F05D2240/12 ,  F05D2240/24 ,  F05D2240/60 ,  F05D2250/37 ,  F05D2260/201 ,  F05D2260/30 ,  F05D2260/4031 ,  F05D2260/70 ,  F05D2270/05 ,  F05D2270/051 ,  F05D2270/121 ,  F05D2270/304 ,  F05D2270/71 ,  F05D2270/81

Abstract: An aircraft defining a longitudinal direction and a lateral direction is provided. The aircraft includes: a fuselage; an engine mounted at a location spaced from the fuselage of the aircraft, the engine comprising a plurality of rotor blades; and a fuselage shield attached to or formed integrally with the fuselage at a location in alignment with the plurality of rotor blades along the lateral direction, the fuselage shield comprising a first layer defining a first density and a second layer defining a second density, the first density being different than the second density.

公开(公告)号：US20230228198A1

公开(公告)日：2023-07-20

申请号：US18070618

申请日：2022-11-29

Applicant: General Electric Company

Inventor： Gregory Carl Gemeinhardt ,  Nicholas Joseph Kray ,  Andreas Mastorakis

IPC: F01D5/28 ,  F02C3/04

CPC classification number: F01D5/282 ,  F02C3/04 ,  F05D2220/32 ,  F05D2300/603 ,  F05D2300/614 ,  F05D2230/50

Abstract: A component for a gas turbine engine. The component includes a continuous fiber blade including an airfoil extending radially between a root and a tip and a blade attachment feature positioned at or adjacent to the root. The component further includes a platform coupled to the root of the continuous fiber blade. The platform includes a plurality of chopped fibers. Additionally, the component includes a thermoplastic polymer contained in both the continuous fiber blade and the platform. Moreover, the continuous fiber blade and platform are coupled together such that the continuous fiber blade and platform form a monolithic composite body.

公开(公告)号：US11668317B2

公开(公告)日：2023-06-06

申请号：US17408986

申请日：2021-08-23

Applicant: General Electric Company

Inventor： Abhijeet Jayshingrao Yadav ,  Nitesh Jain ,  Nicholas Joseph Kray ,  Ravindra Shankar Ganiger ,  Praveen Sharma

IPC: F04D29/36 ,  F04D19/00 ,  F03G7/06

CPC classification number: F04D29/368 ,  F03G7/0614 ,  F04D19/002

Abstract: An airfoil arrangement for a gas turbine engine may include a clearance device using a shape memory alloy movable to provide clearance between an airfoil and one or more other components of the gas turbine engine. The clearance device may be formed as part of a fan blade. The arrangement may be configured to reduce overall weight and dimensions of the gas turbine engine.

公开(公告)号：US20230160307A1

公开(公告)日：2023-05-25

申请号：US17533566

申请日：2021-11-23

Applicant: General Electric Company

Inventor： Li Zheng ,  Nicholas Joseph Kray ,  Scott Roger Finn

IPC: F01D5/14 ,  F01D5/28

CPC classification number: F01D5/147 ,  F01D5/282 ,  F05D2300/505 ,  F05D2300/603

Abstract: Morphable rotor blades for a turbine engine systems include a root portion and an airfoil portion having a morphable portion including a morphable material that changes shape in response to a stimulus.

公开(公告)号：US20230128806A1

公开(公告)日：2023-04-27

申请号：US17511866

申请日：2021-10-27

Applicant: General Electric Company

Inventor： Li Zheng ,  Nicholas Joseph Kray ,  Changjie Sun

IPC: F01D25/00

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：US20230008743A1

公开(公告)日：2023-01-12

申请号：US17368961

申请日：2021-07-07

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Praveen Sharma ,  Abhijeet Jayshingrao Yadav ,  Nitesh Jain ,  Nicholas Joseph Kray

IPC: F01D5/28 ,  F01D5/14 ,  F01D5/30

Abstract: An airfoil arrangement for a gas turbine engine may include a support device using a shape memory alloy to support and control the airfoil. The support device may be formed as part of a fan blade. The arrangement may be configured to reduce overall weight and dimensions of the gas turbine engine.

公开(公告)号：US11499448B2

公开(公告)日：2022-11-15

申请号：US16424843

申请日：2019-05-29

Applicant: General Electric Company

Inventor： Abhijeet Jayshingrao Yadav ,  Nagamohan Govinahalli Prabhakar ,  Nicholas Joseph Kray ,  Shivam Mittal ,  Praveen Sharma ,  Bhujabal Prashant Mahadeo ,  Ravindra Shankar Ganiger

IPC: F01D25/24 ,  F01D25/00 ,  F02K3/06 ,  F03G7/06

Abstract: A composite fan casing for a gas turbine engine defining a central axis is generally provided. The composite fan casing includes a core having a plurality of core layers of reinforcing fibers bonded together with a thermosetting polymeric resin and having an outer surface. The composite fan casing further includes at least one stiffener integrally coupled to an aft portion of the outer surface of the core relative to the central axis. Additionally, the at least one stiffener comprises an elastic material.

公开(公告)号：US20220341333A1

公开(公告)日：2022-10-27

申请号：US17236257

申请日：2021-04-21

Applicant: General Electric Company

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

IPC: F01D5/28 ,  F02C7/24 ,  F01D5/14

Abstract: A component for a turbine engine is provided. The component includes a main body portion having a flow path surface; and a protective layer formed of a chopped fiber material, the protective layer cohered to at least a portion of the flow path surface of the main body portion.

公开(公告)号：US20220341330A1

公开(公告)日：2022-10-27

申请号：US17241948

申请日：2021-04-27

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Nitesh Jain ,  Nicholas Joseph Kray ,  David Crall

IPC: F01D5/14

Abstract: Fan blades for frangibility are disclosed. An example airfoil for use in a gas turbine engine includes a root portion to be disposed adjacent to a disk of the gas turbine engine, a tip portion including a cavity disposed therein, and wherein the tip portion and cavity are configured to fragment when exposed to a threshold force corresponding to a high-stress event.