公开(公告)号：US20230313688A1

公开(公告)日：2023-10-05

申请号：US18329467

申请日：2023-06-05

Applicant: General Electric Company

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

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

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

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 corresponds to a first stiffness and the second hairpin structure corresponds to a second stiffness different than the first stiffness.

公开(公告)号：US20220298926A1

公开(公告)日：2022-09-22

申请号：US17207911

申请日：2021-03-22

Applicant: General Electric Company

Inventor： Nitesh Jain ,  Nicholas Joseph Kray

IPC: F01D21/04

Abstract: Hybrid material components and methods of forming hybrid material components are provided. For example, a hybrid material component comprises a plurality of metallic tows and a plurality of non-metallic tows. Each metallic tow of the plurality of metallic tows is surrounded by a portion of the plurality of non-metallic tows such that the plurality of metallic tows are embedded within the plurality of non-metallic tows. An exemplary hybrid material component is a containment assembly of a gas turbine engine. Methods of forming such components include forming a hybrid material; laying up a plurality of layers of the material to form a layup; and processing the layup such that a plurality of metallic tows and a plurality of non-metallic tows are co-cured.

公开(公告)号：US11286782B2

公开(公告)日：2022-03-29

申请号：US16213653

申请日：2018-12-07

Applicant: General Electric Company

Inventor： Gregory Carl Gemeinhardt ,  Douglas Duane Ward ,  David William Crall ,  Nicholas Joseph Kray

IPC: F01D5/14 ,  F01D5/28 ,  B23P15/04 ,  B64C11/20 ,  B29D99/00

Abstract: An airfoil that includes an airfoil body having a root and a tip, and convex and concave sides that extend between a leading edge and a trailing edge. The airfoil also includes at least a first cladding element that is attached to the airfoil body. The first cladding element includes a first portion and a second portion. The second portion is configured to separate from the first portion when the first cladding element encounters a force of at least a predetermined amount.

公开(公告)号：US11261787B2

公开(公告)日：2022-03-01

申请号：US16015468

申请日：2018-06-22

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Ravindra Shankar Ganiger ,  Viswanadha Gupta Sakala ,  Nicholas Joseph Kray

IPC: F02C7/00 ,  F02C7/047 ,  H05B6/10 ,  H01F7/20

Abstract: An aircraft can include a turbine engine including a rotor and a stator, and also including a compressor, a combustor, and a turbine in axial flow arrangement. The aircraft can further include an anti-icing system with a magnetic field generator having a rotating portion and a non-rotating portion, as well as an array of carbon nanotubes thermally coupled to an exposed surface.

公开(公告)号：US20210339846A1

公开(公告)日：2021-11-04

申请号：US17071308

申请日：2020-10-15

Applicant: General Electric Company

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

IPC: B64C1/38

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 rotor blades; and at least one fuselage shield removably coupled to the fuselage at a location in alignment with the rotor blades along the lateral direction.

公开(公告)号：US11149584B2

公开(公告)日：2021-10-19

申请号：US16594208

申请日：2019-10-07

Applicant: General Electric Company

Inventor： David William Crall ,  Nicholas Joseph Kray ,  Scott Roger Finn ,  Wendy Wenling Lin

IPC: F01D21/04

Abstract: Containment assemblies and methods for forming containment assemblies of gas turbine engines are provided. For example, a containment assembly comprises a containment case including a plurality of coated fibers. Each coated fiber comprises a fiber surrounded by a ceramic material such that the ceramic material coats the fiber. As another example, a containment assembly comprises an inner case and a containment case comprising a plurality of coated fibers. Each coated fiber comprises a fiber surrounded by a ceramic material such that the ceramic material coats the fiber. The containment case includes a greater proportion of the coated fibers at an inner surface of a layer of the containment case than at a location within the containment case that is radially outward from the inner surface. Methods for forming a containment assembly of a gas turbine engine are provided.

公开(公告)号：US11149558B2

公开(公告)日：2021-10-19

申请号：US16161200

申请日：2018-10-16

Applicant: General Electric Company

Inventor： Nitesh Jain ,  Nicholas Joseph Kray ,  Kishore Budumuru

IPC: F01D5/28 ,  F01D21/04 ,  F02K3/06

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 including a first plurality of composite plies. Each of the first plurality of composite plies includes fibers oriented at least partially along a chordwise direction, a thickness direction, or both. The airfoil further includes a residual airfoil portion extending from the frangible line to the root along the span including a second plurality of composite plies. The second plurality of composite plies includes at least one composite ply with fibers oriented along the span. Further, the residual airfoil portion meets the frangible airfoil portion at the frangible line.

公开(公告)号：US11111815B2

公开(公告)日：2021-09-07

申请号：US16161253

申请日：2018-10-16

Applicant: General Electric Company

Inventor： Nicholas Joseph Kray ,  Nitesh Jain ,  Daniel Edward Mollmann

IPC: F01D5/14 ,  F01D21/04 ,  F01D5/28 ,  F01D11/12

Abstract: An airfoil defining a span extending between a root and a tip and a chord at each point along the span extending between a leading edge and a trailing edge. The airfoil 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 the span. The frangible airfoil portion includes an exterior surface. The exterior surface at least partially defines at least one fusion cavity at least partially defining the frangible line. The airfoil further includes a residual airfoil portion extending from the frangible line to the root along the span. The residual airfoil portion meets the frangible airfoil portion at the frangible line. As such, the frangible airfoil portion deforms or partially or fully detaches relative to the residual airfoil portion at the frangible line following an event creating imbalance.

公开(公告)号：US20210102475A1

公开(公告)日：2021-04-08

申请号：US16594208

申请日：2019-10-07

Applicant: General Electric Company

Inventor： David William Crall ,  Nicholas Joseph Kray ,  Scott Roger Finn ,  Wendy Wenling Lin

IPC: F01D25/26

Abstract: Containment assemblies and methods for forming containment assemblies of gas turbine engines are provided. For example, a containment assembly comprises a containment case including a plurality of coated fibers. Each coated fiber comprises a fiber surrounded by a ceramic material such that the ceramic material coats the fiber. As another example, a containment assembly comprises an inner case and a containment case comprising a plurality of coated fibers. Each coated fiber comprises a fiber surrounded by a ceramic material such that the ceramic material coats the fiber. The containment case includes a greater proportion of the coated fibers at an inner surface of a layer of the containment case than at a location within the containment case that is radially outward from the inner surface. Methods for forming a containment assembly of a gas turbine engine are provided.

公开(公告)号：US10938328B2

公开(公告)日：2021-03-02

申请号：US15189026

申请日：2016-06-22

Applicant: General Electric Company

Inventor： Aaron Todd Sellinger ,  Nicholas Joseph Kray

IPC: H02N2/18 ,  H01L41/113 ,  F04D29/38 ,  H01L35/32 ,  G01L1/16 ,  G01K7/02 ,  F01D5/28 ,  F01D15/10 ,  F01D5/16 ,  C04B35/52 ,  C04B35/117 ,  F03G7/08 ,  C04B35/565 ,  F01D25/00 ,  C04B35/80 ,  F01D25/04 ,  F01D5/10 ,  F01D25/06 ,  F01D5/26

Abstract: The present disclosure is directed to an engine component for a gas turbine engine, the engine component including a substrate that includes a composite fiber and defines a surface. An energy harvesting fiber is positioned within the substrate.