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21.发明公开公开(公告)号：US20240183278A1
公开(公告)日：2024-06-06
申请号：US18441039
申请日：2024-02-14
Applicant: General Electric Company
Inventor： Anthony Michael Gunasekera , Nicholas Joseph Kray , Leslie Louis Langenbrunner , Simeon Paul Copple
CPC classification number: F01D9/041 , B64C11/26 , F01D5/282 , F01D25/005 , F04D29/388 , F05D2220/323 , F05D2240/12 , F05D2240/30
Abstract: A composite airfoil having a non-metallic leading edge protective wrap is provided. In one aspect, the airfoil has a composite core having a pressure sidewall and a suction sidewall each extending between a core leading edge and a core trailing edge. A leading edge protective wrap protects the core leading edge and includes a trailing wrap and a leading wrap. The trailing wrap wraps around the core leading edge and is connected to the composite core. The leading wrap wraps around the core leading edge and is connected to the trailing wrap. The trailing and leading wraps both have leading edges that are spaced from one another. A filler is positioned between the leading edges of the trailing and leading wraps. A protective nose is connected to the leading edge of the leading wrap. The components of the leading edge protective wrap are formed of non-metallic materials.
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公开(公告)号：US11970956B2
公开(公告)日：2024-04-30
申请号：US18146511
申请日：2022-12-27
Applicant: General Electric Company
Inventor： Abhijeet Jayshingrao Yadav , Nicholas Joseph Kray , Nitesh Jain , Ricardo Hernandez Pandeli
IPC: F01D7/00
CPC classification number: F01D7/00
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.
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23.发明授权公开(公告)号：US11946391B2
公开(公告)日：2024-04-02
申请号：US17198843
申请日：2021-03-11
Applicant: General Electric Company
Inventor： Anthony Michael Gunasekera , Nicholas Joseph Kray , Leslie Louis Langenbrunner , Simeon Paul Copple
CPC classification number: F01D9/041 , B64C11/26 , F01D5/282 , F01D25/005 , F04D29/388 , F05D2220/323 , F05D2240/12 , F05D2240/30
Abstract: A composite airfoil having a non-metallic leading edge protective wrap is provided. In one aspect, the airfoil has a composite core having a pressure sidewall and a suction sidewall each extending between a core leading edge and a core trailing edge. A leading edge protective wrap protects the core leading edge and includes a trailing wrap and a leading wrap. The trailing wrap wraps around the core leading edge and is connected to the composite core. The leading wrap wraps around the core leading edge and is connected to the trailing wrap. The trailing and leading wraps both have leading edges that are spaced from one another. A filler is positioned between the leading edges of the trailing and leading wraps. A protective nose is connected to the leading edge of the leading wrap. The components of the leading edge protective wrap are formed of non-metallic materials.
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公开(公告)号：US11834965B2
公开(公告)日：2023-12-05
申请号：US17410754
申请日：2021-08-24
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Ian F. Prentice
CPC classification number: F01D7/00 , F01D5/30 , F01D5/3007 , F01D5/3015 , F01D5/3023 , F01D5/32 , F01D5/323 , F04D29/323 , F04D29/34 , F04D29/362 , B64C11/06 , B64C11/343 , F05B2260/74 , F05B2260/77 , F05D2220/32 , F05D2220/323 , F05D2240/30 , F05D2260/70 , F05D2260/74
Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed for a slot to accommodate a blade of an engine. An example blade apparatus includes: a collet including a slot to receive an end of a blade; and a plurality of retainers including a first retainer positioned on a first end of the collet and a second retainer positioned on a second end of the collet to provide axial retention for the blade in the slot.
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公开(公告)号：US11795827B1
公开(公告)日：2023-10-24
申请号：US17712701
申请日：2022-04-04
Applicant: General Electric Company
Inventor： Raghuveer Chinta , Srinivas Nuthi , Gary Willard Bryant, Jr. , Nicholas Joseph Kray
IPC: F01D5/14
CPC classification number: F01D5/147 , F05D2230/10 , F05D2230/50 , F05D2250/283 , F05D2300/612
Abstract: An airfoil assembly comprising a central spar extending along the radial direction; a blade skin positioned around the central spar to define an airfoil that has a pressure side and a suction side extending in the axial direction between a leading edge and a trailing edge, wherein at least one cavity is defined between the blade skin and the central spar; and a support structure positioned at least partially within the at least one cavity. The support structure comprises: a foam; and a foam reinforcement structure embedded within the foam.
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Patent Agency Ranking
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
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.
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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.
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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
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.
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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
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.
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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
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.
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