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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
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.
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公开(公告)号：US12103702B2
公开(公告)日：2024-10-01
申请号：US17071308
申请日：2020-10-15
Applicant: General Electric Company
CPC classification number: B64D45/00 , B32B7/022 , B64C1/38 , B32B2307/558 , B32B2307/72 , B32B2307/732 , B32B2571/02 , B32B2605/18
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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公开(公告)号：US11015461B2
公开(公告)日：2021-05-25
申请号：US15850842
申请日：2017-12-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Viswanadha Gupta Sakala , Douglas Duane Ward , Ming Xie
Abstract: Composite hollow blade and an associated method of forming the composite hollow blade are disclosed. The method includes forming a core by fabricating a grid core structure based on a plurality of design parameters, where the grid core includes a plurality of first reinforcing components disposed in a first curable matrix material. The method further includes forming an outer layer including a plurality of second reinforcing components disposed in a second curable matrix material. Further, the method includes coupling the core to the outer layer and curing the core and the outer layer to form the composite hollow blade.
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公开(公告)号：US10589475B2
公开(公告)日：2020-03-17
申请号：US14860132
申请日：2015-09-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Xiaomei Fang , Christopher Madsen , Ian Francis Prentice , Sultan Shair , Dong-Jin Shim , Douglas Duane Ward
Abstract: A gas turbine engine composite article having a composite article airfoil extending outwardly to an article root to an article airfoil tip. Within the article airfoil is a core including a core airfoil attached to a core root including a core dovetail. A continuous outer three-dimensional braided layer including braided composite material tows are braided on the core and the braided layer covers the entire core airfoil and the core root. The core may be an inflatable mandrel or a composite core made of a composite material. The core may include stiffeners such as an I beam or hollow rectangular cross-section box beams. A method for making such an article includes braiding a continuous outer three-dimensional braided layer including braided composite material tows on the core including covering the entire core airfoil and the core root with the continuous outer three-dimensional braided layer.
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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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Patent Agency Ranking
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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公开(公告)号：US10815804B2
公开(公告)日：2020-10-27
申请号：US15478702
申请日：2017-04-04
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Viswanadha Gupta Sakala , Mitchell Harold Boyer , Ming Xie , Douglas Duane Ward
Abstract: A containment assembly for use in a turbine engine includes a fan case formed from a composite material. The fan case includes a forward end, an aft end, and an opening defined through the fan case between the forward and aft ends. The containment assembly further includes a structural attachment member formed from a metallic material and coupled to the fan case. The structural attachment member is positioned within the opening in the fan case and is configured to receive at least one fastener to couple a component to the structural attachment member.
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公开(公告)号：US20210339867A1
公开(公告)日：2021-11-04
申请号：US17071379
申请日：2020-10-15
Applicant: General Electric Company
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.
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公开(公告)号：US10815798B2
公开(公告)日：2020-10-27
申请号：US15891415
申请日：2018-02-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Gregory Carl Gemeinhardt , Douglas Duane Ward , David William Crall
Abstract: A blade for the fan section of a turbine engine comprising a composite core defining a pressure side and a suction side extending axially between a core leading edge and a core trailing edge defining a chord-wise direction and extending radially between a core root and a core tip defining a span-wise direction and a leading edge strip made of materials with different elasticity and mounted to the core leading edge.
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公开(公告)号：US20200182062A1
公开(公告)日：2020-06-11
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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