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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
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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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
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.
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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
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.
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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
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.
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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
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.
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Patent Agency Ranking
公开(公告)号：US20230008935A1
公开(公告)日：2023-01-12
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
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.
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公开(公告)号：US20230003132A1
公开(公告)日：2023-01-05
申请号：US17366525
申请日：2021-07-02
Applicant: General Electric Company
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. The frangible airfoil portion includes a first plurality of composite plies including fibers having a first fiber modulus. 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 including one or more plies having a second fiber modulus. The second fiber modulus is greater than the first fiber modulus. Further, the residual airfoil portion meets the frangible airfoil portion at the frangible line.
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公开(公告)号：US20230003129A1
公开(公告)日：2023-01-05
申请号：US17363102
申请日：2021-06-30
Applicant: General Electric Company
Inventor： Nitesh Jain , Nicholas Joseph Kray , Daniel Edward Mollmann , David William Crall
Abstract: Composite airfoils and methods for forming composite airfoils are provided. For example, a composite airfoil of a gas turbine engine comprises opposite pressure and suction sides extending radially along a span from a root to a tip, which define opposite radial extremities of the airfoil. The composite airfoil further comprises a body section and a tip section, which includes the tip, that each extend radially along the span. The composite airfoil is formed from a composite material comprising fibers disposed in a matrix material. The tip section has a tip fiber volume, and the body section has a body fiber volume that is greater than the tip fiber volume. Another composite airfoil comprises a tip cap applied over the tip that tapers from a first end to a second end such that each of the pressure and suction side walls of the tip cap narrows from a first thickness to a second thickness.
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公开(公告)号：US11519278B2
公开(公告)日：2022-12-06
申请号：US17193064
申请日：2021-03-05
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Elzbieta Kryj-Kos
Abstract: A rotor blade retention system for a gas turbine engine includes a rotor blade connection component defining a slot, with the rotor blade connection component including a first set of electric leads. Furthermore, the rotor blade retention system includes a rotor blade having a root section received within the slot, with the rotor blade further including a second set of electric leads. In this respect, the first and second sets of electric leads are electrically coupled together to permit electric current to be supplied to the rotor blade.
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公开(公告)号：US20220333492A1
公开(公告)日：2022-10-20
申请号：US17232822
申请日：2021-04-16
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Nitesh Jain
Abstract: In one exemplary embodiment of the present disclosure an airfoil is provided. The airfoil defines a spanwise direction, a root end, and a tip end. The airfoil includes: a body defining a pressure side and a suction side and extending along the spanwise direction between the root end and the tip end, the body formed of a composite material; and a spar enclosed in the body of the airfoil extending along the spanwise direction, the spar comprising a plurality of spar segments arranged in an overlapping configuration along the spanwise direction.
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