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公开(公告)号：US20250052172A1
公开(公告)日：2025-02-13
申请号：US18366800
申请日：2023-08-08
Applicant: General Electric Company
Inventor： Abhijeet Jayshingrao Yadav , Nicholas Joseph Kray , Nitesh Jain
Abstract: A fan assembly for an engine has a fan blade, a disk having a disk segment, a trunnion mechanism having a trunnion extending at least partially through the disk segment, and first and second attachment systems. The trunnion has a platform and a shaft. The fan blade is adjacent to the platform of the trunnion. The trunnion is attached to the disk segment using the first attachment system along a preload path. The first and second attachment systems further include first and second retention features, respectively, separate from the preload path. During normal operation of the fan assembly, the first attachment system retains the trunnion within the disk along a first load path. Upon a failure in the trunnion, the first and second retention features together retain the trunnion within the disk segment along a second load path, the first load path being different than the second load path.
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公开(公告)号：US20240209740A1
公开(公告)日：2024-06-27
申请号：US18427086
申请日：2024-01-30
Applicant: General Electric Company
Inventor： Nicholas J. Kray , Nitesh Jain , Gary W. Bryant
Abstract: Part-span shrouds for pitch controlled aircrafts are disclosed herein. An example A gas turbine engine disclosed herein includes a disk, a first pitch controlled airfoil coupled to the disk, a second pitch controlled airfoil coupled to the disk, the second pitch controlled airfoil circumferentially adjacent to the first pitch controlled airfoil, and a part-span shroud including a first portion extending from the first pitch controlled airfoil, the first portion including a slot, a second portion extending from the second pitch controlled airfoil towards the first pitch controlled airfoil, and a tie rod including a first end rotatably coupled to the first portion, and a second end rotatably coupled to the second portion, and a pin disposed in the slot, the pin coupling the first portion to the tie rod, the pin circumferentially translatable within the slot.
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公开(公告)号：US11982205B1
公开(公告)日：2024-05-14
申请号：US18171490
申请日：2023-02-20
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nitesh Jain , Abhijeet Jayshingrao Yadav , Balaraju Suresh , Nicholas Joseph Kray
CPC classification number: F01D5/147 , F01D5/282 , F01D9/02 , F01D9/04 , F01D9/041 , F01D9/042 , F01D25/243 , F01D25/246 , F05D2220/323 , F05D2300/603
Abstract: An airfoil for a turbine engine having a spar assembly. The spar assembly including a composite spar, a metallic hub, and a composite body. The metallic hub can receive a portion of the composite spar at an interior surface to define an overlapping region. The composite body is located at the overlapping region.
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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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Patent Agency Ranking
公开(公告)号：US20230407750A1
公开(公告)日：2023-12-21
申请号：US18046657
申请日：2022-10-14
Applicant: General Electric Company
Inventor： Abhijeet Yadav , Nicholas J. Kray , Nitesh Jain
IPC: F01D5/16
CPC classification number: F01D5/16 , F05D2220/36
Abstract: An airfoil structure including an airfoil and a spring and damper system. The airfoil including a longitudinal axis. The spring and damper system is connected to the airfoil to rotate the airfoil about the longitudinal axis to change airfoil pitch in response to a load applied to the airfoil.
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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：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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