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公开(公告)号：US20240410285A1
公开(公告)日：2024-12-12
申请号：US18807233
申请日：2024-08-16
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Arthur William Sibbach
Abstract: A turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. The turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.
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公开(公告)号：US12158082B2
公开(公告)日：2024-12-03
申请号：US18171533
申请日：2023-02-20
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Arthur William Sibbach
Abstract: A turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. The turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.
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公开(公告)号：US20240392689A1
公开(公告)日：2024-11-28
申请号：US18792961
申请日：2024-08-02
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Arthur William Sibbach
Abstract: A turbine engine includes a fan and a turbomachine defining an engine centerline. The turbomachine includes a compressor section, a combustion section, and a turbine section in serial flow order. The turbine engine also includes a set of composite airfoils circumferentially arranged about the engine centerline. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.
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公开(公告)号：US20240352862A1
公开(公告)日：2024-10-24
申请号：US18304784
申请日：2023-04-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Tod Winton Davis , Nicholas Mark Daggett , Arthur William Sibbach , Elzbieta Kryj-Kos
CPC classification number: F01D5/3023 , F01D5/282 , F01D5/32 , F05D2260/37 , F05D2300/603
Abstract: An airfoil assembly having a trunnion and a spar. The trunnion having an interior surface defining a flared socket with an open top. The spar extending from the flared socket and through the open top. The spar further having a furcated tail with a set of branches defining an intervening gap between adjacent branches of the set of branches
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公开(公告)号：US12116903B2
公开(公告)日：2024-10-15
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
CPC classification number: F01D5/147 , F01D5/282 , F01D5/284 , F01D21/045 , F05D2220/36 , F05D2240/304 , F05D2240/307 , F05D2300/6033
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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Patent Agency Ranking
公开(公告)号：US20240328431A1
公开(公告)日：2024-10-03
申请号：US18741419
申请日：2024-06-12
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Arthur William Sibbach
CPC classification number: F04D29/388 , F02K3/06 , F05D2220/36 , F05D2300/603
Abstract: A turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. The turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.
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公开(公告)号：US20240288337A1
公开(公告)日：2024-08-29
申请号：US18173479
申请日：2023-02-23
Applicant: General Electric Company
Inventor： Sreekanth Kumar Dorbala , Ravindra Shankar Ganiger , Nicholas Joseph Kray , Karan Oberoi , Debaleena Chakraborty , Wendy Wenling Lin
Abstract: A system for monitoring a health condition of a component is provided. The system includes a sensor network comprising a transmitter and a plurality of receivers. Each receiver is configured to receive an electromagnetic signal from the transmitter. A communications interface module is configured to receive an output signal from the transmitter. A computing system includes one or more memory devices and one or more processors. The one or more memory devices is configured to store instructions that, when executed by the one or more processors, causes the one or more processors to execute operations. The operations include transmitting the electromagnetic signal from the transmitter to the plurality of receivers; receiving the output signal at the communications interface module, wherein the output signal is indicative of an array of the plurality of receivers that received the electromagnetic signal; and determining the health condition based on the output signal to the nominal operating state of the component.
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公开(公告)号：US20240229656A9
公开(公告)日：2024-07-11
申请号：US17970687
申请日：2022-10-21
Applicant: General Electric Company
Inventor： Abhijeet Jayshingrao Yadav , Nicholas Joseph Kray , Nicholas M. Daggett , Nitesh Jain , Matthew Mark Weaver , Srinivas Addagatla
IPC: F01D7/00
CPC classification number: F01D7/00 , F05D2220/323 , F05D2240/30
Abstract: A gas turbine engine includes a turbomachine comprising 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 is rotatable about the fan axis. A pitch change mechanism is operable with the plurality of fan blades to control a pitch of the plurality of fan blades. A counterweight is connected to each respective fan blade. A spring mechanism is operably associated with each fan blade of the plurality of fan blades to create a spring twisting moment on the respective fan blade that is counter to a centrifugal twisting moment of the respective fan blade.
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公开(公告)号：US12031453B1
公开(公告)日：2024-07-09
申请号：US18104452
申请日：2023-02-01
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Nitesh Jain , Abhijeet Jayshingrao Yadav , Balaraju Suresh
CPC classification number: F01D5/147 , F01D5/282 , F05D2220/323 , F05D2230/23 , F05D2250/75 , F05D2300/603
Abstract: A component and blade assembly for a turbine engine, the component having a wall bounding an interior and defining an exterior surface extending radially between a leading edge and a trailing edge to define a chordwise direction, and between a hub and a tip to define a spanwise direction. A metallic spar extending from the hub in the spanwise direction into the interior, the metallic spar defining a socket. A composite spar extending in the spanwise direction between a spar root and a spar tip, the spar root received in the socket. The component further having a stiffener.
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公开(公告)号：US20240209737A1
公开(公告)日：2024-06-27
申请号：US18104452
申请日：2023-02-01
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Nitesh Jain , Abhijeet Jayshingrao Yadav , Balaraju Suresh
CPC classification number: F01D5/147 , F01D5/282 , F05D2220/323 , F05D2230/23 , F05D2250/75 , F05D2300/603
Abstract: A component and blade assembly for a turbine engine, the component having a wall bounding an interior and defining an exterior surface extending radially between a leading edge and a trailing edge to define a chordwise direction, and between a hub and a tip to define a spanwise direction. A metallic spar extending from the hub in the spanwise direction into the interior, the metallic spar defining a socket. A composite spar extending in the spanwise direction between a spar root and a spar tip, the spar root received in the socket. The component further having a stiffener.
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