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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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Patent Agency Ranking
16.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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18.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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