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公开(公告)号：US20250109690A1
公开(公告)日：2025-04-03
申请号：US18480169
申请日：2023-10-03
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Elzbieta Kryj-Kos , Arthur William Sibbach
Abstract: A gas turbine engine includes a fan section, a compressor section, a combustion section, and a turbine section in serial flow arrangement, and defining an engine centerline extending between a forward direction and an aft direction. A disk includes a slot for mounting a composite airfoil to the disk. An axial retainer couples to the disk and secures the composite airfoil to the disk. A compliant portion positioned at the composite airfoil abuts the composite airfoil during operation of the gas turbine engine to secure the composite airfoil to the disk.
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公开(公告)号：US20250084799A1
公开(公告)日：2025-03-13
申请号：US18671084
申请日：2024-05-22
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Brandon Wayne Miller , Andrew Hudecki , Kevin Richard Graziano , Arthur William Sibbach , Inenhe Mohammed Khalid , Andrea Piazza , Stefan Joseph Cafaro
Abstract: A gas turbine engine includes a fan section having a fan rotatable with a fan shaft, a turbomachinery section having a turbine and a turbomachine shaft rotatable with the turbine, a power gearbox mechanically coupled to the fan shaft and the turbomachine shaft such that the fan shaft is rotatable by the turbomachine shaft across the power gearbox, a grounded structure coupled to and supporting the power gearbox, and a torque monitoring system. The torque monitoring system includes a gearbox sensor. The gearbox sensor is coupled to the grounded structure and the torque monitoring system configured to determine a torque across the power gearbox using the gearbox sensor.
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公开(公告)号：US12203390B1
公开(公告)日：2025-01-21
申请号：US18348438
申请日：2023-07-07
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Elzbieta Kryj-Kos , Arthur William Sibbach
IPC: F01D5/28
Abstract: A composite airfoil assembly for a turbine engine includes an airfoil defining an airfoil interior, and an inner support structure at least partially located within the airfoil interior. The inner support structure can include intertwined fibers defining a three-dimensional structure. A laminate overlay surrounds at least a portion of the inner support structure.
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公开(公告)号：US20250012195A1
公开(公告)日：2025-01-09
申请号：US18348438
申请日：2023-07-07
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Elzbieta Kryj-Kos , Arthur William Sibbach
IPC: F01D5/28
Abstract: A composite airfoil assembly for a turbine engine includes an airfoil defining an airfoil interior, and an inner support structure at least partially located within the airfoil interior. The inner support structure can include intertwined fibers defining a three-dimensional structure. A laminate overlay surrounds at least a portion of the inner support structure.
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公开(公告)号：US20250012192A1
公开(公告)日：2025-01-09
申请号：US18348452
申请日：2023-07-07
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Arthur William Sibbach , Nicholas Joseph Kray , Elzbieta Kryj-Kos , Gary Willard Bryant, JR. , Michael John Franks
IPC: F01D5/14
Abstract: A composite airfoil assembly for a turbine engine includes an airfoil defining an airfoil interior, and an inner support structure at least partially located within the airfoil interior. The inner support structure can include a first core, a second core, and at least one pin. A laminate overlay surrounds at least a portion of the inner support structure.
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Patent Agency Ranking
公开(公告)号：US20240401488A1
公开(公告)日：2024-12-05
申请号：US18806835
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：US20240392688A1
公开(公告)日：2024-11-28
申请号：US18792941
申请日：2024-08-02
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：US20240133318A1
公开(公告)日：2024-04-25
申请号：US17972734
申请日：2022-10-24
Applicant: General Electric Company
Inventor： Brian Lewis Devendorf , Arthur William Sibbach
IPC: F01D25/26
CPC classification number: F01D25/265 , F05D2240/14 , F05D2260/36
Abstract: A gas turbine engine, comprising a turbomachine and a housing at least partially encasing a portion of the turbomachine, the housing having an inner surface and defining in part a void between the inner surface and the portion of the turbomachine, the housing moveable relative to the portion of the turbomachine; and an engine component selectively coupled to the portion of the turbomachine or to the housing.
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公开(公告)号：US20240110522A1
公开(公告)日：2024-04-04
申请号：US17959336
申请日：2022-10-04
Applicant: General Electric Company
Inventor： Arthur William Sibbach , Brandon Wayne Miller , Andrew Hudecki
CPC classification number: F02C7/36 , F16D1/10 , F05D2220/323 , F05D2240/60
Abstract: A gas turbine engine includes a rotatably driven engine component including a shaft coupling. The shaft coupling defines a first axial centerline and includes an inner surface. The inner surface includes a plurality of internal splines extending radially inwardly from the inner surface with respect to the first axial centerline. The engine further includes a driving member having a driving end portion and defining a second axial centerline. The driving end portion includes an outer surface and a plurality of external splines extending radially outwardly from the outer surface with respect to the second axial centerline. The plurality of external splines is drivingly engaged with the plurality of internal splines. The plurality of internal splines or the plurality of external splines comprises bowed splines.
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公开(公告)号：US20230407795A1
公开(公告)日：2023-12-21
申请号：US17844863
申请日：2022-06-21
Applicant: General Electric Company
Inventor： Arthur William Sibbach , Brandon Wayne Miller , Jeffrey Douglas Rambo
IPC: F02C7/36
CPC classification number: F02C7/36 , F05D2260/4023
Abstract: A shaft power transfer system includes a first mechanical clutch mechanism operably coupling a high-pressure shaft to a low-pressure shaft. The first mechanical clutch mechanism transfers power from the high-pressure shaft to the low-pressure shaft at a predefined first speed transient condition. The system further includes a second mechanical clutch mechanism that operably couples the low-pressure shaft to the high-pressure shaft. The second mechanical clutch mechanism transfers power from the low-pressure shaft to the high-pressure shaft at a predefined second speed transient condition where the predefined first speed transient condition is different than the predefined second speed transient condition.
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