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公开(公告)号：US20250163815A1
公开(公告)日：2025-05-22
申请号：US19033948
申请日：2025-01-22
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Daniel E. Mollmann , Elzbieta Kryj-Kos , Arthur William Sibbach , Brent Michael Push
Abstract: An airfoil assembly for a turbine engine, the airfoil assembly including a platform defining an inner surface and an outer surface, a variable pitch airfoil extending radially from the outer surface of the platform from a root to a tip to define a span length and a mounting structure connected to the platform.
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公开(公告)号：US12297749B2
公开(公告)日：2025-05-13
申请号：US18966717
申请日：2024-12-03
Applicant: GENERAL ELECTRIC COMPANY
IPC: F01D5/28
Abstract: A turbine engine comprising a compressor section, combustor section, and turbine section in serial flow arrangement, and defining an engine longitudinal axis. The turbine engine includes an airfoil with an outer wall having a pressure side and a suction side, extending between a root and a tip in a span-wise direction, and extending between a leading edge and a trailing edge in a chord-wise direction. The airfoil includes a woven core, a first bonding layer including a toughened region, and a laminate skin provided exterior of the first bonding layer and bonded to the woven core by the first bonding layer.
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公开(公告)号：US12241386B2
公开(公告)日：2025-03-04
申请号：US18171938
申请日：2023-02-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Arthur William Sibbach
Abstract: A gas turbine engine includes a compressor section, combustor section, and turbine section in serial flow arrangement, and defining an engine longitudinal axis. Sets of blades can be rotatably driven about the longitudinal axis in the compressor section and the turbine section, with adjacent vanes provided between sets of blades. The airfoil structure defining one or more of the blades or vanes can include a core structure which includes a woven or foam core, with an exterior woven layer.
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104.发明授权公开(公告)号：US12240615B2
公开(公告)日：2025-03-04
申请号：US18079072
申请日：2022-12-12
Inventor： David Marion Ostdiek , William Joseph Solomon , Mohamed Osama , Arthur William Sibbach , Randy M. Vondrell
Abstract: An electric propulsor is provided. The electric propulsor includes a core cowl and an outer cowl. A first air flowpath is defined radially outward of the outer cowl and a second air flowpath is defined between the core cowl and the outer cowl. The electric propulsor also includes one or more electric machines, a fan rotatably drivable by at least one electric machine, and a booster having a plurality of airfoils disposed at least in part in the second air flowpath, the booster being rotatably drivable by at least one electric machine for compressing air flowing along the second air flowpath. The electric propulsor further includes a heat exchanger disposed within the second air flowpath downstream of the booster, the heat exchanger being in thermal communication with at least one of the one or more electric machines and/or a gearbox mechanically coupled with the fan.
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公开(公告)号：US12234745B1
公开(公告)日：2025-02-25
申请号：US18386867
申请日：2023-11-03
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Daniel E. Mollmann , Elzbieta Kryj-Kos , Arthur William Sibbach , Brent Michael Push
Abstract: An airfoil assembly for a turbine engine, the airfoil assembly including a platform defining an inner surface and an outer surface, a variable pitch airfoil extending radially from the outer surface of the platform from a root to a tip to define a span length and a mounting structure connected to the platform.
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Patent Agency Ranking
公开(公告)号：US12228037B1
公开(公告)日：2025-02-18
申请号：US18527567
申请日：2023-12-04
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Brandon Wayne Miller , Gary Willard Bryant, Jr. , Arthur William Sibbach
Abstract: A guide vane assembly for a nacelle of a gas turbine engine includes a forward vane and an aft vane. The aft vane is located aft of the forward vane and forward of a plurality of fan blades. The forward vane defines a fixed pitch angle and the aft vane is movable between a first pitch angle and a second pitch angle.
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公开(公告)号：US12221980B2
公开(公告)日：2025-02-11
申请号：US18481584
申请日：2023-10-05
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Arthur William Sibbach
Abstract: A gas turbine engine includes a fan having a plurality of fan blades, a turbomachine operably coupled to the fan for driving the fan, the turbomachine including a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath, a nacelle surrounding and at least partially enclosing the fan, the nacelle defining a longitudinal axis, and an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle, wherein the inlet pre-swirl feature is transitionable between a first angle with respect to the longitudinal axis of the nacelle and a second angle with respect to the longitudinal axis of the nacelle.
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公开(公告)号：US12196131B2
公开(公告)日：2025-01-14
申请号：US18650586
申请日：2024-04-30
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Daniel Alan Niergarth , Jorge de Luis , Douglas Downey Turner , Michael Macrorie , Keith W. Wilkinson , Arthur William Sibbach , Vincenzo Martina
Abstract: A gas turbine engine is provided having a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (ADTExit) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine; wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) in degrees Celsius, a maximum drive turbine shaft torque (TOUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows: ( T O U T A D T E x i t ) 2 * E G T A H P C E x i t * 1 0 - 1 1 ; wherein CSP is greater than 0.0001194×EGT2−0.103×EGT+22.14 and less than 0.0003294×EGT2−0.306×EGT+77.91; and wherein EGT is greater than 525 degrees Celsius and less than 1250 degrees Celsius.
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公开(公告)号：US12085024B2
公开(公告)日：2024-09-10
申请号：US18307201
申请日：2023-04-26
Applicant: General Electric Company
Inventor： Arthur William Sibbach , Brandon Wayne Miller , Christopher James Kroger , Jeffrey Donald Clements , Sean Christopher Binion , Tsuguji Nakano
CPC classification number: F02C7/36 , F02K3/06 , F05D2220/36 , F05D2260/40311 , F05D2260/606
Abstract: A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of rotatable fan blades, each fan blade defining a fan tip speed; a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; and a gear box, wherein the turbomachine is operably coupled to the fan through the gear box, wherein a gear ratio of the gear box is greater than or equal to 1.2 and less than or equal to 3.0; wherein during operation of the turbofan engine at a rated speed the fan tip speed is greater than or equal to 1000 feet per second. In exemplary embodiments, during operation of the turbofan engine at the rated speed the fan pressure ratio is less than or equal to about 1.5.
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公开(公告)号：US20240287911A1
公开(公告)日：2024-08-29
申请号：US18173989
申请日：2023-02-24
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Benjamin Thomas Van Oflen , Gary Willard Bryant, Jr. , Michael John Franks , Elzbieta Kryj-Kos , Nicholas Joseph Kray , Arthur William Sibbach
CPC classification number: F01D5/3007 , F01D5/282 , F05D2220/32 , F05D2240/24 , F05D2240/30
Abstract: A turbine engine having a disk and a composite airfoil assembly. The disk having a slot. The composite airfoil assembly having an airfoil portion, a dovetail portion, and a roll snubber. The dovetail portion having a radially inner surface. The roll snubber being provided on the radially inner surface. The radially inner surface spaced from the slot to define a gap therebetween.
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