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公开(公告)号：US20220252008A1
公开(公告)日：2022-08-11
申请号：US17170116
申请日：2021-02-08
Applicant: General Electric Company
Inventor： Arthur William Sibbach , Brandon Wayne Miller , David Marion Ostdiek
Abstract: Propulsion systems and methods of operation are provided. An exemplary propulsion system comprises a rotating element; a stationary element; an inlet duct having an inlet between the rotating and stationary elements, the inlet passing radially inward of the stationary element; a ducted fan disposed in the inlet duct downstream of the inlet and having an axis of rotation and a plurality of blades; a gas turbine engine core having a high pressure compressor, a combustor, and a high pressure turbine in serial relationship; and a booster compressor disposed between the ducted fan and the gas turbine engine core. At least one of the ducted fan and the booster compressor is driven by a variable speed power source such that the rotational speed of the ducted fan and/or booster compressor is controllable independently from the rotational speed of any rotor of the propulsion system.
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公开(公告)号：US20190271237A1
公开(公告)日：2019-09-05
申请号：US15909009
申请日：2018-03-01
Applicant: General Electric Company
Inventor： Andrew J. Martin , Arthur William Sibbach
Abstract: Casings and methods for manufacturing casings are provided. For example, a casing defining radial, axial, and circumferential directions is provided. The casing comprises an annular inner wall and an annular outer wall, each extending along the axial direction, with the outer wall radially spaced apart from the inner wall. The casing also comprises an auxetic structure extending from the inner wall to the outer wall and including a plurality of lattice elements. Each lattice element extends circumferentially and radially from the inner to the outer wall, and the lattice elements are axially spaced apart from one another. The auxetic structure may define at least one aperture for fluid flow from one portion to another of the auxetic structure and/or may be configured to vary the thermal characteristics of the casing along the axial direction. The casing may be integrally formed as a single monolithic component, e.g., by additive manufacturing.
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公开(公告)号：US20250129723A1
公开(公告)日：2025-04-24
申请号：US18489533
申请日：2023-10-18
Applicant: GENERAL ELECTRIC COMPANY
Abstract: A turbine engine with an engine core defining an engine centerline and comprising a rotor assembly and a stator assembly. The turbine engine including a primary stage of airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor assembly. A subsidiary stage of airfoils located upstream of the primary stage of airfoils and circumferentially arranged about the engine centerline.
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公开(公告)号：US20250129722A1
公开(公告)日：2025-04-24
申请号：US18987428
申请日：2024-12-19
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Elzbieta Kryj-Kos , Arthur William Sibbach
IPC: F01D5/28
Abstract: A method of forming a composite airfoil assembly. The method includes forming an inner support structure with at least a first core and a second core each having a core material with at least one of fibers, yarns, braids, or tows. The method includes applying a laminate overlay to surround at least a portion of the inner support structure.
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公开(公告)号：US12270337B1
公开(公告)日：2025-04-08
申请号：US18501173
申请日：2023-11-03
Applicant: General Electric Company
Inventor： James Ryan Reepmeyer , Arthur William Sibbach
Abstract: A gas turbine engine oil flow control system can include a variable flow oil pump useful to provide oil at varying rates to a variety of oil consumers, such as, power gearboxes, engine shaft bearings, electrical generators, etc. Oil flow control valves that have an ability to provide a variable flow of oil can be used in conjunction with the variable flow oil pump. Flow sensors can be used along with an oil flow controller to measure a flow of oil at various points in the gas turbine engine oil flow control system. The oil flow controller can use information from the flow sensors along with a variable consumption demand association with one or more of the oil consumers (either provided to the oil controller or calculated based upon an operational need of the oil consumer) to change operation of the variable flow oil pump and/or oil flow control valve.
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Patent Agency Ranking
公开(公告)号：US20250101919A1
公开(公告)日：2025-03-27
申请号：US18976748
申请日：2024-12-11
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 OUT A DTExit ) 2 * EGT A HPCExit * 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：US20250052162A1
公开(公告)日：2025-02-13
申请号：US18447525
申请日：2023-08-10
Applicant: GENERAL ELECTRIC COMPANY
Abstract: A gas turbine engine includes a fan section, a compressor section, combustion section, and turbine section in serial flow arrangement, that defining an engine centerline extending between a forward direction and an aft direction. A composite component, such as an airfoil, extends between a root and a tip, defining a span-wise direction therebetween, and between a leading edge and a trailing edge, defining a chord-wise direction therebetween. The composite component includes a preform core including a first set of fibers as a first set of warp fibers and a first set of weft fibers.
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公开(公告)号：US12196107B2
公开(公告)日：2025-01-14
申请号：US18172723
申请日：2023-02-22
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：US12168956B2
公开(公告)日：2024-12-17
申请号：US18353472
申请日：2023-07-17
Applicant: General Electric Company
Inventor： Arthur William Sibbach , Allan George van de Wall , Sean Christopher Binion , Brian Lewis Devendorf , Brandon Wayne Miller
Abstract: A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of fan blades; 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; a nacelle surrounding and at least partially enclosing the fan; 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; and a means for reducing ice buildup or ice formation on the inlet pre-swirl feature, the means in communication with the inlet pre-swirl feature.
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公开(公告)号：US20240410317A1
公开(公告)日：2024-12-12
申请号：US18809927
申请日：2024-08-20
Applicant: General Electric Company
Inventor： Arthur William Sibbach , Brandon Wayne Miller
Abstract: A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of fan blades; 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; a nacelle surrounding and at least partially enclosing the fan; 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; and a means for directing incoming objects towards an outer portion of the turbofan engine in communication with the inlet pre-swirl feature.
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