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公开(公告)号：US20250075674A1
公开(公告)日：2025-03-06
申请号：US18432315
申请日：2024-02-05
Applicant: General Electric Company
Inventor： Scott Alan Schimmels , Jeffrey Douglas Rambo , Timothy Richard DePuy , Steven B. Morris , Arthur William Sibbach
Abstract: A heat exchanger positioned within an annular duct of a gas turbine engine is provided. The heat exchanger extends substantially continuously along the circumferential direction and defining a heat exchanger height equal to at least 10% of a duct height. An effective transmission loss (ETL) for the heat exchanger positioned within the annular duct is between 5 decibels and 1 decibels for an operating condition of the gas turbine engine. The heat exchanger includes a heat transfer section defining an acoustic length (Li), and wherein an Operational Acoustic Reduction Ratio (OARR) is greater than or equal to 0.75 to achieve the ETL at the operating condition.
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公开(公告)号：US20250067215A1
公开(公告)日：2025-02-27
申请号：US18942928
申请日：2024-11-11
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：US12209557B1
公开(公告)日：2025-01-28
申请号：US18524054
申请日：2023-11-30
Applicant: General Electric Company
Abstract: A turbofan engine defining an axial direction and a longitudinal centerline along the axial direction is provided. The turbofan engine includes: a fan section having a fan; a turbomachine drivingly coupled to the fan, the turbomachine comprising an outer casing; an outer nacelle surrounding the fan and at least a portion of the turbomachine; an outlet guide vane extending between the turbomachine and the outer nacelle, the outlet guide vane defining a base and a tip and being forward swept from the base to the tip; and an accessory gearbox positioned at least partially inward of the outer casing of the turbomachine.
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公开(公告)号：US20240401489A1
公开(公告)日：2024-12-05
申请号：US18807374
申请日：2024-08-16
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：US20240392687A1
公开(公告)日：2024-11-28
申请号：US18792695
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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Patent Agency Ranking
公开(公告)号：US20240376903A1
公开(公告)日：2024-11-14
申请号：US18777725
申请日：2024-07-19
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：US20240344530A1
公开(公告)日：2024-10-17
申请号：US18755054
申请日：2024-06-26
Applicant: General Electric Company
Inventor： Arthur William Sibbach , Brandon Wayne Miller
CPC classification number: F04D29/66 , F01D9/041 , F01D25/24 , F02C7/045 , F04D29/54 , F04D29/663 , F05D2220/32 , F05D2240/127 , F05D2240/14 , F05D2260/14
Abstract: A turbofan engine is provided. The turbofan engine includes a fan having a plurality of fan blades; a turbomachine operably coupled to the fan for driving the fan, the turbomachine having 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 radius and a longitudinal axis; and an inlet pre-swirl vane located upstream of the plurality of fan blades and defining a chord, the inlet pre-swirl vane coupled to the nacelle, wherein the inlet pre-swirl vane is angled at a first angle with respect to the radius of the nacelle, and wherein the chord of the inlet pre-swirl vane is angled at a second angle with respect to the longitudinal axis of the nacelle.
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公开(公告)号：US12098649B2
公开(公告)日：2024-09-24
申请号：US17972734
申请日：2022-10-25
Applicant: General Electric Company
Inventor： Brian Lewis Devendorf , Arthur William Sibbach
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：US20240309763A1
公开(公告)日：2024-09-19
申请号：US18182559
申请日：2023-03-13
Applicant: GENERAL ELECTRIC COMPANY
CPC classification number: F01D5/147 , F01D5/288 , F05D2220/36 , F05D2300/6034
Abstract: A gas turbine engine includes a fan section, 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 fan section, the compressor section, and the turbine section. The airfoil structure defining one or more of the blades or vanes can include a structure which includes a woven or foam core, with a laminate skin, and an exterior coating.
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公开(公告)号：US20240280027A1
公开(公告)日：2024-08-22
申请号：US18171938
申请日：2023-02-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Arthur William Sibbach
CPC classification number: F01D5/282 , F01D5/147 , F05D2300/6034 , F05D2300/612
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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