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公开(公告)号：US20240392801A1
公开(公告)日：2024-11-28
申请号：US18792952
申请日：2024-08-02
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Arthur William Sibbach
IPC: F04D29/32
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：US20240369071A1
公开(公告)日：2024-11-07
申请号：US18777644
申请日：2024-07-19
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：US20240360768A1
公开(公告)日：2024-10-31
申请号：US18764770
申请日：2024-07-05
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Arthur William Sibbach
CPC classification number: F01D5/282 , F01D9/02 , F01D25/005 , F05D2220/323 , F05D2240/12 , F05D2240/30 , F05D2300/603
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. The leading edge protector includes at least one projection extended past a base of the airfoil to a root of the airfoil.
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公开(公告)号：US20240280024A1
公开(公告)日：2024-08-22
申请号：US18171533
申请日：2023-02-20
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Arthur William Sibbach
CPC classification number: F01D5/147 , F01D5/282 , F05D2220/36 , F05D2240/121 , F05D2240/303 , 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：US12044182B2
公开(公告)日：2024-07-23
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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Patent Agency Ranking
公开(公告)号：US20240159193A1
公开(公告)日：2024-05-16
申请号：US17988302
申请日：2022-11-16
Applicant: General Electric Company
Inventor： Arthur William Sibbach , Michael Anthony Benjamin , Sibtosh Pal , Erich Alois Krammer , Douglas Scott Jacobs , Jacques Paul
CPC classification number: F02C9/40 , F02C7/22 , F02C7/266 , F02C9/263 , F05D2220/323 , F05D2270/44 , F05D2270/54
Abstract: A combustion system for a vehicle having an engine includes a hydrogen fuel system having a fuel source providing a hydrogen fuel, a combustor operable to combust the hydrogen fuel to generate combustion gases, and a fuel delivery assembly operable to deliver the hydrogen fuel from the fuel source to the combustor. A first control system has a first update rate and is operable to control one or more operational aspects of the turbine engine. A second control system is in communication with the first control system and the hydrogen fuel system and has a second update rate faster than the first update rate. The second control system is operable to monitor at least one parameter associated with the hydrogen fuel system and output at least one control signal to the hydrogen fuel system to control the delivery or the combustion of the hydrogen fuel.
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公开(公告)号：US11965424B2
公开(公告)日：2024-04-23
申请号：US17844940
申请日：2022-06-21
Applicant: General Electric Company
Inventor： Arthur William Sibbach , Brandon Wayne Miller , Erich Alois Krammer , Douglas Scott Jacobs , Joseph Alfred Iannotti
CPC classification number: F01D21/02 , F02C9/28 , F02C9/46 , F02C9/50 , F05D2270/021 , F05D2270/304 , F05D2270/335
Abstract: A method for providing overspeed protection for a gas turbine engine having an engine shaft includes monitoring, via an overspeed protection system, a torque of the engine shaft. The method also includes determining, via the overspeed protection system, at least one additional condition of the engine shaft. Further, the method includes determining, via the overspeed protection system, an overspeed condition of the gas turbine engine when the torque of the engine shaft drops below a torque threshold and the at least one additional condition of the engine shaft is indicative of the gas turbine engine being in an operational state. Thus, the overspeed condition is indicative of an above normal rotational speed of the engine shaft. In addition, the method includes initiating a shutdown procedure for the gas turbine engine in response to the determined overspeed condition to reduce the rotational speed of the engine shaft.
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公开(公告)号：US20240011417A1
公开(公告)日：2024-01-11
申请号：US18462064
申请日：2023-09-06
Applicant: General Electric Company
Inventor： Arthur William Sibbach , Aaron Michael Dziech , Scott Alan Schimmels , Robert R. Rachedi , Jeffrey Douglas Rambo , Brandon Wayne Miller
CPC classification number: F01K23/02 , F02C3/30 , F01K25/103 , F02C7/224 , F02C3/22 , F05D2220/31 , F05D2220/32 , F05D2220/72 , F05D2220/74 , F05D2240/36 , F05D2260/213
Abstract: A pericritical fluid system for a thermal management system associated with a turbine engine may include one or more sensors configured to generate sensor outputs corresponding to one or more phase properties of a pericritical fluid flowing through a cooling circuit of the thermal management system, and a controller configured to generate control commands configured to control one or more controllable components of the thermal management system based at least in part on the sensor outputs. The one or more sensors may include one or more phase detection sensors, such as an acoustic sensor.
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公开(公告)号：US11833779B2
公开(公告)日：2023-12-05
申请号：US16953970
申请日：2020-11-20
Applicant: General Electric Company
Inventor： Arthur William Sibbach , Wendy Wenling Lin
IPC: B32B15/08 , B32B15/20 , B32B15/14 , B32B27/32 , C09J7/35 , C09J163/00 , C09J133/08 , F04D29/42 , B32B27/08 , B32B27/18 , B32B7/12
CPC classification number: B32B15/08 , B32B7/12 , B32B15/14 , B32B15/20 , B32B27/08 , B32B27/18 , B32B27/32 , C09J7/35 , C09J133/08 , C09J163/00 , F04D29/4226 , B32B2250/03 , B32B2250/04 , B32B2255/26 , B32B2307/31 , B32B2307/7265 , B32B2311/24 , B32B2313/04 , B32B2323/04 , B32B2323/10 , B32B2363/00 , B32B2367/00 , B32B2603/00 , F05D2300/603
Abstract: A coated component having a composite substrate and a coating system disposed thereon is provided. The coating system is substantially non-porous such that hydrocarbon fuel or other carbonaceous fluids are prevented from contacting and impregnating the polymer matrix composite material. The coating system can include an aluminum layer or a film layer comprising a polyethylene film or a polypropylene film. Also provided is a composite fan casing for a gas turbine engine having a polymer matrix composite substrate and a coating system disposed thereon. Methods for forming a containment assembly of a gas turbine engine are provided.
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公开(公告)号：US20230279872A1
公开(公告)日：2023-09-07
申请号：US17686673
申请日：2022-03-04
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Arthur William Sibbach
CPC classification number: F04D29/542 , F04D19/002
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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