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公开(公告)号：US20140150402A1
公开(公告)日：2014-06-05
申请号：US13690057
申请日：2012-11-30
Applicant: General Electric Company
Inventor： Ahmed Mostafa ElKady , Sherif Hatem Abdulla Mohamed , Narendra Digamber Joshi , Hasan Karim , Gilbert Otto Kraemer , Samuel David Draper , Ashwin Raman
CPC classification number: F02C3/34 , F02C3/20 , F02C7/00 , F23C9/00 , F23C9/006 , F23C2202/30 , F23J15/02 , F23J15/022 , F23J15/025 , F23R2900/00004
Abstract: In one aspect, a combustion system is configured to facilitate preventing the formation of vanadium pentoxide (V2O5) and decrease a concentration of at least one of vanadium trioxide (V2O3) and vanadium tetroxide (V2O4) particles in an exhaust. The combustion system includes a vanadium-containing fuel supply and a combustor. The combustor is configured to generate a combustor exhaust gas including vanadium trioxide (V2O3) and/or vanadium tetroxide (V2O4) particles and to combust a reduced-oxygen mixture including the vanadium-containing fuel, ambient air, and a portion of the combustor exhaust gas. The combustion system also includes a particle separator configured to remove substantially all of the V2O3 and/or V2O4 particles from the combustor exhaust gas. A method for combusting fuel and a power generation system are also provided.
Abstract translation: 在一个方面，燃烧系统被配置为有助于防止五氧化二钒（V 2 O 5）的形成并且减少排气中的三氧化二钒（V 2 O 3）和四氧化钒（V 2 O 4）颗粒中的至少一种的浓度。 燃烧系统包括含钒燃料供应和燃烧器。 燃烧器被配置为产生包括三氧化二钒（V 2 O 3）和/或四氧化钒（V 2 O 4）颗粒的燃烧器废气，并且燃烧包含含钒燃料，环境空气和燃烧器排气的一部分的还原氧混合物 加油站。 该燃烧系统还包括一个颗粒分离器，其构造成从燃烧器废气中基本上除去所有的V 2 O 3和/或V 2 O 4颗粒。 还提供了燃烧燃料和发电系统的方法。
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公开(公告)号：US11745859B2
公开(公告)日：2023-09-05
申请号：US16118878
申请日：2018-08-31
Applicant: General Electric Company
Inventor： Nicholas William Rathay , Narendra Digamber Joshi
CPC classification number: B64C21/04 , F02K1/28 , F23R3/002 , F23R3/28 , F05D2220/323
Abstract: A flow control actuator includes a first side wall, a second side wall opposite and substantially parallel to the first side wall, an upstream wall mechanically coupled to upstream ends of the first and second side walls, and a downstream cap mechanically coupled to downstream ends of the first and second side walls. The first side wall, the second side wall, the upstream wall and the downstream cap collectively define an interior of the flow control actuator. An energy source is disposed in at least one of the first sidewall and the second sidewall. At least one fuel injector is disposed in the upstream wall, the first sidewall and/or the second sidewall for dispersing fuel into the flow control actuator. At least one air inlet is disposed in the upstream wall, the first sidewall and/or the second sidewall for introducing air into the flow control actuator. Fuel from fuel injector and air from the air inlet are ignited in the flow control actuator.
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公开(公告)号：US11536456B2
公开(公告)日：2022-12-27
申请号：US16164474
申请日：2018-10-18
Applicant: General Electric Company
Inventor： Venkat Eswarlu Tangirala , Narendra Digamber Joshi
Abstract: A fuel and air injection handling system for a rotating detonation engine is provided. The system includes a compressor configured to compress air received via a compressor inlet and configured to output the air that is compressed as swirling, compressed air through a compressor outlet. The system also includes an annular rotating detonation combustor fluidly coupled with the compressor outlet. The annular rotating detonation combustor has a detonation cavity that extends around an annular axis, the annular rotating detonation combustor configured to combust the compressed air from the compressor in detonations that rotate within the detonation cavity around the annular axis of the annular rotating detonation combustor. The annular rotating detonation combustor is fluidly and directly coupled with the compressor outlet.
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公开(公告)号：US11267551B2
公开(公告)日：2022-03-08
申请号：US16685504
申请日：2019-11-15
Applicant: General Electric Company
Inventor： Timothy John Sommerer , Nicholas William Rathay , Narendra Digamber Joshi , Douglas Carl Hofer , Hongbo Cao
Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to cool the leading edge of certain portions of the hypersonic aircraft that are exposed to high thermal loads, such as extremely high temperatures and/or thermal gradients. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. A coolant supply may be in fluid communication with at least one fluid passageway that passes through the outer wall to deliver a flow of cooling fluid, such as liquid metal, to the stagnation point. The liquid metal vaporizes when the leading edge experiences a high heat load, thereby transpiration cooling the leading edge and/or facilitating a magnetohydrodynamic process for generating thrust or electricity.
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公开(公告)号：US11225871B2
公开(公告)日：2022-01-18
申请号：US16226703
申请日：2018-12-20
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Narendra Digamber Joshi , Samar Jyoti Kalita , Paul Gerard Marsland , Wayne Allen Spence
IPC: F01D5/14 , F01D11/18 , B22F5/04 , B22F7/06 , B33Y80/00 , B33Y10/00 , B22F10/20 , F01D5/28 , F01D9/04 , F04D29/32 , F04D29/54
Abstract: A turbine engine airfoil apparatus, including an airfoil defined by a plurality of airfoil sections arrayed along a stacking axis that extends between a root and a tip, wherein at least two of the airfoil sections spaced apart from each other have differing airfoil section thermal expansion properties.
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Patent Agency Ranking
公开(公告)号：US20210285376A1
公开(公告)日：2021-09-16
申请号：US17203052
申请日：2021-03-16
Applicant: General Electric Company
Abstract: A gas turbine engine includes; a compressor, a combustor, and a turbine in serial flow relationship; a heat exchanger, the heat exchanger having an inlet, an outlet, and an internal surface coated with a catalyst, the heat exchanger being located upstream of the compressor; a source of hydrocarbon fuel in fluid communication with the inlet of the heat exchanger; a source of oxygen in fluid communication with the inlet of the heat exchanger; and a distribution system for receiving reformed hydrocarbon fuel from the heat exchanger.
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公开(公告)号：US20210285370A1
公开(公告)日：2021-09-16
申请号：US17332504
申请日：2021-05-27
Applicant: General Electric Company
IPC: F02C3/14 , F23R3/00 , F23R3/34 , F23R3/44 , F04D29/54 , F01D9/02 , F04D27/02 , F04D29/56 , F23R3/04 , F23R3/12 , F23R3/26 , F23R3/28 , F23R3/50 , B23P15/04 , F02C3/04 , F23R3/14
Abstract: Embodiments of a combustor for a gas turbine engine are provided herein. In some embodiments, a combustion chamber for a gas turbine engine comprising may include a combustor having an inner volume defined at least partially by a front wall, wherein the wall comprises a plurality of facets each having a through hole fluidly coupled to the inner volume, and wherein the plurality of facets are oriented such that an axis of each of the plurality of facets is offset from a central axis of the combustor by an angle.
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公开(公告)号：US11097849B2
公开(公告)日：2021-08-24
申请号：US16126269
申请日：2018-09-10
Applicant: General Electric Company
Inventor： Nikolai N. Pastouchenko , Randy M. Vondrell , Kurt David Murrow , Jixian Yao , Brandon Wayne Miller , Patrick Michael Marrinan , Daniel Alan Niergarth , Narendra Digamber Joshi
Abstract: A method for operating an electric fan of an aircraft propulsion system includes driving a plurality of fan blades of the electric fan with an electric machine to generate thrust for the aircraft; and driving the electric machine with the plurality of fan blades of the electric fan to generate electrical power subsequent to driving the plurality of fan blades of the electric fan with the electric machine to generate thrust for the aircraft.
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公开(公告)号：US20210139160A1
公开(公告)日：2021-05-13
申请号：US16681292
申请日：2019-11-12
Applicant: General Electric Company
Inventor： Lawrence Bernard Kool , Narendra Digamber Joshi
Abstract: A system for removing heat from an aircraft component includes: an aircraft component; a heat exchanger in proximity to the aircraft component and having an inlet, an outlet, and an internal surface coated with a catalyst; a source of hydrocarbon fuel in fluid communication with the inlet of the heat exchanger; a source of oxygen in fluid communication with the inlet of the heat exchanger; and a distribution system for receiving reformed hydrocarbon fuel from the heat exchanger. A method of removing heat from an aircraft component includes the steps of: providing a heat exchanger in proximity to an aircraft component, the heat exchanger being in fluid communication with a source of hydrocarbon fuel and a source of water and having an internal surface coated with a catalyst; introducing a hydrocarbon fuel into the heat exchanger; introducing oxygen into the heat exchanger; contacting the hydrocarbon fuel with the catalyst; and cracking the hydrocarbon fuel to form a reformed hydrocarbon fuel and remove heat from the aircraft component.
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公开(公告)号：US10910916B2
公开(公告)日：2021-02-02
申请号：US15827335
申请日：2017-11-30
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Anoop Kumar Jassal , Mohamed Osama , Francesco Papini , Narendra Digamber Joshi
IPC: H02K9/08 , H02K3/22 , H02K3/12 , H02K1/32 , H02K3/24 , H02K9/197 , H02K9/00 , H02K3/30 , H02K3/34
Abstract: An electric machine comprising a rotor, a stator, a plurality of bare conductors forming a plurality of windings in at least one of the stator and the rotor, and a fluid in direct physical contact with a plurality of outer surfaces of the plurality of bare conductors, wherein the fluid is electrically insulating and provides direct fluid cooling, to provide cooling for the plurality of bare conductors and electrical insulation between consecutive bare conductors of the plurality of bare conductors.
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