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公开(公告)号：US20180230845A1
公开(公告)日：2018-08-16
申请号：US15430052
申请日：2017-02-10
Applicant: General Electric Company
Inventor： Narendra Digamber Joshi , Michael Solomon Idelchik
CPC classification number: F01D15/10 , B64C11/30 , B64D27/18 , B64D27/24 , B64D2027/026 , F02C6/00 , F02C6/14 , F02C7/32 , F02C7/36 , F02K3/06 , F02K5/00 , F05D2220/323 , F05D2220/36 , F05D2220/76
Abstract: A propulsion system for an aircraft includes a turbomachine, a primary fan, and an electric machine. The turbomachine includes a first turbine and a second turbine, with at least one of the first turbine or second turbine operably connected to the electric machine and the second turbine driving the primary fan. The propulsion system additionally includes an auxiliary propulsor assembly configured to be mounted at a location away from the turbomachine and the primary fan. The electric machine is in electrical communication with the auxiliary propulsor assembly for transferring power with the auxiliary propulsor assembly during operation of the propulsion system.
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公开(公告)号：US20180229851A1
公开(公告)日：2018-08-16
申请号：US15672448
申请日：2017-08-09
Applicant: General Electric Company
Inventor： Narendra Digamber Joshi , Michael Solomon Idelchik
CPC classification number: B64D31/06 , B64D27/18 , B64D27/24 , B64D2027/026 , B64D2033/024 , F02C9/16 , G05D17/02 , Y02T50/62
Abstract: An aircraft propulsor assembly includes a fan having a nacelle and plural fan blades radially disposed within the nacelle. The fan blades are configured to be rotated by torque generated by a turbine engine of an aircraft to generate thrust for propelling the aircraft. The assembly also includes an electric motor including a stator in the nacelle of the fan and a rotor in tips of two or more of the fan blades. The electric motor is configured to generate torque that also rotates the fan blades to generate thrust for propelling the aircraft. The assembly also includes a controller configured to reduce or prevent an increase in an operating temperature of the turbine engine of the aircraft by automatically supplanting at least some of the torque generated by the turbine engine with the torque generated by the electric motor.
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23.发明公开公开(公告)号：US20230228199A1
公开(公告)日：2023-07-20
申请号：US18180988
申请日：2023-03-09
Applicant: General Electric Company
Inventor： Hrishikesh Keshavan , Byron Andrew Pritchard , Cathleen Ann Hoel , Ambarish Jayant Kulkarni , Michael Solomon Idelchik , Bernard Patrick Bewlay
CPC classification number: F01D5/288 , B23K26/364 , C23C4/11 , C23C28/3215 , C23C28/3455 , F01D5/005 , F01D5/284 , F01D25/007 , F05D2230/90 , F05D2300/611
Abstract: A coated component including a slotted ceramic coating with a reactive phase coating disposed thereon for improved resistance to environmental contaminant compositions, along with methods of its formation, is provided. The coated component may include a substrate defining a surface, a ceramic coating disposed on the surface of the substrate, and a reactive phase coating disposed on the layer of environmental contaminant compositions. The ceramic coating includes a plurality of slots disposed in the ceramic coating forming segments of ceramic coating material.
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Patent Agency Ranking
公开(公告)号：US10822103B2
公开(公告)日：2020-11-03
申请号：US15672448
申请日：2017-08-09
Applicant: General Electric Company
Inventor： Narendra Digamber Joshi , Michael Solomon Idelchik
Abstract: An aircraft propulsor assembly includes a fan having a nacelle and plural fan blades radially disposed within the nacelle. The fan blades are configured to be rotated by torque generated by a turbine engine of an aircraft to generate thrust for propelling the aircraft. The assembly also includes an electric motor including a stator in the nacelle of the fan and a rotor in tips of two or more of the fan blades. The electric motor is configured to generate torque that also rotates the fan blades to generate thrust for propelling the aircraft. The assembly also includes a controller configured to reduce or prevent an increase in an operating temperature of the turbine engine of the aircraft by automatically supplanting at least some of the torque generated by the turbine engine with the torque generated by the electric motor.
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25.发明申请公开(公告)号：US20190381524A1
公开(公告)日：2019-12-19
申请号：US16557317
申请日：2019-08-30
Applicant: General Electric Company
Inventor： Ambarish Jayant Kulkarni , Hrishikesh Keshavan , Mehmet Dede , Bernard Patrick Bewlay , Guanghua Wang , Byron Pritchard , Michael Solomon Idelchik
Abstract: An atomizing spray nozzle device includes an atomizing zone housing that receives different phases of materials used to form a coating. The atomizing zone housing mixes the different phases of the materials into a two-phase mixture of ceramic-liquid droplets in a carrier gas. The device also includes a plenum housing fluidly coupled with the atomizing housing and extending from the atomizing housing to a delivery end. The plenum housing includes an interior plenum that receives the two-phase mixture of ceramic-liquid droplets in the carrier gas from the atomizing zone housing. The device also includes one or more delivery nozzles fluidly coupled with the plenum chamber. The delivery nozzles provide outlets from which the two-phase mixture of ceramic-liquid droplets in the carrier gas is delivered onto one or more surfaces of a target object as the coating on the target object.
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26.发明申请公开(公告)号：US20190143350A1
公开(公告)日：2019-05-16
申请号：US15835762
申请日：2017-12-08
Applicant: General Electric Company
Inventor： Ambarish Jayant Kulkarni , Hrishikesh Keshavan , Mehmet Dede , Bernard Patrick Bewlay , Guanghua Wang , Byron Pritchard , Michael Solomon Idelchik
Abstract: An atomizing spray nozzle device includes an atomizing zone housing that receives different phases of materials used to form a coating. The atomizing zone housing mixes the different phases of the materials into a two-phase mixture of ceramic-liquid droplets in a carrier gas. The device also includes a plenum housing fluidly coupled with the atomizing housing and extending from the atomizing housing to a delivery end. The plenum housing includes an interior plenum that receives the two-phase mixture of ceramic-liquid droplets in the carrier gas from the atomizing zone housing. The device also includes one or more delivery nozzles fluidly coupled with the plenum chamber. The delivery nozzles provide outlets from which the two-phase mixture of ceramic-liquid droplets in the carrier gas is delivered onto one or more surfaces of a target object as the coating on the target object.
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公开(公告)号：US10077660B2
公开(公告)日：2018-09-18
申请号：US14802074
申请日：2015-07-17
Applicant: General Electric Company
Abstract: A turbine engine assembly is provided. The assembly includes a low-pressure turbine assembly including a first turbine section configured to rotate in a first rotational direction at a first rotational speed, and a second turbine section configured to rotate in a second rotational direction at a second rotational speed. The second rotational direction is opposite the first rotational direction and the second rotational speed is lower than the first rotational speed. The assembly also includes a first drive shaft coupled to the first turbine section, and a fan assembly including a first fan section coupled to the first drive shaft such that the first fan section rotates in the first rotational direction at the first rotational speed, and a second fan section coupled to the second turbine section such that the second fan section rotates in the second rotational direction at the second rotational speed.
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公开(公告)号：US20150167544A1
公开(公告)日：2015-06-18
申请号：US14103928
申请日：2013-12-12
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Narendra Digamber Joshi , Michael Solomon Idelchik
IPC: F02B53/04
Abstract: A tuned cavity rotating detonation combustion system includes a an annular chamber having an inlet and an outlet; a valve plate at the inlet of the annular chamber and comprising a plurality of openings spaced circumferentially around the inlet; a plurality of tubes each having an open end in communication with a corresponding opening of the valve plate and a closed end forming a tuned cavity, and a first opening between the open end and the closed end for injection of air; and a plurality of fuel injectors corresponding to the plurality of tubes, each fuel injector being configured to inject fuel into the tube between the first opening and the open end. Each of the tuned cavities has a length sized to resonate at a same frequency as a continuous detonation frequency of at least one detonation wave in the annular chamber. Alternately, or additionally, a plurality of flame arresters corresponding to the plurality of tubes are configured to arrest the at least one detonation wave generated in the detonation chamber from travelling into the tube.
Abstract translation: 调谐腔旋转爆震燃烧系统包括具有入口和出口的环形室; 在所述环形室的入口处的阀板，并且包括围绕所述入口周向间隔开的多个开口; 多个管，其各自具有与所述阀板的对应开口连通的开口端，以及形成调谐空腔的封闭端，以及用于喷射空气的所述开口端和所述封闭端之间的第一开口; 以及对应于所述多个管的多个燃料喷射器，每个燃料喷射器构造成在所述第一开口和所述开放端之间将燃料喷射到所述管中。 调谐空腔中的每一个具有尺寸设定成与环形室中至少一个爆震波的连续爆震频率相同的频率的长度。 替代地或另外地，对应于多个管的多个阻火器被配置为阻止在引爆室中产生的至少一个爆震波行进到管中。
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