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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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公开(公告)号：US10724741B2
公开(公告)日：2020-07-28
申请号：US15150844
申请日：2016-05-10
Applicant: General Electric Company
Inventor： Shashank Yellapantula , Anthony John Dean , Narendra Digamber Joshi , Mehmet Muhittin Dede , Jin Yan , Owen James Sullivan Rickey
Abstract: A fuel nozzle assembly includes a centerbody including an outer wall. The outer wall defines a plurality of fuel injection apertures. The fuel injection apertures include a first portion of the plurality of fuel injection apertures configured to induce a first fuel flow rate. The fuel injection apertures also include a second portion of the plurality of fuel injection apertures configured to induce a second fuel flow rate. The second fuel flow rate is less than the first fuel flow rate.
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公开(公告)号：US10720804B2
公开(公告)日：2020-07-21
申请号：US16454419
申请日：2019-06-27
Applicant: General Electric Company
Inventor： Narendra Digamber Joshi , Manoj Ramprasad Shah , James William Bray , Randy Marinus Vondrell , Kurt David Murrow , Jeffrey Anthony Hamel , Samuel Jacob Martin
Abstract: A permanent magnet machine and a rotor assembly for the permanent magnet machine. The permanent magnet machine includes a stator assembly including a stator core including a stator winding to produce electrical currents. The stator assembly extending along a longitudinal axis with an inner surface defining a cavity. The rotor assembly including a rotor core and a rotor shaft. The rotor core is disposed inside the stator cavity and rotates about the longitudinal axis. The rotor assembly including a plurality of permanent magnets for generating a magnetic field which interacts with the stator winding to produce the electrical currents in response to rotation of the rotor assembly. within one or more cavities formed in a sleeve component. The sleeve component is configured to include a plurality of cavities or voids into which the permanent magnets are disposed to retain the permanent magnets therein and form an interior permanent magnet generator.
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公开(公告)号：US20200079513A1
公开(公告)日：2020-03-12
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：US20200023942A1
公开(公告)日：2020-01-23
申请号：US16372546
申请日：2019-04-02
Applicant: General Electric Company
Inventor： Nicholas William Rathay , Narendra Digamber Joshi
Abstract: An aircraft includes a first leading edge defining the forward edge of a left aircraft wing, a second leading edge defining the forward edge of a right aircraft wing, a plurality of plasma actuators disposed along the first and second leading edges, a control processing unit communicatively coupled to each plasma actuator, and at least one flight stability sensor communicatively coupled to the control processing unit. The control processing unit commands at least one plasma actuator to generate plasma in response to a signal from the flight stability sensor.
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Patent Agency Ranking
公开(公告)号：US20190128529A1
公开(公告)日：2019-05-02
申请号：US15795894
申请日：2017-10-27
Applicant: General Electric Company
Inventor： Venkat Eswarlu Tangirala , Narendra Digamber Joshi
Abstract: A rotating detonation combustion system is generally provided. The rotating detonation combustion system includes an outer wall, an upstream wall, and a radial wall. The outer wall is defined circumferentially around a combustor centerline extended along a lengthwise direction. The outer wall defines a first radius portion generally upstream along the outer wall. A second radius portion is defined generally downstream along the outer wall and a transition portion is defined between the first and second radius portions. The first radius portion defines a first radius greater than a second radius at the second radius portion. The transition portion defines a generally decreasing radius from the first radius portion to the second radius portion. The upstream wall is defined circumferentially around the combustor centerline and is extended along the lengthwise direction and inward radially of the first radius portion of the outer wall. An oxidizer passage is defined within the upstream wall. A combustion chamber is defined downstream of the upstream wall and radially inward of the outer wall. The radial wall is coupled to the outer wall and the upstream wall. A fluid injection opening is defined through at least one of the radial wall or the outer wall adjacent to the combustion chamber.
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公开(公告)号：US20190086086A1
公开(公告)日：2019-03-21
申请号：US15711742
申请日：2017-09-21
Applicant: General Electric Company
Inventor： Venkat Eswarlu Tangirala , Anthony Dean , Narendra Digamber Joshi , Sarah Monahan
Abstract: A cavity stabilized detonation combustor assembly for a rotating detonation engine includes opposing inner and outer walls that are radially spaced apart from each other and that both extend around a center axis of the rotating detonation engine. Detonations in the rotating detonation engine rotate around the center axis of the rotating detonation engine. The assembly also includes opposing leading and trailing cavity walls that are coupled with the inner and outer walls and which radially extend away from the center axis, and an axial wall that is coupled with and connects the leading and trailing cavity walls with each other. The axial wall and the leading and trailing cavity walls define a detonation stabilizing cavity in which detonations of the rotating detonation engine occur and are stabilized.
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公开(公告)号：US10161310B2
公开(公告)日：2018-12-25
申请号：US15012173
申请日：2016-02-01
Applicant: GENERAL ELECTRIC COMPANY
Inventor： William Paul Minnear , Ronald Scott Bunker , Narendra Digamber Joshi , Andrei Tristan Evulet
Abstract: A turbine power generation system with enhanced stabilization of refractory carbides provided by hydrocarbon from high carbon activity gases is disclosed. The disclosure also includes a method of using high carbon activity gases to stabilize hot gas path components.
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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：US09836661B2
公开(公告)日：2017-12-05
申请号：US14560311
申请日：2014-12-04
Applicant: General Electric Company
Inventor： Zhi Zhou , Narendra Digamber Joshi , Rui Zhou , Craig Hoover
CPC classification number: G06K9/00805 , B64F1/228 , G08G5/0013 , G08G5/0021 , G08G5/0026 , G08G5/0082 , G08G5/045 , G08G5/065 , Y02T50/826
Abstract: A method implemented using at least one processor includes receiving a plurality of images acquired from a plurality of image sensors disposed on a vehicle configured to engage an aircraft for ground operations. The method further includes determining at least one parameter about a potential obstacle based on the plurality of images and a machine vision algorithm. The method also includes generating an alert signal based on the at least one parameter, useful for avoiding collision of the aircraft.
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