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公开(公告)号：US11149954B2
公开(公告)日：2021-10-19
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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112.发明授权公开(公告)号：US10920595B2
公开(公告)日：2021-02-16
申请号：US15405656
申请日：2017-01-13
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Narendra Digamber Joshi , Nicholas Joseph Kray , Samar Jyoti Kalita , Paul Marsland , Wayne Spence
IPC: F01D5/14 , B22F5/04 , F01D9/04 , F01D25/00 , B33Y10/00 , B22F3/105 , B23K26/342 , B23K26/082 , B33Y80/00 , B23K101/00 , B23K103/18
Abstract: The present disclosure generally relates to turbine engine components having multiple controlled metallic grain orientations. In general, the primary grain orientation is aligned substantially perpendicular to the longitudinal axis of the turbine engine component while the secondary grain orientation is aligned substantially parallel to the longitudinal axis. Such controlled grain orientations provide the blades and vanes with increased strength to withstand the thermal-mechanical stresses of the turbine operation. The disclosure also relates to turbines having these fortified components, and methods of manufacturing the components.
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公开(公告)号：US10807730B2
公开(公告)日：2020-10-20
申请号：US16229125
申请日：2018-12-21
Applicant: General Electric Company
Inventor： Narendra Digamber Joshi , Konrad Weeber , Michael Solomon Idelchik
Abstract: A motor driven propulsor of an aircraft includes magnets disposed in fan shrouds of fan blades connected with a fan hub, a stator having individual conductive coils in a nacelle located radially outside of the fan hub, and a distributed inverter assembly having several inverter power stages and gate drivers, each of the inverter power stages coupled with a separate gate driver of the gate drivers and a separate coil of the coils in the stator. Each of the gate drivers is configured to individually control supply of direct current to the corresponding inverter power stage. Each of the inverter power stages is configured to convert the direct current supplied to the inverter power stage to an alternating current that is supplied to the corresponding coil in the stator to rotate the magnets and the fan blades around a center line of the fan hub for propelling the aircraft.
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公开(公告)号：US10807703B2
公开(公告)日：2020-10-20
申请号：US16039621
申请日：2018-07-19
Applicant: General Electric Company
Inventor： Nicholas William Rathay , Narendra Digamber Joshi
Abstract: A combustion system includes at least one plasma actuator disposed along a substrate at a plasma location, and at least one fuel injector disposed along the substrate at an injection location. The fuel injector disperses fuel toward the plasma location. The plasma from plasma actuator ignites fuel from the fuel injector proximate the plasma location.
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公开(公告)号：US20200248906A1
公开(公告)日：2020-08-06
申请号：US16267469
申请日：2019-02-05
Applicant: General Electric Company
Inventor： Kapil Kumar Singh , Narendra Digamber Joshi , Joel Meier Haynes , Venkat Eswarlu Tangirala , Meghan Borz
Abstract: A rotating detonation combustor includes an annular combustion passage that is non-circular. Specifically, the present rotating detonation combustor includes a forward wall, a radially inner wall, and a radially outer wall. The radially inner wall and the radially outer wall extend downstream from the forward wall around a longitudinal axis of the combustor, thus defining an annular passage between the radially inner wall and the radially outer wall. An air inlet and a fuel inlet are disposed proximate to the forward wall and in fluid communication with the annular passage. The cross-section of the annular passage, which can be elliptical or polygonal, is defined by arcuate and/or straight sides of the inner and outer walls.
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Patent Agency Ranking
公开(公告)号：US10724376B2
公开(公告)日：2020-07-28
申请号：US15891401
申请日：2018-02-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Nitesh Jain , Nagashiresha Gontla , Narendra Digamber Joshi , Paul Gerard Marsland , Wayne Allen Spence
Abstract: A blade and a turbomachine engine having the blade are disclosed. The blade includes an airfoil having a root portion, a tip portion, and a plurality of fins integrally coupled to the root portion. The plurality of fins is disposed along a thickness of the airfoil.
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公开(公告)号：US20190326789A1
公开(公告)日：2019-10-24
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：US20190309951A1
公开(公告)日：2019-10-10
申请号：US15987070
申请日：2018-05-23
Applicant: General Electric Company
Inventor： Narendra Digamber Joshi , Shawn David Wehe , ShihYang Hsieh , Changjin Yoon , Owen James Sullivan Rickey , Joseph Douglas Monty
Abstract: A combustor includes a circumferential main combustion chamber and a plurality of air inlets, the plurality of air inlets dispersing air into the circumferential main combustion chamber. The combustor also includes at least one swirl-stabilized pilot burner, which disperses combustion gases into the circumferential main combustion chamber. The air inlets and the swirl-stabilized pilot burner are aligned at least partially in a radial direction and at least partially in a circumferential direction.
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公开(公告)号：US20190017441A1
公开(公告)日：2019-01-17
申请号：US15651088
申请日：2017-07-17
Applicant: General Electric Company
Inventor： Krishnakumar Venkatesan , Narendra Digamber Joshi
Abstract: A gas turbine engine combustor includes a dome plate, an inner liner, and an outer liner. The inner liner and the outer liner are separately coupled to a rear side of the dome plate and both extend rearward therefrom. The outer and inner liners define an annular combustion chamber therebetween that extends rearward from the dome plate. At least one of the outer liner or the dome plate includes an igniter cavity formed therein that is separated from the combustion chamber by a partition wall. The partition wall defines one or more transfer holes therethrough that fluidly connect the igniter cavity to the combustion chamber.
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120.发明申请公开(公告)号：US20190003713A1
公开(公告)日：2019-01-03
申请号：US16132430
申请日：2018-09-16
Applicant: General Electric Company
Inventor： Sarah Marie Monahan , Joel Meier Haynes , Narendra Digamber Joshi , David James Walker , Junwoo Lim , Krishna Kumar Venkatesan
Abstract: An air-shielded fuel injection assembly for use in a combustion chamber of a turbine assembly. The air-shielded fuel injection assembly generally includes a fuel manifold including a plurality of fuel injection ports and an air manifold including a plurality of air injection ports. Each of the plurality of fuel injection ports is configured to introduce a fuel column into an annular cavity of a mixer assembly. Each of the plurality of air injection ports is configured to introduce an air curtain about an associated fuel injection column to minimize recirculation upstream of the fuel injection column and increase penetration of the fuel injection column into the cavity. Also disclosed are a mixer assembly and a turbine assembly including the air-shielded fuel injection assembly.
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