公开(公告)号：US20220073199A1

公开(公告)日：2022-03-10

申请号：US17329312

申请日：2021-05-25

Applicant: General Electric Company

Inventor： Randy M. Vondrell ,  Matthew Ryan Polakowski ,  Kurt David Murrow ,  Glenn Crabtree ,  Darek Tomasz Zatorski

IPC: B64C29/00 ,  B64C27/28 ,  H02J50/10 ,  A61L9/12 ,  H02J7/00 ,  B64C21/06 ,  B64D27/14 ,  B64D27/24 ,  H02P9/04

Abstract: A propulsion system of an aircraft has at least one unducted fan and at least one ducted fan, the at least one unducted fan and the at least one ducted fan being powered by an electric power source and rotatable between a vertical thrust position and a forward thrust position, and a controller configured to distribute electrical power between the at least one unducted fan and the at least one ducted fan. During a first mode when the at least one unducted fan and the at least one ducted fan are in the vertical thrust position, the controller is configured to distribute the electrical power between the plurality of unducted fans and the plurality of ducted fans such that the at least one unducted fan is a primary source of thrust.

公开(公告)号：US11124306B2

公开(公告)日：2021-09-21

申请号：US16042328

申请日：2018-07-23

Applicant: General Electric Company

Inventor： Kurt David Murrow ,  Darek Tomasz Zatorski

IPC: B64D27/24 ,  B64D29/04 ,  B64C3/10 ,  B64D27/08 ,  B64C29/00 ,  B64C3/32 ,  B64D35/02 ,  B64C3/38 ,  B64D33/04 ,  B64D31/06 ,  B64D27/02 ,  B64D27/26 ,  H02K7/18

Abstract: An aircraft includes a fuselage; a propulsion system including a power source and a vertical thrust electric fan driven by the power source; and a wing extending from the fuselage. The vertical thrust electric fan is positioned on or within the wing, the wing including a diffusion assembly movable between a first position and a second position and positioned at least partially downstream of the vertical thrust electric fan when in the second position, the diffusion assembly including a first member and a second member, the second member movable generally along the vertical direction relative to the first member such that the first member and second member together define at least in part an exhaust flowpath for the first vertical thrust electric fan when the diffusion assembly is in the second position.

公开(公告)号：US11046428B2

公开(公告)日：2021-06-29

申请号：US16502913

申请日：2019-07-03

Applicant: General Electric Company

Inventor： Randy M. Vondrell ,  Matthew Ryan Polakowski ,  Kurt David Murrow ,  Glenn Crabtree ,  Darek Tomasz Zatorski

IPC: B64C29/00 ,  B64C27/28 ,  H02J50/10 ,  A61L9/12 ,  H02J7/00 ,  H02J7/02 ,  B64C21/06 ,  B64D27/14 ,  B64D27/24 ,  H02P9/04 ,  B64C3/38 ,  B64D27/02

Abstract: A method for operating a propulsion system of an aircraft includes moving a plurality of forward and aft propulsors to a vertical thrust position. While in the vertical thrust positions, the method also includes providing a first forward to aft ratio of electric power to the plurality of forward and aft propulsors. The method also includes moving the plurality of forward and aft propulsors to a forward thrust position. While in the forward thrust positions, the method also includes providing a second forward to aft ratio of electric power to the plurality of forward and aft propulsors. The first forward to aft ratio of electric power is different than the second forward to aft ratio of electric power to provide certain efficiencies for the aircraft.

公开(公告)号：US10822101B2

公开(公告)日：2020-11-03

申请号：US15699349

申请日：2017-09-08

Applicant: General Electric Company

Inventor： Kurt David Murrow ,  Darek Tomasz Zatorski ,  Andrew Breeze-Stringfellow ,  Randy M. Vondrell ,  Dominic Barone

IPC: B64D27/24 ,  B64C3/32 ,  B64C29/00 ,  B64C3/38 ,  B64D29/04 ,  B64D27/08 ,  B64D35/02 ,  B64D33/04 ,  B64D31/06 ,  B64D27/02 ,  B64D27/26 ,  H02K7/18

Abstract: An aircraft includes a fuselage; a wing coupled to, and extending from, the fuselage; and a hybrid-electric propulsion system. The hybrid-electric propulsion system includes a power source including a combustion engine and an electric generator; a plurality of vertical thrust electric fans integrated into the wing and oriented to generate thrust along the vertical direction, the plurality of vertical thrust electric fans arranged along a length of the wing and driven by the power source; and a forward thrust propulsor. The forward thrust propulsor it is selectively or permanently mechanically coupled to the combustion engine.

公开(公告)号：US10737797B2

公开(公告)日：2020-08-11

申请号：US15699315

申请日：2017-09-08

Applicant: General Electric Company

Inventor： Kurt David Murrow ,  Darek Tomasz Zatorski ,  Andrew Breeze-Stringfellow ,  Dominic Barone

IPC: B64D27/24 ,  B64C29/00 ,  B64C3/32 ,  B64D27/08 ,  B64D29/04 ,  B64D35/02 ,  B64C3/38 ,  B64D33/04 ,  B64D31/06 ,  B64D27/02 ,  B64D27/26 ,  H02K7/18

Abstract: An aircraft includes a fuselage; a wing coupled to, and extending from, the fuselage; and a propulsion system. The propulsion system includes a plurality of electric fans integrated into the wing and oriented to generate thrust along a vertical direction, the plurality of electric fans arranged along a length of the wing and including an outer-most electric fan along a transverse direction relative to the fuselage. The outer-most electric fan is at least one of a variable pitch fan or a variable speed fan to provide increased stability to the aircraft.

公开(公告)号：US20200251970A1

公开(公告)日：2020-08-06

申请号：US16691975

申请日：2019-11-22

Applicant: General Electric Company

Inventor： Darek Tomasz Zatorski ,  Jia Xiaochuan ,  Kurt David Murrow

IPC: H02K16/02 ,  H02K5/173 ,  H02K5/18 ,  H02K5/20 ,  H02K7/08 ,  H02K9/19 ,  H02K13/00 ,  B64C27/10 ,  B64D27/24

Abstract: An electric machine for a drive system having a first DS rotor and a second DS rotor includes a first EM rotor rotatable about an axis in a first circumferential direction and including a plurality of magnets, the first EM rotor configured for mechanical coupling to the first DS rotor; and a second EM rotor rotatable about the axis in a second circumferential direction and including a plurality of windings, the second EM rotor configured for mechanical coupling to the second DS rotor and the plurality of magnets of the first EM rotor operably engaged with the plurality of windings of the second EM rotor.

公开(公告)号：US10384773B2

公开(公告)日：2019-08-20

申请号：US15259622

申请日：2016-09-08

Applicant: General Electric Company

Inventor： Randy M. Vondrell ,  Matthew Ryan Polakowski ,  Kurt David Murrow ,  Glenn Crabtree ,  Darek Tomasz Zatorski

IPC: B64C29/00 ,  B64C21/06 ,  B64D27/14 ,  B64D27/24 ,  H02K7/18 ,  B64D27/20 ,  B64D29/04 ,  B64D27/02

Abstract: An aircraft includes a fuselage and a wing assembly attached to or formed integrally with the fuselage. The aircraft also includes a propulsion system having a port propulsor and a starboard propulsor. The port and starboard propulsors are each attached to the wing assembly on opposing sides of the fuselage and are rotatable between a forward thrust position and a vertical thrust position. The propulsion system also includes a supplemental propulsor mounted to the fuselage to provide certain efficiencies for the aircraft.

公开(公告)号：US10381889B2

公开(公告)日：2019-08-13

申请号：US14317294

申请日：2014-06-27

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

IPC: H02K1/28 ,  H02K1/27 ,  H02K1/18 ,  H02K1/30 ,  H02K21/24 ,  H02K49/10 ,  H02K21/02

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 configured to generate a magnetic field and extending along a longitudinal axis with an inner surface defining a cavity and a rotor assembly including a rotor core and a rotor shaft. The rotor core is disposed inside the stator cavity and configured to rotate about the longitudinal axis. The rotor assembly further including a plurality of permanent magnets for generating a magnetic field which interacts with the stator magnetic field to produce torque. The permanent magnets are disposed within one or more cavities formed in a sleeve component. The sleeve component configured to include a plurality of cavities or voids therein and thus provide minimal weight to the permanent magnet machine. The permanent magnet machine providing increased centrifugal load capacity, increased power density and improved electrical performance.

公开(公告)号：US20190165708A1

公开(公告)日：2019-05-30

申请号：US15823952

申请日：2017-11-28

Applicant: General Electric Company

Inventor： Justin Paul Smith ,  Kurt David Murrow ,  Darek Tomasz Zatorski ,  Patrick Michael Marrinan

IPC: H02P9/04 ,  F02C7/36 ,  F02C9/32 ,  H02P9/00

Abstract: A turbomachine and method for operating a turbomachine comprising a first rotatable component and a second rotatable component each defining a rotatable speed mechanically independent of one another, and an electric machine electrically coupled to the first rotatable component and the second rotatable component such that a load level relative to the first rotatable component and the second rotatable component is adjustable is generally provided. The method includes adjusting a first load at a first rotor assembly of the electric machine electrically coupled to the first rotatable component such that a first speed of the first rotatable component is increased or decreased based on an engine condition and the first load; adjusting a second load at a second rotor assembly of the electric machine electrically coupled to the second rotatable component such that a second speed of the second rotatable component is decreased or increased based on the engine condition and the second load; and transferring electrical energy generated from at least one of the first rotatable component or the second rotatable component.

公开(公告)号：US20190061964A1

公开(公告)日：2019-02-28

申请号：US16042439

申请日：2018-07-23

Applicant: General Electric Company

Inventor： Kurt David Murrow

IPC: B64D27/24 ,  B64D31/06 ,  B64C29/00 ,  F02C7/36

Abstract: A method is provided for operating a propulsion system of a vertical takeoff and landing aircraft, the propulsion system including a turbomachine, an electric machine, a forward thrust propulsor, and a plurality of vertical thrust electric fans. The method includes driving the forward thrust propulsor with the turbomachine; rotating the electric machine with the turbomachine to generate electrical power; determining a failure condition of the turbomachine; and providing electrical power to the electric machine to drive the forward thrust propulsor with the electric machine in response to determining the failure condition of the turbomachine.