Patents by Inventor Darek Tomasz Zatorski

Darek Tomasz Zatorski has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Publication number: 20210339879
    Abstract: An aircraft defines a vertical direction and includes a fuselage and a propulsion system comprising a power source and a plurality of vertical thrust electric fans driven by the power source. A wing extends from the fuselage. The plurality of vertical thrust electric fans are arranged along a length of the wing along a lengthwise direction of the wing. The wing comprises a diffusion assembly along the lengthwise direction of the wing and includes a first diffusion member positioned downstream of at least one of the plurality of vertical thrust electric fans. The first diffusion member defines a curved shape relative to a longitudinal direction of the aircraft. The longitudinal direction is generally perpendicular to the lengthwise direction of the wing.
    Type: Application
    Filed: July 2, 2021
    Publication date: November 4, 2021
    Inventors: Kurt David Murrow, Andrew Breeze-Stringfellow, Darek Tomasz Zatorski, Dominic Barone
  • Patent number: 11156128
    Abstract: A method is provided for maintaining a gas turbine engine installed on an aircraft, the gas turbine engine including an electric machine mounted at least partially inward of a core air flowpath of the gas turbine engine. The method includes removing a rotor mount connecting a rotor of the electric machine to a rotary component of the gas turbine engine; removing a stator mount connecting a stator of the electric machine to a stationary component of the gas turbine engine; and removing in situ the electric machine.
    Type: Grant
    Filed: August 22, 2018
    Date of Patent: October 26, 2021
    Assignee: General Electric Company
    Inventors: Brandon Wayne Miller, Randy M. Vondrell, Darek Tomasz Zatorski, Christopher Charles Glynn
  • Patent number: 11124306
    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.
    Type: Grant
    Filed: July 23, 2018
    Date of Patent: September 21, 2021
    Assignee: General Electric Company
    Inventors: Kurt David Murrow, Darek Tomasz Zatorski
  • Patent number: 11124307
    Abstract: An aircraft includes a fuselage; a propulsion system including a power source and a plurality of vertical thrust electric fans driven by the power source; and a wing extending from the fuselage. The plurality of vertical thrust electric fans are arranged along the wing, the wing including one or more components being moveable to selectively expose the plurality of vertical thrust electric fans, the wing further including a diffusion assembly positioned downstream of at least one vertical thrust electric fan of the plurality of vertical thrust electric fans, the diffusion assembly defining a diffusion area ratio greater than 1:1 and less than about 2:1.
    Type: Grant
    Filed: July 23, 2018
    Date of Patent: September 21, 2021
    Assignee: General Electric Company
    Inventors: Kurt David Murrow, Andrew Breeze-Stringfellow, Darek Tomasz Zatorski, Dominic Barone
  • Patent number: 11117676
    Abstract: An aircraft includes a fuselage; a propulsion system including a power source and a plurality of vertical thrust electric fans driven by the power source; and a wing extending from the fuselage. The plurality of vertical thrust electric fans are arranged along a length of the wing, the wing including a variable geometry assembly moveable generally along a horizontal direction between a forward thrust position and a vertical thrust position, the variable geometry assembly at least partially covering at least one vertical thrust electric fan of the plurality of vertical thrust electric fans when in the forward thrust position and at least partially exposing the at least one vertical thrust electric fan when in the vertical thrust position.
    Type: Grant
    Filed: July 23, 2018
    Date of Patent: September 14, 2021
    Assignee: General Electric Company
    Inventors: Kurt David Murrow, Andrew Breeze-Stringfellow, Darek Tomasz Zatorski, Dominic Barone
  • Patent number: 11117675
    Abstract: An aircraft includes a fuselage; a propulsion system including a power source and a plurality of vertical thrust electric fans driven by the power source; and a wing extending from the fuselage. The plurality of vertical thrust electric fans are arranged along a length of the wing, the wing including a variable geometry assembly extending along the length of the wing and moveable between a forward thrust position and a vertical thrust position, the variable geometry assembly at least partially covering the plurality of vertical thrust electric fans when in the forward thrust position and at least partially exposing the plurality of vertical thrust electric fans when in the vertical thrust position.
    Type: Grant
    Filed: July 23, 2018
    Date of Patent: September 14, 2021
    Assignee: General Electric Company
    Inventors: Kurt David Murrow, Andrew Breeze-Stringfellow, Darek Tomasz Zatorski, Dominic Barone
  • Publication number: 20210277832
    Abstract: Turbomachines and turbine sections of a turbomachine are provided. For example, a turbomachine comprises a turbine section having a turbine comprising a first plurality and a second plurality of turbine rotor blades, which are alternatingly spaced along an axial direction. At least one turbine blade of the first plurality of turbine blades is attached to a first support member assembly and at least one turbine blade of the second plurality of turbine blades is attached to a second support member assembly. The turbomachine further comprises a spool that connects the turbine with one or more components outside the turbine section, a first rotational support, and a gearbox. Both the first support member assembly and the second support member assembly are attached to the first rotational support and coupled to the gearbox such that the first and second pluralities of turbine rotor blades are rotatable with one another through the gearbox.
    Type: Application
    Filed: February 18, 2021
    Publication date: September 9, 2021
    Inventors: Roberto Maddaleno, Matteo Renato Usseglio, Darek Tomasz Zatorski
  • Patent number: 11105200
    Abstract: The present disclosure is directed to a turbine engine defining a longitudinal direction, a radial direction, and a circumferential direction. The turbine engine includes a power turbine including a first turbine rotor assembly interdigitated with a second turbine rotor assembly along the longitudinal direction; a gear assembly coupled to the first turbine rotor assembly and the second turbine rotor assembly, wherein the gear assembly includes a first input interface coupled to the first turbine rotor assembly, a second input interface coupled to the second turbine rotor assembly, and one or more third gears coupled to the first input interface and the second input interface therebetween; and a first output shaft and a second output shaft, wherein each of the first output shaft and the second output shaft are configured to couple to an electrical load device.
    Type: Grant
    Filed: July 13, 2017
    Date of Patent: August 31, 2021
    Assignee: General Electric Company
    Inventors: Jeffrey Donald Clements, Darek Tomasz Zatorski, Brandon Wayne Miller, Joseph Robert Dickman
  • Patent number: 11098592
    Abstract: A turbomachine includes a spool; and a turbine section including a turbine and a turbine center frame. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along an axial direction and rotatable with one another. The turbomachine also includes a first support member, the first plurality of turbine rotor blades coupled to the spool through the first support member; a second support member, the second plurality of turbine rotor blades supported by the second support member; and a bearing assembly including a first bearing and a second bearing, the first bearing and the second bearing each rotatably supporting the second support member and each being supported by the turbine center frame.
    Type: Grant
    Filed: September 20, 2017
    Date of Patent: August 24, 2021
    Assignee: General Electric Company
    Inventors: Peeyush Pankaj, Shashank Suresh Puranik, Darek Tomasz Zatorski, Christopher Charles Glynn, Richard Schmidt, Bhaskar Nanda Mondal
  • Publication number: 20210249978
    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.
    Type: Application
    Filed: April 28, 2021
    Publication date: August 12, 2021
    Inventors: Justin Paul Smith, Kurt David Murrow, Darek Tomasz Zatorski, Patrick Michael Marrinan
  • Patent number: 11085310
    Abstract: A gas turbine engine including a core having in serial flow order a compressor, a combustor, and a turbine—the compressor, combustor, and turbine together defining a core air flowpath. The gas turbine engine additionally includes a fan section mechanically coupled to the core, the fan section including a plurality of fan blades, and each of the plurality fan blades defining a pitch axis. An actuation device is operable with the plurality fan blades for rotating the plurality fan blades about their respective pitch axes, the actuation device including an actuator located outward of the core air flowpath to, e.g., simplify the gas turbine engine.
    Type: Grant
    Filed: November 13, 2018
    Date of Patent: August 10, 2021
    Assignee: General Electric Company
    Inventors: Daniel Alan Niergarth, Darek Tomasz Zatorski, Brandon Wayne Miller
  • Patent number: 11053014
    Abstract: A method for operating a vertical takeoff and landing aircraft includes modifying a first variable component of a wing associated with a first portion of the plurality of vertical thrust electric fans relative to a second variable component of the wing associated with a second portion of the plurality of vertical thrust electric fans to adjust an exposure ratio of the first portion of the plurality of vertical thrust electric fans relative to the second portion of the plurality of vertical thrust electric fans.
    Type: Grant
    Filed: July 23, 2018
    Date of Patent: July 6, 2021
    Assignee: General Electric Company
    Inventors: Kurt David Murrow, Andrew Breeze-Stringfellow, Darek Tomasz Zatorski, Dominic Barone
  • Patent number: 11046428
    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.
    Type: Grant
    Filed: July 3, 2019
    Date of Patent: June 29, 2021
    Assignee: General Electric Company
    Inventors: Randy M. Vondrell, Matthew Ryan Polakowski, Kurt David Murrow, Glenn Crabtree, Darek Tomasz Zatorski
  • Patent number: 11040779
    Abstract: An aircraft includes a fuselage; a propulsion system including a power source and a vertical thrust electric fan oriented to generate thrust along a vertical direction and powered by the power source; and a wing extending from the fuselage and including the vertical thrust electric fan positioned at least partially therein. The wing includes a variable geometry assembly having partial wing assembly, the partial wing assembly including a frame and a first member, the partial wing assembly moveable generally along a longitudinal direction when the variable geometry assembly is moved between a forward thrust position and a vertical thrust position, the first member moveable relative to the frame to form an exhaust path for the vertical thrust electric fan.
    Type: Grant
    Filed: July 23, 2018
    Date of Patent: June 22, 2021
    Assignee: General Electric Company
    Inventors: Kurt David Murrow, Darek Tomasz Zatorski, Dominic Barone
  • Patent number: 11028718
    Abstract: The present disclosure is directed to a gas turbine engine including a turbine rotor, a turbine frame at least partially surrounding the turbine rotor, and an outer diameter seal assembly. The turbine rotor includes an inner shroud, an outer shroud, and at least one connecting airfoil coupling the inner shroud and the outer shroud. The outer shroud includes a plurality of outer shroud airfoils extended inward along a radial direction. The outer diameter seal assembly includes a sliding portion disposed between the turbine frame and the outer shroud of the turbine rotor. The outer diameter seal assembly defines a secondary tooth at the outer shroud radially inward of a longitudinal face of the sliding portion, and a primary tooth defined axially adjacent to a radial face of the sliding portion.
    Type: Grant
    Filed: September 19, 2019
    Date of Patent: June 8, 2021
    Assignee: General Electric Company
    Inventors: Nathan Evan McCurdy Gibson, Darek Tomasz Zatorski
  • Patent number: 11008883
    Abstract: A turbomachine includes a turbine section including a turbine. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades, the first plurality of turbine rotor blades and second plurality of turbine rotor blades alternatingly spaced along the axial direction. The turbomachine also includes a gearbox. The first plurality of turbine rotor blades and the second plurality of turbine rotor blades are each coupled to one of a ring gear, a planet gear, or a sun gear of the gearbox such that the first plurality of turbine rotor blades is rotatable with the second plurality of turbine rotor blades through the gearbox. The turbomachine also includes an electric machine assembly including a rotor coupled to one of the ring gear, the planet gear, or the sun gear of the gearbox such that the rotor rotates relative to a stator during operation.
    Type: Grant
    Filed: September 20, 2017
    Date of Patent: May 18, 2021
    Assignee: General Electric Company
    Inventors: Darek Tomasz Zatorski, Gert Johannes van der Merwe, Brandon Wayne Miller, Daniel Alan Niergarth
  • Patent number: 10998837
    Abstract: A turbomachine and method for operation turbomachine are provided, the method including adjusting a first load at a first electric machine operably coupled to a first rotatable component, in which the first electric machine is operably 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 electric machine operably coupled to a second rotatable component, in which the second electric machine is operably 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 energy generated from at least one of the first electric machine or the second electric machine.
    Type: Grant
    Filed: April 2, 2020
    Date of Patent: May 4, 2021
    Assignee: General Electric Company
    Inventors: Justin Paul Smith, Kurt David Murrow, Darek Tomasz Zatorski, Patrick Michael Marrinan
  • Patent number: 10961850
    Abstract: A gas turbine engine including a torque frame is provided. The torque frame includes an inner shroud defined circumferentially around the axial centerline, an outer shroud surrounding the inner shroud and defined circumferentially around the axial centerline, and a structural member extended along the radial direction and coupled to the inner shroud and the outer shroud. The torque frame is configured to rotate around the axial centerline.
    Type: Grant
    Filed: September 19, 2017
    Date of Patent: March 30, 2021
    Assignee: General Electric Company
    Inventors: Gert Johannes van der Merwe, Darek Tomasz Zatorski, Richard Alan Wesling, Jeffrey Donald Clements
  • Patent number: 10914194
    Abstract: A turbomachine includes a spool and a turbine section including a turbine rear frame, a turbine, and a support member. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades, the first plurality of turbine rotor blades and second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The support member extends between the first plurality of turbine rotor blades and the spool and couples the first plurality of turbine rotor blades to the spool. The turbomachine also includes a bearing assembly including a bearing, the bearing rotatably supporting the support member and supported by the turbine rear frame, the bearing spaced apart from the spool along the radial direction.
    Type: Grant
    Filed: September 20, 2017
    Date of Patent: February 9, 2021
    Assignee: General Electric Company
    Inventors: Peeyush Pankaj, Shashank Suresh Puranik, Darek Tomasz Zatorski, Christopher Charles Glynn, Richard Schmidt, Bhaskar Nanda Mondal
  • Patent number: 10907495
    Abstract: A unshrouded vane assembly for an unducted propulsion system includes a plurality of vanes which have non-uniform characteristics configured to generate a desired vane exit swirl angle.
    Type: Grant
    Filed: May 11, 2020
    Date of Patent: February 2, 2021
    Assignee: General Electric Company
    Inventors: Andrew Breeze-Stringfellow, Darek Tomasz Zatorski, Richard David Cedar