Patents by Inventor Darek Zatorski

Darek 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: 20220251964
    Abstract: A gas turbine engine includes an electrical machine positioned at least partially inward of a core airflow path, the electrical machine including an electrical rotor component and an electrical stator component, a connecting member positioned between the electrical machine and a rotary member, a disconnection device that is positionable between a disengaged position, in which the disconnection device is disengaged from the connecting member, and an engaged position, in which the disconnection device is engaged with the connecting member, and a controller including a processor, where the processor receives a signal from the electrical machine indicative of a fault, and in response to receiving the signal from the electrical machine indicative of the fault, directs the disconnection device to move from the disengaged position to the engaged position.
    Type: Application
    Filed: February 8, 2021
    Publication date: August 11, 2022
    Applicants: General Electric Company, General Electric Company Polska sp. z o.o., General Electric Deutschland Holding GmbH
    Inventors: Bartlomiej Drozd, Miroslaw Sobaniec, Mohamed Osama, Darek Zatorski
  • Publication number: 20220251965
    Abstract: An electrical machine includes a stator assembly coupled to an engine stator component of a propulsion engine. The stator assembly includes a stator support assembly fixedly attached to the engine stator component and a stator disposed on the stator support structure. An electrical machine shaft is coupled to an end of a shaft of the propulsion engine via an intermediate shaft member extending axially between the end of the shaft and the electrical machine shaft. A bearing support frame extends from the propulsion engine, the bearing support frame defining a bearing cavity in conjunction with the electrical machine shaft. Electrical machine bearings radially extend from the bearing support frame to rotatably contact the electrical machine shaft. A rotor attached to a rotor support structure attached to the electrical machine shaft. The rotor rotates in conjunction with the electrical machine shaft to exchange energy with the shaft of the propulsion engine.
    Type: Application
    Filed: February 8, 2021
    Publication date: August 11, 2022
    Applicants: General Electric Company, General Electric Company Polska sp. z o.o., General Electric Deutschland Holding GmbH
    Inventors: Miroslaw Czarnik, Adam Tomasz Pazinski, Bartlomiej Drozd, Darek Zatorski, Maciej Krzysztof Grunwald, Mohamed Osama, John R. Yagielski
  • Publication number: 20220255401
    Abstract: An electrical machine includes a stator assembly coupled to an engine stator component of a propulsion engine. The stator assembly includes a stator support assembly fixedly attached to the engine stator component and a stator disposed on a supporting surface of the stator support structure. The electrical machine also includes a rotor assembly including a rotor support structure connected to a shaft of the propulsion engine and a rotor attached to the rotor support structure such that the rotor is disposed radially inward of the stator. The rotor exchanges rotational energy with the shaft to operate as either an electrical motor or an electrical generator.
    Type: Application
    Filed: February 8, 2021
    Publication date: August 11, 2022
    Applicants: General Electric Company, General Electric Company Polska sp. z o.o., General Electric Deutschland Holding GmbH
    Inventors: Miroslaw Czarnik, Adam Tomasz Pazinski, Bartlomiej Drozd, Darek Zatorski, Maciej Krzysztof Grunwald, Mohamed Osama, John R. Yagielski
  • Publication number: 20070077144
    Abstract: A gas turbine engine rotor blade includes an airfoil, platform, shank, and dovetail integrally joined together. A dust escape hole extends through the platform adjacent a fillet bridging the platform and shank to bleed dust therefrom during operation.
    Type: Application
    Filed: October 4, 2005
    Publication date: April 5, 2007
    Inventors: Ching-Pang Lee, Darek Zatorski, Brian Norton, Jan Schilling
  • Patent number: 7108480
    Abstract: A method facilitates balancing a gas turbine rotor. The method includes providing a gas turbine rotor including a plurality of turbine blades, wherein at least one turbine blade includes a blade tip shroud that includes a leading edge and a trailing edge that is opposite the leading edge, and coupling a balance clip to the at least one turbine blade. The balance clip includes a first portion having a first length that enables the clip to extend between the tip shroud leading and trailing edges and includes a first hook that couples to the tip shroud leading edge, a shorter second portion that extends only partially from at least one of the tip shroud trailing and leading edges towards the opposite shroud edge, and a second hook that extends between the first and second portions and couples to at least one of the tip shroud leading and trailing edges.
    Type: Grant
    Filed: May 28, 2004
    Date of Patent: September 19, 2006
    Assignee: General Electric Company
    Inventors: Darek Zatorski, Marek Szrajer, Leszek Rzeszutek, John Edward Altman
  • Patent number: 7108479
    Abstract: A method enables a gas turbine engine to be operated. The method comprises supplying cooling fluid into a manifold ring that includes a plurality of distribution ports defined by a sidewall connected by a radially inner wall, channeling the cooling fluid circumferentially through the manifold ring and through at least one distribution port that is defined by a wall that extends arcuately across at least one turbine nozzle, and discharging cooling fluid from the distribution ports radially inwardly towards the at least one turbine nozzle positioned radially inward from the manifold ring.
    Type: Grant
    Filed: June 19, 2003
    Date of Patent: September 19, 2006
    Assignee: General Electric Company
    Inventors: Michael Beverley, Darek Zatorski, Ching-Pang Lee
  • Publication number: 20050265845
    Abstract: A method for balancing a gas turbine rotor includes providing a gas turbine rotor including a plurality of turbine blades, wherein at least one turbine blade includes a blade tip shroud that includes a leading edge and a trailing edge that is opposite the leading edge, and coupling a balance clip to the at least one turbine blade. The balance clip includes a first portion having a first length that enables the clip to extend between the tip shroud leading and trailing edges and includes a first hook that is configured to couple to the tip shroud leading edge, a second portion having a second length that is shorter than the first length, such that the second portion extends only partially from at least one of the tip shroud trailing and leading edges towards the opposite shroud edge, and a second hook that extends between the first and second portions and is configured to couple to at least one of the tip shroud leading and trailing edges.
    Type: Application
    Filed: May 28, 2004
    Publication date: December 1, 2005
    Inventors: Darek Zatorski, Marek Szrajer, Leszek Rzeszutek, John Altman
  • Publication number: 20050089393
    Abstract: A turbine nozzle includes a hollow vane having opposite pressure and suction sides extending in span between outer and inner bands. The vane includes a forward flow channel behind the leading edge, an aft flow channel in front of the trailing edge, and a middle flow channel disposed therebetween. The three flow channels are disposed in flow communication with an outer plenum outside the outer band for receiving cooling air therefrom. The forward and middle channels are also disposed in flow communication with an inner plenum below the inner band for discharging the air. The aft channel discharges air through the inner band outside the inner plenum in split flow at different pressures.
    Type: Application
    Filed: October 22, 2003
    Publication date: April 28, 2005
    Inventors: Darek Zatorski, Humphrey Wills
  • Publication number: 20040258516
    Abstract: A method enables a gas turbine engine to be operated. The method comprises supplying cooling fluid into a manifold ring that includes a plurality of distribution ports defined by a sidewall connected by a radially inner wall, channeling the cooling fluid circumferentially through the manifold ring and through at least one distribution port that is defined by a wall that extends arcuately across at least one turbine nozzle, and discharging cooling fluid from the distribution ports radially inwardly towards the at least one turbine nozzle positioned radially inward from the manifold ring.
    Type: Application
    Filed: June 19, 2003
    Publication date: December 23, 2004
    Inventors: Michael Beverley, Darek Zatorski, Ching-Pang Lee