Patents by Inventor Enrico Ganzitti

Enrico Ganzitti 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).

  • Gas turbine engine nozzles
    Patent number: 11674400
    Abstract: A gas turbine engine including a frame assembly; a turbine assembly; and a nozzle disposed in the turbine assembly, wherein the nozzle defines an inner end along a radial direction and an outer end along the radial direction, wherein the outer end of the nozzle is supported by the frame assembly, wherein the inner end of the nozzle is supported by the frame assembly, and wherein the inner end of the nozzle is displaceable relative to the frame assembly in at least the radial direction.
    Type: Grant
    Filed: August 4, 2021
    Date of Patent: June 13, 2023
    Assignees: GE AVIO S.R.L., AVIO POLSKA SP. Z O.O
    Inventors: Matteo Renato Usseglio, Enrico Ganzitti, Gianfranco Brandino, Rafal Robak, Tomasz Mucha
  • GAS TURBINE ENGINE NOZZLES
    Publication number: 20220290571
    Abstract: A gas turbine engine including a frame assembly; a turbine assembly; and a nozzle disposed in the turbine assembly, wherein the nozzle defines an inner end along a radial direction and an outer end along the radial direction, wherein the outer end of the nozzle is supported by the frame assembly, wherein the inner end of the nozzle is supported by the frame assembly, and wherein the inner end of the nozzle is displaceable relative to the frame assembly in at least the radial direction.
    Type: Application
    Filed: August 4, 2021
    Publication date: September 15, 2022
    Inventors: Matteo Renato Usseglio, Enrico Ganzitti, Gianfranco Brandino, Rafal Robak, Tomasz Mucha
  • Seal for a turbine engine
    Patent number: 10954807
    Abstract: An apparatus for turbine engine including a turbine section with at least one turbine stage having a stationary vane assembly and a rotating blade assembly with combustion gases flowing through the turbine stage in a fore to aft direction. An interface is formed between a portion of the outer casing and a portion of the stationary vane assembly defining a leak flow path (LFP) where a seal is placed to retard combustion gases in the leak path.
    Type: Grant
    Filed: June 4, 2018
    Date of Patent: March 23, 2021
    Assignee: GE AVIO S.r.l.
    Inventors: Matteo Renato Usseglio, Enrico Ganzitti
  • SEAL FOR A TURBINE ENGINE
    Publication number: 20180355740
    Abstract: An apparatus for turbine engine including a turbine section with at least one turbine stage having a stationary vane assembly and a rotating blade assembly with combustion gases flowing through the turbine stage in a fore to aft direction. An interface is formed between a portion of the outer casing and a portion of the stationary vane assembly defining a leak flow path (LFP) where a seal is placed to retard combustion gases in the leak path.
    Type: Application
    Filed: June 4, 2018
    Publication date: December 13, 2018
    Inventors: Matteo Renato Usseglio, Enrico Ganzitti