Patents by Inventor Wojciech Sak

Wojciech Sak 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: 20230184125
    Abstract: An engine component with an abradable material and treatment is disclosed herein. An example engine component includes a substrate having a first thickness and defining at least a first substrate surface, the substrate extending along an axial direction, an abradable material on the first substrate surface, the abradable material defining a first abradable material surface, a second abradable material surface spaced radially apart from the first abradable material surface and defining a second thickness, and a treatment, the treatment extending from the first abradable material surface through at least a portion of the first thickness of the substrate.
    Type: Application
    Filed: December 15, 2021
    Publication date: June 15, 2023
    Inventors: Neelesh Sarawate, Stephan Priebe, Wojciech Sak
  • Patent number: 11359646
    Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine, such as a multi-stage compressor of a gas turbine engine, by reducing an operating air temperature in a space between a seal and a blade post of adjacent stages by routing cooling air through an inlet in the vane, passing the routed cooling air through the vane, and emitting the routed cooling air into the space.
    Type: Grant
    Filed: August 29, 2019
    Date of Patent: June 14, 2022
    Assignee: General Electric Company
    Inventors: Sesha Subramanian, Monty Lee Shelton, Robert Proctor, Mohamed Musthafa Thoppil, Venkateswararao Gurram, Josiah Warren Joiner, Wojciech Sak
  • Publication number: 20200011347
    Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine, such as a multi-stage compressor of a gas turbine engine, by reducing an operating air temperature in a space between a seal and a blade post of adjacent stages by routing cooling air through an inlet in the vane, passing the routed cooling air through the vane, and emitting the routed cooling air into the space.
    Type: Application
    Filed: August 29, 2019
    Publication date: January 9, 2020
    Inventors: Sesha Subramanian, Monty Lee Shelton, Robert Proctor, Mohamed Musthafa Thoppil, Venkateswararao Gurram, Josiah Warren Joiner, Wojciech Sak
  • Patent number: 10451084
    Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine, such as a multi-stage compressor of a gas turbine engine, by reducing an operating air temperature in a space between a seal and a blade post of adjacent stages by routing cooling air through an inlet in the vane, passing the routed cooling air through the vane, and emitting the routed cooling air into the space.
    Type: Grant
    Filed: November 16, 2015
    Date of Patent: October 22, 2019
    Assignee: General Electric Company
    Inventors: Sesha Subramanian, Monty Lee Shelton, Robert Proctor, Mohamed Musthafa Thoppil, Venkateswararao Gurram, Josiah Warren Joiner, Wojciech Sak
  • Patent number: 10287902
    Abstract: A variable stator vane includes airfoil mounted to a button centered about a rotational axis and having cylindrical portion supporting airfoil and a button undercut extending away from cylindrical portion and radially inwardly from circumference of cylindrical portion. Conical portion of button circumscribed about conical axis of revolution extends away from cylindrical portion. Conical axis of revolution may be tilted with respect to and may intersect rotational axis. Airfoil may include airfoil overhang extending radially outwardly beyond circular trailing edge of button. Variable stator vane may include airfoil disposed between spaced apart outer and inner buttons centered about a rotational axis, inner button having a cylindrical portion supporting airfoil and circumscribed about rotational axis, and button undercut extending away from cylindrical portion and radially inwardly from a circumference of cylindrical portion with respect to rotational axis.
    Type: Grant
    Filed: January 6, 2016
    Date of Patent: May 14, 2019
    Assignee: General Electric Company
    Inventors: Wojciech Sak, Timothy William Taylor, Walter Glen Crosby, IV
  • Publication number: 20170191367
    Abstract: A variable stator vane includes airfoil mounted to a button centered about a rotational axis and having cylindrical portion supporting airfoil and a button undercut extending away from cylindrical portion and radially inwardly from circumference of cylindrical portion. Conical portion of button circumscribed about conical axis of revolution extends away from cylindrical portion. Conical axis of revolution may be tilted with respect to and may intersect rotational axis. Airfoil may include airfoil overhang extending radially outwardly beyond circular trailing edge of button. Variable stator vane may include airfoil disposed between spaced apart outer and inner buttons centered about a rotational axis, inner button having a cylindrical portion supporting airfoil and circumscribed about rotational axis, and button undercut extending away from cylindrical portion and radially inwardly from a circumference of cylindrical portion with respect to rotational axis.
    Type: Application
    Filed: January 6, 2016
    Publication date: July 6, 2017
    Inventors: Wojciech Sak, Timothy William Taylor, Walter Glen Crosby, IV
  • Publication number: 20170138372
    Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine, such as a multi-stage compressor of a gas turbine engine, by reducing an operating air temperature in a space between a seal and a blade post of adjacent stages by routing cooling air through an inlet in the vane, passing the routed cooling air through the vane, and emitting the routed cooling air into the space.
    Type: Application
    Filed: November 16, 2015
    Publication date: May 18, 2017
    Inventors: Sesha Subramanian, Monty Lee Shelton, Robert Proctor, Mohamed Musthafa Thoppil, Venkateswararao Gurram, Josiah Warren Joiner, Wojciech Sak
  • Patent number: 7823389
    Abstract: A gas turbine engine includes a compressor, combustor, and turbine having a row of blades mounted inside a surrounding turbine shroud. A heat exchanger is used for cooling pressurized air bled from the compressor. A distribution network joins the heat exchanger to the turbine for selectively channeling air from the heat exchanger below the blades and above the shroud for controlling blade tip clearance.
    Type: Grant
    Filed: November 15, 2006
    Date of Patent: November 2, 2010
    Assignee: General Electric Company
    Inventors: Kenneth Edward Seitzer, Wojciech Sak, Zhifeng Dong, Robert Paul Ziegler, Chris Charles Glynn
  • Patent number: 7740443
    Abstract: A row of turbine blades is surrounded by a turbine shroud. The shroud is supported by a turbine case having a pair of radially outwardly extending rails. The rails are perforate for channeling therethrough control air to control thermal radial movement of the case, and in turn radial position of the shroud supported therefrom.
    Type: Grant
    Filed: November 15, 2006
    Date of Patent: June 22, 2010
    Assignee: General Electric Company
    Inventors: Kenneth Edward Seitzer, Wojciech Sak, Zhifeng Dong, Robert Paul Ziegler, William Lee Herron
  • Publication number: 20080112797
    Abstract: A row of turbine blades is surrounded by a turbine shroud. The shroud is supported by a turbine case having a pair of radially outwardly extending rails. The rails are perforate for channeling therethrough control air to control thermal radial movement of the case, and in turn radial position of the shroud supported therefrom.
    Type: Application
    Filed: November 15, 2006
    Publication date: May 15, 2008
    Inventors: Kenneth Edward Seitzer, Wojciech Sak, Zhifeng Dong, Robert Paul Ziegler, William Lee Herron
  • Publication number: 20080112798
    Abstract: A gas turbine engine includes a compressor, combustor, and turbine having a row of blades mounted inside a surrounding turbine shroud. A heat exchanger is used for cooling pressurized air bled from the compressor. A distribution network joins the heat exchanger to the turbine for selectively channeling air from the heat exchanger below the blades and above the shroud for controlling blade tip clearance.
    Type: Application
    Filed: November 15, 2006
    Publication date: May 15, 2008
    Inventors: Kenneth Edward Seitzer, Wojciech Sak, Zhifeng Dong, Robert Paul Ziegler, Chris Charles Glynn