Patents by Inventor Linnea Taketa

Linnea Taketa 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 vane end devices
    Patent number: 11326464
    Abstract: A turbomachinery component of a gas turbine engine is disclosed having a number of techniques of reducing the effects of a gap flow between an airfoil member of the gas turbine engine and a wall of the gas turbine engine. The airfoil member can be variable and in one form is a variable turbine vane. In one embodiment a brush seal is included between the vane and the wall. In another form a wear surface is disposed between the vane and the wall. In yet another form a moveable member capable of being actuated to change position can be disposed between the vane and the wall to alter the size of a gap between the two.
    Type: Grant
    Filed: June 26, 2019
    Date of Patent: May 10, 2022
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Linnea Taketa, John Munson, Ted J. Freeman
  • GAS TURBINE ENGINE VANE END DEVICES
    Publication number: 20190330993
    Abstract: A turbomachinery component of a gas turbine engine is disclosed having a number of techniques of reducing the effects of a gap flow between an airfoil member of the gas turbine engine and a wall of the gas turbine engine. The airfoil member can be variable and in one form is a variable turbine vane. In one embodiment a brush seal is included between the vane and the wall. In another form a wear surface is disposed between the vane and the wall. In yet another form a moveable member capable of being actuated to change position can be disposed between the vane and the wall to alter the size of a gap between the two.
    Type: Application
    Filed: June 26, 2019
    Publication date: October 31, 2019
    Inventors: Linnea Taketa, John Munson, Ted J. Freeman
  • Gas turbine engine vane end devices
    Patent number: 10370995
    Abstract: A turbomachinery component of a gas turbine engine is disclosed having a number of techniques of reducing the effects of a gap flow between an airfoil member of the gas turbine engine and a wall of the gas turbine engine. The airfoil member can be variable and in one form is a variable turbine vane. In one embodiment a brush seal is included between the vane and the wall. In another form a wear surface is disposed between the vane and the wall. In yet another form a moveable member capable of being actuated to change position can be disposed between the vane and the wall to alter the size of a gap between the two.
    Type: Grant
    Filed: November 28, 2017
    Date of Patent: August 6, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Linnea Taketa, John Munson, Ted J. Freeman
  • GAS TURBINE ENGINE VANE END DEVICES
    Publication number: 20180156052
    Abstract: A turbomachinery component of a gas turbine engine is disclosed having a number of techniques of reducing the effects of a gap flow between an airfoil member of the gas turbine engine and a wall of the gas turbine engine. The airfoil member can be variable and in one form is a variable turbine vane. In one embodiment a brush seal is included between the vane and the wall. In another form a wear surface is disposed between the vane and the wall. In yet another form a moveable member capable of being actuated to change position can be disposed between the vane and the wall to alter the size of a gap between the two.
    Type: Application
    Filed: November 28, 2017
    Publication date: June 7, 2018
    Inventors: Linnea Taketa, John Munson, Ted J. Freeman
  • Gas turbine engine vane end devices
    Patent number: 9938845
    Abstract: A turbomachinery component of a gas turbine engine is disclosed having a number of techniques of reducing the effects of a gap flow between an airfoil member of the gas turbine engine and a wall of the gas turbine engine. The airfoil member can be variable and in one form is a variable turbine vane. In one embodiment a brush seal is included between the vane and the wall. In another form a wear surface is disposed between the vane and the wall. In yet another form a moveable member capable of being actuated to change position can be disposed between the vane and the wall to alter the size of a gap between the two.
    Type: Grant
    Filed: December 18, 2013
    Date of Patent: April 10, 2018
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Linnea Taketa, John Munson, Ted J. Freeman
  • GAS TURBINE ENGINE VANE END DEVICES
    Publication number: 20150003963
    Abstract: A turbomachinery component of a gas turbine engine is disclosed having a number of techniques of reducing the effects of a gap flow between an airfoil member of the gas turbine engine and a wall of the gas turbine engine. The airfoil member can be a variable and in one form is a variable turbine vane. In one embodiment a brush seal is included between the vane and the wall. In another form a wear surface is disposed between the vane and the wall. In yet another form a moveable member capable of being actuated to change position can be disposed between the vane and the wall to alter the size of a gap between the two.
    Type: Application
    Filed: December 18, 2013
    Publication date: January 1, 2015
    Inventors: Linnea Taketa, John Munson, Ted J. Freeman