Patents by Inventor Tara G. Schetzel

Tara G. Schetzel 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).

  • Composite turbine vane with three-dimensional fiber reinforcements
    Patent number: 10767502
    Abstract: A turbine vane made from ceramic matrix composite material and adapted for use in a gas turbine engine. The turbine vane is made from ceramic matrix composite materials with three-dimensionally woven or braided reinforcing tows and includes an inner band, an outer band, and an airfoil that extends between the inner band and the outer band.
    Type: Grant
    Filed: March 17, 2017
    Date of Patent: September 8, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc., Rolls-Royce High Temperature Composites Inc.
    Inventors: Tara G. Schetzel, Ted J. Freeman, Jun Shi, Jeffrey A. Walston, Steven Clarke, Sean Kroszner
  • Vane assemblies for gas turbine engines
    Patent number: 10655482
    Abstract: A vane ring for a gas turbine engine includes an outer end wall and a plurality of spars coupled to the outer end wall. The vane ring further includes an inner end wall positioned radially inward of the outer end wall and coupled to the spars. The outer and inner end walls cooperate to form a flowpath.
    Type: Grant
    Filed: February 4, 2016
    Date of Patent: May 19, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Ted J. Freeman, Jeffrey A. Walston, Jun Shi, Tara G. Schetzel
  • Turbine blade with heat shield
    Patent number: 10612385
    Abstract: An airfoil assembly for use in a gas turbine engine is disclosed. The airfoil assembly includes a root, a tip shroud, and an airfoil located between the root and tip shroud. The airfoil includes a spar, a heat shield arranged around the spar, and a plurality of describe rigid load supports extending between the spar and the heat shield to transfer loads between the heat shield and the spar.
    Type: Grant
    Filed: March 7, 2016
    Date of Patent: April 7, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Tara G. Schetzel, Ted J. Freeman, David J. Thomas
  • Turbine vane with heat shield
    Patent number: 10358939
    Abstract: A gas turbine engine includes a body and a turbine-vane ring coupled to the body. The turbine-vane ring includes a plurality of turbine-vane assemblies. Each turbine-vane assembly includes a vane unit and a heat shield configured to reduce heat transfer to the vane unit from hot exhaust gases during operation of the gas turbine engine.
    Type: Grant
    Filed: March 2, 2016
    Date of Patent: July 23, 2019
    Assignee: Rolls-Royce Corporation
    Inventors: Jeffrey A. Walston, Aaron D. Sippel, Tara G. Schetzel, David J. Thomas, Jun Shi, Brad D. Belcher
  • Nozzle guide vane with composite heat shield
    Patent number: 10329950
    Abstract: A nozzle guide vane for a gas turbine engine is disclosed herein. The nozzle guide vane includes an inner endcap, an outer endcap, and at least one airfoil that extends from the inner endcap to the outer endcap. The nozzle guide vane further includes at least one composite heat shield component adapted to shield metallic components from high temperature gasses.
    Type: Grant
    Filed: March 23, 2016
    Date of Patent: June 25, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Jeffrey A. Walston, Jun Shi, Tara G. Schetzel
  • Turbine blade with heat shield
    Patent number: 10215028
    Abstract: An airfoil assembly for use in a gas turbine engine is disclosed. The airfoil assembly includes a root, a tip shroud, and an airfoil located between the root and tip shroud. The airfoil includes a spar and a heat shield arranged around the spar.
    Type: Grant
    Filed: March 7, 2016
    Date of Patent: February 26, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Tara G. Schetzel, Ted J. Freeman, David J. Thomas
  • COMPOSITE TURBINE VANE WITH THREE-DIMENSIONAL FIBER REINFORCEMENTS
    Publication number: 20180179906
    Abstract: A turbine vane made from ceramic matrix composite material and adapted for use in a gas turbine engine is disclosed in this paper. Turbine vanes in accordance with the present disclosure are made from ceramic matrix composites with three-dimensionally woven or braided reinforcing tows.
    Type: Application
    Filed: March 17, 2017
    Publication date: June 28, 2018
    Inventors: Tara G. Schetzel, Ted J. Freeman, Jun Shi, Jeffrey A. Walston, Steven Clarke, Sean Kroszner
  • TURBINE BLADE WITH HEAT SHIELD
    Publication number: 20170254206
    Abstract: An airfoil assembly for use in a gas turbine engine is disclosed. The airfoil assembly includes a root, a tip shroud, and an airfoil located between the root and tip shroud. The airfoil includes a spar and a heat shield arranged around the spar.
    Type: Application
    Filed: March 7, 2016
    Publication date: September 7, 2017
    Inventors: Tara G. Schetzel, Ted J. Freeman, David J. Thomas
  • TURBINE BLADE WITH HEAT SHIELD
    Publication number: 20170254207
    Abstract: An airfoil assembly for use in a gas turbine engine is disclosed. The airfoil assembly includes a root, a tip shroud, and an airfoil located between the root and tip shroud. The airfoil includes a spar, a heat shield arranged around the spar, and a plurality of describe rigid load supports extending between the spar and the heat shield to transfer loads between the heat shield and the spar.
    Type: Application
    Filed: March 7, 2016
    Publication date: September 7, 2017
    Inventors: Tara G. Schetzel, Ted J. Freeman, David J. Thomas
  • NOZZLE GUIDE VANE WITH COMPOSITE HEAT SHIELDS
    Publication number: 20170022829
    Abstract: A nozzle guide vane for a gas turbine engine is disclosed herein. The nozzle guide vane includes an inner endcap, an outer endcap, and at least one airfoil that extends from the inner endcap to the outer endcap. The nozzle guide vane further includes at least one composite heat shield component adapted to shield metallic components from high temperature gasses.
    Type: Application
    Filed: March 23, 2016
    Publication date: January 26, 2017
    Inventors: Ted J. Freeman, Jeffrey A. Walston, Jun Shi, Tara G. Schetzel
  • TURBINE VANE WITH HEAT SHIELD
    Publication number: 20160265384
    Abstract: A gas turbine engine may include a body and a turbine-vane ring coupled to the body. The turbine-vane ring may include a plurality of turbine-vane assemblies.
    Type: Application
    Filed: March 2, 2016
    Publication date: September 15, 2016
    Inventors: Jeffrey A. Walston, Aaron D. Sippel, Tara G. Schetzel, David J. Thomas, Jun Shi, Brad D. Belcher
  • VANE ASSEMBLIES FOR GAS TURBINE ENGINES
    Publication number: 20160230576
    Abstract: A vane ring for a gas turbine engine includes an outer end wall and a plurality of spars coupled to the outer end wall. The vane ring further includes an inner end wall positioned radially inward of the outer end wall and coupled to the spars. The outer and inner end walls cooperate to form a flowpath.
    Type: Application
    Filed: February 4, 2016
    Publication date: August 11, 2016
    Inventors: Ted J. Freeman, Jeffrey A. Walston, Jun Shi, Tara G. Schetzel