Patents by Inventor Ted J. Freeman

Ted J. Freeman 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).

  • Ceramic matrix composite turbine shroud assembly with joined cover plate
    Patent number: 11255210
    Abstract: An assembly adapted for use in a gas turbine engine includes a carrier and a blade track segment that is supported by the carrier relative to a high temperature zone. The blade track segment provides a heat shield for use in high temperature applications protecting the carrier and other components.
    Type: Grant
    Filed: October 28, 2020
    Date of Patent: February 22, 2022
    Assignees: Rolls-Royce Corporation, Rolls-Royce High Temperature Composites Inc.
    Inventors: Ted J. Freeman, Jeremy Roehm
  • CERAMIC MATRIX COMPOSITE TURBINE VANE AND METHOD FOR MAKING
    Publication number: 20220034233
    Abstract: A turbine vane comprising ceramic matrix composite materials includes a vane support core, an airfoil, and an end wall that at least partially defines a gas path. The turbine vane is formed from a plurality of ceramic plies or preforms that are infiltrated with ceramic matrix material to form a one-piece ceramic matrix composite turbine vane.
    Type: Application
    Filed: October 14, 2021
    Publication date: February 3, 2022
    Inventors: Robert J. Shinavski, Thomas Tran, Kevin Lukhard, Ted J. Freeman, Steffan Brown
  • Turbine shroud assembly with dovetail retention system
    Patent number: 11230937
    Abstract: A turbine shroud assembly for use with a gas turbine engine includes a turbine outer case, a blade track segment, and a carrier. The turbine outer case is arranged circumferentially around an axis. The blade track segment includes an arcuate runner that extends circumferentially partway around the axis to define a gas path boundary of the turbine shroud assembly and an attachment feature that extends radially outward from the runner. The carrier is configured to couple the blade track segment to the turbine outer case.
    Type: Grant
    Filed: May 18, 2020
    Date of Patent: January 25, 2022
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Aaron D. Sippel, Alexandra Baucco, Anthony Razzell, Michael J. Whittle, Jeffrey Crutchfield
  • Combustor liner for a gas turbine engine with ceramic matrix composite components
    Patent number: 11226099
    Abstract: A combustor adapted for use in a gas turbine engine includes a metallic combustor shell forming an interior space, a heat shield, and a liner arranged in the interior space of the metallic case. The liner defines a combustion chamber in which fuel is burned during operation of a gas turbine engine.
    Type: Grant
    Filed: October 11, 2019
    Date of Patent: January 18, 2022
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Ted J. Freeman, Aaron D. Sippel, Jack D. Petty, Gregory W. Zeaton
  • Turbine shroud ring for a gas turbine engine having a tip clearance probe
    Patent number: 11225880
    Abstract: A gas turbine engine assembly includes adjacent components and a probe assembly. The probe assembly is configured to measure a distance between the probe assembly and blades located radially inward of the adjacent components.
    Type: Grant
    Filed: February 2, 2018
    Date of Patent: January 18, 2022
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Brian J. Shoemaker, Ted J. Freeman
  • Turbine shroud assembly with ceramic matrix composite components and cooling features
    Patent number: 11220928
    Abstract: An assembly adapted for use in a gas turbine engine includes a carrier and a blade track segment. The carrier extends at least partway about an axis. The blade track segment is supported by the carrier radially relative to the axis to define a portion of a gas path of the assembly.
    Type: Grant
    Filed: August 24, 2020
    Date of Patent: January 11, 2022
    Assignee: Rolls-Royce Corporation
    Inventors: Alexandra Baucco, Aaron D. Sippel, Ted J. Freeman
  • Assembly with pin-mounted ceramic matrix composite material components
    Patent number: 11220930
    Abstract: A turbine shroud assembly includes a carrier, a blade track segment, and an attachment pin. The carrier is arranged to extend circumferentially at least partway around an axis. The blade track segment includes a runner that faces the axis to define a portion of a primary gas path of the gas turbine engine and an attachment flange that extends radially away from the runner. The attachment pin is configured to mount the blade track segment to the carrier.
    Type: Grant
    Filed: December 3, 2019
    Date of Patent: January 11, 2022
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Shaling Starr, Aaron D. Sippel, Ted J. Freeman, David J. Thomas
  • Turbine shroud with friction mounted ceramic matrix composite blade track
    Patent number: 11220925
    Abstract: A turbine shroud adapted for use in a gas turbine engine includes a seal segment and an attachment unit. The seal segment includes an arcuate shroud wall that extends circumferentially partway around an axis and a mount post that extends radially outward away from the shroud wall. The attachment unit includes a first carrier and a second carrier that cooperate to define a channel that receives at least a portion of the mount post.
    Type: Grant
    Filed: October 12, 2020
    Date of Patent: January 11, 2022
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Aaron D. Sippel, Shaling Starr, Paulo Bazan, Adrian Harding, Jeffrey A. Walston
  • Turbine shroud assembly with ceramic matrix composite components having stress-reduced pin attachment
    Patent number: 11215065
    Abstract: A turbine shroud assembly is adapted to extend around a turbine wheel mounted for rotation about a central reference axis of a gas turbine engine. The turbine shroud assembly includes a carrier segment made from metallic materials and a blade track segment made from ceramic matrix composite materials. The carrier extends at least partway about the axis. The blade track segment is supported by the carrier radially relative to the axis to define a portion of a gas path of the assembly.
    Type: Grant
    Filed: April 24, 2020
    Date of Patent: January 4, 2022
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Shaling H. Starr, Aaron D. Sippel, Ted J. Freeman, David J. Thomas
  • Turbine shroud assembly with integrated ceramic matrix composite component support pins
    Patent number: 11215080
    Abstract: A turbine shroud assembly for use with a gas turbine engine includes a turbine outer case, a blade track segment, and a carrier assembly. The carrier assembly includes a forward carrier segment and an aft carrier segment, and each of the forward carrier segment and aft carrier segment include integrated pins. The carrier assembly is configured to couple the blade track segment to the turbine outer case.
    Type: Grant
    Filed: November 18, 2020
    Date of Patent: January 4, 2022
    Assignee: Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Aaron D. Sippel
  • Turbine shroud assembly with flange mounted ceramic matrix composite turbine shroud ring
    Patent number: 11215075
    Abstract: A turbine assembly adapted for use with a gas turbine engine includes an outer case, a blade track segment, and a carrier. The outer case extends circumferentially at least partway around an axis of the engine. The blade track segment is configured to define a portion of a gas path of the turbine assembly. The carrier is coupled with the outer case and the blade track segment to support the blade track segment in position radially relative to the axis. The carrier is coupled with the outer case for movement with the outer case in response to thermal expansion and contraction of the outer case during use of the turbine assembly.
    Type: Grant
    Filed: November 19, 2019
    Date of Patent: January 4, 2022
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, David J. Thomas, Jeffrey A. Walston, Aaron D. Sippel
  • Turbine shroud having ceramic matrix composite component mounted with cooled pin
    Patent number: 11208896
    Abstract: An assembly adapted for use in a gas turbine engine includes a carrier and a blade track segment. The carrier extends at least partway about an axis. The blade track segment is supported by the carrier radially relative to the axis to define a portion of a gas path of the assembly.
    Type: Grant
    Filed: October 20, 2020
    Date of Patent: December 28, 2021
    Assignee: Rolls-Royce Corporation
    Inventors: Alexandra Baucco, Aaron D. Sippel, Ted J. Freeman
  • Turbine shroud ring segments with ceramic matrix composite components
    Patent number: 11208911
    Abstract: An assembly adapted for use in a gas turbine engine includes a carrier and a blade track segment. The carrier extends at least partway about an axis. The blade track segment is supported by the carrier radially relative to the axis to define a portion of a gas path of the assembly.
    Type: Grant
    Filed: April 23, 2020
    Date of Patent: December 28, 2021
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Keith Sadler, Ted J. Freeman, Aaron D. Sippel, Alexandra Baucco
  • Turbine shroud assembly with case captured seal segment carrier
    Patent number: 11208918
    Abstract: A turbine module includes a turbine rotor assembly, a turbine case, and a turbine shroud assembly. The turbine rotor assembly is mounted to rotate about a central reference axis. The turbine case is spaced radially outward from the turbine rotor assembly circumferentially around the central reference axis. The turbine shroud assembly includes a plurality of turbine shroud segments mounted to the turbine case. Each turbine shroud segment includes a blade track segment that faces the turbine rotor assembly and a carrier mounted to the turbine case.
    Type: Grant
    Filed: November 15, 2019
    Date of Patent: December 28, 2021
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Aaron D. Sippel, Ted J. Freeman
  • HIGH TEMPERATURE HEAT SHIELD ASSEMBLIES
    Publication number: 20210388767
    Abstract: A heat shield assembly adapted for use with gas turbine engines, airframes, and aircraft includes a carrier and a heat-shield tile. The carrier is adapted to couple to the gas turbine engine, airframe, or aircraft. The heat-shield tile includes material different than the carrier and is arranged to cover the carrier to protect the carrier from high-temperature gases surrounding the heat shield assembly.
    Type: Application
    Filed: May 11, 2021
    Publication date: December 16, 2021
    Inventors: Scott Nelson, Quinlan Y. Shuck, Ted J. Freeman, Timothy Fuesting, Jonathan McCrory
  • Turbine shroud with containment features
    Patent number: 11187099
    Abstract: An assembly adapted for use in a gas turbine engine includes a carrier and a blade track segment. The carrier extends at least partway about an axis. The blade track segment is supported by the carrier radially relative to the axis to define a portion of a gas path of the assembly.
    Type: Grant
    Filed: October 20, 2020
    Date of Patent: November 30, 2021
    Assignee: Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Aaron D. Sippel
  • TURBINE SHROUD ASSEMBLY WITH DOVETAIL RETENTION SYSTEM
    Publication number: 20210355835
    Abstract: A turbine shroud assembly for use with a gas turbine engine includes a turbine outer case, a blade track segment, and a carrier. The turbine outer case is arranged circumferentially around an axis. The blade track segment includes an arcuate runner that extends circumferentially partway around the axis to define a gas path boundary of the turbine shroud assembly and an attachment feature that extends radially outward from the runner. The carrier is configured to couple the blade track segment to the turbine outer case.
    Type: Application
    Filed: May 18, 2020
    Publication date: November 18, 2021
    Inventors: Ted J. Freeman, Aaron D. Sippel, Alexandra Baucco, Anthony Razzell, Michael J. Whittle, Jeffrey Crutchfield
  • HYBRID VANE SEGMENT WITH CERAMIC MATRIX COMPOSITE AIRFOILS
    Publication number: 20210348516
    Abstract: A vane assembly for use with a gas turbine engine includes an outer wall, an inner wall, and a plurality of airfoils. The outer wall and the inner wall extend at least partway about an axis. At least one of the airfoils is coupled with the outer end wall and the inner end wall to transmit force loads through the vane assembly.
    Type: Application
    Filed: May 6, 2020
    Publication date: November 11, 2021
    Inventors: Ted J. Freeman, Jay E. Lane, Michael J. Whittle, Anthony Razzell
  • Ceramic matrix composite turbine vane and method for making
    Patent number: 11162377
    Abstract: A turbine vane comprising ceramic matrix composite materials. The turbine vane includes an vane support core, an airfoil, and a pair of end walls that are spaced apart from one another to define a gas path. The turbine vane is formed from a plurality of ceramic plies or preforms that are infiltrated with ceramic matrix material to form a one-piece ceramic matrix composite turbine vane.
    Type: Grant
    Filed: May 31, 2019
    Date of Patent: November 2, 2021
    Assignees: Rolls-Royce High Temperature Composites Inc., Rolls-Royce North American Technologies Inc.
    Inventors: Robert J. Shinavski, Thomas Tran, Kevin Lukhard, Ted J. Freeman, Steffan Brown
  • Turbine vane doublet with ceramic matrix composite material construction
    Patent number: 11162372
    Abstract: The present disclosure is related to turbine vanes comprising ceramic matrix composite materials and vane ring assemblies including the same and adapted for use in gas turbine engines. The turbine vanes each include a platform that defines a gas path of the gas turbine engine and an airfoil that extends away from the platform.
    Type: Grant
    Filed: December 4, 2019
    Date of Patent: November 2, 2021
    Assignees: Rolls-Royce North American Technologies Inc.
    Inventors: Michael J. Whittle, Ted J. Freeman