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).

  • Patent number: 11028722
    Abstract: The present disclosure is directed to a blade track assembly used in a gas turbine engine. The blade track assembly includes blade track segments made from ceramic matrix composite materials and a tip clearance control system for adjusting the inner diameter of the blade track assembly during use in an engine.
    Type: Grant
    Filed: May 30, 2018
    Date of Patent: June 8, 2021
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Aaron D. Sippel
  • Publication number: 20210164365
    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: Application
    Filed: December 3, 2019
    Publication date: June 3, 2021
    Inventors: Shaling Starr, Aaron D. Sippel, Ted J. Freeman, David J. Thomas
  • Patent number: 11021974
    Abstract: A wheel assembly for a gas turbine engine includes a disk, an annular coverplate, and an anti-rotation feature. The disk is adapted to receive blades and rotate about an axis during use of the gas turbine engine. The annular coverplate is coupled with the disk and adapted to block axial movement of the blades. The anti-rotation feature is coupled with the disk and the annular coverplate to resist rotation of the annular coverplate relative to the disk.
    Type: Grant
    Filed: October 10, 2018
    Date of Patent: June 1, 2021
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Aaron D. Sippel, James Sellhorn
  • Publication number: 20210148248
    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.
    Type: Application
    Filed: November 19, 2019
    Publication date: May 20, 2021
    Inventors: Ted J. Freeman, David J. Thomas, Jeffrey A. Walston, Aaron D. Sippel
  • Publication number: 20210148250
    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: Application
    Filed: November 15, 2019
    Publication date: May 20, 2021
    Inventors: Aaron D. Sippel, Ted J. Freeman
  • Publication number: 20210148251
    Abstract: A turbine shroud adapted for use in a gas turbine engine includes a blade track segment and a carrier. The blade track 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 carrier is coupled with the mount post of the blade track segment to support the blade track segment.
    Type: Application
    Filed: November 19, 2019
    Publication date: May 20, 2021
    Inventors: Ted J. Freeman, Aaron D. Sippel, Paulo Bazan
  • Publication number: 20210148252
    Abstract: A turbine shroud assembly for use with a gas turbine engine includes a blade track segment coupled to a carrier segment, and a sheet-metal seal that seals therebetween. The blade track segment includes a shroud wall that extends circumferentially partway around an axis and an attachment feature that extends radially outward from the shroud wall. The carrier is coupled with the attachment feature to support the blade track segment.
    Type: Application
    Filed: November 19, 2019
    Publication date: May 20, 2021
    Inventors: Ted J. Freeman, David J. Thomas, Jeffrey A. Walston, Aaron D. Sippel
  • Publication number: 20210148244
    Abstract: A turbine shroud assembly for use with a gas turbine engine includes a carrier assembly coupled to a blade track segment, and a sheet-metal seal that seals on axial and radial facing surfaces therebetween. The blade track segment includes a shroud wall that extends circumferentially partway around an axis and an attachment feature that extends radially outward from the shroud wall. The carrier is coupled with the attachment feature to support the blade track segment.
    Type: Application
    Filed: November 19, 2019
    Publication date: May 20, 2021
    Inventors: Ted J. Freeman, David J. Thomas, Jeffrey A. Walston, Aaron D. Sippel
  • Patent number: 11008888
    Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a vane support and a vane heat shield comprising ceramic matrix composite materials to insulate the metallic materials of the vane support. The turbine vane assembly further includes an aero-load transfer rib located outside of a primary gas path and configured to carry loads applied to the vane heat shield to the vane support.
    Type: Grant
    Filed: July 17, 2018
    Date of Patent: May 18, 2021
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Aaron D. Sippel, Ted J. Freeman, David J. Thomas, Adam L. Chamberlain
  • Patent number: 11008876
    Abstract: A blade and method for producing the blade for a gas turbine engine are described herein. The blade may include a composite airfoil. The airfoil may comprise a ceramic material, and a distal end. A tip may extend from the distal end of the airfoil. The tip of the airfoil may comprise a substantially porous structure and may comprise infiltrated material extending from an airfoil preform to a tip preform to join the airfoil preform and the tip preform.
    Type: Grant
    Filed: January 10, 2019
    Date of Patent: May 18, 2021
    Assignees: Rolls-Royce North American Technologies, Inc., Rolls-Royce Corporation
    Inventors: Richard C. Uskert, Kang N. Lee, Ted J. Freeman
  • Publication number: 20210140333
    Abstract: A turbine assembly for use with a gas turbine engine includes a bladed wheel assembly, a vane assembly, and an inner seal. The bladed wheel assembly is adapted to interact with gases flowing through a gas path of the gas turbine engine. The vane assembly is located upstream of the bladed wheel assembly and adapted to direct the gases at the bladed wheel assembly. The inner seal is configured to block gases from passing around the vane assembly.
    Type: Application
    Filed: November 11, 2019
    Publication date: May 13, 2021
    Inventors: Michael J. Whittle, Keith Sadler, Ted J. Freeman
  • Patent number: 10995623
    Abstract: The present disclosure relates generally to blades used in gas turbine engines. More specifically designs in accordance with the present disclosure include turbine blades comprising ceramic matrix composite materials with abrasive tips coupled thereto.
    Type: Grant
    Filed: April 23, 2018
    Date of Patent: May 4, 2021
    Assignees: Rolls-Royce Corporation, Rolls-Royce High Temperature Composites Inc., Rolls-Royce North American Technologies Inc.
    Inventors: Aaron D. Sippel, Andrew Glucklich, Sungbo Shim, Ted J. Freeman
  • Publication number: 20210108799
    Abstract: A combustor for a gas turbine engine includes a combustor shell, a burner seal, and a burner seal retainer. The combustor shell includes metallic materials and is formed to define an interior combustion space. The burner seal includes ceramic matrix composite materials and is configured to extend through apertures formed in the combustor shell and the heat shield. The burner seal retainer is configured to retain the burner seal to the combustor shell.
    Type: Application
    Filed: October 11, 2019
    Publication date: April 15, 2021
    Inventors: Ted J. Freeman, Aaron D. Sippel, Jack D. Petty, Gregory W. Zeaton
  • Publication number: 20210108532
    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: Application
    Filed: October 12, 2020
    Publication date: April 15, 2021
    Inventors: Ted J. Freeman, Aaron D. Sippel, Shaling Starr, Paulo Bazan, Adrian Harding, Jeffrey A. Walston
  • Publication number: 20210108798
    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: Application
    Filed: October 11, 2019
    Publication date: April 15, 2021
    Inventors: Ted J. Freeman, Aaron D. Sippel, Jack D. Petty, Gregory W. Zeaton
  • Publication number: 20210108533
    Abstract: An example high-performance system includes an example high-performance component including a substrate and a multilayer abradable track adjacent to the substrate. The abradable track includes a plurality of alternating layers along a thickness of the abradable track. The plurality of alternating layers includes at least one relatively porous abradable layer and at least one relatively dense layer. A porosity of the relatively dense layer is lower than that of the at least one relatively porous abradable layer. The example high-performance system may include a rotating component configured to contact and abrade the multilayer abradable track. An example technique for forming the multilayer abradable track includes thermal spraying a first precursor composition toward the substrate to form a relatively porous abradable layer of a layer pair of a plurality of layer pairs of the multilayer abradable track, and a second precursor composition to form a relatively dense layer of the pair.
    Type: Application
    Filed: December 7, 2020
    Publication date: April 15, 2021
    Inventors: Jun Shi, Li Li, Ted J. Freeman
  • Publication number: 20210102702
    Abstract: A combustor adapted for use in a gas turbine engine a combustor shell, a heat shield, and a heat shield retainer. The combustor shell is made from metallic materials and is formed to define an internal cavity. The heat shield is formed from ceramic matrix composite materials and is coupled to the dome panel. The heat shield retainer is configured to retain the heat shield to the combustor shell.
    Type: Application
    Filed: October 8, 2019
    Publication date: April 8, 2021
    Inventors: Ted J. Freeman, Aaron D. Sippel, Paulo Bazan
  • Publication number: 20210102701
    Abstract: A combustor for a gas turbine engine includes a combustor shell, a heat shield and a burner seal. The combustor shell includes metallic materials and is formed to define an interior combustion space. The heat shield includes ceramic matrix composite materials and is configured to shield a portion of the combustor shell from the interior combustion space. The burner seal includes ceramic matrix composite materials and is configured to extend through apertures formed in the combustor shell and the heat shield.
    Type: Application
    Filed: October 8, 2019
    Publication date: April 8, 2021
    Inventors: Ted J. Freeman, Aaron D. Sippel, Paulo Bazan
  • Patent number: 10954809
    Abstract: A gas turbine engine may comprise a blade track and a method of making the same. The blade track may be constructed of ceramic matrix composite components including main body members and joints.
    Type: Grant
    Filed: May 25, 2018
    Date of Patent: March 23, 2021
    Assignees: Rolls-Royce High Temperature Composites Inc., Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Aaron D. Sippel, Bruce E. Varney, Ted J. Freeman, Christopher Barrett
  • Patent number: 10941942
    Abstract: A combustor of a gas turbine engine and a turbine shroud for a turbine of a gas turbine engine are disclosed. The combustor is configured to ignite a mixture of compressed air and fuel in a combustion chamber included therein. The turbine shroud is configured to direct products of the combustion reaction toward a plurality of rotatable turbine blades of the turbine to cause the plurality of turbine blades to rotate.
    Type: Grant
    Filed: December 16, 2015
    Date of Patent: March 9, 2021
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce High Temperature Composites Inc.
    Inventors: Ted J. Freeman, Wayne S. Steffier