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).

  • Machinable CMC insert
    Patent number: 10458653
    Abstract: An assembly comprising a ceramic matrix composite component, a ceramic insert, and a ply and a method for producing the same. The ceramic matrix composite component may comprise silicon carbide fibers in a silicon carbide matrix. The ceramic inset may be adjacent to the ceramic matrix composite component. The ply may at least partially cover the ceramic insert such that the ceramic insert may be sandwiched between the ply and the ceramic matrix composite component, and the ply may extend beyond the ceramic insert in at least one direction so that the ply is joined to the ceramic matrix composite. The ply may comprise at least one layer of silicon carbide fibers or carbon fibers in a silicon carbide matrix.
    Type: Grant
    Filed: June 3, 2016
    Date of Patent: October 29, 2019
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.
    Inventors: Ted J. Freeman, Thomas D. Nixon, Sean E. Landwehr, Aaron D. Sippel, Donald W. Reinhart
  • Turbine shroud with sealing features
    Patent number: 10458263
    Abstract: A segmented turbine shroud for positioning radially outside of blades of a turbine rotor includes a carrier, a blade track, and retainers. The blade track is mounted onto the retainers, and the retainers are attached to the carrier to support the blade track radially outside of the blades.
    Type: Grant
    Filed: September 27, 2016
    Date of Patent: October 29, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Aaron D. Sippel, Ted J. Freeman, David J. Thomas
  • CERAMIC MATRIX COMPOSITE TURBINE BLADE WITH ABRASIVE TIP
    Publication number: 20190323363
    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: Application
    Filed: April 23, 2018
    Publication date: October 24, 2019
    Inventors: Aaron D. Sippel, Andrew Glucklich, Sungbo Shim, Ted J. Freeman
  • TURBINE DISK WITH PLATFORMS COUPLED TO DISK
    Publication number: 20190323372
    Abstract: A disk assembly for use in a turbine of a gas turbine engine. The disk assembly includes a disk and a plurality of platforms coupled with the disk. The disk includes a plurality of radially extending disk lugs that define slots for receiving airfoils. The platforms are coupled to the disk lugs between neighboring blades to block radially inward movement of hot gasses toward the disk.
    Type: Application
    Filed: April 23, 2018
    Publication date: October 24, 2019
    Inventors: Ted J. Freeman, Aaron D. Sippel
  • TURBINE BLADE WITH ABRADABLE TIP
    Publication number: 20190323364
    Abstract: The present disclosure relates to turbine blades adapted for use in gas turbine engines. In particular, this disclosure is directed to turbine blades that include components made from ceramic matrix composite materials and that incorporate abradable materials.
    Type: Application
    Filed: April 23, 2018
    Publication date: October 24, 2019
    Inventors: Aaron D. Sippel, Ted J. Freeman
  • TURBINE DISK WITH BLADE SUPPORTED PLATFORMS
    Publication number: 20190323371
    Abstract: A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. The blades each fit within slots formed in the rotor disk to couple the blades to the rotor disk. Platform segments are arranged about each of the blades.
    Type: Application
    Filed: April 23, 2018
    Publication date: October 24, 2019
    Inventors: Stephen Harris, Aaron D. Sippel, Ted J. Freeman, Anthony Razzell
  • Turbine blade with ceramic matrix composite material construction
    Patent number: 10443409
    Abstract: A turbine blade of ceramic matrix composite material construction adapted for use in a gas turbine engine is disclosed. The turbine blade includes a root, an airfoil, and a platform. The root is adapted to attach the turbine blade to a disk. The airfoil is shaped to interact with hot gasses moving through the gas path of a gas turbine engine and cause rotation of the turbine blade when the turbine blade is used in a gas turbine engine. The platform is arranged between the root and the airfoil and is shaped to block gasses from the gas path migrating toward the root when the turbine blade is used in a gas turbine engine.
    Type: Grant
    Filed: October 28, 2016
    Date of Patent: October 15, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Aaron D. Sippel, Daniel K. Vetters, Ted J. Freeman, David J. Thomas
  • Seal for a gas turbine engine assembly
    Patent number: 10443419
    Abstract: A gas turbine engine assembly includes a seal formed by the interface between first and second support components. The support components are each formed to include a notch. Adjacent notches cooperate to form a space when assembled. A seal member is located in the space.
    Type: Grant
    Filed: March 25, 2016
    Date of Patent: October 15, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: David J. Thomas, John A. Weaver, Ted J. Freeman
  • FULL HOOP BLADE TRACK WITH KEYSTONING SEGMENTS
    Publication number: 20190301296
    Abstract: A blade track used in gas turbine engines to define an outer boundary of the primary gas path through a turbine section of a gas turbine engine is disclosed. The blade track includes segments comprising ceramic matrix composite materials that are assembled such that the blade track segments keystone against one another to provide a self-supporting full hoop assembly. Circumferentially-extending splines may be used to couple adjacent segments to one. Also disclosed are other heat shielding assemblies used in gas turbine engines that share features with the illustratively disclosed blade track.
    Type: Application
    Filed: March 27, 2018
    Publication date: October 3, 2019
    Inventors: Ted J. Freeman, Aaron D. Sippel
  • Turbine wheel assembly with ceramic matrix composite components
    Patent number: 10428661
    Abstract: A gas turbine engine includes a turbine section having static turbine vane rings and turbine wheel assemblies. The vane rings are arranged to direct combustion products toward blades included in the turbine wheel assemblies to cause the turbine wheel assemblies to rotate.
    Type: Grant
    Filed: October 26, 2016
    Date of Patent: October 1, 2019
    Assignees: Roll-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: David J. Thomas, Ted J. Freeman, Aaron D. Sippel, Daniel K. Vetters
  • Gas turbine engine features for tip clearance inspection
    Patent number: 10428674
    Abstract: Turbine assemblies for a turbine of a gas turbine engine are disclosed herein. The turbine assembly includes a turbine wheel assembly and a turbine shroud. The turbine wheel assembly includes a disk and a plurality of blades that extend outwardly from the disk in a radial direction away from an axis. The turbine shroud extends around the blades of the turbine wheel assembly to block gasses from passing over the blades during operation of the turbine assembly. The turbine shroud includes a plurality of blade track segments arranged circumferentially adjacent to one another about the axis to form a ring. Each blade track segment has a runner that forms a primary track surface facing the axis and spaced from the axis in the radial direction.
    Type: Grant
    Filed: January 31, 2017
    Date of Patent: October 1, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Aaron D. Sippel, Brian J. Shoemaker, Ted J. Freeman
  • TURBINE BLADE ASSEMBLY WITH MOUNTED PLATFORM
    Publication number: 20190292922
    Abstract: A turbine blade assembly adapted for use in a gas turbine engine is disclosed in this paper. A primary member of the turbine blade assembly shaped to form an airfoil and comprises ceramic matrix composite materials. A independent platform of the turbine blade assembly is coupled to the primary member of the turbine blade assembly such that the primary member need not be shaped to provide the platform.
    Type: Application
    Filed: March 23, 2018
    Publication date: September 26, 2019
    Inventors: Ted J. Freeman, Michael A. Kowalkowski
  • BLADE TIP FOR CERAMIC MATRIX COMPOSITE BLADE
    Publication number: 20190292916
    Abstract: Turbine blades for use in gas turbine engines are disclosed herein. Each blade includes an airfoil and a protective crown. The airfoil includes ceramic matrix composite materials. The protective crown includes ceramic-containing materials and is mounted to a radially-outer end portion of the airfoil.
    Type: Application
    Filed: March 20, 2018
    Publication date: September 26, 2019
    Inventors: Ted J. Freeman, Jeremy P. Roehm, Robert J. Shinavski
  • Vane assembly for a gas turbine engine
    Patent number: 10408084
    Abstract: A vane assembly for a gas turbine engine is disclosed herein. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil that extends from the inner platform to the outer platform. The ceramic-containing airfoil is manufactured to have radially discontinuous ribs spaced radially apart from one another between the inner platform and the outer platform.
    Type: Grant
    Filed: February 29, 2016
    Date of Patent: September 10, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: David J. Thomas, Ted J. Freeman, Jeffrey A. Walston, Andrew J. Lazur
  • Machinable CMC insert
    Patent number: 10401028
    Abstract: An assembly comprising a structural component and a sacrificial layer, and method for producing the same. The structural component may comprise silicon carbide fibers within a silicon carbide matrix. The sacrificial layer may be joined to the structural component and may comprising unarranged ceramic fibers, wherein the sacrificial layer may comprise a volume fiber fraction lower than a volume fiber fraction of the structural component.
    Type: Grant
    Filed: June 3, 2016
    Date of Patent: September 3, 2019
    Assignees: Rolls-Royce American Technologies, Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Thomas D. Nixon, Sean E. Landwehr, Aaron D. Sippel, Donald W. Reinhart
  • Turbine blade with reinforced platform for composite material construction
    Patent number: 10392946
    Abstract: A turbine blade of ceramic matrix composite material construction adapted for use in a gas turbine engine is disclosed. The turbine blade includes a root, an airfoil, and a platform. The root is adapted to attach the turbine blade to a disk. The airfoil is shaped to interact with hot gasses moving through the gas path of a gas turbine engine and cause rotation of the turbine blade when the turbine blade is used in a gas turbine engine. The platform has an attachment side facing the root and a gas path side facing the airfoil. The platform is arranged between the root and the airfoil and shaped to extend outwardly from the root and the airfoil in order to block migration of gasses from the gas path toward the root when the turbine blade is used in a gas turbine engine.
    Type: Grant
    Filed: December 21, 2016
    Date of Patent: August 27, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Jay E. Lane
  • Material testing system and method of use
    Patent number: 10371611
    Abstract: The present disclosure relates to a material testing system for use in testing material strength of various gas turbine engine components. The material testing system provides a load force onto portions of gas turbine engine components.
    Type: Grant
    Filed: January 12, 2017
    Date of Patent: August 6, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Jeffrey A. Walston, David J. Thomas, Ted J. Freeman
  • Turbine shroud
    Patent number: 10371008
    Abstract: A turbine shroud for a gas turbine engine includes an annular metallic carrier and a ceramic-containing blade track. A connection is formed between the annular metallic carrier and the ceramic-containing blade track by insert pins extending through metallic carrier into the ceramic-containing blade track.
    Type: Grant
    Filed: December 17, 2015
    Date of Patent: August 6, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Aaron D. Sippel, Bruce E. Varney, Ted J. Freeman, Jeffrey A. Walston, Jun Shi
  • 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
  • Pressure activated seals for a gas turbine engine
    Patent number: 10370994
    Abstract: An assembly for use in a gas turbine engine is disclosed. The assembly includes a first component arranged adjacent to a second component to form a gap therebetween and a pressure activated seal that resists flow through the gap.
    Type: Grant
    Filed: May 19, 2016
    Date of Patent: August 6, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: David J. Thomas, Joseph P. Lamusga, Ted J. Freeman, Aaron D. Sippel