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).

  • GAS TURBINE ENGINE FEATURES FOR TIP CLEARANCE INSPECTION
    Publication number: 20180216481
    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: Application
    Filed: January 31, 2017
    Publication date: August 2, 2018
    Inventors: Aaron D. Sippel, Brian J. Shoemaker, Ted J. Freeman
  • MATERIAL TESTING SYSTEM AND METHOD OF USE
    Publication number: 20180195940
    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: Application
    Filed: January 12, 2017
    Publication date: July 12, 2018
    Inventors: Jeffrey A. Walston, David J. Thomas, Ted J. Freeman
  • 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
  • THREE-DIMENSIONALLY WOVEN CERAMIC MATRIX COMPOSITE TURBINE BLADE
    Publication number: 20180171806
    Abstract: A ceramic matrix composite turbine blade for use in a gas turbine engine includes a root, a platform, and an airfoil.
    Type: Application
    Filed: December 21, 2016
    Publication date: June 21, 2018
    Inventors: Ted J. Freeman, David J. Thomas, Aaron D. Sippel
  • TURBINE BLADE WITH REINFORCED PLATFORM FOR COMPOSITE MATERIAL CONSTRUCTION
    Publication number: 20180171805
    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: Application
    Filed: December 21, 2016
    Publication date: June 21, 2018
    Inventors: Ted J. Freeman, Jay E. Lane
  • 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 with Dovetail Connection Having Contoured Root
    Publication number: 20180149026
    Abstract: A gas turbine engine includes a turbine having turbine blades and a shroud having a blade track for positioning radially outside of the blades. At least one of the blades and the blade track are secured in place using a dovetail connection between a dovetail receiver and a dovetail assembly formed to include a contoured root.
    Type: Application
    Filed: November 30, 2016
    Publication date: May 31, 2018
    Inventors: Daniel K. Vetters, Ted J. Freeman, Andrew J. Lazur, Robert J. Shinavski, Wayne S. Steffier
  • Turbine Shroud Assembly with Locating Pads
    Publication number: 20180149042
    Abstract: An assembly adapted for use in a gas turbine engine has a carrier component and a supported component. The assembly including a mounting system for coupling the supported component to the carrier component and a seal adapted to resist the movement of gasses between the supported component to the carrier component. In an illustrative embodiment, the assembly is a turbine shroud segment for blocking gasses from passing over turbine blades included in the gas turbine engine.
    Type: Application
    Filed: November 3, 2017
    Publication date: May 31, 2018
    Inventors: Ted J. Freeman, Aaron D. Sippel, Daniel K. Vetters, David J. Thomas, Alexandra R. Baucco
  • TURBINE SHROUD WITH HANGER ATTACHMENT
    Publication number: 20180149030
    Abstract: An assembly adapted for use in a gas turbine engine has a carrier component and a supported component. The assembly including a mounting system for coupling the supported component to the carrier component and a seal adapted to resist the movement of gasses between the supported component to the carrier component. In an illustrative embodiment, the assembly is a turbine shroud segment for blocking gasses from passing over turbine blades included in the gas turbine engine.
    Type: Application
    Filed: November 3, 2017
    Publication date: May 31, 2018
    Inventors: Ted J. Freeman, Aaron D. Sippel, Daniel K. Vetters, David J. Thomas, Alexandra R. Baucco
  • TURBINE SHROUD ASSEMBLY WITH TANDEM SEALS
    Publication number: 20180149031
    Abstract: An assembly adapted for use in a gas turbine engine has a carrier component and a supported component. The assembly including a mounting system for coupling the supported component to the carrier component and a seal adapted to resist the movement of gasses between the supported component to the carrier component. In an illustrative embodiment, the assembly is a turbine shroud segment for blocking gasses from passing over turbine blades included in the gas turbine engine.
    Type: Application
    Filed: November 3, 2017
    Publication date: May 31, 2018
    Inventors: Aaron D. Sippel, Ted J. Freeman
  • TURBINE SHROUD ASSEMBLY WITH ANTI-ROTATION FEATURES
    Publication number: 20180149041
    Abstract: An assembly adapted for use in a gas turbine engine has a carrier component and a supported component. The assembly including a mounting system for coupling the supported component to the carrier component and a seal adapted to resist the movement of gasses between the supported component to the carrier component. In an illustrative embodiment, the assembly is a turbine shroud segment for blocking gasses from passing over turbine blades included in the gas turbine engine.
    Type: Application
    Filed: November 3, 2017
    Publication date: May 31, 2018
    Inventors: Ted J. Freeman, Aaron D. Sippel, Daniel K. Vetters, David J. Thomas, Alexandra R. Baucco, Joseph P. Lamusga
  • Vane assembly for a gas turbine engine
    Patent number: 9970317
    Abstract: A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends from the inner platform to the outer platform. A clamp mechanism couples the inner platform and the outer platform to the ceramic-containing airfoil.
    Type: Grant
    Filed: September 29, 2015
    Date of Patent: May 15, 2018
    Assignees: Rolls-Royce North America Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Bruce E. Varney, David J. Thomas, Jeffrey A. Walston
  • Composite components for gas turbine engines
    Patent number: 9963979
    Abstract: A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed as a composite structure including a number of plies of ceramic-containing material. The blades each include a root to fit within dovetail slots of the rotor disk to couple the blades to the rotor disk.
    Type: Grant
    Filed: September 29, 2015
    Date of Patent: May 8, 2018
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Ted J. Freeman
  • TURBINE WHEEL ASSEMBLY WITH CERAMIC MATRIX COMPOSITE COMPONENTS
    Publication number: 20180112543
    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: Application
    Filed: October 26, 2016
    Publication date: April 26, 2018
    Inventors: David J. Thomas, Ted J. Freeman, Aaron D. Sippel, Daniel K. Vetters
  • Segmented turbine shroud with seals
    Patent number: 9945256
    Abstract: A turbine shroud for a gas turbine engine includes a plurality of shroud segments arranged around a central axis. Each shroud segment includes a carrier segment, a blade track segment, and a radial seal element that seals a radial interface between the carrier segment and the blade track segment. The turbine shroud further includes a plurality of circumferential seals that seal circumferential interfaces between the shroud segments.
    Type: Grant
    Filed: June 9, 2015
    Date of Patent: April 17, 2018
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Ted J. Freeman, David J. Thomas, Joseph P. Lamusga, Aaron D. Sippel
  • 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
  • Method for integral joining infiltrated ceramic matrix composites
    Patent number: 9938198
    Abstract: Integrated ceramic matrix composite components for use in gas turbine engines are disclosed along with methods for making the same. The methods include coinfiltrating a greenbody assembly with ceramic matrix to produce an integrated component.
    Type: Grant
    Filed: June 21, 2016
    Date of Patent: April 10, 2018
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc., Rolls-Royce High Temperature Composites Inc.
    Inventors: Sean E. Landwehr, Daniel K. Vetters, Ted J. Freeman, Robert J. Shinavski
  • Turbine shroud with sealed blade track
    Patent number: 9938846
    Abstract: A turbine shroud for a gas turbine engine includes a plurality of shroud segments arranged around a central axis. Each shroud segment includes a carrier component, a blade track component, and a retainer component that couples the blade track component to the carrier component. The turbine shroud further includes a plurality of circumferential seals that seal circumferential interfaces between the shroud segments.
    Type: Grant
    Filed: June 10, 2015
    Date of Patent: April 10, 2018
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, David J. Thomas, Joseph P. Lamusga, Aaron D. Sippel
  • Turbine disk assembly including seperable platforms for blade attachment
    Patent number: 9909430
    Abstract: An apparatus includes a disk, an attachment member, and a blade. The disk has an outer surface including a coupling portion. The attachment member has a coupling portion and defines at least a portion of an opening. The coupling portion of the first attachment member is configured to be coupled to the coupling portion of the disk. A portion of the blade is configured to be disposed within the opening when the coupling portion of the attachment member is coupled to the coupling portion of the disk.
    Type: Grant
    Filed: November 3, 2015
    Date of Patent: March 6, 2018
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Ted J. Freeman
  • METHOD OF ASSEMBLY OF BI-CAST TURBINE VANE
    Publication number: 20180030840
    Abstract: One aspect of the present disclosure includes a turbine vane assembly comprising a vane made from ceramic matrix composite material having an outer wall extending between a leading edge and a trailing edge and between a first end and an opposing second end; an endwall made at least partially from a ceramic matrix composite material configured to engage the first end of the vane; and a retaining region including corresponding bi-cast grooves formed adjacent the first end of the vane and a receiving aperture formed in the endwall; wherein a bond is formed in the retaining region to join the vane and endwall together.
    Type: Application
    Filed: September 21, 2017
    Publication date: February 1, 2018
    Inventors: Ted J. Freeman, Robert F. Proctor, Sean E. Landwehr, Adam L. Chamberlain