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).

  • Turbine vane with ceramic matrix composite airfoil
    Patent number: 10563528
    Abstract: A turbine vane adapted for use in a gas turbine engine is described in this application. The turbine vane illustratively includes ceramic matrix composite components adapted to be coupled to metallic components.
    Type: Grant
    Filed: May 23, 2017
    Date of Patent: February 18, 2020
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Ted J. Freeman
  • TURBINE VANE ASSEMBLY WITH CERAMIC MATRIX COMPOSITE COMPONENTS
    Publication number: 20200024972
    Abstract: Structural rod supports are provided in vanes in a gas turbine assembly in order to provide support to the vanes and an annular seal. Structural rods couple to the turbine case at one end and the annular seal at an opposite end.
    Type: Application
    Filed: July 20, 2018
    Publication date: January 23, 2020
    Inventors: Ted J. Freeman, Daniel K. Vetters, Christopher Nash, Eric Koenig, Michael Whittle
  • ABRASIVE TIPS FOR CERAMIC MATRIX COMPOSITE BLADES AND METHODS FOR MAKING THE SAME
    Publication number: 20200024973
    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: Application
    Filed: January 10, 2019
    Publication date: January 23, 2020
    Inventors: Richard C. Uskert, Kang N. Lee, Ted J. Freeman
  • TURBINE VANE ASSEMBLY WITH CERAMIC MATRIX COMPOSITE COMPONENTS
    Publication number: 20200025025
    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: Application
    Filed: July 17, 2018
    Publication date: January 23, 2020
    Inventors: Aaron D. Sippel, Ted J. Freeman, David J. Thomas, Adam L. Chamberlain
  • TURBINE SHROUD SEGMENT WITH LOAD DISTRIBUTION SPRINGS
    Publication number: 20200025013
    Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.
    Type: Application
    Filed: December 20, 2018
    Publication date: January 23, 2020
    Inventors: Mark O'Leary, Daniel K. Vetters, Matthew R. Brandt, Ted J. Freeman
  • TURBINE WHEEL ASSEMBLY WITH CERAMIC MATRIX COMPOSITE BLADES
    Publication number: 20200018177
    Abstract: A wheel assembly for a gas turbine engine includes a disk, a blade-attachment system, and a plurality of blades. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blade-attachment system is configured to couple the plurality of blades with the disk for rotation therewith.
    Type: Application
    Filed: July 11, 2018
    Publication date: January 16, 2020
    Inventors: Aaron D. Sippel, Ted J. Freeman
  • Seal segment retention ring with chordal seal feature
    Patent number: 10519807
    Abstract: Turbine assemblies for a turbine of a gas turbine engine are disclosed herein. The turbine assemblies include a carrier and a blade track. The blade track extends around blades of a turbine wheel assembly to block gasses passed along a gas path from moving over the blades without causing the blades to rotate during operation of the turbine assembly. The blade track includes a plurality of blade track segments arranged circumferentially adjacent to one another about a central axis to form a ring. A retention ring engages both the carrier and the blade track segments to facilitate coupling and sealing.
    Type: Grant
    Filed: April 19, 2017
    Date of Patent: December 31, 2019
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc., Rolls-Royce High Temperature Composites Inc.
    Inventors: Brian J. Shoemaker, Joseph P. Lamusga, Ted J. Freeman
  • TURBINE WHEEL ASSEMBLY WITH CERAMIC MATRIX COMPOSITE COMPONENTS
    Publication number: 20190390557
    Abstract: The present disclosure is related to turbine wheel assemblies for gas turbine engines. Such turbine wheel assemblies may include ceramic matrix composite airfoil components mounted with different types of coupling to a central disc.
    Type: Application
    Filed: June 22, 2018
    Publication date: December 26, 2019
    Inventors: Jun Shi, Ted J. Freeman
  • TURBINE VANE ASSEMBLY WITH CERAMIC MATRIX COMPOSITE COMPONENTS
    Publication number: 20190390558
    Abstract: A turbine vane assembly includes an airfoil, a support strut, and an inner seal panel. The airfoil is formed to include an interior region of the airfoil. The support strut is located in the interior region of the airfoil and configured to carry loads that act on the airfoil. The inner seal panel extends at least partway about the axis to resist fluid communication between a region upstream of the inner seal panel and a region downstream of the inner seal panel.
    Type: Application
    Filed: June 20, 2018
    Publication date: December 26, 2019
    Inventors: Aaron D. Sippel, Ted J. Freeman, David J. Thomas
  • Compartmentalization of cooling air flow in a structure comprising a CMC component
    Patent number: 10502072
    Abstract: A structure in a gas turbine engine comprises a spar and a CMC component adjoining the spar and separated from the spar by a cavity supplied by cooling air. At least one rope seal is installed in the cavity within a groove made in the spar to thus compartmentalize the cavity and control the flow of cooling air.
    Type: Grant
    Filed: December 19, 2016
    Date of Patent: December 10, 2019
    Assignees: Rolls-Royce North American Technologies, Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, David J. Thomas
  • CERAMIC MATRIX COMPOSITE BLADE TRACK ASSEMBLY WITH TIP CLEARANCE CONTROL
    Publication number: 20190368367
    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: Application
    Filed: May 30, 2018
    Publication date: December 5, 2019
    Inventors: Ted J. Freeman, Aaron D. Sippel
  • TURBINE VANE ASSEMBLY WITH CERAMIC MATRIX COMPOSITE COMPONENTS
    Publication number: 20190368360
    Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes an airfoil, an endwall, and a spar. The airfoil is shaped to interact with hot gases moving axially along a primary gas path of the gas turbine engine. The endwall is shaped to define a boundary of the primary gas path near a radial end of the airfoil. The spar is located in an interior region of the airfoil to carry loads that act on the airfoil during operation of the gas turbine engine.
    Type: Application
    Filed: June 1, 2018
    Publication date: December 5, 2019
    Inventors: Ted J. Freeman, Aaron D. Sippel, David J. Thomas
  • Airfoil for a gas turbine engine having insulating materials
    Patent number: 10487672
    Abstract: An airfoil adapted for use in a gas turbine engine is disclosed. The airfoil may include components made from ceramic materials. The airfoil may include insulating material to thermally isolate portions of the airfoil.
    Type: Grant
    Filed: November 20, 2017
    Date of Patent: November 26, 2019
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Daniel K. Vetters, Ted J. Freeman
  • BLISK BONDED CMC AIRFOIL HAVING ATTACHMENT
    Publication number: 20190345831
    Abstract: A turbine blade is secured with a turbine disk by a retention assembly. The retention assembly is secured with the disk by forming a diffusion joint with the disk.
    Type: Application
    Filed: May 14, 2018
    Publication date: November 14, 2019
    Inventors: Ted J. Freeman, Aaron D. Sippel, Bruce E. Varney
  • Machinable CMC insert
    Patent number: 10472976
    Abstract: An assembly comprising a ceramic matrix composite component, a monolithic insert, and a polymer char and a method for producing the same. The ceramic matrix composite component may include an exterior surface, with the monolithic insert bonded to the exterior surface of the ceramic matrix composite component. The polymer char may be sandwiched between the monolithic insert and the exterior surface of the ceramic matrix composite that may bond the monolithic insert to the ceramic matrix composite component.
    Type: Grant
    Filed: June 3, 2016
    Date of Patent: November 12, 2019
    Assignees: Rolls-Royce Corporation, Rolls-Royce American Technologies, Inc.
    Inventors: Ted J. Freeman, Thomas D. Nixon, Sean E. Landwehr, Aaron D. Sippel, Donald W. Reinhart
  • MULTI-PIECE TURBINE DISK FOR CERAMIC MATRIX COMPOSITE COMPONENTS
    Publication number: 20190338657
    Abstract: A multi-piece disk for use in a turbine of a gas turbine engine. The multi-piece disk includes a fore disk segment and an aft disk segment coupled with the fore disk segment for movement with the fore disk segment. The fore disk segment and the aft disk segment are formed to define slots that extend through the disk segments and are configured to receive turbine blades therein.
    Type: Application
    Filed: May 4, 2018
    Publication date: November 7, 2019
    Inventors: Ted J. Freeman, Christopher Barrett
  • Machinable CMC insert
    Patent number: 10465534
    Abstract: A ceramic matrix composite component and a ceramic insert, and a method for producing the same. The ceramic matrix composite component may include an exterior surface comprising silicon fibers in a silicon carbide matrix. The insert may include a continuous porosity bonded to the exterior surface of the ceramic matrix composite component. The silicon carbide matrix of the ceramic matrix composite component may extend into the porosity of the ceramic insert to bond the ceramic insert to the ceramic matrix composite component.
    Type: Grant
    Filed: June 3, 2016
    Date of Patent: November 5, 2019
    Assignees: Rolls-Royce North 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 ATTACHMENT-SUPPORTED PLATFORM FOR COMPOSITE MATERIAL CONSTRUCTION
    Publication number: 20190330990
    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: Application
    Filed: June 28, 2019
    Publication date: October 31, 2019
    Inventors: Aaron D. Sippel, Daniel K. Vetters, Ted J. Freeman, David J. Thomas
  • GAS TURBINE ENGINE VANE END DEVICES
    Publication number: 20190330993
    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: June 26, 2019
    Publication date: October 31, 2019
    Inventors: Linnea Taketa, John Munson, Ted J. Freeman
  • 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