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).

  • Method of assembly of bi-cast turbine vane
    Patent number: 10612402
    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: Grant
    Filed: September 21, 2017
    Date of Patent: April 7, 2020
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Robert F. Proctor, Sean E. Landwehr, Adam L. Chamberlain
  • Turbine vane assembly with ceramic matrix composite components
    Patent number: 10612399
    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: Grant
    Filed: June 1, 2018
    Date of Patent: April 7, 2020
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Aaron D. Sippel, David J. Thomas
  • TURBINE WHEEL ASSEMBLY WITH CERAMIC MATRIX COMPOSITE BLADES
    Publication number: 20200102842
    Abstract: A turbine wheel assembly adapted for use in a gas turbine engine includes turbine blades made from ceramic matric composite materials. The turbine blades are mounted to a disk and anti-rotation features block movement of the turbine blades around a circumference of the disk.
    Type: Application
    Filed: September 27, 2018
    Publication date: April 2, 2020
    Inventors: Aaron D. Sippel, Ted J. Freeman
  • TURBINE WHEEL ASSEMBLY WITH OFFLOADED PLATFORMS AND CERAMIC MATRIX COMPOSITE BLADES
    Publication number: 20200095875
    Abstract: A wheel assembly for a gas turbine engine includes a disk, a plurality of blades, and a plurality of platforms. The disk is configured to rotate about an axis during operation of the gas turbine engine. Each of the plurality of blades includes a root received in the disk and an airfoil that extends radially away from the root. The platforms are arranged around the blades to define a boundary of a flow path of the gas turbine engine.
    Type: Application
    Filed: September 26, 2018
    Publication date: March 26, 2020
    Inventors: Aaron D. Sippel, Ted J. Freeman
  • TURBINE WHEEL ASSEMBLY WITH PLATFORM RETENTION FEATURES
    Publication number: 20200095874
    Abstract: A wheel assembly for a gas turbine engine includes a disk, a plurality of blades, and a platform system. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blades are coupled with the disk for rotation therewith. The platform system includes a plurality of platforms arranged around the blades and a coverplate that blocks movement of the platforms relative to the disk.
    Type: Application
    Filed: September 26, 2018
    Publication date: March 26, 2020
    Inventors: Ted J. Freeman, Aaron D. Sippel, Anthony Razzell
  • TURBINE VANE ASSEMBLY WITH VARIABLE POSITION SUPPORT
    Publication number: 20200080434
    Abstract: A vane assembly for use in a gas turbine engine includes an airfoil, a strut, and a support member. The airfoil is configured to interact with gases flowing through a primary gas path of the engine. The strut is located in an interior region of the airfoil and configured to carry loads that act on the airfoil by the gases. The support member is configured to compensate for relative thermal expansion between the components of the vane assembly caused by heat generated during use of the engine to locate the airfoil radially in the primary gas path.
    Type: Application
    Filed: September 12, 2018
    Publication date: March 12, 2020
    Inventors: David J. Thomas, Ted J. Freeman, Aaron D. Sippel
  • TURBINE WHEEL ASSEMBLY WITH PINNED CERAMIC MATRIX COMPOSITE BLADES
    Publication number: 20200080431
    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: September 12, 2018
    Publication date: March 12, 2020
    Inventors: Sachin Dhiwar, Ted J. Freeman, Thomas Martin
  • Split line flow path seals
    Patent number: 10584605
    Abstract: A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a seal assembly configured to block gasses from passing through the interface of two adjacent components. The seal assembly includes a rod.
    Type: Grant
    Filed: August 9, 2017
    Date of Patent: March 10, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc., Rolls-Royce High Temperature Composites Inc., Rolls-Royce plc
    Inventors: Aaron D. Sippel, Ted J. Freeman, David J. Thomas, Joseph P. Lamusga, Brian J. Shoemaker, Steven Hillier
  • PINNED PLATFORM FOR BLADE WITH CIRCUMFERENTIAL ATTACHMENT
    Publication number: 20200072063
    Abstract: A wheel assembly for a gas turbine engine includes a disk, a plurality of blades, and a platform system that includes a plurality of platforms and pins. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blades each include a circumferentially extending root received in the disk and an airfoil that extends radially away from the root. The platforms are arranged around the wheel to define a flow path of the gas turbine engine and the pins extend into the platforms and the disk to couple the platforms with the disk.
    Type: Application
    Filed: August 31, 2018
    Publication date: March 5, 2020
    Inventors: Aaron D. Sippel, Ted J. Freeman, Loic Fabries
  • TURBINE BLADE ASSEMBLY WITH CERAMIC MATRIX COMPOSITE COMPONENTS
    Publication number: 20200072065
    Abstract: A wheel assembly for a gas turbine engine includes a disk and a plurality of blades. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blades each include a circumferentially extending root received in the disk and an airfoil that extends radially away from the root.
    Type: Application
    Filed: August 31, 2018
    Publication date: March 5, 2020
    Inventors: Aaron D. Sippel, Ted J. Freeman, Loic Fabries
  • TURBINE VANE ASSEMBLY WITH CERAMIC MATRIX COMPOSITE COMPONENTS MOUNTED TO CASE
    Publication number: 20200072066
    Abstract: A vane assembly for a gas turbine engine is provided having an outer casing and an inner casing radially spaced apart from the outer casing. An airfoil extends radially between the outer casing and the inner casing. The airfoil includes a spar having an outer endwall positioned adjacent the outer casing and an inner endwall positioned adjacent the inner casing. A pressure side and a suction side extend between the inner endwall and the outer endwall. A ceramic matrix composite cover has a pressure side extending along the pressure side of the spar and a suction side extending along the suction side of the spar.
    Type: Application
    Filed: August 31, 2018
    Publication date: March 5, 2020
    Inventors: David J. Thomas, Aaron D. Sippel, Ted J. Freeman
  • PLATFORM WITH AXIAL ATTACHMENT FOR BLADE WITH CIRCUMFERENTIAL ATTACHMENT
    Publication number: 20200072064
    Abstract: A wheel assembly for a gas turbine engine includes a disk, a plurality of blades, and a plurality of platforms. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blades each include a circumferentially extending attachment feature that is received in the disk. The platforms each have an axially extending attachment feature that is received in the disk.
    Type: Application
    Filed: August 31, 2018
    Publication date: March 5, 2020
    Inventors: Aaron D. Sippel, Ted J. Freeman, Loic Fabries
  • Gas turbine engine with dovetail connection having contoured root
    Patent number: 10577951
    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: Grant
    Filed: November 30, 2016
    Date of Patent: March 3, 2020
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce High Temperature Composites Inc.
    Inventors: Daniel K. Vetters, Ted J. Freeman, Andrew J. Lazur, Robert J. Shinavski, Wayne S. Steffier
  • Turbine disk with blade supported platforms
    Patent number: 10577961
    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: Grant
    Filed: April 23, 2018
    Date of Patent: March 3, 2020
    Assignees: Rolls-Royce High Temperature Composites Inc., Rolls-Royce plc, Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Stephen Harris, Aaron D. Sippel, Ted J. Freeman, Anthony Razzell
  • Turbine shroud assembly with anti-rotation features
    Patent number: 10577978
    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: Grant
    Filed: November 3, 2017
    Date of Patent: March 3, 2020
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation, Rolls-Royce High Temperature Composites Inc.
    Inventors: Ted J. Freeman, Aaron D. Sippel, Daniel K. Vetters, David J. Thomas, Alexandra R. Baucco, Joseph P. Lamusga
  • Turbine shroud segment with flange-facing perimeter seal
    Patent number: 10577960
    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: Grant
    Filed: July 11, 2018
    Date of Patent: March 3, 2020
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Mark O'Leary, Daniel K. Vetters, Matthew R. Brandt, Ted J. Freeman
  • TURBINE WHEEL ASSEMBLY
    Publication number: 20200063577
    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: August 22, 2018
    Publication date: February 27, 2020
    Inventors: Michael J. Whittle, Alexander Wong, Anthony Razzell, Ted J. Freeman
  • CERAMIC MATRIX COMPOSITE TURBINE BLADE WITH LIGHTENING HOLE
    Publication number: 20200063571
    Abstract: A turbine blade of ceramic matrix composite material construction adapted for use in a gas turbine engine is disclosed. The turbine blade includes an airfoil and a tip to discourage air leakage over the tip of the turbine blade. The turbine blade is designed considering weight and strength to include a lightening hole.
    Type: Application
    Filed: August 27, 2018
    Publication date: February 27, 2020
    Inventors: Ted J. Freeman, Aaron D. Sippel, Robert J. Shinavski
  • TURBINE BLADE COMPRISING CERAMIC MATRIX COMPOSITE MATERIALS
    Publication number: 20200063575
    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 disk.
    Type: Application
    Filed: August 24, 2018
    Publication date: February 27, 2020
    Inventors: Ted J. Freeman, Anthony Razzell, Michael J. Whittle
  • Composite airfoil for a gas turbine engine
    Patent number: 10563522
    Abstract: Stationary vanes and rotating blades of a gas turbine engine are disclosed that include airfoils formed from ceramic matrix composite materials. The airfoils include at least one layer of ceramic-containing matrix material and ceramic-containing reinforcing fibers suspended in the matrix material. A core of the airfoils is surrounded by the at least one layer of ceramic-containing fiber/matrix material.
    Type: Grant
    Filed: July 13, 2015
    Date of Patent: February 18, 2020
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: David J. Thomas, Ted J. Freeman, Jeffrey A. Walston