Patents by Inventor David J. Thomas

David J. Thomas 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).

  • Shroud cartridge having a ceramic matrix composite seal segment
    Patent number: 11008881
    Abstract: A shroud for radially encasing a turbine in a gas turbine engine is provided. The shroud comprises a carrier which defines a pin-receiving carrier bore, and a ceramic matrix composite (CMC) seal segment comprising an arcuate flange with a surface facing the turbine and a part that defines a pin-receiving seal segment bore. The seal segment bore is radially spaced from the arcuate flange by a spacing flange which extends radially outward from the arcuate flange to effect receipt within the seal segment bore of an elongated pin. The elongated pin extends through the carrier bore and the seal segment bore, and the elongated pin has a lateral cross-sectional dimension of at least three-eighths of an inch.
    Type: Grant
    Filed: July 23, 2018
    Date of Patent: May 18, 2021
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc., Rolls-Royce High Temperature Composites Inc.
    Inventors: Daniel Kent Vetters, David J. Thomas, Ted Freeman, Douglas David Dierksmeier, Jun Shi, Todd Engel
  • Turbine vane assembly with ceramic matrix composite components
    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
  • Ceramic matrix composite seal segment for a gas turbine engine
    Patent number: 10989060
    Abstract: A ceramic matrix composite (CMC) seal segment for use in a segmented turbine shroud for radially encasing a turbine in a gas turbine engine. The CMC seal segment comprises an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin, with the bore having a length that is at least 70% of the length of the elongated pin received therein. The CMC seal segment is carried by the carrier by at least one of the elongated pins being received within the bore. The CMC seal segment portion defining a pin-receiving bore is radially spaced from the arcuate flange by a spacing flange extending radially outward from the arcuate flange.
    Type: Grant
    Filed: April 10, 2020
    Date of Patent: April 27, 2021
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation, Rolls-Royce High Temperature Composites Inc.
    Inventors: Daniel K. Vetters, David J. Thomas, Ted Freeman, Joseph Lamusga, Rick Uskert, Douglas D. Dierksmeier, Jun Shi, Todd Engel, Matt Brandt
  • AIRFOIL ASSEMBLY WITH CERAMIC MATRIX COMPOSITE PARTS AND LOAD-TRANSFER FEATURES
    Publication number: 20210062663
    Abstract: An airfoil assembly includes a vane that includes an outer platform, an inner platform, and an airfoil. The outer platform defines an outer boundary of a gas path. The inner platform is spaced apart axially from the outer platform relative to an axis and defines an inner boundary of the gas path. The airfoil extends axially between and interconnects the outer platform and the inner platform. Force loads caused by gases interacting with the airfoil are configured to be transmitted from the airfoil assembly to a case arranged around the airfoil assembly.
    Type: Application
    Filed: August 20, 2019
    Publication date: March 4, 2021
    Inventors: Michael J. Whittle, Daniel K. Vetters, Ted J. Freeman, Eric Koenig, Jeff Crutchfield, Jeffrey A. Walston, David J. Thomas
  • Segmented turbine shroud with sealing features
    Patent number: 10934871
    Abstract: A turbine shroud for a gas turbine engine is disclosed in this paper. The turbine shroud includes a ceramic-matrix composite blade track. The ceramic-matrix composite blade track includes a plurality of track segments located circumferentially adjacent to one another to form a track ring. Features of the track segments provide tortuous paths for gasses trying to pass through the ceramic-matrix composite blade track that may reduce leakage through the blade track.
    Type: Grant
    Filed: February 22, 2016
    Date of Patent: March 2, 2021
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Peter Broadhead, Aaron D. Sippel, David J. Thomas, Joseph P. Lamusga
  • Turbine vane assembly with variable position support
    Patent number: 10934868
    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: Grant
    Filed: September 12, 2018
    Date of Patent: March 2, 2021
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: David J. Thomas, Ted J. Freeman, Aaron D. Sippel
  • Turbine shroud assembly with locating pads
    Patent number: 10934891
    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 2, 2021
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.
    Inventors: Ted J. Freeman, Aaron D. Sippel, Daniel K. Vetters, David J. Thomas, Alexandra R. Baucco
  • AIRFOIL ASSEMBLY WITH CERAMIC MATRIX COMPOSITE PARTS AND LOAD-TRANSFER FEATURES
    Publication number: 20210054748
    Abstract: An airfoil assembly includes a vane that includes an outer platform, an inner platform, and an airfoil. The outer platform defines an outer boundary of a gas path. The inner platform is spaced apart axially from the outer platform relative to an axis and defines an inner boundary of the gas path. The airfoil extends axially between and interconnects the outer platform and the inner platform.
    Type: Application
    Filed: August 20, 2019
    Publication date: February 25, 2021
    Inventors: Michael J. Whittle, Daniel K. Vetters, Ted J. Freeman, Eric Koenig, Jeff Crutchfield, Jeffrey A. Walston, David J. Thomas
  • Turbine vane assembly with ceramic matrix composite components mounted to case
    Patent number: 10927689
    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: Grant
    Filed: August 31, 2018
    Date of Patent: February 23, 2021
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: David J. Thomas, Aaron D. Sippel, Ted J. Freeman
  • Turbine shroud having ceramic matrix composite seal segment
    Patent number: 10907493
    Abstract: A segmented turbine shroud for radially encasing a rotatable turbine in a gas turbine engine comprising a carrier, a ceramic matrix composite (CMC) seal segment, and an elongated pin. The carrier defines a pin-receiving carrier bore and the CMC seal segment defines a pin-receiving seal segment bore. The elongated pin extends through the carrier bore and the seal segment bore. The pin-receiving carrier bore includes a cantilevered member such that the carrier bore has a length sufficient to effect radial flexion between the carrier bore and the pin received within the carrier bore during operation of the turbine.
    Type: Grant
    Filed: November 13, 2018
    Date of Patent: February 2, 2021
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc., Rolls-Royce High Temperature Composites Inc.
    Inventors: Daniel Kent Vetters, David J. Thomas, Douglas David Dierksmeier, Jun Shi, Todd Engel
  • Anti-rotation feature
    Patent number: 10890085
    Abstract: A blade track assembly and methods thereof includes an anti-rotation device having an arcuate body and tabs extending for engagement within an anti-rotation slot of the blade track. The anti-rotation device may be formed to include an annular shape connected at a flange of the casing to reduce spatial requirements while blocking against rotation of the blade track.
    Type: Grant
    Filed: September 17, 2018
    Date of Patent: January 12, 2021
    Assignee: Rolls-Royce Corporation
    Inventors: David J. Thomas, Jeffrey A. Walston
  • CERAMIC MATRIX COMPOSITE SEAL SEGMENT FOR A GAS TURBINE ENGINE
    Publication number: 20210003024
    Abstract: A ceramic matrix composite (CMC) seal segment for use in a segmented turbine shroud for radially encasing a turbine in a gas turbine engine. The CMC seal segment comprises an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin, with the bore having a length that is at least 70% of the length of the elongated pin received therein. The CMC seal segment is carried by the carrier by at least one of the elongated pins being received within the bore. The CMC seal segment portion defining a pin-receiving bore is radially spaced from the arcuate flange by a spacing flange extending radially outward from the arcuate flange.
    Type: Application
    Filed: April 10, 2020
    Publication date: January 7, 2021
    Inventors: Daniel K. Vetters, David J. Thomas, Ted Freeman, Joseph Lamusga, Rick Uskert, Douglas D. Dierksmeier, Jun Shi, Todd Engel, Matt Brandt
  • Turbine vane assembly with ceramic matrix composite components
    Patent number: 10808560
    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: Grant
    Filed: June 20, 2018
    Date of Patent: October 20, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Aaron D. Sippel, Ted J. Freeman, David J. Thomas
  • Compliant rail hanger
    Patent number: 10787925
    Abstract: A gas turbine engine assembly includes a supporting component and a supported component. The supporting component includes features engaged by the supported component. The supported component comprises ceramic-containing materials.
    Type: Grant
    Filed: September 12, 2018
    Date of Patent: September 29, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: David J. Thomas, Joseph P. Lamusga, Ted J. Freeman, Andrew J. Lazur
  • Turbine shroud with movable attachment features
    Patent number: 10746054
    Abstract: A turbine shroud for positioning radially outside of blades of a turbine rotor includes a carrier, a blade track, and a track attachment system. The blade track is moved radially outwardly into a cavity of the carrier, and the track attachment system is adjusted to block radially inward movement of the blade track out of the cavity.
    Type: Grant
    Filed: January 16, 2019
    Date of Patent: August 18, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce High Temperature High Composites Inc., Rolls-Royce North American Technologies, Inc.
    Inventors: Aaron D. Sippel, Ted J. Freeman, David J. Thomas, Robert J. Shinavski, Zacheriah A. Cole
  • Ceramic matrix composite component assembly and seal
    Patent number: 10718226
    Abstract: A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a seal configured to block gasses from passing through the interface of two adjacent components. The seal assembly includes a strip seal.
    Type: Grant
    Filed: November 21, 2017
    Date of Patent: July 21, 2020
    Assignee: Rolls-Royce Corporation
    Inventors: Daniel K. Vetters, Jeffrey Walston, David J. Thomas
  • Seals for a gas turbine engine assembly
    Patent number: 10704404
    Abstract: A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a pressure-activated seal. The pressure-activated seal is arranged in a channel formed between a first component and a second component that opens toward the high pressure zone.
    Type: Grant
    Filed: March 21, 2016
    Date of Patent: July 7, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Jun Shi, Ted J. Freeman, David J. Thomas
  • Turbine shroud with I-beam construction
    Patent number: 10697314
    Abstract: A turbine shroud assembly of a gas turbine engine for combustion of fuel mixed with air to produce exhaust products includes a blade track having an I-beam construction including ceramic materials and defining a flow surface to guide exhaust products through a turbine section of the gas turbine engine to expand the exhaust products across the turbine section to produce force.
    Type: Grant
    Filed: October 14, 2016
    Date of Patent: June 30, 2020
    Assignee: Rolls-Royce Corporation
    Inventors: David J. Thomas, Jeffrey A. Walston
  • Ceramic matrix composite seal segment for a gas turbine engine
    Patent number: 10619503
    Abstract: A ceramic matrix composite (CMC) seal segment for use in a segmented turbine shroud for radially encasing a turbine in a gas turbine engine. The CMC seal segment comprises an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin, with the bore having a length that is at least 70% of the length of the elongated pin received therein. The CMC seal segment is carried by the carrier by at least one of the elongated pins being received within the bore. The CMC seal segment portion defining a pin-receiving bore is radially spaced from the arcuate flange by a spacing flange extending radially outward from the arcuate flange.
    Type: Grant
    Filed: July 26, 2017
    Date of Patent: April 14, 2020
    Assignees: Rolls-Royce High Temperature Composites Inc., Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Daniel K. Vetters, David J. Thomas, Ted Freeman, Joseph Lamusga, Rick Uskert, Douglas D. Dierksmeier, Jun Shi, Todd Engel, Matt Brandt
  • Turbine blade with heat shield
    Patent number: 10612385
    Abstract: An airfoil assembly for use in a gas turbine engine is disclosed. The airfoil assembly includes a root, a tip shroud, and an airfoil located between the root and tip shroud. The airfoil includes a spar, a heat shield arranged around the spar, and a plurality of describe rigid load supports extending between the spar and the heat shield to transfer loads between the heat shield and the spar.
    Type: Grant
    Filed: March 7, 2016
    Date of Patent: April 7, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Tara G. Schetzel, Ted J. Freeman, David J. Thomas