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).

  • Publication number: 20210164365
    Abstract: A turbine shroud assembly includes a carrier, a blade track segment, and an attachment pin. The carrier is arranged to extend circumferentially at least partway around an axis. The blade track segment includes a runner that faces the axis to define a portion of a primary gas path of the gas turbine engine and an attachment flange that extends radially away from the runner. The attachment pin is configured to mount the blade track segment to the carrier.
    Type: Application
    Filed: December 3, 2019
    Publication date: June 3, 2021
    Inventors: Shaling Starr, Aaron D. Sippel, Ted J. Freeman, David J. Thomas
  • Publication number: 20210148252
    Abstract: A turbine shroud assembly for use with a gas turbine engine includes a blade track segment coupled to a carrier segment, and a sheet-metal seal that seals therebetween. The blade track segment includes a shroud wall that extends circumferentially partway around an axis and an attachment feature that extends radially outward from the shroud wall. The carrier is coupled with the attachment feature to support the blade track segment.
    Type: Application
    Filed: November 19, 2019
    Publication date: May 20, 2021
    Inventors: Ted J. Freeman, David J. Thomas, Jeffrey A. Walston, Aaron D. Sippel
  • Publication number: 20210148248
    Abstract: A turbine assembly adapted for use with a gas turbine engine includes an outer case, a blade track segment, and a carrier. The outer case extends circumferentially at least partway around an axis of the engine. The blade track segment is configured to define a portion of a gas path of the turbine assembly. The carrier is coupled with the outer case and the blade track segment to support the blade track segment in position radially relative to the axis.
    Type: Application
    Filed: November 19, 2019
    Publication date: May 20, 2021
    Inventors: Ted J. Freeman, David J. Thomas, Jeffrey A. Walston, Aaron D. Sippel
  • Publication number: 20210148244
    Abstract: A turbine shroud assembly for use with a gas turbine engine includes a carrier assembly coupled to a blade track segment, and a sheet-metal seal that seals on axial and radial facing surfaces therebetween. The blade track segment includes a shroud wall that extends circumferentially partway around an axis and an attachment feature that extends radially outward from the shroud wall. The carrier is coupled with the attachment feature to support the blade track segment.
    Type: Application
    Filed: November 19, 2019
    Publication date: May 20, 2021
    Inventors: Ted J. Freeman, David J. Thomas, Jeffrey A. Walston, Aaron D. Sippel
  • 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
  • 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
  • Patent number: 11011693
    Abstract: Embodiments of the present disclosure describe integrated quantum circuit assemblies that include quantum circuit components pre-packaged, or integrated, with some other electronic components and mechanical attachment means for easy inclusion within a cooling apparatus. An example integrated quantum circuit assembly includes a package and mechanical attachment means for securing the package within a cryogenic chamber of a cooling apparatus. The package includes a plurality of components, such as a quantum circuit component, an attenuator, and a directional coupler, which are integral to the package. Such an integrated assembly may significantly speed up installation and may help develop systems for rapidly bringing up quantum computers.
    Type: Grant
    Filed: June 24, 2019
    Date of Patent: May 18, 2021
    Assignee: Intel Corporation
    Inventors: Lester Lampert, Ravi Pillarisetty, Nicole K. Thomas, Hubert C. George, Jeanette M. Roberts, David J. Michalak, Roman Caudillo, Thomas Francis Watson, Stephanie A. Bojarski, James S. Clarke
  • Publication number: 20210132609
    Abstract: An autonomous vehicle is configured to move across a floor surface in an environment. The autonomous vehicle includes a proximity sensor that is positionable at different heights on the autonomous vehicle. A location of the autonomous vehicle within the environment is determined. A proximity sensor height is determined based on the location of the autonomous vehicle within the environment. The proximity sensor is positioned at a height on the autonomous vehicle based on the proximity sensor height. A signal is received from the proximity sensor where the signal is indicative of a distance to an object within the environment at the height of the proximity sensor on the autonomous vehicle. An operation of the autonomous vehicle can be controlled based on the signal indicative of the distance to the object.
    Type: Application
    Filed: March 9, 2018
    Publication date: May 6, 2021
    Inventors: Stephen D. Herr, Stephen J. Balas, David M. Knuth, Aurle Y. Gagne, Philip Hennessy, Samuel E. Elzarian, Kevin L. Thomas
  • 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
  • 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
  • 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
  • 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
  • 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
  • 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
  • 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
  • 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
  • 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
  • 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
  • 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
  • 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