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).

  • 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
  • ANTI-ROTATION FEATURE
    Publication number: 20200088065
    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: Application
    Filed: September 17, 2018
    Publication date: March 19, 2020
    Inventors: David J. THOMAS, Jeffrey A. WALSTON
  • 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
  • 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
  • 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
  • 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 blade with three-dimensional CMC construction elements
    Patent number: 10577939
    Abstract: An ceramic matrix composite blade for use in a gas turbine engine is disclosed. The ceramic matrix composite blade includes a root, an airfoil, and a platform located between the root and the airfoil.
    Type: Grant
    Filed: November 1, 2016
    Date of Patent: March 3, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Daniel K. Vetters, David J. Thomas
  • BRAZED BLADE TRACK FOR A GAS TURBINE ENGINE
    Publication number: 20200056493
    Abstract: A blade track for a gas turbine engine includes segments and joints that couple the segments together. Each segment extends part-way around a central axis of the engine and the joints couple together adjacent segments to form a full hoop.
    Type: Application
    Filed: October 23, 2019
    Publication date: February 20, 2020
    Inventors: Aaron D. Sippel, Daniel K. Vetters, Jun Shi, David J. Thomas, Andrew J. Eifert, Peter Broadhead
  • Keystoned blade track
    Patent number: 10563535
    Abstract: A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.
    Type: Grant
    Filed: April 4, 2016
    Date of Patent: February 18, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc., Rolls-Royce plc
    Inventors: Daniel K. Vetters, Aaron D. Sippel, David J. Thomas, Andrew J. Eifert, Paul A. Davis, Simon L. Jones, Peter Broadhead, Bruce E. Varney, Jeffrey A. Walston, Steven Hillier
  • 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
  • Full hoop blade track with flanged segments
    Patent number: 10550709
    Abstract: A blade track assembly is disclosed. The blade track assembly comprises a plurality of ceramic matrix composite blade track segments arranged circumferentially adjacent to one another around a central axis. Each of the blade track segments includes an arcuate runner extending in a circumferential direction around a portion of the central axis and is coupled to circumferentially adjacent blade track segments.
    Type: Grant
    Filed: April 1, 2016
    Date of Patent: February 4, 2020
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation, Rolls-Royce plc, Rolls-Royce High Temperature Composites Inc.
    Inventors: Daniel K. Vetters, Aaron D. Sippel, David J. Thomas, Andrew J. Eifert, Paul A. Davis, Simon L. Jones, Steven M. Hillier, Peter Broadhead, Joseph Doyle, Michael Jacquinto, Wesley Thibault, Jun Shi, Roderick Townes
  • GAS TURBINE ENGINE COMPOSITE VANE ASSEMBLY AND METHOD FOR MAKING THE SAME
    Publication number: 20200024955
    Abstract: A gas turbine engine composite vane assembly and method for making same are disclosed. The method includes providing at least two gas turbine engine airfoil composite preform components. The airfoil composite preform components are interlocked with a first locking component so that mating faces of the airfoil composite preform components face each other. A filler material is inserted between the mating surfaces of the airfoil composite preform components.
    Type: Application
    Filed: November 27, 2018
    Publication date: January 23, 2020
    Inventors: Richard C. USKERT, David J. THOMAS, Wayne S. STEFFIER, Robert J. SHINAVSKI, Adam L. Chamberlain
  • TURBINE SHROUD HAVING CERAMIC MATRIX COMPOSITE SEAL SEGMENT
    Publication number: 20200025012
    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: Application
    Filed: November 13, 2018
    Publication date: January 23, 2020
    Applicants: 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
  • 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 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
  • 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
  • Brazed blade track for a gas turbine engine
    Patent number: 10494935
    Abstract: A blade track for a gas turbine engine includes segments and joints that couple the segments together. Each segment extends part-way around a central axis of the engine and the joints couple together adjacent segments to form a full hoop.
    Type: Grant
    Filed: April 8, 2016
    Date of Patent: December 3, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation, Rolls-Royce plc
    Inventors: Aaron D. Sippel, Daniel K. Vetters, Jun Shi, David J. Thomas, Andrew J. Eifert, Peter Broadhead
  • Gas turbine engine component including a compliant layer
    Patent number: 10487670
    Abstract: A blade for a gas turbine engine comprises a blade portion having a first end and a second end and an engagement portion including a first surface coupled to the second end of the blade portion and a second surface coupled to the second end of the blade portion, the first and second surfaces arranged to extend divergently away from one another. The engagement portion is adapted for coupling to a wheel included in a gas turbine engine wheel.
    Type: Grant
    Filed: December 23, 2013
    Date of Patent: November 26, 2019
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: David J. Thomas, Richard C. Uskert, Adam L. Chamberlain, Matthew Peter Basiletti
  • 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