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 SHROUD WITH SEALING FEATURES
    Publication number: 20170101882
    Abstract: A segmented turbine shroud for positioning radially outside of blades of a turbine rotor includes a carrier, a blade track, and retainers. The blade track is mounted onto the retainers, and the retainers are attached to the carrier to support the blade track radially outside of the blades.
    Type: Application
    Filed: September 27, 2016
    Publication date: April 13, 2017
    Inventors: Aaron D. Sippel, Ted J. Freeman, David J. Thomas
  • Compliant intermediate component of a gas turbine engine
    Patent number: 9593596
    Abstract: One aspect of present application provides an intermediate structure in a gas turbine engine. The intermediate structure is positioned between a first component and another component. The first component may be a composite component. The components may be interlocking. The intermediate structure may be load bearing. Also disclosed is a method using the intermediate structure.
    Type: Grant
    Filed: December 28, 2013
    Date of Patent: March 14, 2017
    Assignee: Rolls-Royce Corporation
    Inventors: Richard C. Uskert, David J. Thomas, Adam L. Chamberlain
  • TURBINE SHROUD HAVING CERAMIC MATRIX COMPOSITE SEAL SEGMENT
    Publication number: 20170044920
    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: May 26, 2015
    Publication date: February 16, 2017
    Inventors: Daniel Kent Vetters, David J. Thomas, Douglas David Dierksmeier, Jun Shi, Todd Engel
  • Compartmentalization of cooling air flow in a structure comprising a CMC component
    Patent number: 9556750
    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 27, 2013
    Date of Patent: January 31, 2017
    Assignees: Rolls-Royce North American Technologies, Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, David J. Thomas
  • TURBINE SHROUD WITH MOVABLE ATTACHMENT FEATURES
    Publication number: 20170002676
    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: Application
    Filed: June 10, 2016
    Publication date: January 5, 2017
    Inventors: Aaron D. Sippel, Ted J. Freeman, David J. Thomas, Robert J. Shinavski, Zacheriah A. Cole
  • SHROUD CARTRIDGE HAVING A CERAMIC MATRIX COMPOSITE SEAL SEGMENT
    Publication number: 20160348527
    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: Application
    Filed: May 26, 2015
    Publication date: December 1, 2016
    Inventors: Daniel Kent Vetters, David J. Thomas, Ted Freeman, Douglas David Dierksmeier, Jun Shi, Todd Engel
  • PRESSURE ACTIVATED SEALS FOR A GAS TURBINE ENGINE
    Publication number: 20160348523
    Abstract: An assembly for use in a gas turbine engine is disclosed. The assembly includes a first component arranged adjacent to a second component to form a gap therebetween and a pressure activated seal that resists flow through the gap.
    Type: Application
    Filed: May 19, 2016
    Publication date: December 1, 2016
    Inventors: David J. Thomas, Joseph P. Lamusga, Ted J. Freeman, Aaron D. Sippel
  • SHROUD CARTRIDGE HAVING A CERAMIC MATRIX COMPOSITE SEAL SEGMENT
    Publication number: 20160348526
    Abstract: A cartridge for a ceramic matrix composite (CMC) seal segment of a segmented turbine shroud of a gas turbine engine is provided. The cartridge comprises a carrier segment and a CMC seal segment. A surface of the carrier segment and a surface of the CMC seal segment form a mating region proximate the entire perimeter of the CMC seal segment. The carrier segment surface may comprise a channel, and a compressible mating element may be disposed within the channel. Air may be supplied to a cavity, formed by the carrier and CMC seal segment, and the mating region.
    Type: Application
    Filed: May 26, 2015
    Publication date: December 1, 2016
    Inventors: Daniel Kent Vetters, David J. Thomas, Ted Freeman, Joseph Lamusga, Rick Uskert
  • CERAMIC MATRIX COMPOSITE SEAL SEGMENT FOR A GAS TURBINE ENGINE
    Publication number: 20160348528
    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: May 26, 2015
    Publication date: December 1, 2016
    Inventors: Daniel Kent Vetters, David J. Thomas, Ted Freeman, Douglas David Dierksmeier, Jun Shi, Todd Engel
  • SPLIT LINE FLOW PATH SEALS
    Publication number: 20160348521
    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: Application
    Filed: May 28, 2015
    Publication date: December 1, 2016
    Inventors: Aaron D. Sippel, Ted J. Freeman, David J. Thomas, Joseph P. Lamusga, Brian J. Shoemaker
  • SEAL FOR A GAS TURBINE ENGINE ASSEMBLY
    Publication number: 20160319687
    Abstract: A gas turbine engine assembly includes a seal formed by the interface between first and second support components. The support components are each formed to include a notch. Adjacent notches cooperate to form a space when assembled. A seal member is located in the space.
    Type: Application
    Filed: March 25, 2016
    Publication date: November 3, 2016
    Inventors: David J. Thomas, John A. Weaver, Ted J. Freeman
  • BRAZED BLADE TRACK FOR A GAS TURBINE ENGINE
    Publication number: 20160319682
    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: April 8, 2016
    Publication date: November 3, 2016
    Inventors: Aaron D. Sippel, Daniel K. Vetters, Jun Shi, David J. Thomas, Andrew J. Eifert, Peter Broadhead
  • SEALS FOR A GAS TURBINE ENGINE ASSEMBLY
    Publication number: 20160319686
    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: Application
    Filed: March 21, 2016
    Publication date: November 3, 2016
    Inventors: Jun Shi, Ted J. Freeman, David J. Thomas
  • KEYSTONED BLADE TRACK
    Publication number: 20160319689
    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: Application
    Filed: April 4, 2016
    Publication date: November 3, 2016
    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
  • FULL HOOP BLADE TRACK WITH FLANGED SEGMENTS
    Publication number: 20160319688
    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: Application
    Filed: April 1, 2016
    Publication date: November 3, 2016
    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
  • COMPLIANT RAIL HANGER
    Publication number: 20160290140
    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: Application
    Filed: March 10, 2016
    Publication date: October 6, 2016
    Inventors: David J. Thomas, Joseph P. Lamusga, Ted J. Freeman, Andrew J. Lazur
  • TURBINE VANE WITH HEAT SHIELD
    Publication number: 20160265384
    Abstract: A gas turbine engine may include a body and a turbine-vane ring coupled to the body. The turbine-vane ring may include a plurality of turbine-vane assemblies.
    Type: Application
    Filed: March 2, 2016
    Publication date: September 15, 2016
    Inventors: Jeffrey A. Walston, Aaron D. Sippel, Tara G. Schetzel, David J. Thomas, Jun Shi, Brad D. Belcher
  • TURBINE ASSEMBLY WITH LOAD PADS
    Publication number: 20160258304
    Abstract: A turbine shroud for a gas turbine engine includes a carrier and a blade track segment. The carrier is formed to include an inwardly opening blade track channel and the blade track segment is positioned in the blade track channel to couple the blade track segment with the carrier.
    Type: Application
    Filed: February 26, 2016
    Publication date: September 8, 2016
    Inventors: Aaron D. Sippel, Ted J. Freeman, David J. Thomas, Richard C. Uskert, Peter J. Loftus, Andrew J. Lazur
  • VANE ASSEMBLY FOR A GAS TURBINE ENGINE
    Publication number: 20160258320
    Abstract: A vane assembly for a gas turbine engine is disclosed herein. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil that extends from the inner platform to the outer platform. The ceramic-containing airfoil is manufactured to have radially discontinuous ribs spaced radially apart from one another between the inner platform and the outer platform.
    Type: Application
    Filed: February 29, 2016
    Publication date: September 8, 2016
    Inventors: David J. Thomas, Ted J. Freeman, Jeffrey A. Walston, Andrew J. Lazur
  • SEGMENTED TURBINE SHROUD WITH SEALING FEATURES
    Publication number: 20160245102
    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: Application
    Filed: February 22, 2016
    Publication date: August 25, 2016
    Inventors: Ted J. Freeman, Peter Broadhead, Aaron D. Sippel, David J. Thomas, Joseph P. Lamusga