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).

  • PATTERNED ABRADABLE COATING AND METHODS FOR THE MANUFACTURE THEREOF
    Publication number: 20160236995
    Abstract: A ceramic article includes a flexible backing selected from paper, woven fabric, non-woven fabric, polymeric films, metal foils, and combinations thereof. A green ceramic layer is on a first side of the flexible backing, wherein the green ceramic layer includes a ceramic material and a polymeric binder. A major surface of the green ceramic layer includes a pattern of features.
    Type: Application
    Filed: February 17, 2016
    Publication date: August 18, 2016
    Inventors: Benjamin John Bowin Lai, Kang N. Lee, David J. Thomas
  • COMPOSITE AIRFOIL FOR A GAS TURBINE ENGINE
    Publication number: 20160177743
    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: Application
    Filed: July 13, 2015
    Publication date: June 23, 2016
    Inventors: David J. Thomas, Ted J. Freeman, Jeffrey A. Walston
  • FULL HOOP BLADE TRACK WITH AXIALLY KEYED FEATURES
    Publication number: 20160177753
    Abstract: A turbine shroud for a gas turbine engine includes an annular metallic carrier, a blade track, and a cross-key connection formed between the annular metallic carrier and the ceramic blade track. The cross-key connection locates the ceramic blade track relative to the metallic carrier.
    Type: Application
    Filed: December 17, 2015
    Publication date: June 23, 2016
    Inventors: Jeffrey A. Walston, Aaron D. Sippel, John A. Weaver, David J. Thomas
  • HANGER SYSTEM FOR A TURBINE ENGINE COMPONENT
    Publication number: 20160169025
    Abstract: A component of a turbine is disclosed. The component includes an carrier segment having a rail, an frame segment including a hanger having a flange supported on the rail of the carrier segment, and an inner surface having a section of a track for a turbine blade defined therein. The component also includes a retainer segment secured to the carrier segment such that the hanger is secured between the retainer segment and the carrier segment.
    Type: Application
    Filed: December 14, 2015
    Publication date: June 16, 2016
    Inventors: Joseph P. Lamusga, Aaron D. Sippel, Ted J. Freeman, David J. Thomas, Simon L. Jones
  • VANE ASSEMBLY FOR A GAS TURBINE ENGINE
    Publication number: 20160123164
    Abstract: A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends from the inner platform to the outer platform. A reinforcement spar made from a metallic material extends from the inner platform to the outer platform through a hollow core of the ceramic-containing airfoil.
    Type: Application
    Filed: September 29, 2015
    Publication date: May 5, 2016
    Inventors: Ted J. Freeman, Bruce E. Varney, David J. Thomas, Jeffrey A. Walston
  • VANE ASSEMBLY FOR A GAS TURBINE ENGINE
    Publication number: 20160123163
    Abstract: A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends from the inner platform to the outer platform. A clamp mechanism couples the inner platform and the outer platform to the ceramic-containing airfoil.
    Type: Application
    Filed: September 29, 2015
    Publication date: May 5, 2016
    Inventors: Ted J. Freeman, Bruce E. Varney, David J. Thomas, Jeffrey A. Walston
  • COMPOSITE ANNULUS FILLER
    Publication number: 20160115794
    Abstract: A composite annulus filler adapted to bridge the gap between two adjacent rotor blades attached to a rim of a rotor disc of a gas turbine engine. The annulus filler includes a unitary body portion having a platform which extends between the adjacent rotor blades and defines an airflow surface for air being drawn through the engine and a support body extending beneath the platform and terminating in a root which, in use, extends along a groove provided in the rim of the rotor disc.
    Type: Application
    Filed: September 29, 2015
    Publication date: April 28, 2016
    Inventors: David J. Thomas, Ted J. Freeman
  • Compliant composite component and method of manufacture
    Patent number: 9249684
    Abstract: A composite component includes a bonded portion and a component mount. The component mount is coupled to the bonded portion to move relative to the bonded portion. The bonded portion includes a fiber portion and a ceramic portion.
    Type: Grant
    Filed: December 3, 2013
    Date of Patent: February 2, 2016
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.
    Inventors: Andrew J. Lazur, Ted J. Freeman, Aaron D. Sippel, David J. Thomas, Adam L. Chamberlain, Joseph P. Lamusga
  • TURBINE SHROUD WITH SEALED BLADE TRACK
    Publication number: 20150377050
    Abstract: A turbine shroud for a gas turbine engine includes a plurality of shroud segments arranged around a central axis. Each shroud segment includes a carrier component, a blade track component, and a retainer component that couples the blade track component to the carrier component. The turbine shroud further includes a plurality of circumferential seals that seal circumferential interfaces between the shroud segments.
    Type: Application
    Filed: June 10, 2015
    Publication date: December 31, 2015
    Inventors: Ted J. Freeman, David J. Thomas, Joseph P. Lamusga, Aaron D. Sippel
  • SEGMENTED TURBINE SHROUD WITH SEALS
    Publication number: 20150377035
    Abstract: A turbine shroud for a gas turbine engine includes a plurality of shroud segments arranged around a central axis. Each shroud segment includes a carrier segment, a blade track segment, and a radial seal element that seals a radial interface between the carrier segment and the blade track segment. The turbine shroud further includes a plurality of circumferential seals that seal circumferential interfaces between the shroud segments.
    Type: Application
    Filed: June 9, 2015
    Publication date: December 31, 2015
    Inventors: Ted J. Freeman, David J. Thomas, Joseph P. Lamusga, Aaron D. Sippel
  • INSULATING COATING TO PERMIT HIGHER OPERATING TEMPERATURES
    Publication number: 20150322795
    Abstract: A gas turbine engine component includes an insulating coating that is adhered to a surface of the component that permits the components to operate at higher temperatures with reduced thermal stress. The coating can be selectively applied to one or more portions of a part feature where, in some embodiments, the part feature may include a portion that does not include the coating. The part feature can include recognized features of a component such as an interior surface of a hollow component, a back side of a blade track, a cooling hole passage, etc.
    Type: Application
    Filed: December 18, 2013
    Publication date: November 12, 2015
    Inventors: David J. Thomas, Ted J. Freeman
  • PLATFORM FOR CERAMIC MATRIX COMPOSITE TURBINE BLADES
    Publication number: 20150247414
    Abstract: The present disclosure provides for a turbine wheel having a blade platform disposed to compliantly secure ceramic turbine blades to a rotatable disk. The platform includes opposing ends to engage a portion of an airfoil of each turbine blade and radial extensions to engage a portion of a root of each turbine blade.
    Type: Application
    Filed: December 31, 2013
    Publication date: September 3, 2015
    Inventors: Richard C. Uskert, Matthew P. Basiletti, David J. Thomas, Ted J. Freeman, Michelle L. Tucker
  • Bicyclic heteroaryl inhibitors of PDE4
    Patent number: 9078887
    Abstract: The present invention relates to compounds and methods which may be useful as inhibitors of phosphodiesterase 4 (PDE4) for the treatment or prevention of inflammatory diseases and other diseases involving elevated levels of cytokines and proinflammatory mediators.
    Type: Grant
    Filed: June 28, 2012
    Date of Patent: July 14, 2015
    Assignees: Kalypsys, Inc., Alcon Laboratories, Inc.
    Inventors: Steven P. Govek, Andrew K. Shiau, Stewart A. Noble, David J. Thomas
  • SEAL FOR GAS TURBINE ENGINES
    Publication number: 20150167557
    Abstract: A gas turbine engine assembly includes a support component, an engine component, and a seal. The annular support component is formed to include a notch. The engine component is mounted in spaced-apart relation to the support component so that a gap is formed between the support component and the engine component. The seal is located in the notch and is adapted to close the gap.
    Type: Application
    Filed: November 17, 2014
    Publication date: June 18, 2015
    Inventors: David J. Thomas, Ted J. Freeman
  • GAS TURBINE ENGINE COMPONENT INCLUDING A COMPLIANT LAYER
    Publication number: 20150050158
    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: Application
    Filed: December 23, 2013
    Publication date: February 19, 2015
    Inventors: David J. Thomas, Richard C. Uskert, Adam L. Chamberlain, Matthew Peter Basiletti
  • Turbine vane for gas turbine engine
    Patent number: 8956105
    Abstract: A turbine vane for a gas turbine engine may include a composite airfoil structure. The composite airfoil structure may have an opening. The turbine vane may include a spar. The spar may have a body, which may be disposed within the opening. A standoff structure may be disposed within the opening. In some non-limiting embodiments, a cooling air gap may be defined between the body and an internal surface of the composite airfoil structure.
    Type: Grant
    Filed: December 21, 2009
    Date of Patent: February 17, 2015
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventors: Richard C. Uskert, Ted Joseph Freeman, David J. Thomas
  • COMPOSITE BLADE WITH AN INTEGRAL BLADE TIP SHROUD AND METHOD OF FORMING THE SAME
    Publication number: 20150044050
    Abstract: A gas turbine engine airflow member including a blade core portion, a shroud tip portion extending from the blade core portion, and an airfoil portion formed exteriorly to the blade core portion, where the blade core portion and the shroud tip portion are constructed as a first unitary structure and the airfoil portion is constructed as a second structure. A method of forming a gas turbine engine component is also disclosed.
    Type: Application
    Filed: December 23, 2013
    Publication date: February 12, 2015
    Inventors: David J. Thomas, Ted J. Freeman, Richard C. Uskert, Larry A. Junod, Joseph Lamusga
  • GAS TURBINE ENGINE COMPONENT HAVING FOAM CORE AND COMPOSITE SKIN WITH COOLING SLOT
    Publication number: 20150040570
    Abstract: In one embodiment, a gas turbine engine component includes a foam based core and a composite skin member. Both the foam based core and the composite skin member can be used to structurally support the gas turbine engine component. The composite skin member can be a CMC material and is used to partially encapsulate the foam core. The gas turbine engine component can take the form of an airfoil member such as a blade or a vane, a combustor liner, etc. A first portion of the composite skin member includes a first surface extending past an edge of the component creating a step approximate an edge section. In another embodiment, composite skin members can be used to form a continuous shape for the edge section such that the foam core forms part of a gas path surface.
    Type: Application
    Filed: December 23, 2013
    Publication date: February 12, 2015
    Inventors: Richard C. Uskert, Ted J. Freeman, David J. Thomas
  • TURBINE SHROUD
    Publication number: 20150044044
    Abstract: A turbine shroud for a gas turbine engine includes an annular metallic carrier, a ceramic blade track, and a cross-key connection formed between the annular metallic carrier and the ceramic blade track. The cross-key connection is formed between the annular metallic carrier and the ceramic blade track to locate the ceramic blade track relative to the annular metallic carrier. The cross-key connection includes a plurality of keys and a plurality of corresponding keyways.
    Type: Application
    Filed: December 2, 2013
    Publication date: February 12, 2015
    Inventors: Aaron D. Sippel, Ted J. Freeman, Joseph P. Lamusga, David J. Thomas
  • COMPARTMENTALIZATION OF COOLING AIR FLOW IN A STRUCTURE COMPRISING A CMC COMPONENT
    Publication number: 20150016971
    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: Application
    Filed: December 27, 2013
    Publication date: January 15, 2015
    Applicant: Rolls-Royce North American Technologies, Inc.
    Inventors: Ted J. Freeman, David J. Thomas