Patents by Inventor Matthew A. Hough

Matthew A. Hough 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).

  • Diffuser case support structure
    Patent number: 10941669
    Abstract: A diffuser case support structure for a gas turbine engine is disclosed. The diffuser case support structure includes a fairing disposed circumferentially about a longitudinal axis. The fairing forms at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. The fairing defines a plurality of apertures extending through the fairing. At least one spoke extends through at least one respective aperture of the plurality of apertures. The at least one spoke is configured to couple an inner diffuser case and an outer diffuser case of the gas turbine engine.
    Type: Grant
    Filed: December 21, 2018
    Date of Patent: March 9, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Matthew A. Hough, Russell B. Hanson, John S. Tu, Paul F. Croteau, Paul K. Sanchez, Stephen C. Harmon, Joshua C. Rathgeb
  • DIFFUSER CASE SUPPORT STRUCTURE
    Publication number: 20200200028
    Abstract: A diffuser case support structure for a gas turbine engine is disclosed. The diffuser case support structure includes a fairing disposed circumferentially about a longitudinal axis. The fairing forms at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. The fairing defines a plurality of apertures extending through the fairing. At least one spoke extends through at least one respective aperture of the plurality of apertures. The at least one spoke is configured to couple an inner diffuser case and an outer diffuser case of the gas turbine engine.
    Type: Application
    Filed: December 21, 2018
    Publication date: June 25, 2020
    Inventors: Matthew A. Hough, Russell B. Hanson, John S. Tu, Paul F. Croteau, Paul K. Sanchez, Stephen C. Harmon, Joshua C. Rathgeb
  • Shim to maintain gap during engine assembly
    Patent number: 10036503
    Abstract: Aspects of the disclosure are directed to a tube of an engine of an aircraft configured to transfer a fluid, a boss of the engine, and a shim coupled to at least one of the tube and the boss that is configured to maintain a gap between the tube and the boss when the engine is assembled.
    Type: Grant
    Filed: April 13, 2015
    Date of Patent: July 31, 2018
    Assignee: United Technologies Corporation
    Inventors: Anthony P. Cherolis, Alexander Broulidakis, Matthew A. Hough, Jonathan Lemoine, Christopher Treat
  • Rotor blade with a conic spline fillet at an intersection between a platform and a neck
    Patent number: 9932834
    Abstract: A rotor blade for a turbine engine includes an airfoil that is connected to a base. The base includes a platform, a neck and a fillet. The fillet extends along at least a portion of an intersection between the platform and the neck. The fillet has a radius that substantially continuously changes as the fillet extends from the platform to the neck.
    Type: Grant
    Filed: March 13, 2014
    Date of Patent: April 3, 2018
    Assignee: United Technologies Corporation
    Inventors: Matthew A. Hough, Jeffrey S. Beattie
  • Snap in platform damper and seal assembly for a gas turbine engine
    Patent number: 9732620
    Abstract: A turbine assembly includes a first turbine blade circumferentially adjacent to a second turbine blade. The first turbine blade includes a first platform with a first underplatform surface. The second turbine blade includes a second platform with a second underplatform surface. The first underplatform surface and the second underplatform surface at least partially defines a cavity. A damper with a platform rub surface is included adjacent the first underplatform surface and the second underplatform surface. A seal is included with a forward portion, an aft portion, and a damper interface portion therebetween. The damper interface portion extends along a damper underside and the forward portion and the aft portion adjacent the first underplatform surface and the second underplatform surface.
    Type: Grant
    Filed: July 23, 2014
    Date of Patent: August 15, 2017
    Assignee: United Technologies Corporation
    Inventor: Matthew A. Hough
  • SHIM TO MAINTAIN GAP DURING ENGINE ASSEMBLY
    Publication number: 20160298472
    Abstract: Aspects of the disclosure are directed to a tube of an engine of an aircraft configured to transfer a fluid, a boss of the engine, and a shim coupled to at least one of the tube and the boss that is configured to maintain a gap between the tube and the boss when the engine is assembled.
    Type: Application
    Filed: April 13, 2015
    Publication date: October 13, 2016
    Inventors: Anthony P. Cherolis, Alexander Broulidakis, Matthew A. Hough, Jonathan Lemoine, Christopher Treat
  • SNAP IN PLATFORM DAMPER AND SEAL ASSEMBLY FOR A GAS TURBINE ENGINE
    Publication number: 20160153303
    Abstract: A turbine assembly includes a first turbine blade circumferentially adjacent to a second turbine blade. The first turbine blade includes a first platform with a first underplatform surface. The second turbine blade includes a second platform with a second underplatform surface. The first underplatform surface and the second underplatform surface at least partially defines a cavity. A damper with a platform rub surface is included adjacent the first underplatform surface and the second underplatform surface. A seal is included with a forward portion, an aft portion, and a damper interface portion therebetween. The damper interface portion extends along a damper underside and the forward portion and the aft portion adjacent the first underplatform surface and the second underplatform surface.
    Type: Application
    Filed: July 23, 2014
    Publication date: June 2, 2016
    Inventor: Matthew A. Hough
  • ROTOR BLADE WITH A CONIC SPLINE FILLET AT AN INTERSECTION BETWEEN A PLATFORM AND A NECK
    Publication number: 20160032727
    Abstract: A rotor blade for a turbine engine includes an airfoil that is connected to a base. The base includes a platform, a neck and a fillet. The fillet extends along at least a portion of an intersection between the platform and the neck. The fillet has a radius that substantially continuously changes as the fillet extends from the platform to the neck.
    Type: Application
    Filed: March 13, 2014
    Publication date: February 4, 2016
    Inventors: Matthew A. Hough, Jeffrey S. Beattie