Patents Assigned to United Technologies Corporation
  • Publication number: 20180328214
    Abstract: A blade outer air seal (BOAS) assembly includes a rotor blade configured to rotate about an axis. The BOAS assembly also includes a BOAS positioned radially outward from the rotor blade and having a forward-facing BOAS face. The BOAS assembly also includes a shroud block positioned radially outward from the BOAS, having an aft-facing shroud face, and being configured to support the BOAS. The BOAS assembly also includes a first bellows seal extending from the forward-facing BOAS face to the aft-facing shroud face and configured to reduce fluid leakage radially between the BOAS and the shroud block.
    Type: Application
    Filed: June 14, 2017
    Publication date: November 15, 2018
    Applicant: UNiTED TECHNOLOGIES CORPORATION
    Inventors: Daniel Barak, Joseph F. Englehart
  • Publication number: 20180328194
    Abstract: A component for a gas turbine engine includes an airfoil section including a free end and an abrasive coating sprayed onto the free end, the abrasive coating including a polymer matrix and an abrasive filler, the abrasive filler between about 50%-75% by volume of the abrasive coating.
    Type: Application
    Filed: July 24, 2018
    Publication date: November 15, 2018
    Applicant: United Technologies Corporation
    Inventor: Christopher W. Strock
  • Publication number: 20180330557
    Abstract: An article of manufacture including a tangible, non-transitory computer-readable storage medium having instructions stored thereon for detecting a fault in a gas turbine engine that, in response to execution by a controller, cause the controller to perform operations comprising receiving, by the controller, a first data output from a first flight data source; receiving, by the controller, a second data output from a second flight data source; determining, by the controller, a first flight realm of the first data output based on the second data output; identifying, by the controller, a fault threshold using a first parameter of the first flight realm; and comparing, by the controller, the first data output to the fault threshold.
    Type: Application
    Filed: May 9, 2017
    Publication date: November 15, 2018
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Linda I. Rivera, Gregory S. Hagen, Alexander I. Khibnik
  • Patent number: 10125629
    Abstract: Systems and methods for assessing the health of a first apparatus by monitoring a second apparatus are described herein. A method for monitoring a health of a first apparatus may comprise receiving a performance parameter from a second apparatus, wherein performance of the second apparatus is dependent upon the health of the first apparatus, assessing the performance parameter, and determining the health of the first apparatus. In various embodiments, the performance parameter may comprise at least one of a speed value of the second apparatus, a position value of the second apparatus, a temperature value of the second apparatus, or a time value of the second apparatus.
    Type: Grant
    Filed: July 29, 2016
    Date of Patent: November 13, 2018
    Assignee: United Technologies Corporation
    Inventor: Floyd R. Emmons
  • Patent number: 10125613
    Abstract: A method includes determining a vibration characteristic of a shrouded turbine blade, which includes an airfoil attached to a shroud. A corner of the shrouded turbine blade can be removed after determining the vibration characteristic.
    Type: Grant
    Filed: December 17, 2013
    Date of Patent: November 13, 2018
    Assignee: United Technologies Corporation
    Inventors: Eric S. Savage, Christopher Corcoran
  • Patent number: 10125724
    Abstract: A gas turbine engine includes a flow control mechanism operable to direct at least a portion of a fan airflow from a secondary flow path into a core flow path.
    Type: Grant
    Filed: January 17, 2012
    Date of Patent: November 13, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gary D. Roberge, Andrew P. Berryann, Scott A. Carr
  • Patent number: 10125723
    Abstract: A method includes providing an exhaust liner as a first duct, providing a second duct having an opening therein, and spacing the first duct radially inward of the second duct. A spring connects the first and second ducts together and has first and second ends. A first mount comprises a first bracket portion associated with the spring and a second bracket portion directly fixed to the first duct. The first bracket portion is directly fixed to the first end of the spring and the second end of the spring is fixed to a second mount that comprises a casing plate having an area greater than the opening. The first end of the spring and the first bracket portion are inserted through the opening and the first bracket portion is attached to the second bracket portion. The casing plate is directly fixed to a radially outward facing surface of the second duct.
    Type: Grant
    Filed: July 16, 2018
    Date of Patent: November 13, 2018
    Assignee: United Technologies Corporation
    Inventors: Paul R. Senofonte, Timothy J. McAlice
  • Patent number: 10125620
    Abstract: A gas turbine engine airfoil assembly includes an airfoil and an attachment structure respectively bonded to opposing sides of a platform. At least one of the airfoil, the platform and the attachment structure are constructed from a ceramic matrix composite.
    Type: Grant
    Filed: June 19, 2014
    Date of Patent: November 13, 2018
    Assignee: United Technologies Corporation
    Inventor: Ioannis Alvanos
  • Patent number: 10125789
    Abstract: A variable area vane arrangement includes a stator vane, a bushing and a vane platform with an aperture. The stator vane rotates about an axis, and includes a shaft that extends along the axis into the aperture. The bushing is connected to the shaft, and is arranged within the aperture between the vane platform and the shaft.
    Type: Grant
    Filed: December 16, 2013
    Date of Patent: November 13, 2018
    Assignee: United Technologies Corporation
    Inventors: David Maliniak, Nathan F. Champion, Kenneth A. Frisk
  • Patent number: 10125695
    Abstract: A method of controlling an airfoil component temperature distribution includes the steps of detecting an airfoil component temperature, comparing the detected airfoil component temperature to a desired airfoil component temperature profile, and controlling a fuel flow in response to the comparing step to maintain the airfoil component temperature within the desired airfoil component temperature profile.
    Type: Grant
    Filed: September 17, 2014
    Date of Patent: November 13, 2018
    Assignee: United Technologies Corporation
    Inventor: Lev Alexander Prociw
  • Patent number: 10125636
    Abstract: A bowed rotor prevention system for a gas turbine engine is provided. The bowed rotor prevention system includes a thermoelectric generator system operable to produce electricity from waste heat of the gas turbine engine. The bowed rotor prevention system also includes a bowed rotor prevention motor operable to drive rotation of turbomachinery of the gas turbine engine using the electricity produced by the thermoelectric generator system.
    Type: Grant
    Filed: February 12, 2016
    Date of Patent: November 13, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: David P. Dube, Richard K. Hayford
  • Patent number: 10125858
    Abstract: An epicyclic gear train for a turbine engine includes a gutter with an annular channel. A rotating structure includes a ring gear. The rotating structure has an aperture that is axially aligned with the annular channel. Axially spaced apart walls extend radially outward relative to the rotating structure to define a passageway. The passageway is arranged radially between the aperture and the annular channel. The walls are configured to inhibit an axial flow of an oil passing from the aperture toward the annular channel.
    Type: Grant
    Filed: April 17, 2018
    Date of Patent: November 13, 2018
    Assignee: United Technologies Corporation
    Inventors: Michael E. McCune, Lawrence E. Portlock
  • Patent number: 10125614
    Abstract: A component for a gas turbine engine according to an exemplary aspect of this disclosure includes a surface having a plurality of cooling holes. The surface includes a first region and a second region each having a plurality of cooling holes. The cooling holes within the first region are arranged differently than the cooling holes in the second region.
    Type: Grant
    Filed: April 17, 2015
    Date of Patent: November 13, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Dominic J. Mongillo, San Quach, Steven Bruce Gautschi, Brandon S. Donnell, Anita L. Tracy, Yafet Girma
  • Patent number: 10126175
    Abstract: A system includes a turbomachine having one or more inspection ports. An LWIR sensor is positioned in the inspection port of the turbomachine to sense thermal energy emitted by a turbomachine component. An imaging device can be operably connected to the LWIR sensor to convert signals from the LWIR sensor to a thermal image of the turbomachine component based on the sensed thermal energy. In some embodiments, the LWIR sensor configured to image a ceramic coated turbine blade.
    Type: Grant
    Filed: December 9, 2014
    Date of Patent: November 13, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Charles W. Haldeman, Andrew Consiglio, Mark F. Zelesky, Joel H. Wagner
  • Patent number: 10125691
    Abstract: A bowed rotor start mitigation system for a gas turbine engine is provided. The bowed rotor start mitigation system includes a variable position starter valve and a controller. The controller is operable to dynamically adjust the variable position starter valve to deliver a starter air supply to a starter to drive rotation of a starting spool of the gas turbine engine according to a dry motoring profile that continuously varies a rotor speed of the starting spool up to a point below a critical rotor speed.
    Type: Grant
    Filed: February 12, 2016
    Date of Patent: November 13, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Matthew R. Feulner, Frederick M. Schwarz
  • Patent number: 10125693
    Abstract: A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in the first direction about the central axis. A power density is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/cubic inches. A fan is connected to the low pressure spool via a speed changing mechanism and rotates in a second direction opposed to the first direction.
    Type: Grant
    Filed: January 9, 2015
    Date of Patent: November 13, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Frederick M. Schwarz, Daniel Bernard Kupratis
  • Patent number: 10125694
    Abstract: A gas turbine engine has a fan section including a fan hub supporting a plurality of fan blades for rotation relative to a fan case. A shaft is rotatable relative to the fan case about an engine center axis. A geared architecture is driven by the shaft and provides driving output to rotate the fan hub. A compressor is driven by the shaft and is positioned forward of the geared architecture. The compressor includes at least first and second stages with the first stage being positioned forward of the plurality of fan blades and the second stage being positioned aft of the plurality of fan blades. The compressor includes at least one set of vanes that rotate in a first direction about the engine center axis and at least one set of compressor blades that rotate in a second direction about the engine center axis. The second direction is opposite of the first direction.
    Type: Grant
    Filed: November 24, 2015
    Date of Patent: November 13, 2018
    Assignee: United Technologies Corporation
    Inventor: John W. Magowan
  • Patent number: 10125722
    Abstract: A turbine engine is provided that include a turbo-compressor, a combustor section and a nacelle which houses the turbo-compressor and the combustor section. The turbo-compressor includes a compressor section and a turbine section. The combustor section is fluidly coupled between the compressor section and the turbine section. The nacelle includes a thrust reverser.
    Type: Grant
    Filed: February 13, 2015
    Date of Patent: November 13, 2018
    Assignee: United Technologies Corporation
    Inventors: Daniel B. Kupratis, William G. Sheridan
  • Publication number: 20180319998
    Abstract: A process for applying a chromium layer on a substrate, specifically a turbine engine airfoil, by contacting at least a portion of the substrate with a gaseous chromium wherein the gaseous chromium is generated from a substantially nitrogen free source.
    Type: Application
    Filed: July 16, 2018
    Publication date: November 8, 2018
    Applicant: United Technologies Corporation
    Inventors: Kevin L. Collins, Michael J. Minor
  • Publication number: 20180320741
    Abstract: A bearing with non-uniform cage clearance is provided. The bearing may comprise an inner ring having a first inner ring surface radially opposite a second inner ring surface; bearing elements in contact with the first inner ring surface; an outer bearing ring surrounding the inner bearing ring and the bearing elements; and a bearing cage having a first bearing cage surface radially opposite a second bearing cage surface and configured to surround and retain the bearing elements. At least one of the first inner ring surface, the first bearing cage surface, the second bearing cage surface, or a second outer ring surface of the outer ring may comprise an out of round shape having one or more peaks and one or more valleys relative to a radial centerpoint of the bearing.
    Type: Application
    Filed: May 8, 2017
    Publication date: November 8, 2018
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Reade W. James, Kevin M. Duffy