Patents Assigned to United Technologies
  • Publication number: 20200096331
    Abstract: An angled face cap probe includes a housing having a radially inner end and a radially outer end, defining a cavity, and configured to be located radially outward from an airfoil. The angled face cap probe further includes a sensor located in the cavity at the radially inner end of the housing, having a sensor body with a sensing face that is angled to match or substantially match an angle of a radially outward face the airfoil, and having a sensor flat that is elongated in a first direction. The angled face cap probe further includes an outer cap located in the cavity, coupled to the housing, and having an outer cap main body and cap legs that extend radially inward from the outer cap main body to interface with the sensor flat to resist rotation of the sensor relative to the housing.
    Type: Application
    Filed: September 20, 2018
    Publication date: March 26, 2020
    Applicant: United Technologies Corporation
    Inventors: Eli C. Warren, Kevin A. Ford, Patrick M. Harrington
  • Publication number: 20200094326
    Abstract: A component includes an additively manufactured component with an internal passage; and an additively manufactured elongated member within the internal passage. A method of additively manufacturing a component including additively manufacturing a component with an internal passage; and additively manufacturing an elongated member within the internal passage concurrent with additively manufacturing the component.
    Type: Application
    Filed: November 26, 2019
    Publication date: March 26, 2020
    Applicant: United Technologies Corporation
    Inventors: Caitlin Oswald, Jesse R. Boyer, Wendell V. Twelves, JR., Monica C. Smith, Krzysztof Barnat
  • Publication number: 20200095891
    Abstract: A wet-dry face seal seat includes a main body having a mating face configured to mate with a sealing member and an outer diameter surface, and defining a pool feed passage that extends to the mating face and a cooling hole that extends to the outer diameter surface. The wet-dry face seal seat further includes an oil capture scoop extending from the main body and defining an oil volume radially inward from the oil capture scoop and in fluid communication with the pool feed passage and the cooling hole, the oil capture scoop having a radial distance that allows oil to flow through the cooling hole in response to oil flow from an oil jet being below a threshold value and through the pool feed passage in response to the oil flow from the oil jet reaching or exceeding the threshold value.
    Type: Application
    Filed: September 21, 2018
    Publication date: March 26, 2020
    Applicant: United Technologies Corporation
    Inventor: Martin J. Walsh
  • Patent number: 10598381
    Abstract: A swirler for a combustor of a gas turbine engine includes a swirler outer body with a swirler threaded section defined around a swirler central longitudinal axis. A bulkhead support shell for a combustor of a gas turbine engine includes a swirler boss with a boss threaded section defined around a swirler central longitudinal axis. A combustor of a gas turbine engine includes a bulkhead support shell with a swirler boss. The combustor also includes a swirler mountable to the swirler boss at a threaded interface defined around a swirler central longitudinal axis.
    Type: Grant
    Filed: May 15, 2014
    Date of Patent: March 24, 2020
    Assignee: United Technologies Corporation
    Inventors: Christopher Drake, Seth A. Max, Meggan Harris
  • Patent number: 10598047
    Abstract: A bowed rotor prevention system for a gas turbine engine includes a core turning motor operable to drive rotation of an engine core of the gas turbine engine. The bowed rotor prevention system also includes an auxiliary electric motor control operable to control the core turning motor to drive rotation of the engine core using electric power while a full authority digital engine control that controls operation of the gas turbine engine is either depowered or in a power state that is less than a power level used by the full authority digital engine control in flight operation.
    Type: Grant
    Filed: February 28, 2017
    Date of Patent: March 24, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Jesse W. Clauson, Frederick M. Schwarz
  • Patent number: 10598378
    Abstract: A combustor wall is provided for a turbine engine. The combustor wall includes a shell, a heat shield and a combustion chamber. The heat shield is connected to the shell by a bonded connection, and defines a portion of the combustion chamber. A cooling cavity is defined between the shell and the heat shield.
    Type: Grant
    Filed: October 7, 2014
    Date of Patent: March 24, 2020
    Assignee: United Technologies Corporation
    Inventors: Gary D. Roberge, Grant O. Cook, III
  • Patent number: 10598379
    Abstract: An assembly for a turbine engine is provided. This turbine engine assembly includes a shell and a heat shield with a cooling cavity between the shell and the heat shield. The heat shield defines a plurality of cooling apertures and an indentation in a side of the heat shield opposite the cooling cavity. The cooling apertures are fluidly coupled with the cooling cavity. The indentation is configured such that cooling air, directed from a first of the cooling apertures, at least partially circulates against the side of the heat shield.
    Type: Grant
    Filed: November 25, 2014
    Date of Patent: March 24, 2020
    Assignee: United Technologies Corporation
    Inventors: Frank J. Cunha, Stanislav Kostka, Jr.
  • Patent number: 10596621
    Abstract: A method of making a composite core includes forming first and second cores of refractory metal and ceramic material. Each of the first and second cores is formed with two layers of a material. The layers are bonded together to form a laminate master pattern, and a flexible mold is formed around the pattern. The pattern is removed from the flexible mold, and slurry material, either pulverulent refractory metal material or ceramic material, is poured into the flexible mold. The slurry material is sintered to form each core. The first core is used as an insert while making the second core to create a final composite core.
    Type: Grant
    Filed: September 1, 2017
    Date of Patent: March 24, 2020
    Assignee: United Technologies Corporation
    Inventors: John Joseph Marcin, Mario P. Bochiechio
  • Patent number: 10598015
    Abstract: An anti-rotation assembly may include a first shaft, a second shaft, and a locking sprocket. The first shaft may have a first crenelated end rim, the second shaft may have a second crenelated end rim, and the locking sprocket may be configured to engage the first crenelated end rim and the second crenelated end rim to anti-rotatably couple the first shaft to the second shaft. That is, the locking sprocket may be configured to prevent relative rotation between the two shafts. The anti-rotation assembly may further include an axial retaining ring configured to axially retain the locking sprocket.
    Type: Grant
    Filed: October 26, 2017
    Date of Patent: March 24, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Nicholas Waters Oren, Ross Wilson
  • Patent number: 10598556
    Abstract: A method of monitoring the residual stress in surface and near surface regions of a component includes identifying predetermined locations on the surface of a component that are expected to experience high stress during normal operating conditions of the component. Marker particles are introduced into the component during additive manufacture of the component at the predetermined locations. Then, the residual stress of the component is measured at a location corresponding with the marker material using x-ray techniques.
    Type: Grant
    Filed: August 8, 2014
    Date of Patent: March 24, 2020
    Assignee: United Technologies Corporation
    Inventors: Lyutsia Dautova, Wendell V. Twelves, Jr., Joe Ott, Evan Butcher, Gary A. Schirtzinger, Rainer J. Herbert
  • Patent number: 10598029
    Abstract: An airfoil includes a core structure that defines a cooling passage, a panel attached with the core structure, and a channel. The panel has an exterior gas path side, an opposed interior side, and side edges. The channel has a first end that opens to the cooling passage and a second end that opens to the exterior gas path side at one of the side edges.
    Type: Grant
    Filed: November 17, 2016
    Date of Patent: March 24, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Tracy A. Propheter-Hinckley
  • Patent number: 10598917
    Abstract: Aspects of the disclosure are directed to a borescope grip defined about a central longitudinal axis, comprising: a reaction case that includes a first flange having a first face that is substantially perpendicular to a central longitudinal axis of the grip, an o-ring that abuts the first face of the first flange, a plunger that includes a second flange having a second face that abuts the o-ring at a first axial position and is disengaged from the o-ring at a second axial position, and a spring that abuts the second flange.
    Type: Grant
    Filed: April 7, 2017
    Date of Patent: March 24, 2020
    Assignee: United Technologies Corporation
    Inventors: Michael D. Chowaniec, Antony J. Giunta
  • Patent number: 10598024
    Abstract: A gas turbine engine includes a compressor section and a compressor case with a low pressure compressor (LPC) and a high pressure compressor (HPC). The HPC is aft of the LPC. The compressor case defines a centerline axis. The compressor section also includes a rotor disk defined between the compressor case and the centerline axis. A plurality of stages are defined radially inward relative to the compressor case. The plurality of stages include at least one tandem blade stage. The tandem blade stage includes a plurality of blade pairs. Each blade pair is circumferentially spaced apart from the other blade pairs, and is operatively connected to the rotor disk. Each blade pair includes a forward blade and an aft blade. The aft blade is configured to further condition air flow with respect to the forward blade without an intervening stator vane stage shrouded cavity therebetween.
    Type: Grant
    Filed: October 14, 2015
    Date of Patent: March 24, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Matthew P. Forcier, Brian J. Schuler
  • Patent number: 10597330
    Abstract: A thermal barrier coating for a turbine engine component contains neodymia, optionally alumina, and zirconia. The thermal barrier coating has resistance to CMAS attack and a low thermal conductivity.
    Type: Grant
    Filed: March 11, 2019
    Date of Patent: March 24, 2020
    Assignee: United Technologies Corporation
    Inventors: Mario P. Bochiechio, David A. Litton, Michael J. Maloney
  • Patent number: 10598020
    Abstract: A spanner nut for a bearing compartment of an engine with a bearing stack on a first shaft that rotates about an engine centerline includes a body, a piloting hook connected to the body, a first threaded portion, and a channel formed by the piloting hook. The piloting hook includes first and second extensions. The first extension is connected to and extends radially inward from the body. The second extension is connected to and extends in an axial direction from the first extension. The second extension includes a radially outward facing surface. The first threaded portion is configured to engage with a second threaded portion on the end of the first shaft. The channel is configured to receive the end of the first shaft. The piloting hook is configured to draw the second extension radially outward as the spanner nut is compressed.
    Type: Grant
    Filed: January 5, 2018
    Date of Patent: March 24, 2020
    Assignee: United Technologies Corporation
    Inventor: Armando Amador
  • Patent number: 10598046
    Abstract: A method of assembling a portion of a gas turbine engine, includes assembling a plurality of static structure rings; attaching a plurality of support straps to an outer diameter of the plurality of static structure rings to form a cartridge; inserting the cartridge at least partially into an outer case assembly along an engine axis.
    Type: Grant
    Filed: July 11, 2018
    Date of Patent: March 24, 2020
    Assignee: United Technologies Corporation
    Inventors: Michael G. McCaffrey, Scott D. Virkler
  • Patent number: 10596526
    Abstract: Disclosed is an ion-exchange membrane that includes a molecular barrier for influencing permeation selectivity through the membrane. The membrane includes fluorinated carbon backbone chains and fluorinated side chains that extend off of the fluorinated carbon backbone chains. The fluorinated side chains include acid groups for ionic conductivity. The acid groups surround and define permeable domains that are free of the fluorinated carbon backbone chains. Molecular barriers are located in the permeable domains and influence permeability through the domains.
    Type: Grant
    Filed: April 24, 2015
    Date of Patent: March 24, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Sergei F. Burlatsky, Vadim Atrazhev, Wei Xie, Robert Mason Darling, Michael L. Perry
  • Patent number: 10597329
    Abstract: A thermal barrier coating for a turbine engine component contains neodymia, optionally alumina, and zirconia. The thermal barrier coating has resistance to CMAS attack and a low thermal conductivity.
    Type: Grant
    Filed: March 11, 2019
    Date of Patent: March 24, 2020
    Assignee: United Technologies Corporation
    Inventors: Mario P. Bochiechio, David A. Litton, Michael J. Maloney
  • Patent number: 10597784
    Abstract: A spray nozzle has a body having a flow passage. At least along a portion of the flow passage the body has a depth-wise compositional variation having: a cemented carbide first region; and a cemented carbide second region closer to the flow passage than the first region and having a higher boron content than a boron content, if any, of the first region.
    Type: Grant
    Filed: July 18, 2017
    Date of Patent: March 24, 2020
    Assignee: United Technologies Corporation
    Inventors: Randolph C. McGee, Aaron T. Nardi
  • Patent number: 10598382
    Abstract: A liner associated with an engine of an aircraft is described. The liner includes a panel and an array of projections configured to enhance a cooling of the panel and distributed on at least part of a first side of the panel that corresponds to a cold side of the panel.
    Type: Grant
    Filed: November 6, 2015
    Date of Patent: March 24, 2020
    Assignee: United Technologies Corporation
    Inventors: John S. Tu, James B. Hoke, Monica Pacheco-Tougas, Alexander W. Williams