Patents Assigned to United Technologies Corporation
  • Publication number: 20190249873
    Abstract: A heat shield panel for use in a gas turbine engine combustor is disclosed. The heat shield panel includes a hot side, a cold side and at least one attachment mechanism having a stud and a central axis extending through the stud and a plurality of standoff pins positioned circumferentially around the stud, the standoff pins having a radial extent, a circumferential extent that is greater than the radial extent, a radially outer surface having a radially convex shape and a radially inner surface having a radially concave shape.
    Type: Application
    Filed: February 9, 2018
    Publication date: August 15, 2019
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Steven D. Porter, James Tilsley Auxier
  • Publication number: 20190249564
    Abstract: An airflow mask tool incudes a pressure side mask portion to seal at least a portion of a pressure side of a component having an array of internal passageways and a suction side mask portion to seal at least a portion of a suction side of the component, at least one of the suction side mask portion and the pressure side mask portion comprising at least one opening to expose at least one exit from the array of internal passageways.
    Type: Application
    Filed: February 9, 2018
    Publication date: August 15, 2019
    Applicant: United Technologies Corporation
    Inventors: Mary Lynn Tall, John D. Laggis, III, Natalie Jean DiStefano
  • Publication number: 20190247914
    Abstract: A refractory metal core laminate assembly, comprising: a first refractory metal core layer having exterior surfaces and a first side and a second side opposite the first side; a second refractory metal core layer having exterior surfaces and a first side and a second side opposite the first side, the second refractory metal core layer being arranged above the first refractory metal core layer with the second refractory metal core layer first side facing the first refractory metal core layer second side; a layer of a powder bed material between the first refractory metal core layer second side and the second refractory metal core layer first side; and a coating of the powder bed material coupled to the first refractory metal core layer exterior surfaces and the second refractory metal core layer exterior surfaces.
    Type: Application
    Filed: February 15, 2018
    Publication date: August 15, 2019
    Applicant: United Technologies Corporation
    Inventor: James Tilsley Auxier
  • Patent number: 10379003
    Abstract: A fuel actuation system may comprise a servo valve (SV) including a torque motor and at least one screen, a metering valve (MV) fluidly connected to the SV, and an electronic engine control (EEC) operatively connected to the SV. The EEC may be configured and disposed to determine a travel time of the MV, a travel distance of the MV, a pressure of a fuel, and/or a temperature of the fuel, generate at least one of a travel time history, a travel distance history, a fuel temperature history, and a fuel pressure history, and determine a level of degradation of the fuel actuation system based on the at least one of the travel time history, the travel distance history, the fuel temperature history, or the fuel pressure history.
    Type: Grant
    Filed: April 30, 2018
    Date of Patent: August 13, 2019
    Assignee: United Technologies Corporation
    Inventors: Angelo Martucci, William Donat, Amy R Grace, Thomas A Bush, Eric Nelson Hettler, Kevin Patrick McCormick
  • Patent number: 10378454
    Abstract: A method of operating a gas turbine engine includes modulating a variable high pressure turbine inlet guide vane of a high pressure spool to performance match a first stage fan section of a low pressure spool and an intermediate stage fan section of an intermediate spool to maintain a generally constant engine inlet flow while varying engine thrust.
    Type: Grant
    Filed: January 13, 2016
    Date of Patent: August 13, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Daniel Bernard Kupratis
  • Patent number: 10378363
    Abstract: An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges and extending in a radial direction. A serpentine cooling passage is provided between the pressure and suction side walls. A passageway adjoins a passage wall and is fluidly interconnected to an upstream turn that has radially spaced apart innermost and outermost contours. The innermost contour is provided at the wall. A resupply hole is configured to exit downstream from the innermost contour.
    Type: Grant
    Filed: April 10, 2017
    Date of Patent: August 13, 2019
    Assignee: United Technologies Corporation
    Inventors: Christopher Whitfield, Carey Clum, Mark Borja
  • Patent number: 10376960
    Abstract: An additively manufactured alloy component has a first portion formed of the alloy and having a first grain size, and a second portion formed of the alloy and having a second grain size smaller than the first grain size. In an embodiment, the alloy component is an alloy turbine disk, the first portion is a rim region of the alloy turbine disk, and the second portion is a hub region of the alloy turbine disk. The first and second grain sizes may be achieved by controllably varying the laser power and/or scan speed during additive manufacturing.
    Type: Grant
    Filed: January 18, 2017
    Date of Patent: August 13, 2019
    Assignee: United Technologies Corporation
    Inventors: John A. Sharon, Daniel V. Viens, Tahany Ibrahim El-Wardany, Gajawalli V. Srinivasan, Joseph J. Sangiovanni, Ranadip Acharya
  • Patent number: 10378360
    Abstract: A turbomachine includes an endwall with a plurality of circumferentially spaced apart, radially extending blades extending from the endwall. A first one of the blades defines a pressure surface of a flow channel, a second one of the blades defines a suction surface of the flow channel, and the endwall defines an inner surface of the flow channel. The endwall includes a radially raised portion that is raised proximate the suction surface, and a radially depressed portion downstream of the raised portion.
    Type: Grant
    Filed: August 1, 2014
    Date of Patent: August 13, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Jeff M. Carrico
  • Patent number: 10376998
    Abstract: A repair tool and repair method for restoring gas turbine engine blade tips to a predetermined configuration is provided. The repair tool is an electrode that includes a tool body and a number of pins. The repair tool can be used to repair turbine blade tips through an electrical discharge machining process, such as a ram- or sink-type electrical discharge machining process.
    Type: Grant
    Filed: June 29, 2015
    Date of Patent: August 13, 2019
    Assignee: United Technologies Corporation
    Inventors: Edward Mierzejewski, William Rose
  • Patent number: 10378374
    Abstract: A gas turbine engine includes a fluid intake. A turbine section includes a turbine case. A firewall is located upstream of the turbine section. A conduit is configured to direct a fluid from the fluid intake to the turbine case. A valve is located on a first side of the firewall opposite from the turbine section and is configured to regulate a flow of the fluid through the conduit.
    Type: Grant
    Filed: March 30, 2015
    Date of Patent: August 13, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Jesse M. Chandler, Nathan Snape
  • Patent number: 10381952
    Abstract: A method of configuring a power conversion cell for a distributed power system according to an example of the present disclosure includes: importing one or more software modules onto a controller of a conversion device configured to control power conversion with one or more of the modules selected based on one or more of a load or source device, and the results of a software simulation.
    Type: Grant
    Filed: October 2, 2015
    Date of Patent: August 13, 2019
    Assignee: United Technologies Corporation
    Inventors: Luis Arnedo, Shashank Krishnamurthy, Vladimir Blasko
  • Patent number: 10378453
    Abstract: A turbine section for a gas turbine engine includes a first rotor assembly with a first rotor assembly bleed air source and an aft cavity that is in fluid communication with the first rotor assembly bleed air source. A second rotor assembly includes a forward cavity. A vane bleed air source is in fluid communication with the forward cavity. A seal extends between the first rotor assembly and the second rotor assembly.
    Type: Grant
    Filed: September 3, 2015
    Date of Patent: August 13, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Julian Partyka, David R. Pack, James D. Hill
  • Patent number: 10376961
    Abstract: One embodiment includes a powder spheroidizing method. The method includes loading a powder into a fluidized bed assembly, fluidizing at least some of the powder in the fluidized bed assembly using an inert gas, and heating the powder while fluidized in the fluidized bed assembly.
    Type: Grant
    Filed: July 30, 2014
    Date of Patent: August 13, 2019
    Assignee: United Technologies Corporation
    Inventors: Michael A. Klecka, Ying She, Tahany Ibrahim El-Wardany, Aaron T. Nardi
  • Patent number: 10378371
    Abstract: A vane for a gas turbine engine includes a radially inner platform and a radially outer platform. At least two airfoils extend between the radially inner platform and the radially outer platform. At least two anti-rotation tabs extend axially from the radially outer platform.
    Type: Grant
    Filed: December 10, 2015
    Date of Patent: August 13, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Russell J. Bergman, Thurman Carlo Dabbs
  • Patent number: 10378370
    Abstract: A turbine exhaust case comprises a frame, a fairing, a heat shield and a mechanical linkage. The frame comprises an outer ring, an inner ring, and a plurality of struts joining the outer ring and the inner ring. The fairing comprising a ring-strut-ring structure disposed within the frame. The heat shield is disposed between the frame and the fairing. The mechanical linkage couples the heat shield to the fairing. In one embodiment, the heat shield comprises a multi-piece heat shield that inhibits heat transfer between the frame and the fairing. In various embodiments, the mechanical linkage comprises a slip joint or a fixed joint for coupling the heat shield to the fairing.
    Type: Grant
    Filed: December 17, 2013
    Date of Patent: August 13, 2019
    Assignee: United Technologies Corporation
    Inventors: Matthew Budnick, Conway Chuong, Jonathan Ariel Scott
  • Patent number: 10378451
    Abstract: A seal assembly is provided for a gas turbine engine. This seal assembly includes a tadpole seal with a bulb and a tail, where the tail is directed toward a backwall. The seal assembly also includes a faying extension that at least partially extends into the channel and into contact with the bulb. An exhaust duct is also provided for a gas turbine engine. This exhaust duct includes a seal assembly between a first exhaust duct section and a second exhaust duct section. The seal assembly includes a tadpole seal with a bulb and a tail, where the tail is directed upstream.
    Type: Grant
    Filed: September 10, 2014
    Date of Patent: August 13, 2019
    Assignee: United Technologies Corporation
    Inventor: Gary J. Dillard
  • Patent number: 10378359
    Abstract: A heat exchanger has a first plurality of passages extending in a first direction and to receive a first fluid and a second plurality of passages extending in a second direction, and to receive a second fluid, and the first plurality of passages being formed across a cross-sectional face of the heat exchanger, and there being distinct combined flow cross-sectional areas of the first plurality of passages in different locations across the cross-sectional face of the heat exchanger. A gas turbine engine and a method of forming a heat exchanger are also disclosed.
    Type: Grant
    Filed: May 17, 2016
    Date of Patent: August 13, 2019
    Assignee: United Technologies Corporation
    Inventors: John W. Golan, Frederick M. Schwarz
  • Patent number: 10378450
    Abstract: A method of manufacturing a gas turbine engine air seal comprising forming at least one MAX phase particle. The method includes coating the at least one MAX phase particle with a metallic shell. The method includes applying the at least one MAX phase metallic coated particle to a surface of a substrate of the air seal to form an abradable layer of a MAXMET composite abradable material from the at least on MAX phase metallic coated particle.
    Type: Grant
    Filed: May 27, 2015
    Date of Patent: August 13, 2019
    Assignee: United Technologies Corporation
    Inventors: Shahram Amini, Christopher W. Strock, Weina Li
  • Patent number: 10378381
    Abstract: A gas turbine engine component has an airfoil extending radially inwardly of an outer platform to an inner platform. A central passage is formed within the airfoil and has an inlet end for receiving cooling air. An outlet end in the inner platform delivers cooling air to a downstream use. The airfoil has a suction wall and a pressure wall, and extends in an axial direction from a leading edge to a trailing edge. A suction skin core is between the central passage and the suction wall. A pressure skin core is between the central passage and the pressure wall.
    Type: Grant
    Filed: October 16, 2014
    Date of Patent: August 13, 2019
    Assignee: United Technologies Corporation
    Inventors: Benjamin F. Hagan, Ryan Alan Waite
  • Patent number: 10378440
    Abstract: A disclosed gas turbine engine includes a fan section including a hub supporting a plurality of fan blades rotatable about an axis, and a bearing assembly supporting rotation of the hub about the axis. A compressor section is in fluid communication with a combustor and a turbine is in fluid communication with the compressor section. A speed reduction device driven by the turbine section for rotating the fan about the axis is mounted forward of the bearing assembly supporting rotation of the hub.
    Type: Grant
    Filed: November 25, 2014
    Date of Patent: August 13, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: William G. Sheridan