Patents Assigned to United Technologies Corporation
  • TWO TIER LUBRICATION SYSTEM
    Publication number: 20200191054
    Abstract: A two-tier lubrication system may comprise an oil nozzle located in a bearing compartment. A main oil system may be configured to provide oil to the oil nozzle. A scavenge system may be configured to collect oil from the bearing compartment. A valve may be fluidly coupled between the main oil system and the scavenge system. The valve may be configured to actuate between a main flow position and a scavenge flow position.
    Type: Application
    Filed: December 18, 2018
    Publication date: June 18, 2020
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventor: Francis Parnin
  • APPARATUS AND METHODS FOR CLEANING INTERNAL CAVITIES OF BLADES
    Publication number: 20200191013
    Abstract: An apparatus for dislodging material within an airfoil element is disclosed. In various embodiments, the apparatus includes a robotic arm configured for multi-axis movement of a mounting head with respect to the airfoil element; a vibration mechanism connected to the mounting head; and a tip member connected to the vibration mechanism and configured for vibratory contact with a surface of the airfoil element.
    Type: Application
    Filed: December 12, 2018
    Publication date: June 18, 2020
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Karthikeyan Baskaran, Garimella Balaji Rao
  • ADAPTIVE MORPHING ENGINE GEOMETRY
    Publication number: 20200191011
    Abstract: A morphing aerodynamic control surface geometry comprising a control surface having an articulated portion comprising a flexible skin coupled at an exterior of the articulated portion, the flexible skin comprising opposed interlocking elements sandwiched within a flexible polymer coupled to the interlocking elements; wherein the flexible skin is configured compliant responsive to an articulation of the articulated portion.
    Type: Application
    Filed: December 13, 2018
    Publication date: June 18, 2020
    Applicant: United Technologies Corporation
    Inventors: Zaffir A. Chaudhry, Andrzej Ernest Kuczek, Dilip Prasad
  • FAN AND LOW PRESSURE COMPRESSOR GEARED TO LOW SPEED SPOOL OF GAS TURBINE ENGINE
    Publication number: 20200191062
    Abstract: A gas turbine engine may include a high speed spool, a low speed spool, a first epicyclic gear system, and a second epicyclic gear system. Generally, the high speed spool mechanically connects a high pressure turbine to a high pressure compressor, and the low speed spool mechanically connects a low pressure turbine to at least one of a fan and a prop via the first epicyclic gear system and to a low pressure compressor via the second epicyclic gear system, according to various embodiments. The first epicyclic gear system and the second epicyclic gear system may include a common sun gear shaft.
    Type: Application
    Filed: November 1, 2019
    Publication date: June 18, 2020
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: William G. Sheridan, Michael E. McCune
  • ADDITIVELY CONTROLLED SURFACE ROUGHNESS FOR DESIGNED PERFORMANCE
    Publication number: 20200191018
    Abstract: A process for additively controlled surface features of a gas turbine engine casing. The process comprises forming the casing having an inner surface and an outer surface opposite the inner surface; forming a surface feature on the casing proximate the inner surface, wherein the surface feature comprises a structure on the inner surface configured to align or misalign with respect to a flow direction of a working fluid in a flow path of the casing.
    Type: Application
    Filed: December 17, 2018
    Publication date: June 18, 2020
    Applicant: United Technologies Corporation
    Inventors: Vijay Narayan Jagdale, Jesse R. Boyer, Om P. Sharma, Evan Butcher, Lawrence Binek, Bryan G. Dods
  • Gas turbine engine component platform cooling
    Patent number: 10683760
    Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having an outer surface and an inner surface that axially extend between a leading edge portion and a trailing edge portion. At least one augmentation feature is disposed on at least the leading edge portion or the trailing edge portion of the outer surface of the platform.
    Type: Grant
    Filed: May 15, 2015
    Date of Patent: June 16, 2020
    Assignee: United Technologies Corporation
    Inventors: Eleanor D. Kaufman, Matthew A. Devore
  • FLUID INJECTION SYSTEMS FOR GAS TURBINE ENGINES
    Publication number: 20200182113
    Abstract: A fluid injection system for a gas turbine engine may comprise a fluid injector configured to inject a fluid into an exhaust flow exiting a turbine section of the gas turbine engine. The fluid injector may be coupled to a turbine exit guide vane located at a forward end of an exhaust system of the gas turbine engine. The fluid may decrease a temperature of the exhaust flow exiting the turbine section and/or increase a thrust of the gas turbine engine.
    Type: Application
    Filed: September 27, 2019
    Publication date: June 11, 2020
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Daniel B. Kupratis, Neil Terwilliger, Gary Roberge
  • LOW PRESSURE COMPRESSOR CONTROL FOR A GAS TURBINE ENGINE
    Publication number: 20200182158
    Abstract: A gas turbine engine includes a low speed spool mechanically interconnecting a low pressure turbine and at least one of a fan and a prop, a high speed spool mechanically interconnecting a high pressure turbine and a high pressure compressor, and an epicyclic gear system mechanically coupled to the high speed spool. The gas turbine engine also includes a low pressure compressor mechanically coupled to the high speed spool via the epicyclic gear system. The low pressure compressor may be mechanically independent of the low speed spool. The gas turbine engine may include a plurality of motor-generators for transferring power between the high speed spool and the low pressure compressor.
    Type: Application
    Filed: October 17, 2019
    Publication date: June 11, 2020
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventor: Daniel Bernard Kupratis
  • AXIAL FLOW COOLING SCHEME WITH CASTABLE STRUCTURAL RIB FOR A GAS TURBINE ENGINE
    Publication number: 20200182069
    Abstract: A component for a gas turbine engine includes a interleaved structural rib that extends between the first multiple of axial standoff ribs and the second multiple of axial standoff ribs. The second multiple of structural rib span segments that extend from the second sidewall, the first multiple of structural rib span segments interleaved with the second multiple of structural rib span segments to form an interleaved structural rib that extends between the first sidewall and the second sidewall.
    Type: Application
    Filed: December 5, 2018
    Publication date: June 11, 2020
    Applicant: United Technologies Corporation
    Inventors: Brandon W. Spangler, Adam P. Generale
  • AXIAL FLOW COOLING SCHEME WITH STRUCTURAL RIB FOR A GAS TURBINE ENGINE
    Publication number: 20200182068
    Abstract: A component for a gas turbine engine. The component includes a first multiple of axial standoff ribs that extend from the first sidewall and a second multiple of axial standoff ribs that extend from the second sidewall. The structural rib that extends between the first multiple of axial standoff ribs and the second multiple of axial standoff ribs.
    Type: Application
    Filed: December 5, 2018
    Publication date: June 11, 2020
    Applicant: United Technologies Corporation
    Inventors: Brandon W. Spangler, Adam P. Generale
  • DUAL COOLING AIRFLOW TO BLADES
    Publication number: 20200182060
    Abstract: An airfoil may comprise a root and an airfoil body radially outward of the root. The airfoil body may define a first cooling chamber and a second cooling chamber. A first passage may be defined within the root and configured to direct a first airflow radially outward through the root into the first cooling chamber. A second passage may be defined within the root and configured to direct a second airflow radially outward through the root and into the second cooling chamber. A tangential onboard injector (TOBI) may be disposed in the first airflow path. A radial onboard injector (ROBI) may be disposed in the second airflow path.
    Type: Application
    Filed: February 19, 2020
    Publication date: June 11, 2020
    Applicant: United Technologies Corporation
    Inventors: Matthew A. Devore, Jonathan Ortiz
  • INTERNAL COOLING CAVITY WITH TRIP STRIPS
    Publication number: 20200182070
    Abstract: An airfoil is provided. The airfoil may comprise a cross over, an impingement chamber in fluid communication with the cross over, and a first trip strip disposed on a first surface of the impingement chamber. A cooling system is also provided. The cooling system may comprise an impingement chamber, a first trip strip on a first surface of the impingement chamber, and a second trip strip on a second surface of the impingement chamber. An internally cooled engine part is further provided. The internally cooled part may comprise a cross over and an impingement chamber in fluid communication with the cross over. The cross over may be configured to direct air towards a first surface of the impingement chamber. A first trip strip may be disposed on the first surface of the impingement chamber.
    Type: Application
    Filed: February 18, 2020
    Publication date: June 11, 2020
    Applicant: United Technologies Corporation
    Inventors: San Quach, Atul Kohli, Matthew A. Devore, Steven Bruce Gautschi
  • CONFORMAL ACCESSORY GEARBOX FOR LOW BYPASS GAS TURBINE ENGINE
    Publication number: 20200182157
    Abstract: A gas turbine engine includes an engine case along an engine axis, a conformal accessory drive gearbox housing mounted to the engine case, and at least one accessory mounted to the conformal housing
    Type: Application
    Filed: December 6, 2018
    Publication date: June 11, 2020
    Applicant: United Technologies Corporation
    Inventor: Gary D. Roberge
  • Turbine blade with airfoil tip vortex control
    Patent number: 10677066
    Abstract: A rotor blade for a gas turbine engine is provided. The rotor blade having: an attachment; an airfoil extending from the attachment to a tip; and a tip shelf located in a surface of the tip proximate to a pressure side of the airfoil, wherein the tip shelf has a ledge portion extending from the pressure side to a wall portion extending upwardly from the ledge portion to the tip and wherein the wall portion is configured to have a convex portion with respect to the pressure side of the airfoil as it extends from a leading edge to a trailing edge of the airfoil.
    Type: Grant
    Filed: February 8, 2016
    Date of Patent: June 9, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Scott D. Lewis, Kyle C. Lana
  • METHOD FOR MAGNETIC FLUX COMPENSATION IN A DIRECTIONAL SOLIDIFICATION FURNACE UTILIZING AN ACTUATED SECONDARY COIL
    Publication number: 20200171567
    Abstract: A process for directional solidification of a cast part comprises energizing a primary inductive coil coupled to a chamber having a mold containing a material; generating an electromagnetic field with the primary inductive coil within the chamber, wherein said electromagnetic field is partially attenuated by a susceptor coupled to said chamber between said primary inductive coil and said mold; determining a magnetic flux profile of the electromagnetic field after it passes through the susceptor; sensing a component of the magnetic flux in the interior of the susceptor proximate the mold; positioning a mobile secondary compensation coil within the chamber; generating a control field from a secondary compensation coil, wherein said control field controls said magnetic flux; and casting the material within the mold.
    Type: Application
    Filed: February 4, 2020
    Publication date: June 4, 2020
    Applicant: United Technologies Corporation
    Inventors: Thomas Anthony Rebbecchi, Joseph V. Mantese, Ryan C. Breneman, Andrew Boyne, John Joseph Marcin, Dustin W. Davis, David Ulrich Furrer, James Tilsley Auxier
  • THERMAL MANAGEMENT SYSTEM FOR LOW BYPASS GAS TURBINE ENGINE
    Publication number: 20200173365
    Abstract: A thermal management system for a gas turbine engine includes an additively manufactured outer engine duct structure, at least a portion of an internal surface of the additively manufactured outer engine duct structure forming an additively manufactured heat exchanger
    Type: Application
    Filed: December 3, 2018
    Publication date: June 4, 2020
    Applicant: United Technologies Corporation
    Inventor: Gary D. Roberge
  • ROTOR OVERSPEED PROTECTION ASSEMBLY
    Publication number: 20200173297
    Abstract: A gas turbine engine may include a rotor overspeed protection (ROP) assembly. The ROP assembly may include an annular blade outer air seal (BOAS) assembly including a ROP segment. The ROP assembly may include a stator vane coupled with the BOAS assembly/. The stator vane may include a stator flange disposed about a forward edge portion of the stator vane. The ROP segment may include a ROP flange extending in an axially aft direction from a main body of the ROP segment toward the stator vane, wherein the ROP flange is disposed radially inward of the stator flange.
    Type: Application
    Filed: December 3, 2018
    Publication date: June 4, 2020
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brian Merry, Paul W. Duesler
  • THERMAL MANAGEMENT SYSTEM FOR GAS TURBINE ENGINE
    Publication number: 20200173307
    Abstract: A thermal management system for a gas turbine engine includes an additively manufactured nacelle component, at least a portion of the additively manufactured nacelle component forming an additively manufactured heat exchanger that extends into a fan bypass flow.
    Type: Application
    Filed: December 3, 2018
    Publication date: June 4, 2020
    Applicant: United Technologies Corporation
    Inventor: Gary D. Roberge
  • Air seal attachment
    Patent number: 10669877
    Abstract: A gas turbine engine includes a coupling and an air seal attachment. The annular coupling extends along a centerline and has coupling teeth that extend axially rearward. The annular air seal attachment includes an air seal at an axially rearward end and air seal attachment teeth at an axially forward end that extend axially forward to interlock with the coupling teeth such that the air seal attachment teeth and the coupling teeth alternate in a circumferential direction.
    Type: Grant
    Filed: December 21, 2017
    Date of Patent: June 2, 2020
    Assignee: United Technologies Corporation
    Inventor: Brian P. Cigal
  • BEVELED COVERPLATE
    Publication number: 20200165925
    Abstract: A gas turbine engine includes a platform that has a gas path side, a non-gas path side, a first mate face, and a second mate face. The second mate face has a beveled edge sloping towards the first mate face. The gas turbine engine also includes a coverplate that includes a first bend, a flat portion substantially parallel to the first mate face and a first wing substantially parallel to the second mate face.
    Type: Application
    Filed: January 29, 2020
    Publication date: May 28, 2020
    Applicant: United Technologies Corporation
    Inventor: BRANDON W. SPANGLER