Patents Assigned to United Technologies Corp.
  • Vibration Management for Gas Turbine Engines
    Publication number: 20090110541
    Abstract: Systems and methods involving vibration management of gas turbine engines are provided. In this regard, a representative method includes: detecting vibrations of a gas turbine engine; automatically adjusting rotational speed of a component of the gas turbine engine in order to attempt to reduce the vibrations to within predefined vibration limits; and automatically adjusting operating parameters of the gas turbine engine such that, if the vibrations are reduced to within the predefined vibration limits, thrust of the gas turbine engine is set to an amount of thrust corresponding to the amount of thrust provided prior to the adjusting of the rotational speed of the component.
    Type: Application
    Filed: October 25, 2007
    Publication date: April 30, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: Robert D. Southwick, Joseph P. Pascuitti
  • Gas Turbine Engine Systems Involving Rotatable Annular Supports
    Publication number: 20090101787
    Abstract: Gas turbine engine systems involving rotatable annular supports are provided. In this regard, a representative support assembly for a gas turbine engine includes: a rotatable member having a first end located about a first annulus; and a stationary member located about a second annulus; the first end of the rotatable member being rotatably coupled with the stationary member, with at least a portion of the first annulus being coextensive with at least a portion of the second annulus, the first end being operative to rotate locally with respect to a corresponding portion of the stationary member.
    Type: Application
    Filed: October 18, 2007
    Publication date: April 23, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventor: James A. Dierberger
  • Systems and Methods Involving Rotable Components
    Publication number: 20090106130
    Abstract: Systems and methods involving rotable gas turbine engine components are provided. In this regard, a representative system includes: a component pool control system; an inventory system operative to store inventory information corresponding to a current inventory of rotable components and to provide the inventory information to the component pool control system; and an inspection system operative to store inspection information corresponding to analyzed one of the rotable components and to provide the inspection information to the component pool control system.
    Type: Application
    Filed: October 17, 2007
    Publication date: April 23, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventor: Daniel E. Quinn
  • Systems and Methods for Testing Gas Turbine Engines
    Publication number: 20090100918
    Abstract: Systems and methods for testing gas turbine engines are provided. In this regard, a representative system for testing a gas turbine engine having an inlet includes an inflatable seal having an interior chamber operative to receive pressurized gas such that the seal inflates to engage circumferentially about the exterior of an inlet of a gas turbine engine.
    Type: Application
    Filed: September 26, 2007
    Publication date: April 23, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventor: Miguel A. Cires
  • Gas Turbine Engine Systems Involving Gear-Driven Variable Vanes
    Publication number: 20090104022
    Abstract: Gas turbine engine systems involving gear-driven variable vanes are provided. In this regard, a representative gas turbine engine system includes: a ring gear assembly operative to be mounted within an engine casing; and a vane module having a first vane airfoil and a first gear, the first gear being operative to engage the ring gear assembly such that movement of the ring gear alters a position of the first vane airfoil.
    Type: Application
    Filed: October 22, 2007
    Publication date: April 23, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: George T. Suljak, JR., Michael G. McCaffrey
  • Gas Turbine Engines and Related Systems Involving Blade Outer Air Seals
    Publication number: 20090104025
    Abstract: Gas turbine engines and related systems involving blade outer air seals are provided. In this regard, a representative blade outer air seal assembly for a gas turbine engine includes: an annular arrangement of outer air seal segments defining an inner diameter surface; intersegment gaps located between the outer air seal segments, each of the gaps being located between a corresponding adjacent pair of the segments; and recesses spaced about the inner diameter surface, each of the recesses communicating with a corresponding one of the gaps.
    Type: Application
    Filed: October 17, 2007
    Publication date: April 23, 2009
    Applicant: United Technologies Corp.
    Inventors: Paul M. Lutjen, Susan M. Tholen
  • Gas Turbine Engines Systems and Related Methods Involving Dimensionally Restored Fasteners
    Publication number: 20090104003
    Abstract: Gas turbine engines systems and related methods involving dimensionally restored fasteners are provided. In this regard, a representative method for dimensionally restoring a mechanical fastener for a gas turbine engine includes: providing a mechanical fastener; and relocating existing material of the fastener such that a dimension of the fastener is restored.
    Type: Application
    Filed: October 18, 2007
    Publication date: April 23, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: Derek W. Anderson, Allen W. Brown
  • Vacuum Pressure Systems
    Publication number: 20090096230
    Abstract: Vacuum pressure systems are provided. In this regard, a representative vacuum pressure system includes: an inlet; and a linear actuator having a permanent magnet, a coil, an inner ferromagnetic core and an outer ferromagnetic core, the outer ferromagnetic core surrounding at least a portion of each of the permanent magnet, the coil, and the inner ferromagnetic core; the linear actuator being operative to exhibit relative motion between the permanent magnet and the coil responsive to an electrical current being applied to the coil such that the linear actuator forms vacuum pressure and draws fluid into the inlet.
    Type: Application
    Filed: October 12, 2007
    Publication date: April 16, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: Jacek F. Gieras, Thomas G. Tillman, Hayden M. Reeve
  • Systems and Methods Involving Abradable Air Seals
    Publication number: 20090097970
    Abstract: Systems and methods involving air seals are provided. In this regard, a representative air seal for a gas turbine engine comprises a layer of ceramic exhibiting patterned surface features, wherein a substrate supporting the layer of ceramic lacks the patterned surface features.
    Type: Application
    Filed: October 16, 2007
    Publication date: April 16, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: Susan M. Tholen, Christopher W. Strock
  • Gas Turbine Engines and Related Systems Involving Variable Vanes
    Publication number: 20090097966
    Abstract: Gas turbine engines and related systems involving variable vanes are provided. In this regard, a representative vane assembly for a gas turbine engine includes: a first inner diameter platform; a first outer diameter platform spaced from the first inner diameter platform; and a variable vane airfoil rotatably attached to and extending between the first inner diameter platform and the first outer diameter platform such that at least a portion of the vane airfoil extends beyond a periphery of at least one of the first inner diameter platform and the first outer diameter platform.
    Type: Application
    Filed: October 15, 2007
    Publication date: April 16, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventor: Michael G. McCaffrey
  • Gas Turbine Engine Systems and Related Methods Involving Heat Exchange
    Publication number: 20090097972
    Abstract: Gas turbine engine systems and related methods involving heat exchange are provided. In this regard, a representative heat exchange system for a gas turbine engine includes: a heat exchanger; and a flow restrictor operative to selectively restrict a flow of gas flowing along an annular gas flow path; in an open position, the flow restrictor enabling gas to flow along the gas flow path and, in a closed position, the flow restrictor restricting the flow of gas such that at least a portion of the gas is provided to the heat exchanger, the heat exchanger being located radially outboard of the flow restrictor.
    Type: Application
    Filed: October 10, 2007
    Publication date: April 16, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventor: Michael Joseph Murphy
  • Systems and Methods for Altering Inlet Airflow of Gas Turbine Engines
    Publication number: 20090092482
    Abstract: Systems and methods for altering airflow to gas turbine engines are provided. In this regard, a representative system includes a gas turbine engine inlet having a slat, the slat being movable between a retracted position and an extended position. In the extended position, the slat increases an effective diameter of the inlet compared to the diameter of the inlet when in the retracted position.
    Type: Application
    Filed: October 9, 2007
    Publication date: April 9, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventor: Michael Winter
  • Systems and Methods Involving Multiple Torque Paths for Gas Turbine Engines
    Publication number: 20090092487
    Abstract: Systems and methods involving multiple torque paths of gas turbine engines are provided. In this regard, a representative spool assembly for a gas turbine engine, which incorporates a compressor, a turbine and a gear assembly, includes: a shaft operative to be driven by the turbine; a first spool segment operative to couple the shaft to the compressor; and a second spool segment operative to couple the shaft to the gear assembly. The first spool segment and the second spool segment are not coupled to each other.
    Type: Application
    Filed: October 9, 2007
    Publication date: April 9, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: Michael E. McCune, Brian D. Merry, Gabriel L. Suciu
  • Systems and Methods for Performing Cooling Airflow Analysis of Gas Turbine Engine Components
    Publication number: 20090084170
    Abstract: Systems and methods for performing cooling airflow analysis of gas turbine engine components are provided. In this regard, a representative system includes an airflow insert operative to form a seal with a component, the airflow insert having a main portion and a removable sacrificial portion, the sacrificial portion being sized and shaped to engage the component, the main portion having a cavity sized and shaped to removably receive the sacrificial portion, the main portion being sized and shaped to form a seal about the sacrificial portion and a corresponding portion of the component.
    Type: Application
    Filed: September 27, 2007
    Publication date: April 2, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: Daniel E. Quinn, Kurt A. Hassett
  • Methods for Repairing Gas Turbine Engine Components
    Publication number: 20090071002
    Abstract: Methods for repairing the gas turbine engine components are provided. In this regard, a representative method includes: determining the presence of a previous repair to a component; determining a characteristic of the previous repair using X-ray fluorescence analysis; and repairing the component.
    Type: Application
    Filed: September 18, 2007
    Publication date: March 19, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: Andrew J. Lutz, Aaron T. Frost
  • Systems Involving Inlet-Mounted Engine Controls
    Publication number: 20090064684
    Abstract: Systems involving inlet-mounted engine control components are provided. A representative system includes: a forward keep out zone defined by converging inner and outer walls of a nacelle; an aft keep out zone defined by a containment zone; and an engine control component, at least a portion of which is located between the forward keep out zone and the aft keep out zone, and between the inner and outer walls of the nacelle.
    Type: Application
    Filed: July 13, 2007
    Publication date: March 12, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventor: Thomas G. Cloft
  • Methods for Performing Gas Turbine Engine Casing Repairs and Repaired Cases
    Publication number: 20090064479
    Abstract: Methods for repairing gas turbine engine casings and repaired casings are provided. In this regard, a representative method for repairing a gas turbine engine casing includes: removing an annular portion of the engine casing; and attaching an annular replacement portion to the engine casing.
    Type: Application
    Filed: September 12, 2007
    Publication date: March 12, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: Derek W. Anderson, Kevin Nicholas Shultis
  • Gas Turbine Engine Systems and Related Methods Involving Vane-Blade Count Ratios Greater than Unity
    Publication number: 20090068003
    Abstract: Gas turbine engine systems and related methods involving vane-blade count ratios greater than unity are provided. In this regard, a representative turbine stage for a gas turbine engine includes a first set of rotatable blades operative to be positioned downstream of and adjacent to a first set of vanes, a number of blades of the first set of blades being less than a number of vanes of the first set of vanes.
    Type: Application
    Filed: September 6, 2007
    Publication date: March 12, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: Om P. Sharma, Michael F. Blair
  • Roller Bearings, and Struts and Gas Turbine Engines Having such Bearings
    Publication number: 20090067985
    Abstract: Roller bearings, and struts and gas turbine engines using such bearings are provided. In this regard, a representative roller bearing for a gas turbine engine includes: a roller having a rolling surface and an end; a race having a flange and defining a raceway, the raceway terminating at the flange, the raceway being operative to receive the roller such that the rolling surface of the roller engages in rolling contact with the raceway; and a hard coating applied to the flange such that the end of the roller engages in sliding contact with the coating.
    Type: Application
    Filed: September 12, 2007
    Publication date: March 12, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: Louis J. Dobek, JR., David M. Daley
  • Systems and Methods for Determining Airflow Parameters of Gas Turbine Engine Components
    Publication number: 20090064773
    Abstract: Systems and methods for determining airflow parameters of gas turbine engine components are provided. In this regard, a representative method includes: receiving information from multiple test systems regarding a first airflow parameter of a gas turbine engine component; and using the information to establish a desired performance parameter that is to be exhibited by a repaired component.
    Type: Application
    Filed: September 12, 2007
    Publication date: March 12, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: Thomas McCall, Kurt A. Hassett