Patents Assigned to United Technologies Corp.
  • Gas Turbine Engine Systems and Methods Involving Vibration Monitoring
    Publication number: 20090301055
    Abstract: Gas turbine engine systems and methods involving vibration monitoring are provided. In this regard, a representative vibration monitoring method for a gas turbine engine includes: receiving information corresponding to detected vibrations of a gas turbine engine; isolating vibrations attributable to rotating blades of the gas turbine engine from the detected vibrations; and comparing the isolated vibrations to information corresponding to predicted vibrations of the rotating blades.
    Type: Application
    Filed: June 4, 2008
    Publication date: December 10, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventor: Pattada A. Kallappa
  • Systems and Methods Involving Multiplexed Engine Control Signals
    Publication number: 20090292437
    Abstract: Systems and methods involving multiplexed engine control signals are provided. In this regard, a representative engine control system for a gas turbine engine includes: a signal relay device operative to receive multiplexed signals from an engine electronic control (EEC), demultiplex the signals, and provide demultiplexed signals to corresponding ones of multiple control devices of the engine.
    Type: Application
    Filed: May 22, 2008
    Publication date: November 26, 2009
    Applicant: United Technologies Corp.
    Inventor: Thomas G. Cloft
  • Systems and Methods Involving Surface Fitting
    Publication number: 20090281774
    Abstract: Systems and methods involving surface fitting are provided. In this regard, a representative method includes: receiving information corresponding to discrete data points of a portion of a surface; determining curvature estimates associated with the data points prior to performing curve fitting with respect to the data points; identifying curvature shock based on the curvature estimates, the curvature shock being defined as a curvature threshold corresponding to an absolute value of curvature between adjacent data points; breaking C2 continuity between adjacent data points exhibiting curvature shock; and performing surface fitting with respect to the data points to generate Non-Uniform Rational B-Splines (NURBS) data such that breaks in the C2 continuity associated with curvature shock are maintained in the NURBS data.
    Type: Application
    Filed: May 8, 2008
    Publication date: November 12, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: Sue-Li Chuang, Perry Bowes, Steven R. Haggerty
  • Computed Tomography Systems and Related Methods Involving Localized Bias
    Publication number: 20090274264
    Abstract: Computed tomography systems and related methods involving localized measurements are provided. In this regard, a representative computed tomography system for analyzing a target is operative to determine, with a biased density value differing from an average density value for the target, a location of an interface of the target.
    Type: Application
    Filed: April 30, 2008
    Publication date: November 5, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: Edwin L. Strickland, III, Rodney H. Warner
  • Gas Turbine Engine Systems and Related Methods Involving Thermally Isolated Retention
    Publication number: 20090272123
    Abstract: Gas turbine engine systems and related methods involving thermally isolated retention are provided. In this regard, a representative method for attaching a gas turbine engine component includes using a fastener, varying in diameter along a length thereof, to prevent a portion of a component from being crimped between surfaces to which the component is attached such that the component moves relative to the surfaces responsive to thermal cycling of a gas turbine engine of which the surfaces and the component are constituent parts.
    Type: Application
    Filed: April 30, 2008
    Publication date: November 5, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: Andreas Sadil, Claude I. Barnett, JR., Ricky A. Daigle
  • X-Ray Detector Assemblies and Related Computed Tomography Systems
    Publication number: 20090272908
    Abstract: X-ray detector assemblies and related computed tomography systems are provided. In this regard, a representative X-ray detector assembly includes: a scintillator assembly having a scintillation component and an optical fiber; the scintillation component being operative to emit light responsive to X-rays being incident thereon; the optical fiber being positioned to receive light emitted from the scintillation component.
    Type: Application
    Filed: April 30, 2008
    Publication date: November 5, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: Rodney H. Warner, Royce McKim
  • Premix Nozzles and Gas Turbine Engine Systems Involving Such Nozzles
    Publication number: 20090266079
    Abstract: Premix nozzles and gas turbine engine systems involving such nozzles are provided. In this regard, a representative industrial gas turbine engine includes: a combustion section having a nozzle assembly operative to provide a fuel-air mixture for combustion, the nozzle assembly having an array of shuttered nozzles and non-shuttered nozzles; each of the shuttered nozzles being operative in an open position, in which air is directed through the shuttered nozzle for mixing with fuel, and a closed position, in which a reduced amount of air is directed through the shuttered nozzle; each of the shuttered nozzles being inoperative to independently alter an amount of air being directed therethrough.
    Type: Application
    Filed: April 28, 2008
    Publication date: October 29, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventor: Brian G. Donnelly
  • Gas Turbine Engine Systems Involving Turbine Blade Platforms with Cooling Holes
    Publication number: 20090269184
    Abstract: Gas turbine engine systems involving turbine blade platforms with mateface cooling holes are provided. In this regard, a representative turbine blade for a gas turbine engine includes: an airfoil having a leading edge, a trailing edge, a pressure side and a suction side; and a blade platform on which the airfoil is disposed, the blade platform having a pressure side mateface located adjacent to the pressure side of the airfoil and a suction side mateface located adjacent to the suction side of the airfoil, the blade platform having a cooling hole operative to direct a flow of cooling air toward an adjacent blade platform.
    Type: Application
    Filed: April 29, 2008
    Publication date: October 29, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: Brandon W. Spangler, Corneil S. Paauwe
  • Computed Tomography Systems and Related Methods Involving Multi-Target Inspection
    Publication number: 20090257552
    Abstract: Computed tomography (CT) systems and related methods involving multi-target inspection are provided are provided. In this regard, a representative method includes: simultaneously directing X-rays toward multiple targets from an X-ray source; during the directing of the X-rays, independently reorienting the targets with respect to the X-ray source; and obtaining information corresponding to attenuation of the X-rays attributable to the multiple targets for producing computed tomography images of the targets.
    Type: Application
    Filed: April 9, 2008
    Publication date: October 15, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: Rodney H. Warner, Royce McKim
  • Systems and Methods for Positioning Fairing Sheaths of Gas Turbine Engines
    Publication number: 20090243176
    Abstract: Systems and methods for positioning fairing sheaths are provided. In this regard, a representative method includes using vacuum pressure to assist in moving opposing portions of a fairing sheath away from each other.
    Type: Application
    Filed: March 31, 2008
    Publication date: October 1, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventor: Phillip Alexander
  • Gas Turbine Engine Seals and Engines Incorporating Such Seals
    Publication number: 20090243228
    Abstract: Gas turbine engine seals and engines incorporating such seals are provided. In this regard, a representative seal includes: an annular seal body having an inner diameter and an outer diameter, the seal body extending along an axis of symmetry between a first end and a second end; the seal body being formed of a strip of material having first and second opposing edges, the strip of material being deformed to exhibit a first sealing surface at the first end, a second sealing surface at the second end, and a third sealing surface along the inner diameter, the first edge being located adjacent to the third sealing surface, the second edge being located adjacent to the second sealing surface; the first edge being spaced from the second edge to define an annular opening, the annular opening providing access to an annular cavity of the seal body.
    Type: Application
    Filed: March 27, 2008
    Publication date: October 1, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: Kurt R. Heinemann, Jose Paulino, Scot A. Webb, Mark Ring, Charles H. Warner
  • Gas Turbine Engine Systems Involving Variable Nozzles with Flexible Panels
    Publication number: 20090241550
    Abstract: Gas turbine engine systems involving flexible panels are provided. In this regard, a representative flexible panel assembly for a gas turbine engine includes: a flexible panel operative to define at least one of a throat area and an exit area of a nozzle of a gas turbine engine, the panel being further operative to selectively exhibit a range of positions to regulate exhaust of the engine.
    Type: Application
    Filed: March 25, 2008
    Publication date: October 1, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: Dale William Petty, Timothy A. Swanson, Shawn M. McMahon
  • Gas Turbine Engine Systems Involving Fairings with Locating Data
    Publication number: 20090238686
    Abstract: Gas turbine engine systems involving fairings with locating data are provided. In this regard, a representative a fairing assembly for a gas turbine engine includes: a first locating component having a leading edge, first and second sides extending from the leading edge, and a recess oriented parallel to the leading edge, the recess having a first datum surface, the first locating component being operative to be positioned between a portion of a strut and a portion of an interior surface of a fairing sheath such that the first datum surface establishes a desired orientation of the fairing sheath relative to the strut.
    Type: Application
    Filed: March 18, 2008
    Publication date: September 24, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: David R. Lyders, Carl Brian Klinetob, Phillip Alexander
  • Cooling Air Manifold Splash Plates and Gas Turbines Engine Systems Involving Such Splash Plates
    Publication number: 20090232637
    Abstract: Cooling air manifold splash plates and gas turbine engine systems involving such splash plates are provided. In this regard, a representative cooling air manifold splash plates includes: a base having an aperture; and an air deflector supported by the base, the air deflector being positioned relative to the base to receive, from the aperture, a radial flow of gas turbine engine cooling air, the air deflector being operative to redirect at least some of the air received circumferentially.
    Type: Application
    Filed: March 11, 2008
    Publication date: September 17, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: Tracy A. Propheter-Hinckley, Charles C. Wu
  • X-Ray Collimators, and Related Systems and Methods Involving Such Collimators
    Publication number: 20090225954
    Abstract: X-ray collimators, and related systems and methods involving such collimators are provided. In this regard, a representative X-ray collimator includes: a first member having channels located on a surface thereof; and a second member having protrusions located on a surface thereof; the first member and the second member being oriented such that the protrusions extend into the channels to define collimator apertures, each of the collimator apertures being defined by a portion of the first member and a portion of the second member.
    Type: Application
    Filed: March 6, 2008
    Publication date: September 10, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: Royce McKim, Rodney H. Warner
  • Hydrodynamic Tapered Roller Bearings and Gas Turbine Engine Systems Involving Such Bearings
    Publication number: 20090214147
    Abstract: Tapered roller bearings and gas turbine engine systems involving such bearings are provided. In this regard, a representative bearing cage for a gas turbine engine includes: an outer cage rim and an inner cage rim; the outer cage rim having a rounded edge at a location of contact between the outer cage rim and a roller.
    Type: Application
    Filed: February 25, 2008
    Publication date: August 27, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventor: Loc Duong
  • Computed Tomography Systems and Related Methods Involving Forward Collimation
    Publication number: 20090213994
    Abstract: Computed tomography (CT) systems and related methods involving forward collimation are provided are provided. In this regard, a representative method involving forward collimation of X-rays includes: emitting X-rays from a housing in which an X-ray source is mounted; collimating the X-rays downstream of the housing; and directing the collimated X-rays at a target.
    Type: Application
    Filed: February 26, 2008
    Publication date: August 27, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: Rodney H. Warner, Royce McKim
  • Self-Balancing Face Seals and Gas Turbine Engine Systems Involving Such Seals
    Publication number: 20090212501
    Abstract: Self-balancing face seals and gas turbine engine systems involving such seals are provided. In this regard, a representative self-balancing face seal assembly includes: a rotatable seal runner having a first seal runner face and an opposing second seal runner face; a first face seal operative to form a first seal with the first seal runner face, the first face seal being one of a hydrostatic seal and a hydrodynamic seal; and a second face seal operative to form a second seal with the second seal runner face, the first face seal being one of a hydrostatic seal and a hydrodynamic seal.
    Type: Application
    Filed: February 27, 2008
    Publication date: August 27, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: Jorn A. Glahn, Peter M. Munsell
  • Computed Tomography Systems and Related Methods Involving Post-Target Collimation
    Publication number: 20090213984
    Abstract: Computed tomography (CT) systems and related methods involving post-target collimation are provided are provided. In this regard, a representative method involving post-target collimation of X-rays includes: emitting X-rays toward a target; and collimating the X-rays downstream of the target.
    Type: Application
    Filed: February 26, 2008
    Publication date: August 27, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: Rodney H. Warner, Royce McKim
  • Gas turbine engine systems and methods involving blade outer air seals
    Publication number: 20090208322
    Abstract: Gas turbine engine systems and methods involving full ring outer air seals are provided. In this regard, a representative blade outer air seal assembly for a gas turbine engine includes a continuous, annular seal body formed of ceramic matrix composite (CMC) material.
    Type: Application
    Filed: February 18, 2008
    Publication date: August 20, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventor: Michael G. McCaffrey