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United Technologies Corp. Patents
Assignee:
United Technologies Corp.
Address:
Hartford, CT
No. of patents:
94
Patents:


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Patent Number Title Of Patent Date Issued
RE43710 Swept turbomachinery blade October 2, 2012
A swept turbomachinery blade for use in a cascade of such blades is disclosed. The blade (12) has an airfoil (22) uniquely swept so that an endwall shock (64) of limited radial extent and a passage shock (66) are coincident and a working medium (48) flowing through interblade passages
RE30713 Cross beam rotor August 18, 1981
A helicopter rotor having opposed blades interconnected by a common flexible spar which passes across the rotor axis is connected to the drive shaft by clamped hub plates. A spanwise extending torque tube having a pitch horn at its inner end forms a rigid connection with the spar and
D270151 Helicopter August 16, 1983
8266886 Systems and methods involving multiple torque paths for gas turbine engines September 18, 2012
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
8257045 Platforms with curved side edges and gas turbine engine systems involving such platforms September 4, 2012
Platforms with curved side edges and gas turbine engine systems involving such platforms are provided. In this regard, a representative airfoil assembly for a gas turbine engine includes: a platform having a gas path side, a non-gas path side, a leading edge, a trailing edge, a first sid
8241003 Systems and methods involving localized stiffening of blades August 14, 2012
Systems and methods involving localized stiffening of blades are provided. In this regard, a representative a gas turbine engine blade includes: a recess located in a surface of the blade; and material positioned at least partially within the recess such that the material provides a
8240987 Gas turbine engine systems involving baffle assemblies August 14, 2012
Gas turbine engine systems involving baffle assemblies are provided. In this regard, a representative baffle assembly for a gas turbine engine includes: a cooling plenum defining a cooling air path; and a baffle sized and shaped to extend between surfaces of the cooling plenum such t
8240983 Gas turbine engine systems involving gear-driven variable vanes August 14, 2012
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
8240979 Gas turbine engine systems involving integrated fluid conduits August 14, 2012
Gas turbine engine systems involving integrated fluid conduits are provided. In this regard, a representative engine casing for a gas turbine engine includes: a casing wall; and a fluid conduit integrated into the casing wall.
8238521 X-ray collimators, and related systems and methods involving such collimators August 7, 2012
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; th
8235599 Hydrodynamic tapered roller bearings and gas turbine engine systems involving such bearings August 7, 2012
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
8235345 Gas turbine engine systems and related methods involving thermally isolated retention August 7, 2012
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 co
8206092 Gas turbine engines and related systems involving blade outer air seals June 26, 2012
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, each of the segments having ends, the segments be
8202043 Gas turbine engines and related systems involving variable vanes June 19, 2012
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 varia
8197209 Systems and methods involving variable throat area vanes June 12, 2012
Systems and methods involving variable throat area vanes are provided. In this regard, a representative gas turbine engine includes: a vane extending into a gas flow path and having: an interior operative to receive pressurized air; a pressure surface portion; and a first port commun
8182208 Gas turbine systems involving feather seals May 22, 2012
Systems involving feather seals are provided. A representative vane assembly for a gas turbine engine includes: a first mounting platform having a first slot; a first airfoil extending from the first mounting platform; and a feather seal having opposing faces, a first side extending
8167545 Self-balancing face seals and gas turbine engine systems involving such seals May 1, 2012
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
8161728 Gas turbines with multiple gas flow paths April 24, 2012
A representative gas turbine includes: a high pressure spool; a high pressure compressor; a high pressure turbine mechanically coupled to the high pressure spool; a lower pressure spool; a lower pressure turbine mechanically coupled to the lower pressure spool; a fan having a first s
8140242 Systems and methods involving multiplexed engine control signals March 20, 2012
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
8128349 Gas turbine engines and related systems involving blade outer air seals March 6, 2012
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 g
8122700 Premix nozzles and gas turbine engine systems involving such nozzles February 28, 2012
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
8109717 Gas turbine engine systems involving hydrostatic face seals with integrated back-up seals February 7, 2012
Gas turbine engine systems involving hydrostatic face seals with back-up seals are provided. In this regard, a representative seal assembly for a gas turbine engine includes: a hydrostatic seal having a seal face and a seal runner; and a back-up seal; wherein, in a normal mode of operati
8109716 Gas turbine engine systems involving hydrostatic face seals with anti-fouling provisioning February 7, 2012
Gas turbine engine systems involving hydrostatic face seals with anti-fouling provisioning are provided. In this regard, a representative turbine assembly for a gas turbine engine comprises: a turbine having a hydrostatic seal; the hydrostatic seal having a seal face, a seal runner,
8105651 Artifacts, methods of creating such artifacts and methods of using such artifacts January 31, 2012
Artifacts, methods of creating such artifacts and methods of using such artifacts are provided. In this regard, an exemplary embodiment of a method for creating an artifact for quantifying measurement accuracy of non-contact sensors included in optical three-dimensional (3-D) measuring
8105039 Airfoil tip shroud damper January 31, 2012
A turbine disk includes a rotor and a plurality of turbine blades, each comprising a root at a proximal end secured to the rotor and a tip having a shroud at a distal end. The shroud includes a inner diameter surface, an outer diameter surface and a segmented sidewall surface separating
8105021 Gas turbine engine systems involving hydrostatic face seals with integrated back-up seals January 31, 2012
Gas turbine engine systems involving hydrostatic face seals with integrated back-up seals are provided. In this regard, a representative seal assembly for a gas turbine engine includes: a stator assembly and a rotor assembly configured to operatively engage each other to form a first
8104953 Systems and methods for determining heat transfer characteristics January 31, 2012
Systems and methods for determining heat transfer characteristics are provided. In this regard, a representative system for determining heat transfer characteristics includes: a stereolithographic model of a component, the model having a surface; and a test article mounted to the sur
8104289 Systems and methods involving multiple torque paths for gas turbine engines January 31, 2012
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
8100633 Cooling air manifold splash plates and gas turbines engine systems involving such splash plates January 24, 2012
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 po
8089028 Methods for repairing gas turbine engine knife edge seals January 3, 2012
Methods for repairing a gas turbine engine knife edge seals are provided. A representative method includes: providing a knife edge of a gas turbine component, the component comprising IN-100, the knife edge being degraded; directing a laser beam toward the knife edge; and dispensing
8083511 Systems and methods involving pattern molds December 27, 2011
System and methods involving pattern molds are provided. In this regard, a representative system includes a mold assembly unit having a movable fixture holder operative to engage a portion of a pattern mold and position the pattern mold for assembly.
8061978 Systems and methods involving abradable air seals November 22, 2011
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.
8058591 Systems and methods for providing localized heat treatment of gas turbine components November 15, 2011
Systems and methods for providing localized heat treatment of gas turbine components are provided. In this regard, an exemplary method includes: identifying an area of a gas turbine component to which localized heat treatment is to be performed; positioning a resistance heating element,
8051663 Gas turbine engine systems involving cooling of combustion section liners November 8, 2011
Gas turbine engine systems involving cooling of combustion section liners are provided. In this regard, a representative liner includes: an outer side, an inner side, an upstream end and a downstream end, the outer side being configured to face away from a combustion reaction, the inner
8051662 Transition duct assemblies and gas turbine engine systems involving such assemblies November 8, 2011
Transition duct assemblies and gas turbine engine systems involving such assemblies are provided. In this regard, a representative a transition duct assembly for a gas turbine engine includes: an impingement sheet having cooling holes formed therethrough, an inlet end and a non-flanged
8029234 Systems and methods involving aerodynamic struts October 4, 2011
Systems and methods involving struts are provided. In this regard, a representative system includes a gas turbine engine defining a gas flow path. The gas turbine engine comprises a strut extending into the gas flow path. The strut has an interior operative to receive pressurized air
8020295 Methods for dimensionally restoring a fastener for a gas turbine engine September 20, 2011
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
8016546 Systems and methods for providing vane platform cooling September 13, 2011
Systems and methods for cooling vane platforms are provided. In this regard, a representative method for cooling a vane platform includes: providing a cooling channel on a platform from which a vane airfoil extends, the cooling channel being defined by a cooling surface and a channel
8005581 Systems and methods for communicating aircraft data August 23, 2011
Systems and methods for communicating aircraft data are provided. In this regard, a representative system includes a data reduction system operative to: receive aircraft data; store a first set of the aircraft data; analyze a next set of the aircraft data; and store the next set of t
7984607 Gas turbine engine systems and related methods involving vane-blade count ratios greater than un July 26, 2011
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 fi
7931436 Roller bearings, and struts and gas turbine engines having such bearings April 26, 2011
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
7888647 X-ray detector assemblies and related computed tomography systems February 15, 2011
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
7886875 Systems and methods for monitoring gas turbine engines February 15, 2011
Systems and methods for monitoring gas turbine engines are provided. In this regard, a representative method includes: monitoring lubrication oil at multiple locations of the gas turbine engine to detect a presence of debris in the oil; determining a characteristic of the debris in the o
7876875 Computed tomography systems and related methods involving multi-target inspection January 25, 2011
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, indepe
7869026 Targeted artifacts and methods for evaluating 3-D coordinate system measurement accuracy of opti January 11, 2011
A method for evaluating three-dimensional (3-D) coordinate system measurement accuracy of an optical 3-D measuring system using targeted artifacts is provided. In this regard, an exemplary embodiment of a method for evaluating 3-D coordinate system measurement accuracy using targeted
7853441 Systems and methods involving engine models December 14, 2010
Systems and methods involving engine models are provided. A representative method for updating a gas turbine engine reference model includes: determining whether an absolute difference between a dominant time constant of a sensor and an assumed sensor model time constant is outside a
7825721 Systems and methods for filtering signals corresponding to sensed parameters November 2, 2010
Systems and methods for filtering analog signals corresponding to sensed parameters are provided. In this regard, a representative method includes: sampling the analog signal to acquire a sequential series of data points; determining a first cumulative change in value with respect to
7762509 Gas turbine engine systems involving rotatable annular supports July 27, 2010
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 annul
7639777 Computed tomography systems and related methods involving forward collimation December 29, 2009
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
7565996 Transient liquid phase bonding using sandwich interlayers July 28, 2009
Systems and methods for transient liquid phase bonding are described herein. Embodiments of these systems and methods utilize sandwich interlayers to produce stronger, more homogeneous bonds than currently possible. These sandwich interlayers have a middle bonding layer sandwiched be
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