UNITED TECHNOLOGIES CORP. Patent applications |
Patent application number | Title | Published |
20100307165 | Gas Turbine Engine Systems Involving I-Beam Struts - Gas turbine engine systems involving I-beam struts are provided. In this regard, a representative strut assembly for a gas turbine engine includes a first I-beam strut having first and second flanges spaced from each other and interconnected by a web, the first strut exhibiting a twist along a length of the web. | 12-09-2010 |
20100199677 | Transition Duct Assemblies and Gas Turbine Engine Systems Involving Such Assemblies - 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 outlet end, the impingement sheet being operative to be positioned about an exterior of a transition duct such that cooling air is directed to flow about the transition duct; the non-flanged outlet end of the impingement sheet being operative to attach the impingement sheet to the transition duct such that the inlet end is positioned adjacent to an intake end of the transition duct and the outlet end is positioned adjacent to an exhaust end of the transition duct. | 08-12-2010 |
20100166543 | Inlet Guide Vanes and Gas Turbine Engine Systems Involving Such Vanes - Inlet guide vanes and gas turbine engine systems involving such vanes are provided. In this regard, a representative an inlet guide vane for a gas turbine engine includes: a fixed strut; and a variable flap located downstream of the fixed strut and being movable with respect thereto; the fixed strut having a leading edge, a trailing edge and side surfaces extending between the leading edge and the trailing edge, the side surfaces being asymmetric with respect to each other. | 07-01-2010 |
20100128752 | Systems and Methods for Determining Heat Transfer Characteristics - 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 surface such that an extension of the test article protrudes from and is thermally insulated from the surface of the model. | 05-27-2010 |
20100106462 | Systems and Methods for Diagnosing Gas Turbine Engine Faults - Systems and methods for diagnosing gas turbine engine faults are provided. In this regard, a representative method includes: dynamically assessing detected symptoms based, at least in part, on failure rates of components of the gas turbine engine as functions of usage of the components such that suspected faults are identified. | 04-29-2010 |
20100101208 | Systems and Methods Involving Reduced Thermo-Acoustic Coupling of Gas Turbine Engine Augmentors - Systems and methods reducing thermo-acoustic coupling of a gas turbine engine augmentors are provided. In this regard, a representative method includes: determining acoustic resonances and heat release phase relationships associated with the augmentor; and determining relative axial positions of a fuel injector and a flame holder of the augmentor that result in reduced thermo-acoustic coupling of the augmentor during operation. | 04-29-2010 |
20100097132 | Systems and Methods for Filtering Signals Corresponding to Sensed Parameters - 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 a first of the data points relative to at least two subsequent data points in the series, the subsequent data points including a second of the data points; determining a second cumulative change in value with respect to the second of the data points relative to at least two data points adjacent to the second of the data points in the series, the at least two adjacent data points including an immediately preceding and an immediately succeeding one of the data points relative to the second of the data points; comparing the first cumulative change and the second cumulative change to respective data thresholds; and outputting a filtered analog signal based, at least in part, on results of the comparing. | 04-22-2010 |
20100050646 | Systems and Methods Involving Improved Fuel Atomization in Air-Blast Fuel Nozzles of Gas Turbine Engines - Systems and methods involving improved fuel atomization in air-blast fuel nozzles of gas turbine engines are provided. In this regard, a representative method includes: providing fuel to a chamber defined by an inner surface; and continuously atomizing a portion of the fuel via interaction of the fuel with the inner surface. | 03-04-2010 |
20100050643 | Gas Turbine Engine Systems and Methods Involving Enhanced Fuel Dispersion - Gas turbine engine systems and methods involving enhanced fuel dispersion are provided. In this regard, a representative method for operating a gas turbine engine includes: providing a gas path through the engine; introducing a spray of fuel along the gas path downstream of a turbine of the engine; and impinging the spray of fuel with a relatively higher velocity flow of air such that atomization of the fuel is increased. | 03-04-2010 |
20100050434 | Gas Turbine Airfoil Assemblies and Methods of Repair - Gas turbine airfoil assemblies and methods of repair are provided. In this regard, a representative method includes: separating the airfoil from the platform; forming a depression in the platform, the depression being sized and shaped to receive a replacement airfoil; and affixing the replacement airfoil within the depression such that the replacement airfoil is attached to the platform. | 03-04-2010 |
20100050408 | Preforms and Related Methods for Repairing Abradable Seals of Gas Turbine Engines - Methods for repairing abradable seals of gas turbine engines include providing an abradable seal component of a gas turbine engine, the seal component having a structural substrate; providing a first preform to restore the structural substrate; and providing a second preform to form an abradable layer of the component. Preforms include a multilayer stack having a first layer and a second layer. | 03-04-2010 |
20100042289 | Systems and Methods for Communicating Aircraft Data - 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 the aircraft data if the next set of aircraft data differs from the first set of the aircraft data. | 02-18-2010 |
20100040479 | Gas Turbine Engine Systems Involving Baffle Assemblies - 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 that a cooling air path of reduced cross-section is formed between the baffle and the surfaces, the baffle being operative to increase a flow rate of cooling air as the cooling air directed to the cooling air path is redirected through the cooling air path of reduced cross-section. | 02-18-2010 |
20100040478 | Cooled Airfoils and Gas Turbine Engine Systems Involving Such Airfoils - Cooled airfoils and gas turbine engine systems involving such airfoils are provided. In this regard, a representative cooled airfoil includes: an exterior surface defining a leading edge, a trailing edge, a suction side and a pressure side; an interior surface defining an interior cavity; trenches in the exterior surface oriented spanwise along the leading edge; and cooling holes communicating between the interior cavity and the trenches such that cooling air provided to the interior cavity flows from the interior cavity though the cooling holes into the trenches, the cooling holes having exterior apertures located in the trenches and interior apertures located at the interior surface. | 02-18-2010 |
20100040460 | Platforms with Curved Side Edges and Gas Turbine Engine Systems Involving Such Platforms - 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 side edge extending between the leading edge and the trailing edge and exhibiting a first curve along a length thereof, and a second side edge extending between the leading edge and the trailing edge and exhibiting a second curve along a length thereof; and an airfoil extending from the gas path side of the platform; the platform and the airfoil exhibiting a unitary construction such that a continuous exterior surface blends from the airfoil to the platform. | 02-18-2010 |
20100032415 | Repair Methods Involving Conductive Heat Resistance Welding - Repair methods involving conductive heat resistance welding includes repairing a crack of a gas turbine engine component using a conductive heat resistance welding technique and a welding technique other than conductive heat resistance welding. | 02-11-2010 |
20100031627 | Heater Assemblies, Gas Turbine Engine Systems Involving Such Heater Assemblies and Methods for Manufacturing Such Heater Assemblies - Heater assemblies, gas turbine engine systems involving such heater assemblies and methods for manufacturing such heater assemblies are provided. In this regard, a representative method includes: providing a substrate; forming a heating element using a thermal sprayed metal process such that the metal heater comprises an aggregation of sprayed metal particles; attaching the heating element to the substrate; and consolidating at least some of the metal particles located at an exterior of the heating element to form an electrical contact pad of the heating element. | 02-11-2010 |
20100025158 | Gas Turbine Engine Systems and Methods Involving Oil Flow Management - Gas turbine engines systems and methods involving oil flow management are provided. In this regard, a oil pressure analysis system for a gas turbine engine is operative to: receive information corresponding to measured oil pressure and rotational speed during a start up of the engine; correlate the information into data sets, each of the data sets containing a measured oil pressure and a corresponding rotational speed; and determine whether the oil flow valve is functioning properly based on the information contained in the data sets. | 02-04-2010 |
20090324852 | Systems and methods for forming components with thermal barrier coatings - Systems and methods for forming components with thermal barrier coatings are provided. In this regard, a representative method includes: providing a component having a first side and an opposing second side; and using a preformed mask to obstruct vapors from being deposited on the second side of the component while moving the component relative to the vapors such that the vapors form a thermal barrier coating on the first side of the component. | 12-31-2009 |
20090301055 | Gas Turbine Engine Systems and Methods Involving Vibration Monitoring - 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. | 12-10-2009 |
20090292437 | Systems and Methods Involving Multiplexed Engine Control Signals - 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. | 11-26-2009 |
20090281774 | Systems and Methods Involving Surface Fitting - 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. | 11-12-2009 |
20090274264 | Computed Tomography Systems and Related Methods Involving Localized Bias - 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. | 11-05-2009 |
20090272908 | X-Ray Detector Assemblies and Related Computed Tomography Systems - 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. | 11-05-2009 |
20090272123 | Gas Turbine Engine Systems and Related Methods Involving Thermally Isolated Retention - 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. | 11-05-2009 |
20090269184 | Gas Turbine Engine Systems Involving Turbine Blade Platforms with Cooling Holes - 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. | 10-29-2009 |
20090266079 | Premix Nozzles and Gas Turbine Engine Systems Involving Such Nozzles - 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. | 10-29-2009 |
20090257552 | Computed Tomography Systems and Related Methods Involving Multi-Target Inspection - 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. | 10-15-2009 |
20090243228 | Gas Turbine Engine Seals and Engines Incorporating Such Seals - 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. | 10-01-2009 |
20090243176 | Systems and Methods for Positioning Fairing Sheaths of Gas Turbine Engines - 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. | 10-01-2009 |
20090241550 | Gas Turbine Engine Systems Involving Variable Nozzles with Flexible Panels - 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. | 10-01-2009 |
20090238686 | Gas Turbine Engine Systems Involving Fairings with Locating Data - 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. | 09-24-2009 |
20090232637 | Cooling Air Manifold Splash Plates and Gas Turbines Engine Systems Involving Such Splash Plates - 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. | 09-17-2009 |
20090214147 | Hydrodynamic Tapered Roller Bearings and Gas Turbine Engine Systems Involving Such Bearings - 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. | 08-27-2009 |
20090213994 | Computed Tomography Systems and Related Methods Involving Forward Collimation - 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. | 08-27-2009 |
20090213984 | Computed Tomography Systems and Related Methods Involving Post-Target Collimation - 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. | 08-27-2009 |
20090212501 | Self-Balancing Face Seals and Gas Turbine Engine Systems Involving Such Seals - 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. | 08-27-2009 |
20090208322 | Gas turbine engine systems and methods involving blade outer air seals - 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. | 08-20-2009 |
20090205800 | Systems and Methods for Reducing the Potential for Riser Backfilling During Investment Casting - Systems and methods for reducing the potential for riser backfilling during investment casting are provided. In this regard, a representative method for performing investment casting includes: providing a mold having an opening communicating with an interior, the interior having a part cavity and a riser; providing an insert; and using the insert to form a physical barrier to reduce a potential for molten metal to backfill into the riser while the molten metal is introduced into the interior of the mold via the opening. | 08-20-2009 |
20090188334 | Accessory Gearboxes and Related Gas Turbine Engine Systems - Accessory gearboxes and related gas turbine engine systems are provided. In this regard, a representative accessory gearbox for a gas turbine engine is operative to be driven by rotational energy extracted from the gas turbine engine and imparted to the gearbox by multiple tower shafts. | 07-30-2009 |
20090185911 | Systems and Methods Involving Localized Stiffening of Blades - 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 localized increase in stiffness of the blade. | 07-23-2009 |
20090163390 | Artifacts, Methods of Creating Such Artifacts and Methods of using Such Artifacts - 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 systems, comprises: fabricating an artifact using a base material; and coating the artifact with an approximately uniform coating of dry film lubricant. | 06-25-2009 |
20090162189 | Systems and Methods Involving Variable Throat Area Vanes - 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 communicating between the interior and pressure surface portion, the first port being operative to receive the pressurized air from the interior and emit the pressurized air, wherein the emitted pressurized air displaces the gas flow path such that a throat area defined, at least in part, by the vane is modified. | 06-25-2009 |
20090161122 | Targeted Artifacts and Methods for Evaluating 3-D Coordinate System Measurement Accuracy of Optical 3-D Measuring Systems using Such Targeted Artifacts - 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 artifacts comprises: taking a series of measurements from different positions and orientations using target dots on a targeted artifact with an optical 3-D measuring system; and calculating measurement errors using the series of measurements. An exemplary embodiment of a targeted artifact used with the method includes a base and target dots located on the base. | 06-25-2009 |
20090148295 | Gas Turbine Engine Systems Involving Rotor Bayonet Coverplates and Tools for Installing Such Coverplates - Gas turbine engine systems involving rotor bayonet coverplates and tools for installing such coverplates are provided. In this regard, a representative turbine assembly for a gas turbine engine includes: a turbine disk operative to mount a set of turbine blades; and a coverplate having an annular main body portion and a spaced annular arrangement of tabs extending radially inwardly from the main body portion with open-ended gaps being located between the tabs, the tabs being operative to secure an inner diameter of the coverplate to the turbine disk. | 06-11-2009 |
20090148277 | Gas Turbine Engines and Related Systems Involving Blade Outer Air Seals - 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 being positioned in an end-to-end orientation such that each adjacent pair of the segments forms an intersegment gap therebetween, each intersegment gap being defined, at least partially, by a first recess and a first protrusion, the first protrusion being sized and shaped to be received by the first recess, one of the first recess and the first protrusion being located on an end of a first segment of an adjacent pair of the segments, another of the first recess and the first protrusion being located on an end of a second segment of the adjacent pair of the segments. | 06-11-2009 |
20090148269 | Gas Turbine Engines and Related Systems Involving Air-Cooled Vanes - Gas turbine engines and related systems involving air-cooled vanes are provided. In this regard, a representative vane for a gas turbine engine includes: an airfoil having a leading edge, a pressure surface, a trailing edge and a suction surface; and a cooling air channel; the suction surface being formed by an exterior surface of a first wall portion and an exterior surface of a second wall portion, the first wall portion spanning a length of the suction surface between the second wall portion and the trailing edge; the cooling air channel being defined, at least in part, by an interior surface of the first wall portion, the first wall portion exhibiting a thickness that is thinner than a thickness exhibited by the second wall portion. | 06-11-2009 |
20090146341 | Systems and Methods Involving Pattern Molds - 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. | 06-11-2009 |
20090145102 | Gas Turbine Engine Systems Involving Tip Fans - Gas turbine engine systems involving tip fans are provided. In this regard, a representative gas turbine engine system includes: a multi-stage fan having a first rotatable set of blades and a second counter-rotatable set of blades, the first rotatable set of blades defining an inner fan and a tip fan; and an epicyclic differential gear assembly operative to receive a torque input and differentially apply the torque input to the first set of blades and the second set of blades. | 06-11-2009 |
20090142182 | Gas Turbine Engines and Related Systems Involving Offset Turbine Frame Struts - Gas turbine engines and related systems involving offset hub struts are provided. In this regard, a representative bearing assembly for a gas turbine engine includes: a bearing operative to support a rotatable shaft; an annular hub positioned about the bearing; and an annular array of struts extending radially outwardly from the hub, at least two of the struts being positioned in different planes, the planes being oriented transversely with respect to the rotatable shaft. The method of assembling the struts by mounting first and second pluralities of struts, each plurality in a common plane, between the hub and the turbine exhaust case, with the second plurality of struts longitudinally offset from the first plurality of struts. | 06-04-2009 |
20090142181 | Gas Turbine Engine Systems Involving Mechanically Alterable Vane Throat Areas - Gas turbine engine systems involving mechanically alterable vane throat areas are provided. In this regard, a representative vane for a gas turbine engine includes: a leading edge; a trailing edge; a suction side surface extending between the leading edge and the trailing edge; a cavity having an aperture located in the suction side surface; and a barrel located within the cavity and being moveable therein such that movement of the barrel alters an extent to which the barrel protrudes through the aperture. | 06-04-2009 |
20090120101 | Organic Matrix Composite Components, Systems Using Such Components, and Methods for Manufacturing Such Components - Organic matrix composite components, systems using such components, and methods for manufacturing such components are provided. In this regard, a representative organic matrix composite component includes: an organic matrix composite; a layer of aluminum applied to the organic matrix composite; and a wear resistant coating applied to the aluminum layer. | 05-14-2009 |
20090120096 | Gas Turbine Engine Systems Involving Cooling of Combustion Section Liners - 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 side being configured to face the combustion reaction; a cooling air channel, at least a portion of the cooling air channel being located in a vicinity of the downstream end; and cooling holes formed through the inner side of the liner, the cooling holes being in fluid communication with the cooling air channel such that cooling air provided to the cooling air channel is directed through the cooling holes and to the inner side of the liner such that at least a portion of the inner side of the liner receives cooling air despite a corresponding portion located on the outer side of the liner being obstructed from directly receiving cooling air. | 05-14-2009 |
20090110546 | Feather Seals and Gas Turbine Engine Systems Involving Such Seals - Feather seals and gas turbine engine systems involving such seals are provided. In this regard, a representative feather seal for a gas turbine engine includes: an elongate body portion; and a locating tab extending longitudinally along the body portion and extending outwardly therefrom. | 04-30-2009 |
20090110541 | Vibration Management for Gas Turbine Engines - 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. | 04-30-2009 |
20090110537 | Gas Turbine Engine Systems Involving Integrated Fluid Conduits - 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. | 04-30-2009 |
20090107237 | Shaft Trim Balancing Devices, Related Systems and Methods - Shaft trim balancing devices, related systems and methods are provided. In this regard, an representative device for trim balancing a rotatable shaft includes: an intermediate section being annularly shaped and having terminating ends spaced from each other in an uncompressed state of the device; and first and second sets of counterweights extending longitudinally from opposing sides of the intermediate section. | 04-30-2009 |
20090107106 | Gas Turbine Engine Systems Involving Hydrostatic Face Seals - Gas turbine engine systems involving hydrostatic face seals are provided. In this regard, representative compressor assembly for a gas turbine engine includes a compressor having a hydrostatic seal formed by a seal face and a seal runner. | 04-30-2009 |
20090106130 | Systems and Methods Involving Rotable Components - 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. | 04-23-2009 |
20090104025 | Gas Turbine Engines and Related Systems Involving Blade Outer Air Seals - 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. | 04-23-2009 |
20090104022 | Gas Turbine Engine Systems Involving Gear-Driven Variable Vanes - 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. | 04-23-2009 |
20090104003 | Gas Turbine Engines Systems and Related Methods Involving Dimensionally Restored Fasteners - 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. | 04-23-2009 |
20090101787 | Gas Turbine Engine Systems Involving Rotatable Annular Supports - 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. | 04-23-2009 |
20090100918 | Systems and Methods for Testing Gas Turbine Engines - 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. | 04-23-2009 |
20090097972 | Gas Turbine Engine Systems and Related Methods Involving Heat Exchange - 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. | 04-16-2009 |
20090097970 | Systems and Methods Involving Abradable Air Seals - 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. | 04-16-2009 |
20090097966 | Gas Turbine Engines and Related Systems Involving Variable Vanes - 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. | 04-16-2009 |
20090096230 | Vacuum Pressure Systems - 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. | 04-16-2009 |
20090092487 | Systems and Methods Involving Multiple Torque Paths for Gas Turbine Engines - 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. | 04-09-2009 |
20090092482 | Systems and Methods for Altering Inlet Airflow of Gas Turbine Engines - 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. | 04-09-2009 |
20090084170 | Systems and Methods for Performing Cooling Airflow Analysis of Gas Turbine Engine Components - 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. | 04-02-2009 |
20090071002 | Methods for Repairing Gas Turbine Engine Components - 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. | 03-19-2009 |
20090068003 | Gas Turbine Engine Systems and Related Methods Involving Vane-Blade Count Ratios Greater than Unity - 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. | 03-12-2009 |
20090067985 | Roller Bearings, and Struts and Gas Turbine Engines Having such Bearings - 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. | 03-12-2009 |
20090065494 | Systems and methods for providing localized heat treatment of gas turbine components - 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, sized and shaped to transfer heat to the area, adjacent the area; electrically coupling a current-limiting power controller to the resistance heating element; and locally heating the area using the resistance heating element, with power being provided to the resistance heating element via the current-limiting power controller. | 03-12-2009 |
20090064773 | Systems and Methods for Determining Airflow Parameters of Gas Turbine Engine Components - 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. | 03-12-2009 |
20090064684 | Systems Involving Inlet-Mounted Engine Controls - 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. | 03-12-2009 |
20090064479 | Methods for Performing Gas Turbine Engine Casing Repairs and Repaired Cases - 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. | 03-12-2009 |
20090056309 | Gas Turbine Engine Systems and Related Methods Involving Multiple Gas Turbine Cores - Gas turbine engine systems and related methods involving multiple gas turbine cores are provided. In this regard, a representative gas turbine engine includes: an inlet; a blade assembly mounted to receive intake air via the inlet; and multiple gas turbine cores located downstream of the blade assembly, each of the multiple gas turbine cores being independently operative in a first state, in which rotational energy is provided to rotate the blade assembly, and a second state, in which rotational energy is not provided to rotate the blade assembly. | 03-05-2009 |
20090055145 | Systems and Methods Involving Engine Models - 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 tolerance value; and responsive to determining that the absolute difference is outside the tolerance value, updating the assumed sensor model time constant with the dominant time constant of the sensor. | 02-26-2009 |
20090051120 | Gas Turbine Engine Systems Involving Hydrostatic Face Seals - Gas turbine engine systems involving hydrostatic face seals are provided. In this regard, representative turbine assembly for a gas turbine engine includes a turbine having a hydrostatic seal formed by a seal face and a seal runner. | 02-26-2009 |
20090051119 | Gas Turbine Engine Systems Involving Hydrostatic Face Seals with Integrated Back-up Seals - 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 seal and a second seal; the first seal being provided by a hydrostatic seal having a seal face and a seal runner; and the second seal being provided by a back-up seal such that responsive to a failure of the first seal, the back-up seal maintains at least a portion of a pressure differential established by the first seal prior to the failure. | 02-26-2009 |
20090047124 | Gas Turbine Engine Systems Involving Hydrostatic Face Seals with Anti-Fouling Provisioning - 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, a carrier, and a biasing member; the seal face and the seal runner defining a high-pressure side and a lower-pressure side of the seal; the carrier being operative to position the seal face relative to the seal runner; and the biasing member being located on the lower-pressure side of the seal and being operative to bias the carrier such that interaction of the biasing member and gas pressure across the seal causes the carrier to position the seal face relative to the seal runner. | 02-19-2009 |
20090047123 | Gas Turbine Engine Systems Involving Hydrostatic Face Seals with Integrated Back-Up Seals - 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 operation of the hydrostatic seal, interaction of the seal face and the seal runner maintains a pressure differential within the gas turbine engine and, in a failure mode of operation of the hydrostatic seal, the back-up seal maintains a pressure differential within the gas turbine engine. | 02-19-2009 |
20090035477 | Masks and Related Methods for Repairing Gas Turbine Engine Components - Masks and related methods for repairing a gas turbine engine components are provided. A representative method includes using a self-coiling strip of material as a mask during application of a coating to a surface of the component. | 02-05-2009 |
20090030563 | Systems And Methods For Providing Localized Heat Treatment Of Metal Components - Systems and methods for defining information provided by aircraft are provided. An exemplary method, involving an aircraft that is operative to provide information in a first report format, includes: communicating information corresponding to a second report format definition to the aircraft, wherein the information corresponding to the second report format definition is received at the aircraft via wireless communication; and receiving, from the aircraft, information complying with the second report format definition. | 01-29-2009 |
20090028698 | Systems and Methods Involving Aerodynamic Struts - 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, an outer surface, and ports communicating between the outer surface and the interior of the strut, the ports are operative to receive the pressurized air from the interior and emit the pressurized air into the gas flow path such that an effective aerodynamic length of the strut along the gas flow path is increased. | 01-29-2009 |
20090028692 | Systems and Methods for Providing Vane Platform Cooling - 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 cover, the channel wall being spaced from the cooling surface and located such that the cooling surface is positioned between a gas flow path of the vane and the channel cover; and directing a flow of cooling air through the cooling channel such that heat is extracted from the cooling surface of the platform by the flow of cooling air. | 01-29-2009 |
20090026183 | Methods for Repairing Gas Turbine Engine Knife Edge Seals - 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 IN-100 powder such that the IN-100 powder is melted by the laser beam and is deposited on the knife edge. | 01-29-2009 |
20090026174 | Methods for Performing Manual Laser Deposition - Methods for performing manual laser deposition are provided. In this regard, a representative method includes: directing a laser beam at a first deposit location of a substrate to re-melt: at least a portion of a first deposit of weld filler, at least a portion of a second deposit of weld filler located at a second deposit location that partially overlaps the first deposit, and at least a portion of the substrate. | 01-29-2009 |
20090020523 | Systems and Methods for Providing Localized Heat Treatment of Metal Components - Systems and methods for providing localized heat treatment of metal components are provided. In this regard, a representative method includes: identifying a portion of a metal component to which localized heat treatment is to be performed; shielding an area in a vicinity of the portion of the metal component; and directing electromagnetic energy in the infrared (IR) spectrum toward the portion of the metal component such that the portion is heated to a desired temperature and such that the area in the vicinity of the portion that is subjected to shielding does not heat to the temperature desired for the heat treatment. | 01-22-2009 |
20090016873 | Gas Turbine Systems Involving Feather Seals - 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 between the faces, and a first tab, the first tab extending outwardly beyond the first side; the first slot being sized and shaped to receive the feather seal including the first tab. | 01-15-2009 |
20090016871 | Systems and Methods Involving Variable Vanes - Systems and methods involving vanes are provided. In this regard, a representative method for modifying the throat area between vanes of a gas turbine engine includes: directing a gas flow path of the gas turbine engine between a first vane and a second vane, wherein each of the first vane and the second vane has an outer surface and an interior; and emitting pressurized air from outlet ports communicating between the outer surface and the interior of the first vane, wherein the emitted pressurized air from the first vane modifies a throat area between the first vane and the second vane. | 01-15-2009 |
20090014245 | Systems and Methods for Monitoring Gas Turbine Engines - 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 oil; and correlating the characteristic of the debris with the location of detection to determine, while the gas turbine engine is operating, whether the engine is operating within predetermined limits. | 01-15-2009 |
20090013695 | Floatwell Panel Assemblies and Related Systems - Floatwall panel assemblies and related systems are provided. A floatwall panel assembly includes a panel formed of porous ceramic material, the porous ceramic material exhibiting a porosity gradient along at least one of a length, a width and a depth of the panel, the panel lacking a substrate, formed of a material other than porous ceramic material, for supporting the porous ceramic material. | 01-15-2009 |
20090000271 | Gas Turbines with Multiple Gas Flow Paths - Gas turbines with multiple gas flow paths are provided. In this regard, a representative gas turbine includes: a spool; a compressor; a turbine mechanically coupled to the spool; the compressor having a first set of blades and a second set of blades, the second set of blades being located downstream of the first set of blades, the first set of blades and the second set of blades being driven by the spool; and means for enabling the first set of blades to rotate at a lower rotational speed than the second set of blades. | 01-01-2009 |
20090000270 | Gas Turbines with Multiple Gas Flow Paths - 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 set of fan blades and a second set of fan blades, the second set of fan blades being located downstream of the first set of fan blades and being operative to rotate at a rotational speed corresponding to a rotational speed of the lower pressure spool; and a gear assembly mechanically coupled to the lower pressure spool and engaging the first set of fan blades such that rotation of the lower pressure spool rotates the first set of fan blades at a lower rotational speed than the rotational speed of the second set of fan blades. | 01-01-2009 |
20090000265 | Gas Turbines with Multiple Gas Flow Paths - An representative gas turbine includes: a first annular gas flow path; a second annular gas flow path located radially outwardly from the first gas flow path; in series order, a multi-stage fan, radially inboard portions of a first set of high pressure compressor blades, a second set of high pressure compressor blades, a combustion section and a high pressure turbine, positioned along the first gas flow path; and in series order, the multi-stage fan and radially outboard portions of the first set of high pressure compressor blades, positioned along the second gas flow path such that the inboard portions of the first set of high pressure compressor blades, the second set of high pressure compressor blades, the combustion section and the high pressure turbine are not positioned along the second gas flow path. | 01-01-2009 |
20090000101 | Methods for Repairing Gas Turbine Engines - Methods for repairing gas turbines are provided. A representative method includes: identifying an affected area of a surface of a component of the gas turbine, the surface of the component defining a portion of a gas flow path through the gas turbine; applying an epoxy-based filler to the affected area; curing the epoxy-based filler; and blending the epoxy-based filler with the surface of the component. | 01-01-2009 |