Patent application number | Description | Published |
20130071878 | TWO HELIX BINDERS - Provided herein are isolated polypeptides derived from the staphylococcal protein A protein B domain comprising a pair of anti-parallel alpha helices that are capable of binding a target. Also provided are nucleic acid sequences encoding such two helix binders, vectors containing the nucleic acid sequences encoding for two helix binders, and host cells transformed with vectors containing the nucleic acid sequences encoding for the two-helix binders. Also provided are methods of using the two helix binders. | 03-21-2013 |
20130205589 | System and Method For Modifying A Rotor - A system for modifying a slot in a rotor includes a drill, a clamp connected to the drill and configured to engage with an interior surface of the slot, and means for supporting the drill from a stationary platform adjacent to the rotor. A method for modifying a slot in a rotor includes connecting a coupling to a stationary platform adjacent to the rotor, connecting a drill to the coupling, and locating the drill proximate to the slot. The method further includes inserting a clamp into the slot, engaging the clamp with an interior surface of the slot, and operating the drill to create a cavity in the slot. | 08-15-2013 |
20130206363 | FLEXIBLE METALLIC HEAT CONNECTOR - A thermal connector configured to be placed within a recess of a heat sink between the heat sink and a heat generating component and transfer heat from the component to the heat sink, including a heat spreader configured to fit within the recess of the heat sink, a spring configured to sit between the heat spreader and with the heat sink and bias the heat spreader towards and away from the heat sink, a flexible membrane attached to the heat sink and the heat spreader and seal off the recess, and a phase change material that fills the recess, wherein the flexible membrane contains the phase change material and allows it to contract or expand in response to the movement of the heat spreader towards or away from the heat sink. | 08-15-2013 |
20130206373 | SYNTHETIC JET EMBEDDED HEAT SINK - A system and method for cooling heat-producing devices using synthetic jet embedded heat sinks is disclosed. The cooling system includes a heat sink comprising a base portion and a plurality of fins disposed on the base portion and extending vertically out therefrom, the plurality of fins spaced to define a channel between adjacent fins. The cooling system also includes at least one synthetic jet actuator attached to the heat sink, with each of the at least one synthetic jet actuators comprising a plurality of orifices therein and being configured to generate and project a series of fluid vortices out from the plurality of orifices and toward at least a portion of the channels of the heat sink. | 08-15-2013 |
20130207763 | COOLING DEVICE FOR ELECTRICAL DEVICE AND METHOD OF COOLING AN ELECTRICAL DEVICE - A cooling device for an electrical apparatus having an air gap. The cooling device includes a heat transfer element coupled to the core. The heat transfer element includes a first material to facilitate transferring heat out of the core. The cooling device further includes an electrical insulator coupled to the heat transfer element. The insulator includes a second material to facilitate flow of magnetic flux across the air gap. | 08-15-2013 |
20130210140 | CELL CARRIERS AND METHODS FOR CULTURING CELLS - A carrier for growing stem cells is provided, the carrier comprises a substrate comprising one or more outer surfaces; and a hydrophilic, water soluble coating material disposed and dried on one or more of the outer surfaces. The carrier comprises one or more structured indentations on one or more of the outer surfaces, wherein the carrier has a length at least about 0.2 mm, a width at least about 0.2 mm, and a height in a range from about 0.05 mm to 1.2 mm and each of the structured indentations has a major axis in a range from about 0.1 mm to 0.5 mm, a minor axis in a range from about 0.1 mm to 0.5 mm and a depth in a range from about 0.025 mm to about 0.5 mm. A method of culturing stem cells and stromal cells using the same carrier are also provided. | 08-15-2013 |
20130211550 | Methods and Apparatuses for Advanced Multiple Variable Control with High Dimension Multiple Constraints - A method and apparatus for multiple variable control of a physical plant with high dimension multiple constraints, includes: mathematically decoupling primary controlled outputs of a controlled physical plant from one another and shaping the pseudo inputs/controlled outputs desired plant dynamics; tracking primary control references and providing pseudo inputs generated by desired primary output tracking for selection; mathematically decoupling constraints from one another; mathematically decoupling constraints from non-traded off primary controlled outputs of the controlled physical plant; shaping the pseudo inputs/constraint outputs desired plant dynamics; tracking constraint control limits; providing pseudo inputs generated by desired constraint output tracking for selection; selecting the most limiting constraints and providing the smooth pseudo inputs for the decoupled primary control; and controlling the physical plant using the decoupled non-traded off primary controlled outputs and the decoupled selected most limiting constraints. | 08-15-2013 |
20130213618 | SYNTHETIC JET EMBEDDED HEAT SINK - A system and method for cooling heat-producing devices using synthetic jet embedded heat sinks is disclosed. The cooling system includes a heat sink comprising a base portion and a plurality of fins disposed on the base portion and extending vertically out therefrom, the plurality of fins spaced to define a channel between adjacent fins. The cooling system also includes at least one synthetic jet actuator attached to the heat sink, with each of the at least one synthetic jet actuators comprising a plurality of orifices therein and being configured to generate and project a series of fluid vortices out from the plurality of orifices and toward at least a portion of the channels of the heat sink. | 08-22-2013 |
20130214435 | EPOXY ENCAPSULATING AND LAMINATION ADHESIVE AND METHOD OF MAKING SAME - An adhesive includes an epoxy resin and a hardener. The hardener includes trioxdiamine, diaminodicyclohexylmethane, toluene diamine, and bisphenol-A dianhydride. | 08-22-2013 |
20130217882 | ORGANIC COMPOUNDS - A compound of formula IV: | 08-22-2013 |
20130218040 | APPARATUS, ARRANGENT AND METHOD FOR ANALYZING BREATHING GAS FLOWING ALONG A BREATHING TUBING FOR SUBJECT BREATHING - An apparatus and method is provided for analyzing a breathing gas flowing along a breathing tubing for subject breathing. The breathing gas comprises breathing cycles having different phases. Liquid particles can be delivered intermittently depending on the phase, or continuously into the breathing gas. The apparatus comprises a gas sample supplier for adjusting gas sample supply from the breathing gas, and a gas analyzer for receiving the gas sample adjusted by the gas sample supplier and for measuring the gas sample property. The apparatus further comprises a processing unit for receiving a signal indicative of one of the phases of the breathing cycle and the delivery timing of the liquid particles. The processing unit is able to control the sample supplier based on the signal to limit access of liquid particles with the gas sample towards the gas analyzer. | 08-22-2013 |
20130218520 | SAND LEVEL MONITORING SYSTEM - A system for monitoring a sand reservoir includes: (a) a sand reservoir carried on an off-highway vehicle; and (b) at least one sand level indicator carried by the sand reservoir which provides a visual display external to the sand reservoir indicative of the quantity of sand within the sand reservoir. | 08-22-2013 |
20130219718 | BLADE INSERT FOR A WIND TURBINE ROTOR BLADE AND RELATED METHODS - A method for retrofitting a rotor blade of a wind turbine is disclosed. The method may generally include cutting the rotor blade at a specified location in order to form a root segment and a tip segment and positioning a blade insert between the root segment and the tip segment | 08-29-2013 |
20130221849 | FLUORESCENT LAMP ASSEMBLY WITH IMPROVED RUN-UP - A discharge lamp having an improved run-up time is disclosed. In an embodiment, the discharge lamp includes a light-transmissive discharge tube extending from a first end to a second end and having an inner surface and an outer surface, a phosphor coating layered onto the inner surface of the discharge tube, and a fill gas composition capable of sustaining a discharge sealed within the discharge tube. Also included is a resistive heating wire positioned about the outer surface of the discharge tube. In some embodiments, a lamp driver circuit is included that operates when the lamp is turned ON to provide power to electrodes in the discharge tube and to provide power to the resistive heating wire, and operates to disconnect power from the resistive heating wire when the discharge lamp achieves a predetermined percentage of its stabilized lumen output. | 08-29-2013 |
20130223590 | SYSTEMS AND METHODS FOR BIOPSY GUIDANCE - Systems and methods for biopsy guidance are provided. One system includes a gantry and a breast immobilization plate mounted to the gantry, wherein the breast immobilization plate is configured to be coupled with a biopsy unit. The biopsy unit includes at least one nuclear medicine imaging detector in an angled orientation with respect to the breast immobilization plate. The breast imaging system also includes a nuclear medicine imaging detector mounted to the gantry parallel to the breast immobilization plate, wherein the nuclear medicine imaging detector mounted to the gantry and the breast immobilizing plate are configured to immobilize a breast therebetween. | 08-29-2013 |
20130224032 | BLADE INSERT FOR A WIND TURBINE ROTOR BLADE AND RELATED METHODS - A blade insert for coupling a first blade segment to a second blade segment is disclosed. The blade insert may include an aerodynamic body extending between a first end configured to be coupled to the first blade segment and a second end configured to be coupled to the second blade segment. The aerodynamic body may include a pressure side and a suction side extending between a leading edge and a trailing edge. In addition, the aerodynamic body may define a chord, wherein the chord at the first end is substantially equal to the chord at the second end. | 08-29-2013 |
20130297328 | INTERFACE FEED ANALYZER FOR CODE MAPPING - Certain examples provide systems, methods, and apparatus to provide clinical terminology services. Certain examples provide systems, methods, and apparatus to analyze and map a new interface message feed. An example clinical interface feed analysis system includes an interface analyzer to: receive a clinical message feed including content; automatically compare the content from the clinical message feed to a reference to match and map the content to at least one of reference clinical data and coded terminology included in the reference without user input; and provide a proposed interface output for review. The example system includes a tester to facilitate testing of the proposed interface output in conjunction with a clinical system to release the proposed interface output as an interface for incoming messages. The example system is to update the reference based on the content from the clinical message feed and the interface mapping. | 11-07-2013 |
20130309079 | TURBINE NOZZLE OUTER BAND AND AIRFOIL COOLING APPARATUS - A turbine nozzle segment includes: an arcuate outer band segment; an airfoil-shaped turbine vane extending radially inward from the outer band segment, the turbine vane having a hollow interior; an impingement baffle assembly secured to the outer band so as to define an impingement cavity in cooperation with the outer band segment, wherein the impingement baffle assembly has at least one impingement hole formed therein which is arranged to direct cooling air at the outer band segment; and at least one impingement insert having at least one impingement hole formed therein disposed in the interior of the turbine vane, the impingement insert mating with an opening in the impingement baffle assembly such that the impingement baffle is isolated from direct fluid communication with the impingement cavity. | 11-21-2013 |
20140060461 | POWER GENERATION SYSTEM UTILIZING A FUEL CELL INTEGRATED WITH A COMBUSTION ENGINE - A power generation system utilizing a fuel cell is described. The system includes a fuel cell having an anode configured to generate a tail gas. The anode includes an inlet and an outlet. The system further includes a fuel path configured to divert a first portion of the anode tail gas to the inlet of the anode; and a second portion of the anode tail gas to a reciprocating engine. The associated reciprocating engine is at least partially powered by the second portion of the anode tail-gas. Another embodiment of the invention is directed to a power generation system that includes the anode and an external fuel reforming system, along with a gas splitting mechanism to divide the reformed fuel into two streams. One stream is directed back to the fuel cell anode, while another stream is used to completely or partially power an external or internal combustion engine. | 03-06-2014 |
20140062032 | SPRING-LOADED SEAL ASSEMBLY - A seal assembly is provided. The seal assembly includes a first outer shim and a second outer shim The second outer shim is operably coupled to the first outer shim and comprises at least one substantially impermeable portion that spans across a gap between at least two turbomachine components. The second outer shim further engages the at least two turbomachine components to substantially seal the gap. The substantially impermeable portion is substantially planar at least along a width of the seal assembly. The seal assembly further includes a resilient member that is either coupled to at least a portion of an outer surface of the first outer shim or comprises an integral portion of the first outer shim The resilient member engages the seal assembly to contact bottom surfaces of a cavity defined between the at least two turbomachine components. | 03-06-2014 |
20140064937 | FAN BLADE BRUSH TIP - A fan assembly is provided. The fan assembly includes a rotor having a hub and a plurality of rotor blades extending radially outward from the hub. Each rotor blade includes a blade tip at a radially distal end of each blade. The rotor blade tips define a rotor diameter. The fan assembly also includes a first cylindrical casing substantially axially aligned with the blade tips, the first casing including a first inner diameter that is greater than the rotor diameter. The fan assembly further includes a brush seal assembly coupled to the blade tip of a least one of the plurality of rotor blades, the brush seal assembly configured to contact the casing segment during a first operational mode of the fan assembly, the brush seal assembly configured to avoid contact with the casing segment during a second operational mode of the fan assembly. | 03-06-2014 |
20140072736 | METHOD OF PRODUCING AN INTERNAL CAVITY IN A CERAMIC MATRIX COMPOSITE AND MANDREL THEREFOR - A process for producing an internal cavity in a CMC article and mandrels used therewith. The process entails incorporating a mandrel made of a material that is substantially absorbed during thermal treatment of a preform to form the CMC article. The mandrel material is preferably reactive with one or more constituents of the CMC preform during the thermal treatment. The material is preferably silicon or a silicon alloy. | 03-13-2014 |
20140083110 | SEAL FOR FUEL DISTRIBUTION PLATE - A fuel flow passes through a micromixer section of a gas turbine that includes a plurality of mixing tubes for transporting a fuel/air mixture and a distribution plate including a plurality of distribution holes and a plurality of tube holes for accommodating the mixing tubes. Each of the mixing tubes includes a plurality of fuel holes through which fuel enters the mixing tubes. The tube holes and the mixing tubes form a plurality of annulus areas between the distribution plate and the mixing tubes. The distribution holes and the annulus areas are configured to pass the fuel flow through the distribution plate toward the fuel holes. A flow management device modifies an effective size of the annulus areas to control a distribution of the fuel flow through the distribution holes and the annulus areas of the distribution plate to provide a uniform fuel/air composition in each of the mixing tubes. | 03-27-2014 |
20140083639 | BACKSTRIKE PROTECTION DURING MACHINING OF COOLING FEATURES - A method of machining a component is provided. The component includes a substrate having an outer surface and an inner surface, where the inner surface defines at least one interior space. A core is disposed within each interior space. The method includes forming at least one hole in the substrate while the core is disposed within the respective interior space. Each hole extends through the substrate to provide fluid communication with the respective interior space. The method further includes removing the core from the respective interior space. The core may be a casting core or a subsequently formed core. | 03-27-2014 |
20140090457 | METALIZED CERAMIC LEADING EDGE NOZZLE KIELS FOR HIGH-TEMPERATURE TURBINE APPLICATIONS - A pressure probe includes an elongated cable provided with a sensing tip, a portion of the elongated cable and sensing tip enclosed within a ceramic shroud, the ceramic shroud at least partially formed of a metalized ceramic material. | 04-03-2014 |
20140093878 | MUTANT ENDONUCLEASE V ENZYMES AND APPLICATIONS THEREOF - Provided herein are mutant endonuclease V enzymes that are capable of nicking an inosine-containing DNA sequence. Nucleic acid assays and agents that employ such mutant endonuclease V enzymes to introduce a nick into a target DNA including one or more inosine, and uses a DNA polymerase to generate amplicons of a target DNA are also described. | 04-03-2014 |
20140096529 | SYSTEM AND METHOD FOR FUEL AND STEAM INJECTION WITHIN A COMBUSTOR - A system includes a gas turbine combustor configured to combust a fuel and an oxidant, such as O | 04-10-2014 |
20140096538 | PLATFORM COOLING OF A TURBINE BLADE ASSEMBLY - A turbine blade generally includes a platform having a pressure side, a suction side, a leading edge, a trailing edge, a pressure side slash face and a suction side slash face. A platform cooling circuit extends within the platform. The platform cooling circuit may extend from the suction side of the platform to the pressure side of the platform. The platform cooling circuit generally defines a fluid flow path that directs a cooling medium from the platform suction side to the platform pressure side. | 04-10-2014 |
20140099188 | WIDE DISCOURAGER TOOTH - Oil sump seal pressurization apparatus for turbine engines are disclosed. An example oil sump seal pressurization apparatus may include a non-rotating oil sump housing a bearing; an oil seal isolating an interior of the oil sump; a passage arranged to supply pressurization air to an outward side of the oil seal; a drain arranged to allow draining of oil and venting of at least some of the pressurization air, the drain being positioned axially between the passage and the oil seal; a wide discourager tooth disposed on the shaft and extending radially outward towards a non-rotating land, which may be disposed axially between the passage and the drain, the wide discourager tooth being spaced apart from the land in a radial direction by a gap, the wide discourager tooth including an upper surface; and/or an adjacent tooth disposed on the shaft and extending radially outward from the shaft. | 04-10-2014 |
20140103820 | Boost Converter of Driver Circuit With Thermal Compensation - A circuit for providing thermal compensation for a driver circuit used to drive light emitting diodes (LEDs) is provided. The driver circuit can include a rectifier circuit configured to rectify an AC power source into a DC power source providing a DC source voltage. The driver circuit can further include a boost circuit configured to boost the DC source voltage to provide a drive voltage for driving the light emitting diodes. The boost circuit can include a switching element that is controlled based at least in part on a current sense circuit having a sense transistor. A thermal tracking transistor is provided as part of the reference to the sense circuit. | 04-17-2014 |
20140109418 | DIGITAL FEELER GAUGE AND METHOD OF USING SAME - The present application provides for feeler gauges. The feeler gauges include a plurality of elongate measuring leaves rotatably coupled on a common axis of rotation with an elongate housing. The leaves may be manually, selectively rotatable between a “home” position wherein the leaves are substantially aligned with the housing and an “extended” position wherein the leaves are spaced from the housing. The leaves may be relatively flexible and substantially flat such that they define a substantially constant thickness. One or more extended leaves may be used to measure the thickness of a clearance or gap. The gauges may be configured to detect, determine or measure the thickness of the leaves that are in the “home” position and/or the “extended” position, and thereby determine the total thickness of a clearance or gap measured by the extended leaves. | 04-24-2014 |
20140112793 | Systems and Methods to Axially Retain Blades - Embodiments of the present disclosure include a gas turbine engine system. The system may include a rotor wheel having a number of blades mounted about a periphery of the rotor wheel. Further, the system may include a retention device. The retention device may include a number of projections extending from a radial surface of the rotor wheel to form a number of circumferential slots about the rotor wheel. The retention device may also include a number of elongated members positioned within the circumferential slots to impede axial movement of the blades. | 04-24-2014 |
20140112796 | COMPOSITE BLADE WITH UNI-TAPE AIRFOIL SPARS - A gas turbine engine composite blade includes an airfoil having pressure and suction sides extending outwardly in a spanwise direction from a blade root along a span to a blade tip. A core section of the blade including composite quasi-isotropic plies extends spanwise outwardly through the blade. One or more spars including a stack of uni-tape plies having predominately a 0 degree fiber orientation with respect to the span and extending spanwise outwardly through the root and a portion of the airfoil towards the tip. Spars may include pressure and suction side spars sandwiching a chordwise extending portion of the core section in the airfoil and which be located near or along the pressure and suction sides respectively. Chordwise extending portion may be centered about a maximum thickness location of the airfoil. Spars may have height, width, and thickness that avoids flexural airfoil modes. | 04-24-2014 |
20140133975 | Double Fan Outlet Guide Vane with Structural Platforms - The assembly has a first guide vane having a first end, a second end opposed to the first end, and a second guide vane having a first end, a second end opposed to its first end. A first end structure spans between the first guide vane first end and the second guide vane first end. A second end structure spans between the first guide vane second end and the second guide vane second end. The first guide vane, the second guide vane, the first end structure, and the second end structure are integrally formed together to form a double vane with a continuous outer surface, and a continuous inner surface. | 05-15-2014 |
20140137408 | METHODS OF FABRICATING AND COATING TURBINE COMPONENTS - In one aspect, a method of forming a hot gas path component is provided. The method includes forming at least one groove in an outer surface of a substrate, wherein the at least one groove has a base and a top. The method further includes filling the at least one groove with a filler. The method also includes applying at least one cover layer over at least a portion of the outer surface of the substrate such that the at least one groove and the at least one cover layer define at least one micro-channel for cooling the component. The filler is automatically removed from the at least one micro-channel during application of the at least one cover layer. Methods for coating a hot gas component and for assembling a turbine engine assembly are also provided. | 05-22-2014 |
20140137533 | EXHAUST GAS DIFFUSER FOR A GAS TURBINE - An exhaust gas diffuser for a gas turbine generally includes an inner wall that extends along an axial centerline of the exhaust gas diffuser. An outer wall is coaxially aligned with the inner wall. The outer wall is radially separated from the inner wall so as to define a flow passage therebetween. An airfoil shaped strut is disposed in the flow passage. The strut extends between the inner and the outer walls. The strut includes a leading edge and a trailing edge positioned relative to a direction of flow through the flow passage. The leading edge and the trailing edge are tapered from the inner wall to the outer wall in the direction of flow through the passage. | 05-22-2014 |
20140140805 | Inducer Guide Vanes - According to one embodiment, there is disclosed an inducer assembly for use with a gas turbine engine. The inducer assembly may include a cavity. The inducer assembly may also include an inducer in fluid communication with the cavity. Moreover, the inducer assembly may include at least one guide vane disposed within the cavity. | 05-22-2014 |
20140140832 | Quick Engine Change Assembly for Outlet Guide Vanes - A quick engine change assembly, comprises a first circular frame member, a plurality of doublet supports spaced about the first circular frame member, the doublet supports being contoured along the axial direction, a flow surface defined between the plurality of doublet supports and, a plurality of cradles, each of the cradles including the doublet supports, the doublet supports from a lower portion of the cradle to the flow surface. | 05-22-2014 |
20140144242 | METHOD AND SYSTEM FOR USE IN CONDITION MONITORING OF PRESSURE VESSELS - A condition monitoring system for a pressure vessel includes at least one vibration monitoring probe coupled to at least one pressure vessel component. The system also includes at least one computing device that includes a memory device configured to store data associated with the at least one vibration monitoring probe. The computing device also includes at least one input channel configured to receive the data associated with the at least one vibration monitoring probe. The computing device further includes a processor coupled to the memory device and the at least one input channel. The processor is programmed to determine a deterioration of the material condition of the at least one pressure vessel component by comparing at least a portion of the data associated with the at least one vibration monitoring probe with predetermined vibration parameters. | 05-29-2014 |
20140147387 | NANOPARTICLE CONTRAST AGENTS FOR DIAGNOSTIC IMAGING - Compositions of nanoparticles functionalized with at least one zwitterionic moiety, methods for making a plurality of nanoparticles, and methods of their use as diagnostic agents are provided. The nanoparticles have characteristics that result in minimal retention of the particles in the body compared to other nanoparticles. The nanoparticle comprising a nanoparticulate transition metal oxide covalently functionalized with a silane-functionalized non-targeting zwitterionic moiety. | 05-29-2014 |
20140150455 | COATED ARTICLE - The present invention is a coated article containing at least two adjacent cooling holes that are substantially uncoated. In an embodiment, the coated article includes a base material, an outer surface and a coating on a portion of the outer surface. Here, the adjacent cooling holes are arranged along an axis on the outer surface and extend within the base material at an angle to the outer surface. The coating may include at least one unfinished edge oriented substantially parallel to the axis and set off at an oblique angle and a distance from the adjacent cooling holes. | 06-05-2014 |
20140151009 | THERMAL INTERFACE ELEMENT AND METHOD OF PREPARATION - An article and method of assembling the article is disclosed. The method of assembling includes positioning a pre-fabricated thermal interface element between a heat source and a heat-sink. The pre-fabricated thermal interface element includes an indium substrate and a plurality of nanosprings disposed on the indium substrate. | 06-05-2014 |
20140154063 | AIRFOIL AND A METHOD FOR COOLING AN AIRFOIL PLATFORM - An airfoil includes an outer surface having a leading edge, a trailing edge downstream from the leading edge, and a convex surface between the leading and trailing edges. A cavity is inside the outer surface, and a platform is connected to the outer surface and defines a top surface around at least a portion of the outer surface. A first plurality of trenches is beneath the top surface of the platform upstream from the leading edge, wherein each trench in the first plurality of trenches is in fluid communication with the cavity inside the outer surface. A first plurality of cooling passages provide fluid communication from the first plurality of trenches through the top surface of the platform. | 06-05-2014 |
20140161585 | TURBO-MACHINE COMPONENT AND METHOD - A component, a component manufacturing process, and a component operation process are disclosed. The component has a diffuser permitting compressible fluid to flow throughout a first region and a second region of the diffuser at a decreasing velocity. The diffuser includes a coating collection feature. The component manufacturing process includes positioning the component and applying the coating to at least a surface of the component outside of the diffuser and to at least a portion of the second region, not to the first region, to the coating collection feature, or a combination thereof. The component operation process includes positioning the component and transporting the compressible fluid through the diffuser. | 06-12-2014 |
20140174103 | SYSTEMS AND METHODS FOR OXIDATION OF BOIL-OFF GAS - A system in one embodiment includes a mixing module, an oxidation module, and a heat exchanger. The mixing module is configured to receive and mix a boil-off gas stream from a cryotank. The oxidation module is configured to receive the mixed stream, and to oxidize the boil-off gas in the mixed stream to produce an exhaust stream. The heat exchanger is configured to exchange heat between streams passing through a first passage configured to receive at least a portion of the exhaust stream, and a second passage configured to receive a fluid including the boil-off gas. The heat exchanger is configured to heat the fluid including the boil-off gas and cool the at least a portion of the exhaust stream. The fluid including the boil-off gas is heated by the heat exchanger upstream of the oxidation module. | 06-26-2014 |
20140186684 | ELECTROCHEMICAL CELL - An electrochemical cell is presented. The cell includes a housing formed of a metallic material. A component is disposed within an anode compartment of the cell that contains an alkali metal. The component comprises a sacrificial metal that has an oxidation potential less than the oxidation potential of the housing material. An energy storage device including such an electrochemical cell is also provided. | 07-03-2014 |
20140186946 | CELL CARRIER, ASSOCIATED METHODS FOR MAKING CELL CARRIER AND CULTURING CELLS USING THE SAME - A carrier for expansion of pluripotent stem cells is provided, wherein the carrier comprises a substrate comprising one or more outer surfaces, wherein the one or more outer surfaces are modified with gas plasma treatment, and one or more structured indentations on one or more of the outer surfaces. The carrier has a length at least about 0.2 mm, a width at least about 0.2 mm, and a height in a range from about 0.05 mm to 1.2 mm and each of the structured indentations has a major axis in a range from about 0.1 mm to 0.5 mm, a minor axis in a range from about 0.1 mm to 0.5 mm and a depth in a range from about 0.025 mm to about 0.5 mm. A method of making the carrier, and culturing stromal cells using the same carrier are also provided. | 07-03-2014 |
20140198365 | MULTI-BEAM LASER SCANNING SYSTEM AND METHOD - A multi-beam laser scanning system comprising a laser, a beam splitter, a first scanning unit, a second scanning unit, and a control unit is disclosed herein. The laser is used for generating an initial laser beam. The beam splitter is used for splitting the initial laser beam into a first laser beam and a second laser beam. The first scanning unit is used for deflecting the first laser beam along a desired direction. The second scanning unit is used for deflecting the second laser beam along a desired direction. The control unit is coupled to the first and second scanning units and arranged to output control signals to the first and second scanning units to manufacture an object. | 07-17-2014 |
20140205072 | POWER GENERATION SYSTEM AND PACKAGE - A power generation system includes an input to receive a low-voltage alternating current and a number N of voltage-conversion modules coupled to the input, each electrically connected in series. Each voltage-conversion module includes a transformer configured to convert the low-voltage alternating current into a high-voltage alternating current. Each voltage-conversion module includes a multiplier configured to convert the high-voltage alternating current from the transformer into a high-voltage direct current. The multiplier includes a positive multiplier part and a negative multiplier part. The positive multiplier part and the negative multiplier part each includes a pair of input terminals connected in parallel with the transform and at least one multiplier stage comprising a single diode and a capacitor assembly. The number N is an even number between 4 and 24. | 07-24-2014 |
20140205472 | DUAL PUMP/DUAL BYPASS FUEL PUMPING SYSTEM - An example dual pump/dual bypass fuel pumping assembly may include a dual bypass valve including a first inlet port, a second inlet port, and a movable spool arranged to modulate fuel flow from the first inlet port to a first bypass port and a first discharge port and arranged to modulate fuel flow from the second inlet port to a second bypass port and a second discharge port based on a position of the movable spool; a first pump arranged to supply fuel to the first inlet port; a second pump arranged to supply fuel to the second inlet port; a supply header arranged to supply fuel to the first pump and the second pump; a bypass header fluidically coupled to the first bypass port, the second bypass port, and the supply header; and/or a discharge header fluidically coupled to the first discharge port and the second discharge port. | 07-24-2014 |
20140209286 | GAS TURBINE ENGINE INTEGRATED HEAT EXCHANGER - A heat exchanger apparatus including at least one cooling channel formed within and about an engine booster lip or an engine nacelle and configured to receive a flow of a circulating working fluid; and at least one fluid port communicating with the at least one cooling channel and an exterior of the engine booster lip or the engine nacelle. | 07-31-2014 |
20140212284 | HYBRID TURBINE NOZZLE - A turbine nozzle apparatus for a gas turbine engine includes: an annular inner band; an annular outer band circumscribing the inner band; a plurality of airfoil-shaped structural vanes extending between and interconnecting the inner band and the outer band; and a plurality of airfoil-shaped non-structural vanes extending between the inner band and the outer band, each non-structural vane having a root end received by the inner band and a tip end received by the outer band, such that each non-structural vane is free to move to a limited degree relative to the inner and outer bands. | 07-31-2014 |
20140217300 | DYNAMIC HIGH VOLTAGE BIAS FOR HIGH PRESSURE ION CHAMBERS - An environmental radiation monitor including a high pressure ionization chamber (HPIC) configured to produce a current signal responsive to gamma impingement. The monitor includes an electrometer electrically connected with the HPIC. The electrometer includes an electrical amplifier receiving the current signal. The electrical amplifier is configured to convert the current signal to a voltage signal indicative of gamma impingement. The monitor includes a voltage supply electrically connected to the HPIC to provide a bias voltage amount to the high pressure ionization chamber. The voltage supply is controllable to vary the bias voltage amount provided to the HPIC. The monitor includes a processor operatively connected to the electrometer to receive information indicative of gamma impingement and operatively connected to the voltage supply to control the voltage supply to vary the bias voltage amount in response to received information indicative of gamma impingement. An associated method is also provided. | 08-07-2014 |
20140220253 | MICRO-CHANNEL COATING DEPOSITION SYSTEM AND METHOD FOR USING THE SAME - Methods of pressure coating a target surface of an article comprising one or more grooves formed in an outer surface of an article include fluidly connecting a pressure masker comprising a pressurized masking fluid to one or more coolant supply holes on a first side of the article. The one or more coolant supply holes in fluidic communication with the one or more grooves. Passing the pressurized masking fluid through the one or more grooves from the first side to a second side comprising the target surface at a pressure less than the coating pressure of the coating material, and, coating the target surface with the coating material to allow the coating material to bridge over the one or more grooves and form one or more micro-channels. The pressurized masking fluid passing through the one or more grooves prevents the coating material from permanently altering a cross sectional area of the one or more grooves along its length. | 08-07-2014 |
20140234117 | APPARATUS AND METHOD TO REDUCE WEAR AND FRICTION BETWEEN CMC-TO-METAL ATTACHMENT AND INTERFACE - An apparatus to reduce wear and friction between CMC-to-metal attachment and interface, including a metal layer configured for insertion between a surface interface between a CMC component and a metal component. The surface interface of the metal layer is compliant relative to asperities of the surface interface of the CMC component. A coefficient of friction between the surface interface of the CMC component and the metal component is about 1.0 or less at an operating temperature between about 300° C. to about 325° C. and a limiting temperature of the metal component. | 08-21-2014 |
20140245752 | SYSTEM AND METHOD FOR ATTACHING A ROTATING BLADE IN A TURBINE - A system for attaching a rotating blade in a turbine includes a bush having an axial slot and a radial slot that intersects with the axial slot. A radial retention member fits within the radial slot, and an axial retention member fits within the axial slot and engages with the radial retention member. A method for attaching a rotating blade in a turbine includes inserting a bush into an axial passage in a rotor wheel and inserting a radial retention member into a radial passage in the rotor wheel and through at least a portion of the bush. The method further includes inserting the rotating blade in a slot in the rotor wheel, inserting the radial retention member into a retention slot in the rotating blade, and inserting an axial retention member into the bush. | 09-04-2014 |
20140255194 | TIP SHROUDS OF TURBINE ROTOR BLADES AND METHODS OF MANUFACTURE RELATED THERETO - A rotor blade for use in a turbine of a turbine engine is described. The rotor blade may include an airfoil that extends from a connection with a root. The airfoil may include a pressure sidewall and a suction sidewall that define an outer periphery and an outboard tip. The rotor blade may further include a tip shroud assembly disposed at the outboard tip of the airfoil. The tip shroud assembly includes a non-integral tip shroud. | 09-11-2014 |
20140255203 | Hybrid Spinner Support - A hybrid support ring comprises a suspender and a belt, the suspender defined by a flange and a leg rearwardly extending having a lug, the suspender also extending circumferentially, the suspender formed of a first material, the belt extending circumferentially and disposed in the lug, the belt being formed of a second material. | 09-11-2014 |
20140255207 | TURBINE ROTOR BLADES HAVING MID-SPAN SHROUDS - A rotor blade for use in a turbine of a combustion turbine engine is described. The rotor blade may include an airfoil that extends from a connection with a root. The rotor blade may further include a mid-span shroud configured to engage a corresponding mid-span shroud on at least one neighboring rotor blades during operation. Outboard of the mid-span shroud, the airfoil may include an outboard region that is substantially hollow, and inboard of the mid-span shroud, the airfoil may include an inboard region that is substantially solid. | 09-11-2014 |
20140260269 | SYSTEMS AND APPARATUS RELATING TO DOWNSTREAM FUEL AND AIR INJECTION IN GAS TURBINES - A gas turbine engine that includes: a combustor coupled to a turbine and a downstream injection system that includes two injection stages, a first stage and a second stage, positioned within an interior flowpath, wherein the first stage comprises an axial position that is aft of the primary air and fuel injection system and the second stage comprising an axial position that is aft of the first stage. Each of the first stage and the second stage include a plurality of circumferentially spaced injectors, each injector of which is configured to inject air and fuel into a flow through the interior flowpath. The first stage and the second stage have a configuration that limits a fuel injected at the second stage to less than 50% of a fuel injected at the first stage. | 09-18-2014 |
20140260270 | SYSTEMS AND APPARATUS RELATING TO DOWNSTREAM FUEL AND AIR INJECTION IN GAS TURBINES - A gas turbine engine that includes: an interior flowpath defined through a combustor and a turbine; an aft frame forming an interface between the combustor the turbine, the aft frame comprising a rigid structural member that circumscribes the interior flowpath, wherein the aft frame includes an inner wall that defines an outboard boundary of the interior flowpath; a circumferentially extending fuel plenum formed through the aft frame; and outlet ports formed through the inner wall of the aft frame. The outlet ports may be configured to connect the fuel plenum to the interior flowpath. | 09-18-2014 |
20140260299 | FUEL-AIR MIXING SYSTEM FOR GAS TURBINE SYSTEM - Embodiments of the present disclosure are directed to systems and methods for premixing fuel and air prior to combustion within a combustion chamber. The system includes a plurality of fuel injectors and a plurality of mixing tubes, wherein each mixing tube has a first portion for receiving one of the plurality of fuel injectors and a second portion having a mixing chamber that is configured to mix fuel and air. The length of the mixing chamber varies among the plurality of mixing tubes to allow for different mixing times. | 09-18-2014 |
20140260327 | COOLED ARTICLE - The present invention is an article containing internal cooling channels located near at least one surface. In an embodiment, the cooled article includes a base material, a first layer, and a second layer. Here, the first layer is bonded to the base material and the second layer is bonded to the first layer, wherein at least one closed cooling channel is disposed within a portion of the first layer and a portion of the second layer. | 09-18-2014 |
20140265682 | SYSTEMS AND METHODS FOR ISOLATING A CONDUIT ENCLOSURE USING AN ADAPTER PLATE FOR AN EXPLOSION PROOF MOTOR - An enclosure system includes a stator enclosure defining an enclosure opening, and an adapter having a first entry port, and defines a center cavity having a first volume. Enclosure system includes a conduit enclosure coupled to one or more of stator enclosure and adapter. Conduit enclosure includes a base member having at least one side wall, a rear wall coupled to side wall and defining a second entry port, an interior cavity, and a terminal connection block coupled to base member and having at least one terminal. Enclosure system includes at least one electrical lead extending from the stator enclosure through first enclosure opening, through first entry port, through center cavity, through second entry port, and into the interior cavity. Electrical lead occupies a portion of first volume and leaves a remaining volume. Enclosure system includes sealing compound coupled with adapter such that substantially all of remaining volume is occupied. | 09-18-2014 |
20140271168 | Radial Diffuser Exhaust System - The present application provides a radial diffuser exhaust system for use with a gas turbine engine. The radial diffuser exhaust system may include a radial diffuser positioned within an asymmetric exhaust collector. The asymmetric exhaust collector may include a closed end chamber and an exhaust end chamber. The closed end chamber may have a first size, the exhaust end chamber may have a second size, and the first size may be smaller than the second size. | 09-18-2014 |
20140271208 | SYSTEMS AND METHOD FOR A COMPOSITE BLADE WITH FILLET TRANSITION - A system includes a turbomachine blade segment including an airfoil with an exterior surface, and a platform coupled to the airfoil having a first side and a second side. The system also includes a concave fillet transition extending between the airfoil and the platform. The concave fillet transition includes one or more interface ply segments extending across the exterior surface of the airfoil and the first or the second side of the platform to form a continuous surface between the airfoil and the platform. | 09-18-2014 |
20140271225 | INTERIOR COOLING CIRCUITS IN TURBINE BLADES - A rotor blade comprising an airfoil portion and a root portion, and an internal cooling circuit having flow passages in the root portion and the airfoil portion, wherein the internal cooling circuit includes: a first flow passage; and a non-integral plug. The plug may include a plug channel configured to correspond to a desired level of coolant flow through the first cooling passage. The plug may be connected to the rotor blade in a fixed blocking position relative to the first flow passage. | 09-18-2014 |
20140271226 | Turbine Blade Tip With Tip Shelf Diffuser Holes - A turbine blade having a tip including a tip shelf through which pass one or more diffuser cooling holes, the diffuser cooling holes directing the flow of cooling gas along the tip shelf, spreading the flow of cooling gas more evenly along the tip shelf and enhancing the formation of a curtain of cooling air along the tip shelf, leading to lower blade tip temperatures, reduced diversion of cooling air, and greater turbine blade life. | 09-18-2014 |
20140272104 | COATING METHODS AND PRESSURIZED MASKING SYSTEMS FOR CONTROLLING COATING MICROSTRUCTURES - Methods for coating a target surface of an article having one or more passageways include fluidly connecting a temperature controlled fluid to at least one passageway, passing the temperature controlled fluid through the at least one passageway, wherein the temperature controlled fluid at least partially controls a temperature profile of the article, and coating the target surface, wherein the temperature profile of the article at least partially controls a microstructure of the coating. | 09-18-2014 |
20140277853 | SYSTEM AND METHOD FOR DETERMINING AIRCRAFT OPERATIONAL PARAMETERS AND ENHANCING AIRCRAFT OPERATION - A method for identifying variations in aircraft operational parameters includes processing a four-dimensional (4D) aircraft trajectory for a flight along a defined route. The method also includes determining an aircraft intent corresponding to the flight along the defined route based at least in part on an aircraft performance model from a trajectory predictor. The aircraft intent includes multiple segments and corresponding intent parameters. In addition, the method includes adjusting the intent parameters such that a computed 4D trajectory substantially corresponds to the 4D aircraft trajectory. The method further includes determining a computed operational parameter based at least in part on the computed 4D trajectory and the aircraft performance model from the trajectory predictor. In addition, the method includes identifying variations between the computed operational parameter and a corresponding measured operational parameter. | 09-18-2014 |
20140283522 | MULTI-INJECTOR MICROMIXING SYSTEM - Embodiments of the present disclosure are directed to a system having components for premixing fuel and air prior to combustion within a combustion chamber. The system includes a plurality of mixing tubes configured to receive and to mix fuel and air. Each mixing tube is paired with a fuel injector, and the fuel injector is positioned axially within a portion of the mixing tube. Fuel is injected from the fuel injector into the respective mixing tube, and air flows radially into each mixing tube through one or more apertures formed on the mixing tube. The fuel and air are mixed within the mixing tube and are deposited into a combustion chamber for combustion. | 09-25-2014 |
20140286756 | DEVICE, SYSTEM AND METHOD FOR PREVENTING LEAKAGE IN A TURBINE - A turbine disk and blade assembly comprises a turbine disk including a plurality of disk posts extending radially therefrom and a plurality of disk slots between adjacent disk posts. The turbine disk is of a first material having a first coefficient of thermal expansion. The assembly further comprises a plurality of turbine blades. One of the turbine blades is received in each disk slot. The turbine blades are of a second material having a second coefficient of thermal expansion. The assembly further comprises a plurality of seal plates, wherein one of the seal plates is positioned in each disk slot radially inward of the turbine blade. The seal plates are of a material having a coefficient of thermal expansion substantially similar to that of either the disk posts or the turbine blade. | 09-25-2014 |
20140286766 | Compressor Casing Assembly Providing Access To Compressor Blade Sealing Assembly - A compressor casing assembly includes a forward compressor casing, a removable cover and a seal assembly. A midcompressor casing is provided with a cavity adapted to receive the seal assembly, and a cover groove adapted to receive the removable cover. The removable cover secures the seal assembly. | 09-25-2014 |
20140286771 | COOLING PASSAGES FOR TURBINE BUCKETS OF A GAS TURBINE ENGINE - The present application and the resultant patent provide a turbine bucket for a gas turbine engine. The turbine bucket may include a platform, an airfoil extending radially from the platform, and a number of cooling passages defined within the airfoil and near an outer surface of the airfoil. Each of the cooling passages may include a radially inner portion having a first cross-sectional area and at least one radially outer portion having a second cross-sectional area, wherein the first cross-sectional area may be greater than the second cross-sectional area. The present application and the resultant patent further provide a method of cooling a turbine bucket used in a gas turbine engine. | 09-25-2014 |
20140286785 | METHOD OF PRODUCING A HOLLOW AIRFOIL - A method of producing an airfoil is provided. The method includes forming a steel airfoil preform with a pocket on at least one of the pressure and suction surfaces, forming a cover plate for the pocket and welding the cover plate over the pocket. | 09-25-2014 |
20140286790 | Dust Mitigation for Turbine Blade Tip Turns - A dust mitigation system for airfoils includes a plurality of contoured tip turns which curve about at least two axes. This inhibits recirculation areas common within airfoils and further inhibits dust build up within the cooling flow path of the airfoil. | 09-25-2014 |
20140290254 | Cyclonic Dirt Separating Turbine Accelerator - A dirt separator assembly for a gas turbine engine comprises a cyclonic accelerator in flow communication with compressor discharge air, the accelerator having a plurality of passages, each passage having an inlet, an outlet and at least one vent located in the passage, a plurality of turning vanes disposed along each of the passages, the passage turning tangentially between the inlet and the outlet, the accelerator passages decreasing from a first cross-sectional area to a second cross-sectional area and said turning vanes inducing helical swirl of compressed cooling air, and, at least one vent located in the accelerator passages for expelling dust separated from the swirling compressed cooling air. | 10-02-2014 |
20140294594 | HYBRID TURBINE BLADE INCLUDING MULTIPLE INSERT SECTIONS - A hybrid turbine blade and method of fabrication, comprising a shank portion and an airfoil portion. The airfoil portion comprising a composite outer structure having a recess formed therein and an alternating stack of at least one composite section and at least two insert sections disposed in the recess. The outer composite structure and the at least one composite section having a first density. The at least two insert sections having a second mass density, which is less than the first mass density. The composite outer structure and the alternating stack of at least one composite section and at least two insert sections together define an airfoil portion that meets all mechanical load carrying requirements of said hybrid turbine blade such that no load transfer needs to occur through said at least two insert sections. | 10-02-2014 |
20140294595 | ROTOR BLADE ASSEMBLY FOR WIND TURBINE HAVING LOAD REDUCTION FEATURES - Rotor blade assemblies for wind turbines are provided. In one embodiment, a rotor blade assembly includes a rotor blade having exterior surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge each extending between a tip and a root. The rotor blade further defines a span and a chord. A span-wise portion of the pressure side includes along a chord-wise cross-section a plurality of inflection points. The plurality of inflection points include a first inflection point and a second inflection point, the first and second inflections points positioned within approximately 50% of the chord from the leading edge. | 10-02-2014 |
20140296694 | METHOD AND SYSTEM FOR ULTRASOUND NEEDLE GUIDANCE - A method and medical system for providing needle guidance. The method and system includes acquiring ultrasound data while manipulating a needle and tracking the needle tip while manipulating the needle. The method and system includes displaying a first live image including at least a portion of the needle in a first viewing pane and displaying a second live image including the needle tip in a second viewing pane at the same time as the first live image. The second live image includes a portion of the first live image at a greater level of zoom than the first live image. | 10-02-2014 |
20140315029 | REPAIR PROCESS AND A REPAIRED COMPONENT - Matrix composite component repair processes are disclosed. The matrix composite repair process includes applying a repair material to a matrix composite component, securing the repair material to the matrix composite component with an external securing mechanism and curing the repair material to bond the repair material to the matrix composite component during the securing by the external securing mechanism. The matrix composite component is selected from the group consisting of a ceramic matrix composite, a polymer matrix composite, and a metal matrix composite. In another embodiment, the repair process includes applying a partially-cured repair material to a matrix composite component, and curing the repair material to bond the repair material to the matrix composite component, an external securing mechanism securing the repair material throughout a curing period, In another embodiment, the external securing mechanism is consumed or decomposed during the repair process. | 10-23-2014 |
20140318141 | HOT STREAK ALIGNMENT FOR GAS TURBINE DURABILITY - Embodiments of hot streak alignment for gas turbine durability include structures and methods to align hot streaks with the leading edges of aligned first stage nozzle vanes in order to improve mixing of the hot streaks with cooling air at a stator nozzle of a first stage turbine and reduce usage of cooling air at first stage non-aligned stator nozzle vanes disposed adjacent to the aligned stator vanes. | 10-30-2014 |
20140321977 | DURABLE TURBINE VANE - A durable nozzle vane includes a leading edge where hot combustion gas impinges on the vane, a pressure side extending from the leading edge to a trailing edge and a suction side extending from the leading edge to the trailing edge, a blunt region along the suction side between the leading edge and a high curvature region, the blunt region having small curvature in the length between the leading edge and the high curvature region allowing for at least two rows of cooling apertures. | 10-30-2014 |
20140321994 | HOT GAS PATH COMPONENT FOR TURBINE SYSTEM - A hot gas path component for a turbine system is disclosed. The hot gas path component includes a shell and one or more porous media having an exterior surface and an interior surface and positioned adjacent the shell. The one or more porous media is configured to include varying permeability in one of an axial direction, a radial direction, an axial and a radial direction, an axial and a circumferential direction, a radial and a circumferential direction or an axial, a radial and a circumferential direction, the porous media is positioned adjacent the shell. The one or more porous media is further configured to control one of an axial, a radial, an axial and a radial, an axial and a circumferential, a radial and a circumferential or an axial, a radial and a circumferential flow of a cooling medium flowing therethrough. | 10-30-2014 |
20140322008 | Method and Apparatus for Cooling Gas Turbine and Rotor Blades - Apparatuses and methods are taught for cooling a turbine blade wherein at least one circuit is isolated along a cool suction side of the blade and the circuit turns aft toward a trailing edge. | 10-30-2014 |
20140327023 | PHOSPHOR ASSEMBLY FOR LIGHT EMITTING DEVICES - A method for fabricating a light emitting device is disclosed. The light emitting device includes a light emitting diode (LED). The method includes disposing a layered phosphor composite or a thick phosphor composite radiationally coupled to the LED to form a light emitting device. The layered phosphor composite includes a first phosphor layer including a yellow-emitting phosphor over a second phosphor layer including manganese-doped potassium fluorosilicate (PFS). The second phosphor layer is disposed closer to the LED. The mass of the PFS of this light emitting device is at least 15% less than mass of the PFS in a reference light emitting device that has the same color temperature as the above mentioned light emitting device, but includes a blend of PFS and the yellow emitting phosphor instead of a layered configuration or has a decreased thickness. | 11-06-2014 |
20140338338 | SYSTEM AND METHOD FOR TUBE LEVEL AIR FLOW CONDITIONING - A system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle includes multiple mixing tubes. Each mixing tube includes an annular wall disposed about a central passage and an air inlet region configured to be disposed about a fuel injector extending into the central passage. The central passage extends from an upstream end to a downstream end of the annular wall relative to a direction of flow through the central passage. The air inlet region includes an air entry surface of the annular wall that gradually decreases in diameter in the direction of flow. | 11-20-2014 |
20140338339 | SYSTEM AND METHOD HAVING MULTI-TUBE FUEL NOZZLE WITH MULTIPLE FUEL INJECTORS - A system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle includes multiple fuel injectors. Each fuel injector is configured to extend into a respective premixing tube of a plurality of mixing tubes. Each fuel injector includes a body, a fuel passage, and multiple fuel ports. The fuel passage is disposed within the body and extends in a longitudinal direction within a portion of the body. The multiple fuel ports are disposed along the portion of the body and coupled to the fuel passage. A space is disposed between the portion of the body with the fuel ports and the respective premixing tube. | 11-20-2014 |
20140338340 | SYSTEM AND METHOD FOR TUBE LEVEL AIR FLOW CONDITIONING - A system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle includes multiple tubes. Each tube includes a first end, a second end, and an annular wall disposed about a central passage. The first end is configured to be disposed about a fuel injector. Each tube also includes an air flow conditioner having multiple air ports disposed adjacent the first end. The multiple air ports extend through the wall into the central passage. | 11-20-2014 |
20140338342 | FUEL INJECTOR HAVING AN IGNITOR FOR IGNITING A COMBUSTOR OF A GAS TURBINE - A fuel injector for a combustor of a gas turbine includes an annular main body. A fluid circuit extends at least partially through the main body. An axially extending inner body extends within the main body. The inner body at least partially defines an inner chamber that extends at least partially through the inner body. The inner chamber is in fluid communication with the fluid circuit. A retractable igniter extends linearly outward from the inner chamber when the fluid circuit is charged. | 11-20-2014 |
20140338349 | Combustion Nozzle with Floating Aft Plate - The present application provides a combustion nozzle for use with a gas turbine engine. The combustion nozzle may include a number of mixing tubes, an outer shell surrounding the mixing tubes, and a floating aft plate assembly. The floating plate assembly may enclose the outer shell. The mixing tubes may extend through the aft plate assembly. | 11-20-2014 |
20140338356 | System Having a Multi-Tube Fuel Nozzle with an Aft Plate Assembly - A system including a first multi-tube fuel nozzle including a plurality of first tubes extending in an axial direction, wherein each first tube of the plurality of first tubes includes a first air inlet, a first fuel inlet, and a first fuel-air mixture outlet, a second multi-tube fuel nozzle including a plurality of second tubes extending in an axial direction, wherein each second tube of the plurality of second tubes includes a second air inlet, a second fuel inlet, and a second fuel-air mixture outlet, and an aft plate including a plurality of first tube apertures and a plurality of second tube apertures, wherein the plurality of first tubes extend to the plurality of first tube apertures, and the plurality of second tubes extend to the plurality of second tube apertures. | 11-20-2014 |
20140341702 | FLOW SLEEVE FOR THERMAL CONTROL OF A DOUBLE-WALL TURBINE SHELL AND RELATED METHOD - A turbine casing includes at least one shell adapted to enclose one or more turbine stages in a gas turbine engine; an air inlet in the at least one shell; a flow sleeve secured to an inside surface of the at least one shell, the flow sleeve comprising at least two arcuate segments. Each arcuate segment includes an arcuate base, a pair of sidewalls extending radially outwardly of the base thereby forming a circumferentially-extending flow channel defined by the base, the sidewalls and the inside surface. The air inlet is aligned with the flow channel and the sleeve is configured to distribute air flowing in the channel into spaces proximate the one or more turbine stages in circumferential, radial and axial directions, including along the inside surface of the at least one shell. | 11-20-2014 |
20140341723 | GAS TURBINE VANE INSERT TO CONTROL PARTICULATE DEPOSITION - A guide tube assembly in one embodiment includes a guide tube and a collection impingement feature. The guide tube includes an inlet and at least one first impingement opening. The inlet is configured to direct a cooling air flow along the length of the tube in an inlet direction. The at least one impingement feature is configured to direct at least a portion of the cooling air received via the inlet along a first impingement direction. The collection impingement feature receives the at least a portion of the cooling airflow directed in the first impingement direction, collects particulate matter from the cooling airflow upon impingement of the cooling airflow with the collection impingement feature, and directs the at least a portion of the cooling air flow in a second impingement direction toward a surface of the turbine component to be cooled by the cooling air flow. | 11-20-2014 |
20140341750 | PROCESS FOR SELECTIVELY PRODUCING THERMAL BARRIER COATINGS ON TURBINE HARDWARE - A process of depositing a ceramic coating on an airfoil component and the component formed thereby is provided. The process includes depositing a bond coat on an airfoil component including on a trailing edge region thereof that defines a trailing edge of the airfoil component, within holes located within the trailing edge region and spaced apart from the trailing edge, and on lands located within the trailing edge region and between the holes. A ceramic coating is then deposited on the bond coat including on the trailing edge region of the airfoil component, within the holes located within the trailing edge region, and on the lands between the holes. The ceramic coating within the holes is selectively removed without completely removing the ceramic coating on the trailing edge region and the lands between the holes. | 11-20-2014 |
20140345253 | MULTI-NOZZLE FLOW DIVERTER FOR JET ENGINE - An exhaust system for a variable cycle aircraft engine. The exhaust system comprises a core exhaust for bypass air and hot gases of combustion. The core exhaust includes a convergent-divergent nozzle. The convergent-divergent nozzle is formed from a plurality of flaps and seals. The exhaust system comprises a third air duct for a third stream of air. The third stream of air is selectively exhausted from the third duct through a secondary nozzle or divergent slots in the convergent-divergent nozzle, or both depending upon the flight mode. A diverter valve is positioned in the third stream duct to selectively control the flow of third stream air through the secondary nozzle, the divergent slots and combinations thereof. | 11-27-2014 |
20140345254 | SECONDARY NOZZLE FOR JET ENGINE - A third stream duct producing a third air stream at reduced pressure that is exhausted through a separate nozzle that is concentric with the main or primary engine nozzle. The third stream exhaust air from the separate concentric nozzle is exhausted to a location at which pressure is ambient or sub-ambient. The location at which the third stream air is exhausted contributes to the thrust of the aircraft. The airstream from the third air duct is exhausted through an exhaust nozzle of the third duct that is positioned at the interface between the aft of the airframe and the leading edge of the engine outer flaps. This location is a low pressure region that has a recirculation zone. The exhaust of third stream air to this low pressure region substantially reduces or eliminates this recirculation zone and associated boat tail drag, thereby improving the efficiency of the engine. | 11-27-2014 |
20140348642 | CONJOINED GAS TURBINE INTERFACE SEAL - A device including a conjoined laminate interface seal shaped for reducing inter-seal gap (e.g., an angled gap, an ‘L’-shaped gap, etc.) leakage in gas turbines is disclosed. In one embodiment, a seal device for a gas turbine includes: a first flange shaped to be disposed within a first slot of a first arcuate component and a first adjacent slot of a second arcuate component; a conjoined layer connected to a first surface of the first flange, the first surface configured to face a working fluid flow of the gas turbine; and a second flange shaped to be disposed within a second slot of the first arcuate component and a second adjacent slot of the second arcuate component, the second flange including a second surface connected to the conjoined layer. | 11-27-2014 |
20140352321 | GAS TURBINE ENGINE SYSTEM AND AN ASSOCIATED METHOD THEREOF - A gas turbine engine system includes a compressor, a combustor, and a turbine. The combustor is coupled to the compressor and disposed downstream of the compressor. The combustor includes a secondary combustor section coupled to a primary combustor section and disposed downstream of the primary combustor section. The combustor also includes a transition nozzle coupled to the secondary combustor section and disposed downstream of the secondary combustor section. The combustor further includes an injector coupled to the secondary combustor section, for injecting an air-fuel mixture to the secondary combustor section. The turbine is coupled to the combustor and disposed downstream of the transition nozzle; wherein the transition nozzle is oriented substantially tangential to the turbine. | 12-04-2014 |
20140356134 | DAMPERS FOR FAN SPINNERS OF AIRCRAFT ENGINES - Dampers for fan spinners of aircraft engines are disclosed. An example fan module for a gas turbine engine may include a fan disk; fan blades mounted to the fan disk and extending radially therefrom; a fan spinner operatively coupled to the fan disk at an axially upstream position; and/or one or more elastic vibration dampers operatively interposing the fan spinner and the fan disk. The elastic vibration dampers may be disposed circumferentially around an interface between the fan spinner and the fan disk and may be compressed axially and/or radially. | 12-04-2014 |
20140360193 | SUPPORT FRAME AND METHOD FOR ASSEMBLY OF A COMBUSTION MODULE OF A GAS TURBINE - A support frame for assembling a combustion module for a gas turbine includes a base plate disposed at a bottom end of the support frame and a support plate that is vertically separated from the base plate by one or more vertical support members. The support plate defines an opening that is sized to allow a portion of the combustion module to pass therethrough. A support block extends vertically from the base plate towards the support plate where the support block defines one or more fastener holes for connecting an aft end of a combustion liner of the combustion module to the support block. A central support column extends vertically from the base plate towards the support plate. A horizontal support extends radially outward from the central support column to align the combustion liner with the opening in the support plate. | 12-11-2014 |