Patent application number | Description | Published |
20080289716 | LOW TENSILE CREEP BELT - An endless fabric belt subjected to a substantial running tension. The belt has an endless woven fabric formed from a plurality of MD (machine direction) ultra high molecular weight polymer strands approaching zero creep at high tensile loads. A plurality of CMD (cross machine direction) strands are interwoven with the MD strands. The plurality of MD strands have first and second ends spliced to one another to form an endless belt, the splices forming a significant linear MD overlap of about 30 cm with each other. | 11-27-2008 |
20090075543 | MALLEABLE POLYMER MONOFILAMENT FOR INDUSTRIAL FABRICS - The present invention relates to malleable polymer monofilaments that show shape malleability under heat and stress. The monofilaments can be used in closely woven industrial fabrics, especially in paper machine fabrics, as weft materials that protect load bearing warp yarns for better wear resistance. | 03-19-2009 |
20090311529 | HIGH TENACITY THERMOPLASTIC POLYURETHANE MONOFILAMENT AND PROCESS FOR MANUFACTURING THE SAME - The present invention relates to a high tenacity polyurethane monofilament and a process for manufacturing the same, comprising of orienting and dynamic annealing of a polyurethane-containing monofilament. In addition to high tenacity, the present invention imparts reduced shrinkage and elongation to monofilament fibers, facilitating the use of thermoplastic elastomers in industrial fabrics, particularly in paper machine clothing (PMC). The brief abstract is neither intended to define the invention disclosed in this specification nor intended to limit the scope of the invention in any way. | 12-17-2009 |
20100099320 | Pet yarns with improved loop tensile properties - Poly(ethylene terephthalate) monofilaments having improved loop strength and toughness as well as improved tensile strength and tensile toughness. The yarns can have a loop toughness of at least 2 gf/den, a loop tenacity of at least 7 gf/den, a tensile toughness of at least 0.9 gf/den, a tensile tenacity of at least 4 gf/den, and a DSC crystallinity of at least 35%. A process for the production of poly(ethylene terephthalate) monofilaments includes melt extrusion, orientation of the extrudates by stretching, and further stretching as well as heat treating the stretched monofilaments. Industrial fabrics, especially fabrics for paper machine clothing, can be made of such monofilaments as load bearing yarns that resist loop failure and that resist fabric creep at high temperature and high load. | 04-22-2010 |
Patent application number | Description | Published |
20100073942 | LAMP HOLDER - A lamp holder comprising a lamp holder base, a lamp holder housing and a microswitch. In a preferred embodiment, the lamp holder base is substantially cup-shaped around a longitudinal axis and has an arcuate actuator finger coupled to and shielded within the lamp holder base. The lamp holder housing is removably coupleable to the lamp holder base, and the microswitch is mounted within the lamp holder housing, wherein the microswitch is activated by the arcuate actuator finger when the lamp holder housing is coupled to the lamp holder base. | 03-25-2010 |
20100307164 | SYSTEM FOR CONDITIONING THE AIRFLOW ENTERING A TURBOMACHINE - An embodiment of the present invention provides an air conditioning system (ACS) for conditioning the airstream entering an air-breathing machine, such as, but not limiting of, a gas turbine. Conditioning may be considered a process that adjusts at least one physical property of the airstream. The physical property may comprise: a wet-bulb temperature, a dry-bulb temperature, relative humidity, density, or the like. In an embodiment of the present invention, the major components of the ACS may be located in a single structure, which may be considered a module. Depending on the application of the ACS, multiple modules may be physically and/or operationally integrated on the air-breathing machine. | 12-09-2010 |
20100319384 | SYSTEM FOR COOLING GAS TURBINE INLET AIR - A system includes a turbine air quality device. The turbine air quality device includes a liquid desiccant path configured to circulate a liquid desiccant through an air flow directed to a turbine inlet. The turbine air quality device also includes a porous media disposed in the liquid desiccant path, wherein the porous media is configured to pass the air flow in direct contact with the liquid desiccant. | 12-23-2010 |
20110042836 | SYSTEM FOR CONDITIONING THE AIRFLOW ENTERING A TURBOMACHINE - An embodiment of the present invention provides an air conditioning system (ACS) for conditioning the airstream entering an air-consuming machine, such as, but not limiting of, a gas turbine. Conditioning may be considered a process that adjusts at least one physical property of the airstream. The physical property may comprise: a wet-bulb temperature, a dry-bulb temperature, relative humidity, density, or the like. In an embodiment of the present invention, the major components of the ACS may be located in a single structure, which may be considered a module. Depending on the application of the ACS, multiple modules may be physically and/or operationally integrated on the air-consuming machine. An alternate embodiment of the ACS may comprise a module having multiples stages. Here, each stage may operate independently other stages. Furthermore, each stage may use a separate fluid from other stages. | 02-24-2011 |
20110173947 | SYSTEM AND METHOD FOR GAS TURBINE POWER AUGMENTATION - A gas turbine power augmentation system and method are provided. The system includes a chiller, a controller, a heat exchanger, and a gas turbine inlet air flow. The chiller may be operable to chill a coolant flow using energy from a heat source. The controller may be operably connected to the chiller and configured to regulate operation of the chiller in relation to at least one environmental condition. The heat exchanger may be in fluid communication with the chiller and configured to allow the coolant flow to pass through the heat exchanger. The gas turbine inlet air flow may be directed through the heat exchanger before entering a gas turbine inlet, allowing the air flow to interact with the coolant flow, thereby cooling the air flow. | 07-21-2011 |
20110299973 | Pre-Filtration Bypass For Gas Turbine Inlet Filter House - An inlet filter house is provided for use with a turbine engine including an inlet duct. The inlet filter house is coupled to the inlet duct and includes an inlet hood including a filter assembly selectively positionable between an operating position and a bypass position. An actuating assembly is coupled to the filter assembly to selectively position the filter assembly. A sensor is configured to detect at least one operating parameter. A controller is coupled to the sensor for actuating the actuating assembly based on the at least one operating parameter. | 12-08-2011 |
20120031596 | HEAT EXCHANGER MEDIA PAD FOR A GAS TURBINE - A media sheet for a heat exchanger is disclosed. The media sheet includes a first layer having a first outer surface and a second layer having a second outer surface. The first and second layers define a plurality of passages extending therebetween. At least one of the first and second outer surfaces comprises a plurality of depressions. The plurality of depressions further define the plurality of passages therebetween. The media sheet is polymer fiber-based and wettable. | 02-09-2012 |
20120033435 | LAMP HOLDER - A lamp holder comprising a lamp holder base, a lamp holder housing and a microswitch. In a preferred embodiment, the lamp holder base has a longitudinal axis and an actuator finger coupled to and shielded within the lamp holder base. The lamp holder housing is removably coupleable to the lamp holder base, and the microswitch is mounted within the lamp holder housing, wherein the microswitch is activated by the actuator finger when the lamp holder housing is inserted into and rotated with respect to the lamp holder base. | 02-09-2012 |
20120073215 | ENCLOSURE FOR POWER GENERATION SYSTEM - An enclosure for a power generation system is disclosed. The enclosure includes a plurality of sidewalls and a roof extending generally transverse to the plurality of sidewalls. The enclosure further includes a plurality of latches, each of the plurality of latches associated with one of the roof or a sidewall, and a plurality of engagement features, each of the plurality of engagement features associated with the other of the roof or a sidewall. Each of the plurality of latches is configured to engage one of the plurality of engagement features to releasably fasten the roof to the plurality of sidewalls. | 03-29-2012 |
20120087783 | SYSTEM AND METHOD FOR TURBINE COMPARTMENT VENTILATION - According to an aspect of the invention, a method for ventilating a turbine compartment is provided, the method comprising directing an air flow from an air intake to a first air conduit, transferring a first heat between the air flow and a first fluid within a heat exchange apparatus and pumping the first fluid through a fluid circuit in fluid communication with the heat exchange apparatus, wherein a portion of the fluid circuit is located underground. The method further includes transferring a second heat between the first fluid and a surrounding ground and directing a conditioned air flow from the heat exchange apparatus to a turbine compartment via a second air conduit. | 04-12-2012 |
20130199150 | STEAM INJECTION ASSEMBLY FOR A COMBINED CYCLE SYSTEM - A steam injection assembly for a combined cycle system includes a heat recovery system having at least one superheater configured to generate a steam supply. Also included is a gas turbine system having an inlet and a compressor, wherein the inlet receives an air supply and the steam supply for combined injection into the compressor. | 08-08-2013 |
20130199192 | SYSTEM AND METHOD FOR GAS TURBINE NOX EMISSION IMPROVEMENT - In one embodiment of the present disclosure, a gas turbine system for NOx emission reduction and part load efficiency improvement is described. The system includes a gas turbine having a compressor which receives inlet-air. A direct-contact heat exchanger heats and humidifies the inlet-air before the inlet-air flows to the compressor. Heating the inlet-air reduces an output of the gas turbine and extends the turndown range. Humidifying the inlet-air can lower NOx emissions from the gas turbine unit. | 08-08-2013 |
20130199196 | SYSTEM AND METHOD FOR GAS TURBINE PART LOAD EFFICIENCY IMPROVEMENT - In one embodiment of the present disclosure, a gas turbine system for part load efficiency improvement is described. The system includes a gas turbine having a compressor which receives inlet-air. An evaporative cooler system using heated fluid heats the inlet-air before the inlet-air flows to the compressor. Heating the inlet-air reduces an output of the gas turbine and extends the turndown range. | 08-08-2013 |
20130199202 | SYSTEM AND METHOD FOR GAS TURBINE INLET AIR HEATING - In one embodiment of the present disclosure, a gas turbine system for part load efficiency improvement and anti-icing within the inlet and at the compressor inlet is described. The system includes a gas turbine having a compressor which receives inlet-air. A direct-contact heat exchanger heats the inlet-air before the inlet-air flows through the inlet and to the compressor. Heating the inlet-air reduces an output of the gas turbine and extends the turndown range, and avoids ice-forming conditions within the inlet and at the compressor inlet bellmouth. The direct-contact heat exchanger may also be configured to act as an evaporative cooler, air chiller, or use liquid dessicant. | 08-08-2013 |
20130255208 | QUICK ENGAGEMENT METHOD FOR GAS TURBINE INLET FILTER INSTALLATION AND REPLACEMENT - A filter installation arrangement and an associated method of installing a filter assembly to a partition. A filter assembly includes a filter element that extends along a longitudinal axis. The filter element includes an end cap disposed at an end of the filter element. An adjustment device of the installation arrangement axially displaces the end cap of the filter element in a first direction. An insert portion is inserted adjacent the end cap subsequent to the axial displacement of the end cap. The insert portion is configured to limit axial displacement of the end cap in a second direction that is opposite the first direction. | 10-03-2013 |
20140069076 | GAS TURBINE INLET FOGGING SYSTEM USING ELECTROHYDRODYNAMIC (EHD) ATOMIZATION - A gas turbine inlet fogging system using electrohydrodynamic (EHD) atomization is disclosed. In one embodiment, the inlet fogging system includes: a gas turbine system including an air inlet duct, and a plurality of electrohydrodynamic (EHD) nozzles coupled to a water supply, the plurality of EHD nozzles configured to provide a water-spray for reducing a temperature of inlet air drawn into the air inlet duct. In another embodiment, an inlet fogging system for a gas turbine system includes: a plurality of electrohydrodynamic (EHD) nozzles, and a water supply in fluid communication with the plurality of EHD nozzles. | 03-13-2014 |
20140123674 | Inlet Bleed Heat System with Integrated Air Knife/Silencer Panels - The present application provides an inlet bleed heat system for supplying a flow of bleed air to a flow of incoming air into a compressor of a gas turbine engine. The inlet bleed heat system may include an air knife and a silencer panel. The air knife may include a compressor bleed air port in communication with the flow of bleed air and a discharge gap to discharge the flow of bleed air into the flow of incoming air. The air knife may and the silencer panel may form an integrated air knife/silencer panel. | 05-08-2014 |
20140230444 | System and Method for Reducing Back Pressure in a Gas Turbine System - In a first embodiment, a system, including an exhaust duct configured to flow an exhaust gas, and an air injection system coupled to the exhaust duct, wherein the air injection system comprises a first air injector configured to inject air into the exhaust duct to assist flow of the exhaust gas through the exhaust duct. | 08-21-2014 |
20140321967 | Gas Turbine Power Augmentation System - The present application provides a power augmentation system for use with a gas turbine engine. The power augmentation system may include a compressor discharge manifold, an inlet bleed heat system in communication with the compressor discharge manifold via an inlet bleed heat line, and an auxiliary compressor in communication with the compressor discharge manifold via the inlet bleed heat line. | 10-30-2014 |
Patent application number | Description | Published |
20100073408 | ENERGY ACTIVATED PRINTING PROCESS - Reactive inks and methods of generating an image on a substrate using both reactive and heat activated inks are presented. An image is printed on a substrate, without reacting the reagents in the ink. Subsequently, the reagents are reacted to fix the image to a substrate, with substantial permanency and fastness. Sublimation or similar heat activated dyes are printed are also printed on the substrate. The sublimation or similar heat activated dyes are activated, and have an affinity for polymer that is applied to the substrate. | 03-25-2010 |
20100091058 | HEAT ACTIVATED PRINTING PROCESS - Reactive inks and methods of generating an image on a substrate using both reactive and heat activated inks are presented. An image is printed on a substrate, without reacting the reagents in the ink. Subsequently, the reagents are reacted to fix the image to a substrate, with substantial permanency and fastness. Sublimation or similar heat activated dyes are printed are also printed on the substrate. The sublimation or similar heat activated dyes are activated, and have an affinity for polymer that is applied to the substrate. | 04-15-2010 |
20100129572 | IMAGE RECEIVER MEDIA AND PRINTING PROCESS - A transfer medium is provided for receiving images formed on the medium by inks or toners comprising thermally diffusible colorants, including disperse dye and sublimation dye, and methods of using the medium to present images on substrates. The medium provides an opaque layer that allows transfer of the image from the medium to a substrate, and provides a background for the image when the image is transferred to a dark colored substrate, so that the dark colored substrate does not obscure the image. | 05-27-2010 |
20110111188 | PROCESS FOR FORMING AN IMAGE ON A TRANSPARENT ACRYLIC ARTICLE - A method of imaging thermoplastics, such as acrylic glass, is presented. An image is formed on a transfer sheet or medium, and is heat transferred to the acrylic glass substrate on which the image is to permanently appear. An opaque pass-through coating is applied to one surface of the clear or transparent acrylic glass article. Heat activatable dye forms the image, and the heat activatable dye, when heat activated in close relationship to the opaque pass-through coating, passes through the opaque pass-through coating to the thermoplastic substrate. The image reflects light through the thermoplastic material and is visible through the material and from the side opposite the opaque coating. The opaque pass-through coating layer permanently bonds to the acrylic glass surface. | 05-12-2011 |
20140161996 | PROCESS FOR FORMING AN IMAGE ON A TRANSPARENT ACRYLIC ARTICLE - A method of imaging acrylic glass is presented. An image is formed on a transfer sheet or medium, and is heat transferred to the acrylic glass substrate on which the image is to permanently appear. An opaque pass-through coating is applied to one surface of the clear or transparent acrylic glass article. Heat activatable dye forms the image, and the heat activatable dye, when heat activated in close relationship to the opaque pass-through coating, passes through the opaque pass-through coating to the acrylic glass substrate. The image reflects light through the acrylic glass and is visible through the material and from the side opposite the opaque coating. The opaque pass-through coating layer permanently bonds to the acrylic glass surface. | 06-12-2014 |
Patent application number | Description | Published |
20110236183 | BIMETALLIC SPLINE SEAL - A spline seal for a hot gas path component is provided. The spline seal may include a first metal layer and a second metal layer. The first metal layer may have a first volumetric thermal expansion coefficient. The second metal layer may be disposed adjacent the first metal layer and have a second volumetric thermal expansion coefficient. The second volumetric thermal expansion coefficient may be higher than the first volumetric thermal expansion coefficient. When the spline seal is exposed to a heat source, the first and second metal layers may deform to provide a seal between the hot gas path component and an adjacent hot gas path component. | 09-29-2011 |
20120114480 | SYSTEM AND METHOD FOR COOLING A TURBINE BUCKET - A turbine bucket includes an airfoil, a platform adjacent to the airfoil, and a shank adjacent to the platform. The shank defines a shank cavity, and a divider in the shank cavity creates a pressure differential across the shank cavity. A method for cooling a turbine bucket includes directing a fluid to a forward shank cavity and creating a pressure differential between the forward shank cavity and an aft shank cavity. | 05-10-2012 |
20130094969 | SYSTEM FOR SEALING A SHAFT - An embodiment of the present invention takes the form of a seal that may substantially reduce cross-shank leakage between components mounted on a shaft. Embodiments of the seal may be connected to a wide variety of rotatable components including, but not limited to, compressor blades, turbine buckets, or the like. | 04-18-2013 |
20130315748 | COOLING STRUCTURES IN THE TIPS OF TURBINE ROTOR BLADES - A turbine rotor blade used in a gas turbine engine, which includes an airfoil having a tip at an outer radial edge, is described. The airfoil includes a pressure sidewall and a suction sidewall that join together at a leading edge and a trailing edge of the airfoil, the pressure sidewall and the suction sidewall extending from a root to the tip. The tip includes a tip plate and, disposed along a periphery of the tip plate, a rail. The rail includes a microchannel connected to a coolant source. | 11-28-2013 |
20130315749 | COOLING STRUCTURES IN THE TIPS OF TURBINE ROTOR BLADES - A turbine rotor blade for a gas turbine engine is described. The turbine rotor blade includes an airfoil that includes a tip at an outer radial end. The tip includes a rail that defines a tip cavity; and the rail includes a circumscribing rail microchannel. The circumscribing rail microchannel is a microchannel that extends around at least a majority of the length of the inner rail surface. | 11-28-2013 |
20140030101 | TURBINE BUCKET WITH SQUEALER TIP - A turbine bucket having an airfoil is disclosed. The airfoil may include a pressure side wall and a suction side wall extending between a leading edge and a trailing edge. In addition, the airfoil may include a base and a tip disposed opposite the base. The tip may include a tip floor and pressure and suction side tip walls extending outwardly from the tip floor. Moreover, the tip may include an intermediate tip wall extending outwardly from the tip floor between the pressure and suction side tip walls. The intermediate tip wall may define a height that is less than a height of the pressure and/or suction side tip walls. | 01-30-2014 |
20140030102 | TURBINE BUCKET WITH NOTCHED SQUEALER TIP - A turbine bucket having an airfoil is disclosed. The airfoil may include a pressure side and a suction side extending between a leading edge and a trailing edge. In addition, the airfoil may include a tip. The tip may include a tip floor and a tip wall extending outwardly from the tip floor. The tip wall may include an inner surface defining an inner perimeter of the tip wall. Moreover, a plurality of notches may be defined by the inner surface around at least a portion of the inner perimeter. | 01-30-2014 |
20140064984 | COOLING ARRANGEMENT FOR PLATFORM REGION OF TURBINE ROTOR BLADE - A platform cooling arrangement in a turbine rotor blade having a platform at an interface between an airfoil and a root. The platform may include a pressure side slashface and a suction side slashface. The platform cooling arrangement may include: a cooling channel formed within the interior of the platform, the cooling channel extending from a first end toward one of the pressure side slashface and the suction side slashface. At a second end, the cooling channel may include a pocket. The pocket may include an abrupt increase in cross-sectional flow area just before the cooling channel reaches the slashface. | 03-06-2014 |
20140099193 | ROTOR BLADE AND METHOD FOR COOLING THE ROTOR BLADE - A rotor blade includes an airfoil having a tip plate that extends across an outer radial end. A rim extends radially outward from the tip plate and surrounds at least a portion of the airfoil and includes a concave portion opposed to a convex portion. A plurality of dividers extend between the concave and convex portions to define a plurality of pockets between the concave and convex portions at the outer radial end. A plurality of cooling passages through the tip plate provide fluid communication through the tip plate to the plurality of pockets. A first fluid passage in at least one divider provides fluid communication between adjacent pockets across the at least one divider. | 04-10-2014 |
20140112753 | SEALING ARRANGEMENT FOR A TURBINE SYSTEM AND METHOD OF SEALING BETWEEN TWO TURBINE COMPONENTS - A sealing arrangement for a turbine system includes a bucket having an outer tip and at least one bucket ridge extending radially outwardly from the outer tip, the at least one bucket ridge comprising an abradable material. Also included is a stationary shroud disposed radially outwardly from the outer tip of the bucket. Further included is at least one shroud ridge extending radially inwardly from the stationary shroud toward the outer tip of the bucket, the at least one shroud ridge comprising the abradable material. | 04-24-2014 |
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 |
20140161625 | TURBINE COMPONENT HAVING COOLING PASSAGES WITH VARYING DIAMETER - Systems and devices configured to cool turbine components in a turbine by passing a cooling flow through the turbine component via a cooling passage with a variable diameter are disclosed. In one embodiment, a turbine component includes: at least one elongated cooling passage extending from a root of the bucket to a tip of the bucket, wherein the elongated cooling passage has a variable diameter along a length of the bucket. | 06-12-2014 |
20150064010 | Turbine Bucket Tip Shroud - The present application provides a turbine bucket. The turbine bucket may include an airfoil and a tip shroud attached to the airfoil. The tip shroud may include a cooling core and an enhanced cooling surface. | 03-05-2015 |
Patent application number | Description | Published |
20140045033 | SEPARATOR MEMBRANES FOR LITHIUM ION BATTERIES AND RELATED METHODS - A battery separator for a secondary lithium battery includes a microporous/porous membrane with a ceramic coating of one or more layers, a layer may include one or more particles and/or binders. | 02-13-2014 |
20140079980 | THIN BATTERY SEPARATORS AND METHODS - In accordance with at least selected aspects, objects or embodiments, optimized, novel or improved membranes, battery separators, batteries, and/or systems and/or related methods of manufacture, use and/or optimization are provided. In accordance with at least selected embodiments, the present invention is related to novel or improved battery separators that prevent dendrite growth, prevent internal shorts due to dendrite growth, or both, batteries incorporating such separators, systems incorporating such batteries, and/or related methods of manufacture, use and/or optimization thereof. In accordance with at least certain embodiments, the present invention is related to novel or improved ultra thin or super thin membranes or battery separators, and/or lithium primary batteries, cells or packs incorporating such separators, and/or systems incorporating such batteries, cells or packs. In accordance with at least particular certain embodiments, the present invention is related to shutdown membranes or battery separators, and/or lithium primary batteries, cells or packs incorporating such separators, and/or systems incorporating such batteries, cells or packs. | 03-20-2014 |