Patent application number | Description | Published |
20080218006 | METHOD OF ASSEMBLING A ROTOR SHAFT ASSEMBLY - A method of assembling a rotor shaft assembly is provided. The method includes assembling a self-aligning bearing seat from a first assembly and a second assembly such that the self-aligning bearing seat substantially circumscribes a rotor shaft. The method also includes creating an interface defined between the first assembly and the second assembly, such that when the rotor shaft experiences misalignment the interface accommodates misalignment of the rotor shaft. | 09-11-2008 |
20090064587 | NOZZLES FOR USE WITH GASIFIERS AND METHODS OF ASSEMBLING THE SAME - A method for assembling a nozzle is provided. The method includes providing an injection tube that includes an outlet that is configured to discharge fuel therefrom. A face plate is also provided that extends about the injection tube such that the face plate substantially circumscribes the outlet. A cooling chamber is defined within the injection tube and configured to channel cooling fluid adjacent to the face plate. At least one surface defining the cooling chamber is configured to disrupt a flow of the cooling fluid flowing through the cooling chamber. | 03-12-2009 |
20090092494 | DISK ROTOR AND METHOD OF MANUFACTURE - A disk rotor comprises a hub having a bore, and a plurality of spoke segments radially extending from the hub, each spoke segment including a base portion being attached to the hub and a rim portion, wherein the rim portion includes one or more airfoils integrally formed thereon, the plurality of spoke segments collectively forming a ring. | 04-09-2009 |
20090220343 | HUB PITCH GEAR REPAIR METHOD - A method for repairing a hub pitch gear assembly. The method includes providing a ring assembly for adjusting a pitch angle of a wind turbine blade having a plurality of gear teeth. A segment of the ring assembly is removed, the segment including at least a portion of at least one gear tooth, to form a repair cavity. A repair segment configured to mate the repair cavity is provided and the repair segment is directed into the repair cavity and fastened in position. A repaired pitch gear assembly and wind turbine are also disclosed. | 09-03-2009 |
20090285677 | Systems And Methods For Cooling Heated Components In A Turbine - Systems and methods for cooling heated components in a turbine are provided. According to one embodiment, a system for cooling a turbine is provided that may include at least one liquid source which may include a coolant liquid. The system may also include at least one liquid nozzle in fluid communication with the liquid source or sources and operable to deliver the coolant liquid in an atomized form adjacent to at least one heated turbine component positioned in a hot gas path of the turbine. Upon delivering the atomized coolant liquid adjacent to the heated turbine component or components, at least a portion of the coolant liquid substantially changes phase to a gas. | 11-19-2009 |
20100101203 | FEED INJECTOR COOLING JACKET - A feed injector for providing feed to a gasifier of an integrated gasification combined cycle system includes: a base leading to a body and terminating in a tip, the tip including an exitway for injecting feed into the gasifier; the tip including a mating of an inner shell disposed within a core insert, with an outer shell in which the core insert is disposed; a plurality of spacers disposed between the core insert and inner shell thus providing an inner annular space, and another plurality of spacers disposed between the core insert and outer shell thus providing an outer annular space; the inner annular space and the outer annular space being in fluid communication at the tip and providing for a flow of coolant from the base to the tip and back to the base. A method of fabrication and an integrated gasification combined cycle power plant are also disclosed. | 04-29-2010 |
20100104446 | FABRICATED HYBRID TURBINE BLADE - A blade for a turbine includes: a support structure of high strength material as a central portion of the blade, the support structure including a root and a body extending to a tip, the body providing a leading edge, a trailing edge and mounting section; and a honeycomb skin attached to the mounting section for providing a lightweight airfoil portion of the blade. A method and a turbine are included. | 04-29-2010 |
20100106454 | METHOD AND SYSTEM FOR ROTATION TRACKING OF A TURBOMACHINE COMPONENT - Disclosed is a method for tracking rotation of a turbomachine component including locating at least one tilt sensor at the turbomachine component and rotating the turbomachine component about a central axis to observe a portion of interest on the turbomachine component. The at least one tilt sensor detects an angle of rotation of the turbomachine component and transmits the angle of rotation from the at least one tilt sensor to a device which converts the angle of rotation to an indicia of the portion of interest. Further disclosed is a rotor including at least one tilt sensor and a system for tracking rotation of a turbomachine component including at least one tilt sensor and a device. | 04-29-2010 |
20100139167 | GASIFIER ADDITIVES FOR IMPROVED REFRACTORY LIFE - Embodiments disclosed herein provide hydrocarbon additives and methods of making and using the same. The additives are suitable for use in conjunction with gasifiers, furnaces, or other high-temperature vessels. The additives may be part of an input stream to a reaction vessel of a hydrocarbon gasifier. The additives may include materials that at least partially reduce the infiltration of slag into the refractory material. | 06-10-2010 |
20100229558 | Methods and Apparatus for Providing A Sacrificial Shield For A Fuel Injector - Embodiments of methods and apparatus for providing a sacrificial shield for a fuel injector are provided. According to one example embodiment, a method for shielding a fuel injector associated with a combustion device is provided. The method can include providing at least one shield support device operable to mount to a tip of a fuel injector. The method can also include mounting a plurality of shields to the at least one support device, wherein each of the plurality of shields is spaced apart from each respective adjacent shield by at least one segmentation, and wherein each of the plurality of shields is operable to reduce heat exposure to the tip of the fuel injector. | 09-16-2010 |
20100237173 | FUEL INJECTOR GASSIFER NOZZLE HAVING ADJUSTABLE ANNULUS - A fuel injector for injecting fuel into a gasifier includes a mating end including a nozzle portion and a first flange fixedly coupled to the mating end and having a first receiving hole there through and including a first diaphragm disposed therein. The injector also includes a fuel transmission nozzle displaced at least partially within the mating end and passing through the first receiving hole arranged and configured such that a secondary oxygen channel exists between the fuel transmission nozzle and the mating end, the fuel transmission nozzle being fixedly coupled to the first diaphragm and further including a fuel inlet for receiving fuel for introduction into the gasifier. | 09-23-2010 |
20100327535 | Fiber seal for ceramic matrix composite components - A fiber brush seal attached with metallic structure, suitable for use with SiC-SiC ceramic matrix composite (CMC) components. The fibers may be selected from oxides, carbides and nitrides of silicon, tungsten, chromium, iron, titanium, boron, zirconium and aluminum, and may optionally be coated with a boron nitride based coating. | 12-30-2010 |
20110027120 | DEVICE AND METHOD FOR HOT ISOSTATIC PRESSING - Improved methods and containers for forming billets using hot isostatic pressing are provided. The methods and containers have features that control the deformations of the container during the high temperatures and pressures experienced in such processing so that the loss or removal of material from the resulting billet can be optimized. | 02-03-2011 |
20110059332 | Oxidation and Corrosion Resistant and Ductile Alloy Composition and Method of Making - Composition containing a MCrAlY, wherein M is selected from the group consisting of cobalt (Co), nickel (Ni), iron (Fe) and mixtures thereof, and germanium in an amount of about 10% by weight or less of germanium. Coated articles coated with the composition are also provided. | 03-10-2011 |
20110135483 | COMPOSITE TURBINE BLADE AND METHOD OF MANUFACTURE THEREOF - A composite turbine blade and a method of manufacture thereof is disclosed. The composite turbine blade comprises a turbine blade portion comprising a first material and a first tip plate comprising a second material. The turbine blade portion has an exterior wall and an interior wall surrounding a hollow interior cavity, and a top surface extending from the exterior wall to the interior wall bounding an orifice that is fluidly connected to the hollow interior cavity. The first tip plate may be attached to the turbine blade along the top surface and extending from proximate the exterior wall of the turbine blade across the orifice to cover the orifice. | 06-09-2011 |
20110251721 | SYSTEM AND METHOD FOR ONLINE MONITORING OF MOLTEN SALT CORROSION - A system and method for online monitoring of molten salt corrosion of a component of an apparatus is disclosed. First and second electrodes are electrically isolated from each other within the component and exposed to a corrosive operating environment of the apparatus. The first and second electrodes are electrically coupled such that when an electrical potential difference exists between the first and second electrodes an electrical current flows between the first electrode and the second electrode. The electrical potential difference between the first electrode and the second electrode is based at least in part on molten salt corrosion at the first electrode or the second electrode. At least one of the electrical potential difference or the electrical current flowing between the first electrode and second electrode is measured and analyzed such that a corrosion characteristic of the component can be predicted. | 10-13-2011 |
20110256358 | CERAMIC COMPOSITE COMPONENTS AND METHODS OF FABRICATING THE SAME - A method for fabricating a ceramic composite includes forming a first ceramic composite layer (CCL), positioning a form against the first CCL, positioning a second CCL against the form such that the form is at least partially circumscribed by the first CCL and the second CCL. The method also includes coupling the first CCL to the second CCL, such that at least a first passage extends in a first direction across at least a portion of the ceramic composite component and is defined at least partially by the first CCL and the second CCL in a location vacated by the first form. | 10-20-2011 |
20110278271 | SYSTEM AND METHOD FOR LASER SHOCK PEENING - A system for laser shock peening includes a laser positioned to direct a laser pulse at a first side of a work piece and a coupler on a second side of the work piece. The system further includes a Doppler shift detector positioned to measure a velocity of the coupler. A method for laser shock peening includes depositing an amount of energy from a laser pulse into a first side of a work piece and transmitting a pulse having a first frequency at a second side of the work piece. The method further includes receiving a reflected pulse having a second frequency from the second side of the work piece and determining the velocity of the work piece based on the difference between the first frequency and the second frequency. | 11-17-2011 |
20110284367 | SYSTEM FOR PROTECTING TURBINE ENGINE SURFACES FROM CORROSION - According to various embodiments, a system includes a turbine engine component that includes a first material having a surface exposed to a fluid flow path and a sacrificial anode layer disposed on the surface. The sacrificial anode layer includes a second material that is electrochemically more active than the first material and the second material is configured to preferentially corrode to protect the first material from corrosion. | 11-24-2011 |
20110284368 | SYSTEM FOR PROTECTING GASIFIER SURFACES FROM CORROSION - According to various embodiments, a system includes a gasifier that includes a shell made of a first material exposed to a gasification region inside the gasifier and a patterned anode layer coupled to the shell inside the gasifier. The patterned anode layer is made of a second material, and the patterned anode layer is configured to protect the shell from corrosion by condensing hot gas in the gasification region. | 11-24-2011 |
20120000892 | HYBRID LASER ARC WELDING PROCESS AND APPARATUS - A welding method and apparatus for welding workpieces together by conducting a laser beam welding process on a joint region that includes a weld seam defined by and between faying surfaces of the workpieces, and then conducting a hybrid laser arc welding process on the joint region. The laser beam welding process entails causing a first laser beam to travel along the joint region, penetrate the weld seam and form a weldment. The hybrid laser arc welding process remelts the weldment by simultaneously causing an electric arc and a second laser beam to overlap and travel along the joint region and form a weld pool in the weldment. On cooling, a weld joint is formed within the joint region and its weld seam. | 01-05-2012 |
20120102835 | SYSTEM AND METHOD FOR PROTECTING GASIFIER QUENCH RING - A system includes a gasifier, which includes a reaction chamber configured to convert a feedstock into a synthetic gas, a quench chamber configured to cool the synthetic gas, a quench ring configured to provide a water flow to the quench chamber, and a quench ring protection system configured to protect the quench ring from the synthetic gas or a molten slag. The quench ring protection system includes a protective barrier disposed within an inner circumferential surface of the quench ring. The protective barrier substantially overlaps the inner circumferential surface in an axial direction along an axis of the quench ring. | 05-03-2012 |
20120111009 | SYSTEM FOR COOLING SYNGAS - A system includes a syngas cooler configured to cool a syngas. The syngas cooler includes a first syngas cooler section configured to cool the syngas and a second syngas cooler section configured to cool the syngas and generate a first superheated steam with an enthalpy of less than approximately 3800 kJ/kg. | 05-10-2012 |
20120152058 | GASIFIER ADDITIVES FOR IMPROVED REFRACTORY LIFE - Embodiments disclosed herein provide hydrocarbon additives and methods of making and using the same. The additives are suitable for use in conjunction with gasifiers, furnaces, or other high-temperature vessels. The additives may be part of an input stream to a reaction vessel of a hydrocarbon gasifier. The additives may include materials that at least partially reduce the infiltration of slag into the refractory material. | 06-21-2012 |
20120174396 | METHOD FOR MANUFACTURING A CORROSION SENSOR - A method for manufacturing a corrosion sensor includes applying a first layer of non-conductive material to a substrate, writing a conductive material at discrete locations on the non-conductive material, and writing the conductive material at discrete locations on the previously written conductive material. The method further includes applying a second layer of non-conductive material over the conductive material and machining at least a portion of the second layer of non-conductive material to expose at least a portion of the conductive material. | 07-12-2012 |
20120176147 | CORROSION SENSOR AND METHOD FOR MANUFACTURING A CORROSION SENSOR - A corrosion sensor includes a plurality of conductive portions and at least one non-conductive portion between adjacent conductive portions, wherein the at least one non-conductive portion has a dimension less than approximately 500 microns. A method for manufacturing a corrosion sensor includes applying a non-conductive material to a substrate and applying a conductive material to discrete locations on the non-conductive material. The method further includes applying a brazing material around each discrete location of the conductive material. | 07-12-2012 |
20120177811 | METHOD FOR MANUFACTURING A CORROSION SENSOR - A method for manufacturing a corrosion sensor includes spraying a non-conductive material on a substrate and spraying a conductive material at discrete locations on the substrate or on the non-conductive material. The method further includes spraying the non-conductive material around the discrete locations of the conductive material. | 07-12-2012 |
20120181355 | SYSTEM FOR FLOW CONTROL IN FUEL INJECTORS - A system includes a gasification fuel injector. The gasification fuel injector includes a body having a tip portion, a first conduit extending through the body toward the tip portion, a second conduit extending through the body toward the tip portion, and a flow control device disposed in the first conduit upstream of the tip portion. The flow control device is configured to limit a first flow through the first conduit. | 07-19-2012 |
20120241279 | LOAD COUPLING FOR POWER GENERATION SYSTEMS - A load coupling for transmitting a torque load between a first shaft and a second shaft is disclosed. The load coupling may generally include a first shaft segment configured to be fixedly attached to the first shaft and a second shaft segment configured to be fixedly attached to the second shaft. The second shaft segment may be frictionally fit within the first shaft segment such that a frictional interface is defined between the first and second shaft segments. Additionally, the frictional interface may be configured such that the first and second shaft segments rotationally disengage when the torque load exceeds a torque threshold and rotationally reengage when the torque load is reduced to or below the torque threshold. | 09-27-2012 |
20130058786 | CREEP INDICATION SYSTEM AND METHOD FOR DETERMINING CREEP AMOUNT - A creep indication system and a method for determining a creep amount are disclosed. The system includes a first creep indicating member on a first rotating component and a second creep indicating member on a second rotating component. The second creep indicating member has at least one different creep characteristic from the first creep indicating member. The system further includes at least one measurement device configured to measure a change in radial position of at least one of the first creep indicating member or the second creep indicating member. The method includes measuring a first creep amount of a first creep indicating member and measuring a second creep amount of a second creep indicating member. The method further includes estimating a temperature of a rotating component using the first creep amount and the second creep amount. | 03-07-2013 |
20130089463 | TURBINE BLADE EROSION SENSOR - An erosion sensor that can separately monitor erosion and corrosion of a substrate, such as a wind turbine blade or a turbine blade used in devices such as gas turbines, aircraft engines, microturbines, steam turbines, and the like is disclosed. The sensor can include a first element or “erosion part” that is made of a corrosion resistant material. The first element of the sensor has similar erosion properties to the substrate being monitored. The sensor can further include a second element or a “corrosion part” that is made of a material having similar erosion and corrosion properties to the substrate. The sensor can provide an erosion indicator based on the erosion of the first element and a corrosion indicator based on the erosion and corrosion of the second element. | 04-11-2013 |
20130180432 | COATING, A TURBINE COMPONENT, AND A PROCESS OF FABRICATING A TURBINE COMPONENT - Disclosed is a coating, a turbine component, and a process of fabricating a turbine component. The coating includes a ceramic phase formed by ceramic particles and a ductile matrix having a ductility greater than the ceramic phase. The ceramic phase includes substantially the same microstructure as the ceramic particles. The turbine component includes a surface having the coating. The process includes applying the coating to the surface of the turbine component. | 07-18-2013 |
20130216798 | COATED ARTICLE AND PROCESS OF COATING AN ARTICLE - A coated article and a coating application process are disclosed. The coated article includes a metallic surface, a first layer positioned proximal to the metallic surface, the first layer having a first ductility, and a second layer positioned distal from the metallic surface, the second layer having a second ductility. The first ductility is at least about 20% greater than the second ductility. The process includes providing an article, the article comprising a metallic surface, applying a first layer proximal to the metallic surface, the first layer having a first ductility, and applying a second layer distal from the metallic surface, the second layer having a second ductility. | 08-22-2013 |
20130255248 | THERMALLY-CONTROLLED COMPONENT AND THERMAL CONTROL PROCESS - A thermally-controlled component and thermal control process are disclosed. The thermally-controlled component includes thermally-responsive features. The thermally-responsive features are configured to modify a flow path to control temperature variation of the thermally-controlled component. The thermally-responsive features deploy from or retract toward a surface of the thermally-controlled component in response to a predetermined temperature change. The thermal control process includes modifying the flow path in the thermally-controlled component to control temperature variation of the thermally-controlled component and/or cooling a region of the thermally-controlled component through the thermally-responsive features deploying from or retracting toward a surface of the thermally-controlled component. | 10-03-2013 |
20130255796 | FLOW-CONTROL DEVICE, COMPONENT HAVING A FLOW-CONTROL DEVICE, AND METHOD OF PRODUCING A FLOW-CONTROL DEVICE - A flow-control device, a component, and method of producing a flow-control device are disclosed. The flow-control device includes thermally-adjustable features positioned along a surface of the flow-control device configured to be adjacent to a flow, and a heating member in direct or indirect contact with the thermally-adjustable features. The thermally-adjustable features deploy from or retract toward the surface in response to a predetermined temperature change provided by the heating member. The deploying from or the retracting toward of the thermally-adjustable features increases or decreases turbulation of the flow along the surface. The component includes the flow-control device. The method includes forming the thermally-adjustable features along the surface of the flow-control device, in direct or indirect contact with a heating member. The thermally-adjustable features deploy from or retract toward the surface in response to a predetermined temperature change provided by the heating member. | 10-03-2013 |
20130259640 | METALLIC SEAL ASSEMBLY, TURBINE COMPONENT, AND METHOD OF REGULATING AIRFLOW IN TURBO-MACHINERY - A metallic seal assembly, a turbine component, and a method of regulating flow in turbo-machinery are disclosed. The metallic seal assembly includes a sealing structure having thermally-responsive features. The thermally-responsive features deploy from or retract toward a surface of the sealing structure in response to a predetermined temperature change. The turbine component includes the metallic seal assembly. The method of regulating flow in turbo-machinery includes providing the metallic seal assembly and raising or retracting the thermally-responsive features in response to the predetermined temperature change. | 10-03-2013 |
20130260169 | Components Having Tab Members - A components comprising a plurality of tab members formed thereon are provided. The plurality of tab members include at least one dissimilar metallic layer applied to the component. The plurality of tab members are configured to extend away from or retract toward a surface of the component in response to a temperature change. | 10-03-2013 |
20130287587 | COMPOSITE TURBINE BLADE AND METHOD OF MANUFACTURE - A composite turbine blade and a method of manufacture thereof is disclosed. The composite turbine blade comprises a turbine blade portion comprising a first material and a first tip plate comprising a second material. The turbine blade portion has an exterior wall and an interior wall surrounding a hollow interior cavity, and a top surface extending from the exterior wall to the interior wall bounding an orifice that is fluidly connected to the hollow interior cavity. The first tip plate may be attached to the turbine blade along the top surface and extending from proximate the exterior wall of the turbine blade across the orifice to cover the orifice. | 10-31-2013 |
20130323533 | REPAIRED SUPERALLOY COMPONENTS AND METHODS FOR REPAIRING SUPERALLOY COMPONENTS - Methods for repairing superalloy components include disposing a single crystal coupon in a void of the superalloy component, disposing one or more shims between the single crystal coupon and the superalloy component, and, welding the one or more shims to join with the single crystal coupon and the superalloy component using a high energy density beam welder. | 12-05-2013 |
20140174163 | Systems and Methods For Measuring Fouling in a Turbine System - Systems and methods for measuring fouling in a gas turbine compressor include a conductivity resistance sensor disposed in a compressor inlet mouth. The degree of compressor fouling is correlated to changes in resistance measured by the conductivity resistance sensor. Measurements of resistance changes are converted to an indicia of fouling and used to trigger cleaning of the compressor. | 06-26-2014 |
20140199173 | CERAMIC MATRIX COMPOSITE ARTICLE AND PROCESS OF FABRICATING A CERAMIC MATRIX COMPOSITE ARTICLE - A ceramic matrix composite article and a process of fabricating a ceramic matrix composite are disclosed. The ceramic matrix composite article includes a matrix distribution pattern formed by a manifold and ceramic matrix composite plies laid up on the matrix distribution pattern, includes the manifold, or a combination thereof. The manifold includes one or more matrix distribution channels operably connected to a delivery interface, the delivery interface configured for providing matrix material to one or more of the ceramic matrix composite plies. The process includes providing the manifold, forming the matrix distribution pattern by transporting the matrix material through the manifold, and contacting the ceramic matrix composite plies with the matrix material. | 07-17-2014 |
20140237784 | METHOD OF FORMING A MICROCHANNEL COOLED COMPONENT - A method of forming a microchannel cooled component is provided. The method includes forming at least one microchannel within a surface of a relatively planar plate. The method also includes placing a relatively planar cover member over the surface having the at least one microchannel formed therein. The method further includes adhering the relatively planar cover member to the relatively planar plate. The method yet further includes curving the microchannel cooled component by pressing the relatively planar cover member with a forming component for at least a portion of a time period of adhering the relatively planar cover member to the relatively planar plate. | 08-28-2014 |
20140272467 | CALCIUM-MAGNESIUM-ALUMINOSILICATE RESISTANT COATING AND PROCESS OF FORMING A CALCIUM-MAGNESIUM-ALUMINOSILICATE RESISTANT COATING - A process of forming a calcium-magnesium-aluminosilicate (CMAS) penetration resistant coating, and a CMAS penetration resistant coating are disclosed. The process includes providing a thermal barrier coating having a dopant, and exposing the thermal barrier coating to calcium-magnesium-aluminosilicate and gas turbine operating conditions. The exposing forming a calcium-magnesium-aluminosilicate penetration resistant layer. The coating includes a thermal barrier coating composition comprising a dopant selected from the group consisting of rare earth elements, non-rare earth element solutes, and combinations thereof. Additional or alternatively, the coating includes a thermal barrier coating and an impermeable barrier layer or a washable sacrificial layer positioned on an outer surface of the thermal barrier coating. | 09-18-2014 |
20140315001 | CERAMIC COMPOSITE COMPONENTS - A method for fabricating a ceramic composite includes forming a first ceramic composite layer (CCL), positioning a form against the first CCL, positioning a second CCL against the form such that the form is at least partially circumscribed by the first CCL and the second CCL. The method also includes coupling the first CCL to the second CCL, such that at least a first passage extends in a first direction across at least a portion of the ceramic composite component and is defined at least partially by the first CCL and the second CCL in a location vacated by the first form. | 10-23-2014 |