SIEMENS POWER GENERATION, INC. Patent applications |
Patent application number | Title | Published |
20130230739 | Thermally Protective Multiphase Precipitant Coating - A thermally protective coating ( | 09-05-2013 |
20130167538 | Apparatus for mixing fuel and air in a combustion system - A fuel shroud assembly ( | 07-04-2013 |
20130142630 | AIRFOIL SEAL SYSTEM FOR GAS TURBINE ENGINE - A turbine airfoil seal system of a turbine engine having a seal base with a plurality of seal strips extending therefrom for sealing gaps between rotational airfoils and adjacent stationary components. The seal strips may overlap each other and may be generally aligned with each other. The seal strips may flex during operation to further reduce the gap between the rotational airfoils and adjacent stationary components. | 06-06-2013 |
20120148794 | CMC ANCHOR FOR ATTACHING A CERAMIC THERMAL BARRIER TO METAL - A ceramic matrix composite (CMC) anchor ( | 06-14-2012 |
20110008154 | Sealing Arrangement for Turbine Engine Having Ceramic Components - A sealing arrangement for use in a turbine engine having ceramic components. The sealing arrangement is retained in a seal gap formed between adjacent segments and is compliant to accommodate variations in the size of the seal gap as the adjacent segments move relative to one another. | 01-13-2011 |
20100278680 | Combustion Turbine Component Having Rare-Earth Strengthened Alloy and Associated Methods - A method of making a combustion turbine component includes forming a metallic powder including at least one metal and at least one rare-earth element and processing the metallic powder including at least one metal and at least one rare-earth element to form a cohesive metallic mass. A primary aging heat treatment may be performed on the cohesive metallic mass. A homogenization heat treatment may be performed on the cohesive metallic mass prior to the primary aging heat treating. Furthermore, a secondary aging heat treatment may be performed on the cohesive metallic mass after the primary aging heat treating. | 11-04-2010 |
20100080953 | Formation of Imprints and Methodology for Strengthening a Surface Bond in a Hybrid Ceramic Matrix Composite Structure - A hybrid ceramic matrix composite structure and method for fabricating such an structure are provided. A ceramic matrix composite substrate | 04-01-2010 |
20100080687 | Multiple Piece Turbine Engine Airfoil with a Structural Spar - A multiple piece turbine airfoil having an outer shell with an airfoil tip that is attached to a root with an internal structural spar is disclosed. The root may be formed from first and second sections that include an internal cavity configured to receive and secure the one or more components forming the generally elongated airfoil. The internal structural spar may be attached to an airfoil tip and place the generally elongated airfoil in compression. The configuration enables each component to be formed from different materials to reduce the cost of the materials and to optimize the choice of material for each component. | 04-01-2010 |
20100075106 | SUBSURFACE INCLUSION OF FUGITIVE OBJECTS AND METHODOLOGY FOR STRENGTHENING A SURFACE BOND IN A HYBRID CERAMIC MATRIX COMPOSITE STRUCTURE - A hybrid ceramic matrix composite (CMC) structure | 03-25-2010 |
20100071378 | Alternately Swirling Mains in Lean Premixed Gas Turbine Combustors - A gas turbine combustor for producing hot gas by burning a fuel in compressed air comprising a combustor central axis and multiple main swirlers with respective swirler axes disposed about and parallel to the combustor central axis, each main swirler delivering an air fuel mixture flowing through it and about its swirler axis, wherein each swirler imparts rotation to the air fuel mixture flowing through it in a direction opposite that of adjacent swirlers. This combustor configuration reduces shear where the outer edges of adjacent flows meet, allowing for greater tuning of the combustion chamber and reduced NOx and CO emissions. | 03-25-2010 |
20100071374 | Spiral Cooled Fuel Nozzle - A fuel nozzle for delivery of fuel to a gas turbine engine. The fuel nozzle includes an outer nozzle wall and a center body located centrally within the nozzle wall. A gap is defined between an inner wall surface of the nozzle wall and an outer body surface of the center body for providing fuel flow in a longitudinal direction from an inlet end to an outlet end of the fuel nozzle. A turbulating feature is defined on at least one of the central body and the inner wall for causing at least a portion of the fuel flow in the gap to flow transverse to the longitudinal direction. The gap is effective to provide a substantially uniform temperature distribution along the nozzle wall in the circumferential direction. | 03-25-2010 |
20100071373 | Pilot Burner for Gas Turbine Engine - A pilot burner ( | 03-25-2010 |
20100066315 | Method and System for Monitoring the Condition of Generator End Windings - A method and system for monitoring the operating conditions of an electric generator. The system includes a triad sensor array formed within a predetermined section of a fiber optic conductor. The triad sensor array is formed of a group of sensors including a first sensor including a Bragg grating for producing a first signal representative of strain in a stator bar of the generator, a second sensor including a Bragg grating for producing a second signal representative of temperature in the stator bar, and a third sensor including a Bragg grating for producing a third signal representative of vibration amplitude in the stator bar. | 03-18-2010 |
20100061875 | Combustion Turbine Component Having Rare-Earth Elements and Associated Methods - A method of making a combustion turbine component includes forming a nanosized powder including a plurality of metals and at least one rare-earth element and agglomerating the nanosized powder to form a microsized powder including a plurality of metals and at least one rare-earth element. The microsized powder is processed to form a cohesive metallic mass and a primary aging heat treating is performed on the cohesive metallic mass. A solution heat treating may be performed on the cohesive metallic mass prior to the primary aging heat treating. A secondary aging treating may be performed on the cohesive metallic mass after the primary aging treating. | 03-11-2010 |
20100061858 | Composite Blade and Method of Manufacture - A method of making a composite blade that is attachable to a rotating shaft using a conventional metal blade attachment. A blade is formed from a composite material with a blade root at one end thereof. A metallic member having an external shape conforming to a conventional metal blade root is shaped with an interior cavity having an opening for receipt of the blade root. Before the composite material is fully cured, a bladder is formed into or is inserted into an end of the blade root and inflated, thereby forcing the composite material into intimate contact with the interior cavity of the metallic member, thereby ensuring a fret-free interface upon final curing of the composite material. The interior cavity of the metallic member may be shaped or surfaced to improve the load carrying capability there between. | 03-11-2010 |
20100058770 | Method and System for Controlling Fuel to a Dual Stage Nozzle - A method and system for controlling delivery of fuel to a dual stage nozzle in the combustor of a gas turbine. A liquid fuel is conveyed from a single stage fuel supply through a plurality of primary fuel supply lines to a first nozzle stage including a plurality of primary nozzles. A predetermined operating condition of the gas turbine is identified and a signal is produced in response to the identified operating condition. The signal effects actuation of valves located on secondary fuel supply lines extending from each of the primary fuel supply lines to supply fuel to respective secondary nozzles. | 03-11-2010 |
20100058040 | USING EDS FOR EXTENDING A DESCRIPTION OF A LOADWARE UPDATE MECHANISM - The invention refers to a computer-implemented method and system for loading a loadware file on a CANopen device. The CANopen device comprises an electronic data sheet, which is extended to comprise a load object. After reading the load object with the load parameters, the respective loadware file is located, selected and accessed. Accessing the loadware file is done by applying the read load parameters. | 03-04-2010 |
20100054932 | Circumferential Shroud Inserts for a Gas Turbine Vane Platform - Protective insert plates ( | 03-04-2010 |
20100051765 | Turbine Engine Cover Plate Assembly Stand - A holding structure associated with a lifting device for supporting a removed turbine engine cover plate assembly. The holding structure includes an upper support member and a lower support member. The upper support member is formed with a plurality of service areas, where each service area is configured for servicing a cover plate assembly. Each service area includes a plurality of slots extending inwardly from a peripheral edge of the upper support member to receive and support components of the cover plate assembly during a disassembly and service operation. | 03-04-2010 |
20100039779 | Wireless Telemetry Electronic Circuit Board for High Temperature Environments - A circuit assembly ( | 02-18-2010 |
20100039290 | Wireless Telemetry Electronic Circuitry for Measuring Strain in High-Temperature Environments - In a telemetry system for use in an engine, a circuit structure ( | 02-18-2010 |
20100039289 | Wireless Telemetry Electronic Circuit Package for High Temperature Environments - A circuit assembly ( | 02-18-2010 |
20100039288 | Wireless Telemetry Circuit Structure for Measuring Temperature in High Temperature Environments - A circuit affixed to a moving part of an engine for sensing and processing the temperature of the part. The circuit generates a signal representative of the temperature sensed by a thermocouple ( | 02-18-2010 |
20100031624 | FUEL HEATING VIA EXHAUST GAS EXTRACTION - A method and system for heating fuel for a gas turbine engine by using excess heat energy in the engine exhaust gas to heat the fuel and returning the cooled exhaust gas back to the engine exhaust gas stream upstream of an emissions sensor is disclosed. The method and system comprises providing a heat exchanger having an exhaust gas passage and a fuel passage, extracting high temperature exhaust gas from the engine exhaust gas stream and passing the high temperature exhaust gas through the exhaust gas passage. Fuel is passed through the fuel passage where excess heat energy in the high temperature exhaust gas is used to heat the fuel. The temperature of the heated fuel is controlled by controlling the flow of the high temperature exhaust gas through the exhaust gas passage. | 02-11-2010 |
20100028163 | Injection Molded Component - An intermediate component includes a first wall member, a leachable material layer, and a precursor wall member. The first wall member has an outer surface and first connecting structure. The leachable material layer is provided on the first wall member outer surface. The precursor wall member is formed adjacent to the leachable material layer from a metal powder mixed with a binder material, and includes second connecting structure. | 02-04-2010 |
20100028131 | Component for a Turbine Engine - A component for use in a turbine engine including a first member and a second member associated with the first member. The second member includes a plurality of connecting elements extending therefrom. The connecting elements include securing portions at ends thereof that are received in corresponding cavities formed in the first member to attach the second member to the first member. The connecting elements are constructed to space apart a first surface of the second member from a first surface of the first member such that at least one cooling passage is formed between adjacent connecting elements and the first surface of the second member and the first surface of the first member. | 02-04-2010 |
20100021713 | STRUCTURE AND METHOD FOR PROTECTING A HYBRID CERAMIC STRUCTURE FROM MOISTURE ATTACK IN A HIGH TEMPERATURE ENVIRONMENT - A hybrid ceramic structure and a method for protecting the hybrid ceramic structure from moisture attack in a high temperature combustion environment are provided. The structure includes a ceramic matrix composite (CMC) substrate ( | 01-28-2010 |
20100021643 | Method of Forming a Turbine Engine Component Having a Vapor Resistant Layer - A method of forming a turbine component that includes a ceramic matrix composite-ceramic insulation composite with a vapor resistant layer is disclosed. The method includes providing an inner tool and an outer tool, wherein the inner and outer tools define a mold for forming a turbine component. A vapor resistant layer can be applied to the inner tool, and a ceramic insulation layer can be applied over the vapor resistant layer in the mold. The vapor resistant layer and the ceramic insulation layer can be partially fired to form a bisque turbine component, and the outer tool can be removed. The inner tool can include a transitory material. A layer of ceramic matrix composite material can be applied to the outside of the bisque turbine component to form a component, and the component can be fired to form a turbine component. | 01-28-2010 |
20100019412 | METHOD OF MANUFACTURING A THERMAL INSULATION ARTICLE - A method of manufacturing a thermal insulation article may include positioning, between opposing mold walls, a first layer comprising a ceramic matrix composite (CMC) material and a second layer comprising a plurality of tiles. The method may further include moving the opposing mold walls together to compress together the first and second layers, and curing the compressed together first and second layers to produce the thermal insulation article. | 01-28-2010 |
20100018209 | INTEGRAL FLOW SLEEVE AND FUEL INJECTOR ASSEMBLY - A fuel injector assembly for use in a turbine engine having a combustion section and a turbine section downstream from the combustion section. The fuel injector assembly includes a flow sleeve defining a pre-mixing passage of the combustion section and including a sleeve wall having a forward end proximate to a cover plate of the combustion section and an opposed aft end. An annular cavity in fluid communication with a source of fuel is formed in the sleeve wall adjacent the aft end. A fuel dispensing structure is associated with the cavity and includes at least one fuel distribution aperture for distributing fuel from the cavity to the pre-mixing passage. | 01-28-2010 |
20100018208 | TURBINE ENGINE FLOW SLEEVE - A flow sleeve for use in a turbine engine including a compressor section, a combustion section, and a turbine section downstream from the combustion section. The flow sleeve includes a sleeve wall defining a pre-mixing passage of the combustion section and has a forward end proximate to a cover plate of the combustion section and an opposed aft end. The sleeve wall includes a first wall section extending axially from the sleeve wall forward end and a second wall section extending from the first wall section between the forward and aft ends of the sleeve wall toward the aft end of the sleeve wall A cavity is formed between the first wall section and the second wall section. | 01-28-2010 |
20100015394 | CERAMIC MATRIX COMPOSITE WALL WITH POST LAMINATE STITCHING - A stitching geometry and method for selective interlaminar reinforcement of a CMC wall ( | 01-21-2010 |
20100015350 | PROCESS OF PRODUCING AN ABRADABLE THERMAL BARRIER COATING WITH SOLID LUBRICANT - A process ( | 01-21-2010 |
20100013494 | ELECTRICAL PARTIAL DISCHARGE PULSE MARKET DISCRIMINATION - A marker pulse discriminator monitor that enables filtering of partial discharge pulses for monitoring the condition of a generator in a power plant system. The monitor detects partial discharge pulses emanating from the generator and includes a plurality of first modules connected to respective isophase buses adjacent to the generator. Each of the first modules generate a marker pulse in response to a partial discharge pulse. The monitor also includes an analyzer unit connected to the isophase buses adjacent to a step-up transformer. The analyzer unit receives each partial discharge pulse and each marker pulse and determines a differential value corresponding to a difference between a time of arrival of a partial discharge pulse and a time of arrival of a corresponding marker pulse to identify partial discharge pulses originating at the generator and to identify the isophase bus associated with the corresponding partial discharge pulse. | 01-21-2010 |
20100011776 | ELIMINATION OF PLATE FINS IN COMBUSTION BASKETS BY CMC INSULATION INSTALLED BY SHRINK FIT - A combustor basket ( | 01-21-2010 |
20100011769 | FORWARD-SECTION RESONATOR FOR HIGH FREQUENCY DYNAMIC DAMPING - A gas turbine combustor having a Helmholtz resonator in a post-swirler homogenization zone upstream of the combustor zone. Embodiments of the present invention provide Helmholtz resonators that include cavities that occupy a remainder of a post-swirler homogenization zone, which also includes at least one flow-directing structure that passes a fuel/oxidizer mixture from a main swirler assembly into a combustion zone of a combustor. Thus, an open annular region of the combustor is converted into a multi-purpose zone that includes at least one Helmholtz resonator. | 01-21-2010 |
20100009228 | SOLID OXIDE FUEL CELL WITH TRANSITIONED CROSS-SECTION FOR IMPROVED ANODE GAS MANAGEMENT AT THE OPEN END - A solid oxide fuel cell ( | 01-14-2010 |
20100009091 | Fabrication of Copper-Based Anodes Via Atmosphoric Plasma Spraying Techniques - A fuel electrode anode ( | 01-14-2010 |
20100003071 | Fastener Assembly with Cyclone Cooling - A fluid cooled fastener assembly for use in a high temperature environment and a method of fluid cooling a fastener assembly are provided. The fastener has a coolant passage extending axially through the fastener and a coolant collector coupled to an end of the fastener. The coolant collector includes a collector opening configured to capture a portion of a cooling fluid flowing past the coolant collector and a contoured passage in communication with the collector opening and the passage in the fastener. The contoured passage is configured to accelerate the cooling fluid captured by the coolant collector and to direct it into the coolant passage in the fastener. | 01-07-2010 |
20090324841 | METHOD OF RESTORING NEAR-WALL COOLED TURBINE COMPONENTS - A method is provided for restoring a near-wall channeled gas turbine engine component ( | 12-31-2009 |
20090314092 | Method of Analyzing Non-Synchronous Vibrations Using a Dispersed Array Multi-Probe Machine - A method for identifying an unfolded non-synchronous blade vibration frequency in blades on a rotating rotor using a plurality of probes spaced from each other about the rotor. A set of data is acquired from the probes during a predetermined number of rotor revolutions and is processed using a Fourier analysis to generate an output representative of frequencies and phase shift angles corresponding to blade vibrations. The phase shift angles are used to identify a subharmonic for a blade vibration frequency to provide an output identifying the vibration frequency. A space dispersion and time dispersion of probes is described to increase the accuracy of the subharmonic determination using the phase shift angles. | 12-24-2009 |
20090302862 | METHOD AND SYSTEM FOR MONITORING PARTIAL DISCHARGE WITHIN AN ELECTRIC GENERATOR - Electrical generators used for power generation typically operate at high voltage. The High operating voltage results in a severe electrical stress environment for the generator conductor insulation system. The high electrical stress cal lead to a phenomena such as corona, partial discharge and arcing that can cause damage to the insulation and conductors. Disclosed is a novel method and system of detecting partial discharge activity within an electric generator. The method employs at least two Rogowski loops non-contactingly surrounding individual iso-phase bus conductors, where the loops are wired in differential mode to detect fast moving electrical pulses indicative of partial discharge. | 12-10-2009 |
20090301168 | Apparatus For Impact Testing For Electric Generator Stator Wedge Tightness - A remote-controlled dynamoelectric machine inspection vehicle that can fit and travel within a narrow air gap between a stator and rotor of a dynamoelectric machine. The inspection vehicle has an effectuator that can remotely activate a hammer driven by a high pressure pneumatic three-stage miniature piston that propels the hammer against a stator slot wedge creating an impact force that causes the wedge to vibrate. The vibrations are sensed to determine the tightness of the wedge. | 12-10-2009 |
20090289420 | SHAFT SEAL ASSEMBLY FOR HYDROGEN COOLED TURBINE GENERATOR - A seal assembly forming a seal with a rotatable shaft of a hydrogen-cooled generator is provided. The seal assembly includes a ring assembly disposed about the rotatable shaft. The ring assembly includes a fluid inlet and a fluid outlet. A hydrogen side ring is coupled to a generator frame of the generator. An insulating structure is positioned between the hydrogen side ring and the generator frame to provide electrical insulation between the hydrogen side ring and the generator frame. An air side ring is disposed adjacent to the hydrogen side ring and the seal structure is coupled to the air side ring. Structure for supplying oil to the ring assembly is provided, such that the oil flows through the ring assembly to an interface between the rotatable shaft and the seal structure so as to substantially limit direct contact between the rotatable shaft and the seal structure. | 11-26-2009 |
20090285740 | CATALYTIC PROCESS FOR CONTROL OF NOx EMISSIONS USING HYDROGEN - A selective catalytic reduction process with a palladium catalyst for reducing NO | 11-19-2009 |
20090280362 | FUEL CELL GENERATOR WITH FUEL ELECTRODES THAT CONTROL ON-CELL FUEL REFORMATION - A fuel cell for a fuel cell generator including a housing including a gas flow path for receiving a fuel from a fuel source and directing the fuel across the fuel cell. The fuel cell includes an elongate member including opposing first and second ends and defining an interior cathode portion and an exterior anode portion. The interior cathode portion includes an electrode in contact with an oxidant flow path. The exterior anode portion includes an electrode in contact with the fuel in the gas flow path. The anode portion includes a catalyst material for effecting fuel reformation along the fuel cell between the opposing ends. A fuel reformation control layer is applied over the catalyst material for reducing a rate of fuel reformation on the fuel cell. The control layer effects a variable reformation rate along the length of the fuel cell. | 11-12-2009 |
20090278414 | Electric Machine Having Electrically Conductive Member and Associated Insulation Assembly and Related Methods - An electric machine includes a shaft and a rotor carried by the shaft and having a rotor body, a plurality of rotor windings carried by the rotor body, and a retaining ring surrounding the rotor windings adjacent an end of the rotor body. An electrically conductive stud extends radially outwardly from the shaft adjacent the end of the rotor body. An electrically conductive member includes a first end section coupled to the electrically conductive stud and having a loop shape, a second end section coupled to a corresponding one of the rotor windings, and an intermediate section between the first and second end sections. An insulation assembly is between the shaft and the retaining ring and surrounding the intermediate section to define at least one gap with adjacent portions thereof. | 11-12-2009 |
20090263243 | Combustion Turbine Including a Diffuser Section with Cooling Fluid Passageways and Associated Methods - A combustion turbine includes a compressor section, a combustion section downstream from the compressor section, and a turbine section downstream from the combustion section. A diffuser section is downstream from the turbine section and has an outer wall, an inner wall, and at least one strut member extending therebetween. The outer wall has at least one first gas passageway therein, the inner wall has at least one second gas passageway therein, and the at least one strut member has at least one third gas passageway therein. The at least one first, second and third gas passageways deliver gas therethrough to assist attachment of a boundary layer to adjacent surfaces of the outer wall, the inner wall, and the at least one strut, respectively. | 10-22-2009 |
20090261670 | Electrical Machine Including Axial Connector Assemblies and Related Methods - An electrical machine may include a plurality of stator coil ends each having a fluid passageway therein. The electrical machine may further include a plurality of rings and a plurality of axial connector assemblies for connecting the plurality of stator coil ends to the plurality of rings. Each axial connector assembly may include a header cap including an open end received on a respective stator coil end and a closed end opposite the open end, the closed end defining a coil spherical connector portion. The header cap may have a fluid port therein coupled to the fluid passageway of the respective stator coil end. A ring spherical connector portion may be carried by a respective ring, and a pair of connector members may receive therebetween the coil and ring spherical connector potions. | 10-22-2009 |
20090260364 | Apparatus Comprising a CMC-Comprising Body and Compliant Porous Element Preloaded Within an Outer Metal Shell - An apparatus for a gas turbine engine, such as a transition ( | 10-22-2009 |
20090258247 | Anisotropic Soft Ceramics for Abradable Coatings in Gas Turbines - A layered abradable thermal barrier coating (TBC) | 10-15-2009 |
20090252907 | HYBRID CERAMIC STRUCTURE WITH INTERNAL COOLING ARRANGEMENTS - A structure for use in high temperature applications is provided. The structure may include an inner ceramic matrix composite (CMC) material ( | 10-08-2009 |
20090252602 | TURBINE BLADE TIP GAP REDUCTION SYSTEM - A turbine blade sealing system for reducing a gap between a tip of a turbine blade and a stationary shroud of a turbine engine. The sealing system includes a plurality of flexible seal strips extending from a pressure side of a turbine blade generally orthogonal to the turbine blade. During operation of the turbine engine, the flexible seal strips flex radially outward extending towards the stationary shroud of the turbine engine, thereby reducing the leakage of air past the turbine blades and increasing the efficiency of the turbine engine. | 10-08-2009 |
20090246006 | Mechanically Affixed Turbine Shroud Plug - A sealing interface for a component in a turbine machine, wherein a plug is mechanically affixed within an entrance passage of an aperture. The plug is secured in place within the entrance passage through deformation of an inner end of the plug to cause the plug to mechanically engage a groove formed adjacent the entrance passage. | 10-01-2009 |
20090243419 | Method of In Slot Tightness Measuring of Stator Coil - A method for measuring a tangential tightness of a stator coil within an armature slot of a stator assembly in an electric generator. The stator coil is excited to produce a vibratory response therein. The vibratory response of the stator coil is detected and a frequency response function of the vibratory response is determined. A tangential tightness of the stator coil within the armature slot is estimated based on the frequency response function of the vibratory response of the stator coil. | 10-01-2009 |
20090241544 | Method of Increasing Service Interval Periods in a Steam Turbine - A method of increasing service interval periods in a steam turbine by neutralizing sodium hydroxide in contaminated steam in a high temperature and a high pressure portion of a steam turbine by placing a protective covering over at least a portion of each of the bolts of a nozzle block assembly. The protective covering neutralizes contaminants in contaminated steam to reduce stress cracking of the bolts during steam turbine operation, and thus extend the useful life of the bolts and reduce the need for service work to repair or replace damaged bolts. | 10-01-2009 |
20090235635 | Igniter Assembly for a Gas Turbine - A gas turbine component ( | 09-24-2009 |
20090235525 | Method of Producing a Turbine Component with Multiple Interconnected Layers of Cooling Channels - A method for making a gas turbine component ( | 09-24-2009 |
20090214349 | Airfoil Structure Shim - An airfoil structure, shim and retention member combination is provided. The combination comprises an airfoil structure, a retention member and a shim. The airfoil structure may comprise a first recess. The retention member may comprising a second recess. The first and second recesses may define a cavity. The shim may comprise a main body and a plurality of first fins extending outwardly from a first side of the main body. The first fins may further extend transverse to a longitudinal axis of the main body. The shim may be positioned in the cavity such that the first fins extend in a direction substantially transverse to a longitudinal axis of the cavity. | 08-27-2009 |
20090196813 | HIGH TEMPERATURE CATALYST AND PROCESS FOR SELECTIVE CATALYTIC REDUCTION OF NOX IN EXHAUST GASES OF FOSSIL FUEL COMBUSTION - A process for producing a stable high-temperature catalyst for reduction of nitrogen oxides in combustion exhaust gases at operating temperatures from 300° C. to over 700° C. without the need for exhaust dilution. A zeolite material is steam-treated at a temperature and duration sufficient to partially de-aluminize the zeolite to approximately a steady state, but not sufficient to fully collapse its chemical structure. Iron is added to the zeolite material. The zeolite material is calcined at a temperature, humidity, and duration sufficient to stabilize the zeolite material. Examples and specifications for ranges, order, and durations of steaming, calcining, and other steps are provided. | 08-06-2009 |
20090196761 | METAL INJECTION JOINING - A method of joining a first part together with a second part is disclosed. The method may comprise providing a first part having a first joining portion including a first channel and a second part having a second joining portion including a second channel. The method may further comprise positioning the first part adjacent to the second part such that the first channel and second channel align with one another to define a cavity. The method may still further comprise preparing a mixture comprising at least one of a metal powder and a polymer binder, placing the mixture into the cavity so as to form a preform and solidifying the preform forming a metal element in the cavity. The metal element joins the first part together with the second part | 08-06-2009 |
20090194346 | Automated Remote Carriage for Tightening Generator Wedges - A remote-controlled dynamoelectric machine maintenance vehicle that can fit and travel within the air gap between a stator and rotor of a dynamoelectric machine. The maintenance vehicle has an effectuator that can remotely attach to an adjustable wedge within a coil slot of the stator and tighten the wedge in position and then move on to repeat the process until all the wedges on the stator are secured. | 08-06-2009 |
20090191050 | SEALING BAND HAVING BENDABLE TANG WITH ANTI-ROTATION IN A TURBINE AND ASSOCIATED METHODS - The turbine includes a plurality of successive stages each having a rotatable disk and blades carried thereby. A pair of adjacent rotatable disks define an annular gap therebetween and have respective opposing sealing band receiving slots aligned with the annular gap. At least one of the rotatable disks has at least one notch therein coupled to the respective sealing band receiving slot, and a sealing band is in the opposing sealing band receiving slots to seal the corresponding annular gap. The sealing band includes at least one sealing strip and at least one movable locking tang carried thereby and extending into the at least one notch to define an anti-rotational feature for the sealing band. | 07-30-2009 |
20090188097 | METHOD OF LAYERED FABRICATION - A method of creating a complex three-dimensional object by assembling a plurality of prefabricated elements in a predetermined arrangement and coupling the elements together into an integral three-dimensional object is disclosed. | 07-30-2009 |
20090183850 | Method of Making a Combustion Turbine Component from Metallic Combustion Turbine Subcomponent Greenbodies - A method of making a combustion turbine component includes assembling a plurality of metallic combustion turbine subcomponent greenbodies together to form a metallic greenbody assembly and sintering the metallic greenbody assembly to thereby form the combustion turbine component. Each of the plurality of metallic combustion turbine subcomponent greenbodies may be formed by direct metal fabrication (DMF). In addition, each of plurality of metallic combustion turbine subcomponent greenbodies may include an activatable binder and the activatable binder may be activated prior to sintering. | 07-23-2009 |
20090148280 | Turbine Vane for a Gas Turbine Engine - A turbine vane for a gas turbine engine having an outer wall of nonuniform thickness. The turbine vane may be formed from a generally elongated airfoil formed from an outer wall having a leading edge, a trailing edge, a pressure side, a suction side, a first endwall at a first end, a second endwall at a second end opposite the first end, and an internal cooling system positioned internally of the outer wall. The outer wall may be formed of a non-uniform thickness such that aspects of the outer wall positioned between an outboardmost portion of the outer wall and an inboardmost portion of the outer wall are thinner than the outboardmost and inboardmost portions of the outer wall. | 06-11-2009 |
20090129934 | Turbine Blade Tip Cooling System - A turbine blade for a turbine engine having a cooling system in the turbine blade including a camber-line rib extending radially outward from a tip of the blade and extending from a trailing edge of the blade toward a leading edge. The camber-line rib may form pressure and suction side cooling slots at the tip of the blade. The camber-line rib my include a cooling channel positioned in the camber-line rib and in fluid communication with the at least one cavity forming the cooling system in the blade for cooling aspects of the tip at the trailing edge. | 05-21-2009 |
20090129915 | Turbine Airfoil Cooling System with Recessed Trailing Edge Cooling Slot - A cooling system for a turbine airfoil of a turbine engine having a trailing edge cooling slot positioned within the generally elongated, hollow airfoil and extending from the trailing edge chordwise into the generally elongated, hollow airfoil toward the leading edge such that a secondary trailing edge is offset upstream from the trailing edge. As such, the trailing edge cooling slot reduces stress formation at the trailing edge of the turbine airfoil. | 05-21-2009 |
20090126367 | SEQUENTIAL COMBUSTION FIRING SYSTEM FOR A FUEL SYSTEM OF A GAS TURBINE ENGINE - A gas turbine combustion system for a turbine engine is disclosed. The gas turbine combustion system may include a plurality of combustor baskets positioned circumferentially about a longitudinal axis of the turbine engine, at least one firing nozzle extending into each of the plurality of combustor baskets and a fuel delivery system in communication with each of the at least one firing nozzles and in communication with at least one fuel source. Each combustor basket may include a fuel flow control device of the fuel delivery system inline with each of the at least one firing nozzles in that combustor basket such that fuel flow to some of the combustor baskets can be shut off while fuel flow to firing nozzles in other combustor baskets remains unobstructed, thereby permitting some combustor baskets to remain non-fired while other combustor baskets are firing to reduce CO emissions. | 05-21-2009 |
20090123292 | Turbine Blade Tip Cooling System - A turbine blade for a turbine engine having a cooling system in the turbine blade formed from at least one elongated tip cooling chamber forming a portion of the cooling system and at least partially defined by the tip wall proximate to the first end. An inner surface of the tip wall may include a plurality of curved bumper protrusions extending from the inner surface radially inward toward the root. The cooling system may include a plurality of ribs generally aligned with the trailing edge, and the curved bumper protrusions may be offset in a chordwise direction relative to the ribs. A throat section may extend between a first forwardmost curved bumper protrusion and a second immediately adjacent downstream curved bumper protrusion and may be offset radially outward from an inner tip surface, thereby creating a first recessed tip slot with a reduced tip wall thickness. | 05-14-2009 |
20090121896 | Instrumented Component for Wireless Telemetry - A telemetry system for use in a combustion turbine engine ( | 05-14-2009 |
20090110954 | Bimetallic Bond Layer for Thermal Barrier Coating on Superalloy - A bimetallic bond layer ( | 04-30-2009 |
20090094985 | Non-Rectangular Resonator Devices Providing Enhanced Liner Cooling for Combustion Chamber - Embodiments of the present invention provide resonators ( | 04-16-2009 |
20090084187 | Non-Synchronous Vibrational Excitation of Turbine Blades Using a Rotating Excitation Structure - A method of measuring vibration in a bladed rotor structure with a vibration monitor. The vibration monitor includes a sensor for sensing passage of the sensor targets on radially outer portions of the blade structure, and the sensor generates signals corresponding to target passing events. An excitation structure is provided including at least one air jet for providing an excitation force to the blade structure. The blade structure is rotated about an axis of rotation and the air jet is driven in a circular path about the axis of rotation at a different rotational speed to apply a non-synchronous excitation force to the blade structure. | 04-02-2009 |
20090081517 | Solid Oxide Fuel Cell Generator Including a Glass Sealant - A solid oxide fuel cell generator is provided for electrochemically reacting a fuel gas with a flowing oxidant gas at an elevated temperature to produce power. The generator includes a generator section receiving a fuel gas and a plurality of elongated fuel cells extending through the generator section and having opposing open fuel cell ends for directing an oxidant gas between opposing plena in the generator. A sealant defines a seal on the fuel cells adjacent at least one of the fuel cell ends. The sealant is a modified lanthanum borate aluminosilicate glass composition having a minimal amount of boron oxide and silica, and in which the sealant maintains substantially constant physical characteristics throughout multiple thermal cycles. | 03-26-2009 |
20090081478 | Crack-Free Erosion Resistant Coatings on Steels - A method for preparing a protective layer ( | 03-26-2009 |
20090081033 | Stacked Lamellae Ceramic Gas Turbine Ring Segment Component - A gas turbine ring segment ( | 03-26-2009 |
20090081029 | Gas Turbine Component with Reduced Cooling Air Requirement - Introducing a plurality of geometrically shaped members ( | 03-26-2009 |
20090079139 | Ring Segment Coolant Seal Configuration - A configuration of seals disposed around and between a plurality of ring segments ( | 03-26-2009 |
20090078450 | Electrical Insulation Tape with Controlled Bonding and Resin Impregnation Properties - A mechanical interface for relieving stress between an outer layer and an inner insulating layer in a layered insulating tape structure surrounding an electrical conductor. The interface tape includes a porous non-woven carrier having opposing sides including a release region located at a first side and a non-release region located at an opposite second side. The release region is treated with a release material for substantially inhibiting adhesion between the first side and an adjacent outer surface. The non-release region is untreated by the release material for substantially facilitating adhesion between the second side and an adjacent inner surface. | 03-26-2009 |
20090078390 | Integral Single Crystal/Columnar Grained Component and Method of Casting the Same - A hybrid cast component ( | 03-26-2009 |
20090078369 | Method and Apparatus for Forming Insulated Rotor Conductors - An apparatus is disclosed for forming an insulated rotor conductor by bonding an insulating material onto a single side of a flat electrical conductor under controlled heat and mechanical pressure. The rotor conductor is suitable for assembly into the rotor assembly of a rotating electrical machine such as an alternating current generator. The apparatus includes modules to facilitate easy relocation within a manufacturing environment and to make efficient use of available manufacturing space. A corresponding method is also disclosed. | 03-26-2009 |
20090078053 | Method and Apparatus for Tracking a Rotating Blade Tip for Blade Vibration Monitor Measurements - A method and apparatus for monitoring vibrations in a blade structure of a turbine including generating signals from a probe located adjacent to a radial outer edge of the blade structure to provide signals corresponding to vibrations at predetermined locations along the tips of the blades. A leading edge of a blade tip is detected during a blade tracking operation, and a known location along the length of the blade tips is monitored during a vibration measurement operation. The measurement operation may be performed simultaneously with the tracking operation to provide measurements as the axial location of the blades change during transitional modes of operation of the turbine. | 03-26-2009 |
20090078052 | Method of Matching Sensors in a Multi-Probe Turbine Blade Vibration Monitor - A method of matching sensors in a multi-probe blade vibration monitor for a turbine. The method includes providing at least two probes mounted in a casing of the turbine adjacent to a rotating blade structure of the turbine. Targets are provided on radially outer portions of the blade structure. Each of the probes includes a sensor generating signals corresponding to target passing events, and a set of synchronous harmonics of the rotational speed of the rotor are produced for each sensor. The position of the sensors is adjusted such that the sets of harmonics of the sensors are substantially matched, indicating that the positions of the sensors are matched. | 03-26-2009 |
20090078051 | Method of On-Line Turbine Blade Slope and Sensor Position Verification - A method of monitoring vibrations in a blade structure of a turbine including generating signals from a sensor located adjacent to a radial outer edge of the blade structure to sense passage of targets located on the blade structure. The sensor is mounted eccentrically and the signals are obtained with the sensor located at different angular positions. In a first aspect of the invention, the signals from the sensor are used to determine a target slope angle of a target on a first turbine blade during operation of the turbine. In a second aspect of the invention, the signals from the sensor are used to position the sensor in response to a sensed variation in the axial position of the target on the first turbine blade. | 03-26-2009 |
20090076874 | Method and Tool for Optimized System Maintenance - A method for maintaining a system consisting of a plurality of components, comprises the steps of collecting maintenance information for each component of the system for which maintenance information is available; providing a maintenance schedule for components of the system; operating the system; and maintaining the system wherein during scheduled maintenance of a component information about the status of that component is acquired, during a failure of a component information about the failure of that component is acquired, and modifying the maintenance schedule according to the acquired information. | 03-19-2009 |
20090075112 | Combustion Turbine Component Having Rare Earth FeCrAl Coating and Associated Methods - A combustion turbine component ( | 03-19-2009 |
20090075111 | Combustion Turbine Component Having Rare Earth NiCrAl Coating and Associated Methods - A combustion turbine component ( | 03-19-2009 |
20090075110 | Combustion Turbine Component Having Rare Earth NiCoCrAl Coating and Associated Methods - A combustion turbine component ( | 03-19-2009 |
20090075101 | Combustion Turbine Component Having Rare Earth CoNiCrAl Coating and Associated Methods - A combustion turbine component ( | 03-19-2009 |
20090075057 | IMPARTING FUNCTIONAL CHARACTERISTICS TO ENGINE PORTIONS - A method of imparting one or more of a variety of functional characteristic to a portion of an engine (e.g., a turbine or diesel engine) by depositing particles from different particle feedstocks so as to form a high temperature resistant coating on a surface of the engine portion, where the particle feedstocks are varied in-situ while the particle are being deposited and at least one functional characteristic corresponds to, or results from, using different particle feedstocks. | 03-19-2009 |
20090074961 | ENGINE PORTIONS WITH FUNCTIONAL CERAMIC COATINGS AND METHODS OF MAKING SAME - A ceramic coating for imparting one or more of a variety of functional characteristics (e.g., reducing vibration levels) to one or more components or portions of an engine (e.g., ring segments, transition ducts, combustors, blades, vanes and shrouds of a turbine engine, portions thereof, and portions of a diesel engine), the components or portions comprising such a coating, and methods of making same. The ceramic coating exhibits a gradient or other change in the functional characteristic(s) through the thickness of the coating, across the surface area of the coating or both. | 03-19-2009 |
20090074588 | AIRFOIL WITH COOLING HOLE HAVING A FLARED SECTION - An airfoil is provided for a gas turbine engine. The airfoil may comprise a main body comprising a leading edge having a leading edge outer surface, a trailing edge having a trailing edge outer surface, a suction side having a suction side outer surface and a pressure side having a pressure side outer surface. The main body may further comprise at least one interior cooling passage and a plurality of cooling holes extending from the cooling passage to at least one of the leading edge outer surface, the trailing edge outer surface, the suction side outer surface and the pressure side outer surface. Preferably, at least one of the cooling holes includes a proximal metering section having a first dimension extending transverse to an axis extending in a flow direction of a cooling fluid passing through the one cooling hole, a flared section and an exit opening having a second dimension transverse to the axis which is larger than the first dimension. The flared section is preferably curvilinear as it extends from the proximal metering section towards the exit opening. | 03-19-2009 |
20090071160 | Wavy CMC Wall Hybrid Ceramic Apparatus - A ceramic hybrid structure ( | 03-19-2009 |
20090071159 | Secondary Fuel Delivery System - A secondary fuel delivery system for delivering a secondary stream of fuel and/or diluent to a secondary combustion zone located in the transition piece of a combustion engine, downstream of the engine primary combustion region is disclosed. The system includes a manifold formed integral to, and surrounding a portion of, the transition piece, a manifold inlet port, and a collection of injection nozzles. A flowsleeve augments fuel/diluent flow velocity and improves the system cooling effectiveness. Passive cooling elements, including effusion cooling holes located within the transition boundary and thermal-stress-dissipating gaps that resist thermal stress accumulation, provide supplemental heat dissipation in key areas. The system delivers a secondary fuel/diluent mixture to a secondary combustion zone located along the length of the transition piece, while reducing the impact of elevated vibration levels found within the transition piece and avoiding the heat dissipation difficulties often associated with traditional vibration reduction methods. | 03-19-2009 |
20090071157 | MULTI-STAGE AXIAL COMBUSTION SYSTEM - A gas turbine combustion system is provided comprising a combustion chamber ( | 03-19-2009 |
20090067101 | Method and System for Limiting a Current in an Alternating Current Generator - A method of connecting a superconducting fault current limiter to an alternating current generator to limit a current flowing in the generator is disclosed. A superconducting fault current limiter is connected in proximity with the generator to limit the current flowing in the generator. A system comprising a superconducting fault current limiter, a generator and a circuit is also disclosed. | 03-12-2009 |
20090060729 | Gas Turbine Engine Adapted for Use in Combination with an Apparatus for Separating a Portion of Oxygen from Compressed Air - A gas turbine engine is provided comprising an outer shell, a compressor assembly, at least one combustor assembly, a turbine assembly and duct structure. The outer shell includes a compressor section, a combustor section, an intermediate section and a turbine section. The intermediate section includes at least one first opening and at least one second opening. The compressor assembly is located in the compressor section to define with the compressor section a compressor apparatus to compress air. The at least one combustor assembly is coupled to the combustor section to define with the combustor section a combustor apparatus. The turbine assembly is located in the turbine section to define with the turbine section a turbine apparatus. The duct structure is coupled to the intermediate section to receive at least a portion of the compressed air from the compressor apparatus through the at least one first opening in the intermediate section, pass the compressed air to an apparatus for separating a portion of oxygen from the compressed air to produced vitiated compressed air and return the vitiated compressed air to the intermediate section via the at least one second opening in the intermediate section. | 03-05-2009 |
20090053056 | Turbine Vane Securing Mechanism - A turbine vane attachment system configured to eliminate movement of a turbine vane relative to a turbine vane carrier. The turbine vane attachment system may include a base attached to a turbine airfoil. The base may be configured to contact a wedge support along a plane that is generally nonparallel and nonorthogonal with a longitudinal axis of the airfoil. A bolt may connect the base with the wedge support. The bolt may change a distance between a channel in the base and an outer bearing surface. The turbine vane may be positioned in a vane carrier such that tongues extending from the vane carrier are positioned in the channels. As the bolt is advanced, the wedge support is moved laterally along the support surface of the base and the channels engage the tongues, thereby preventing movement of the turbine vane. | 02-26-2009 |
20090048100 | METHOD OF FORMING A CATALYST ELEMENT HAVING A THERMAL BARRIER COATING AS THE CATALYST SUBSTRATE - A combustion catalyst coating ( | 02-19-2009 |
20090041615 | Corrosion Resistant Alloy Compositions with Enhanced Castability and Mechanical Properties - Disclosed are novel nickel-base alloy compositions that may be cast as a single crystal or directionally solidified alloy consisting essentially of, by weight: 8-12% Cr, 10-14% Co, 0.3-0.9% Mo, 3-7% W, 2-8% Ta, 2.0-5.5% Al, 1.5-5.0% Ti, up to 2% Nb, less than 0.1% B, less than 0.1% Zr, 0.05-0.15% C, less than 0.5% Hf, 2-4% Re, 0.05-0.2% Si, up to 0.015% S, up to 0.1% La, up to 0.1% Y, up to 0.1% Ce, up to 0.1% Nd, up to 0.1% Dy, up to 0.1% Pr, up to 0.1% Gd, balance is Ni, and wherein (La+Y+Ce+Nd+Dy+Pr+Gd) is 0.001-0.1%. The compositions for the nickel-base superalloy have a balance between oxidation resistance, corrosion resistance, castability, and mechanical properties, such as creep resistance and thermo-mechanical fatigue resistance. | 02-12-2009 |
20090000102 | Turbine vane restoration system - A system and method for reconfiguring a turbine vane. In at least one embodiment, the system may be used to straighten an airfoil of a turbine vane segment to remove lean, twist, or racking, or any combination thereof. The airfoil may be straightened by fixing portions of the forward and aft hooks of the inner and outer shrouds of the turbine vane, restricting other portions of the forward and aft hooks of the inner and outer shrouds of the turbine vane to only move rotationally about a centerline of the inner or outer shrouds, and applying a load to various portions of the inner and outer shrouds and the airfoil to return the turbine vane to be within predetermined specifications. | 01-01-2009 |
20080317591 | CENTERLINE SUSPENSION FOR TURBINE INTERNAL COMPONENT - A centerline suspension arrangement ( | 12-25-2008 |
20080299016 | SYSTEM AND METHOD FOR SELECTIVE CATALYTIC REDUCTION OF NITROGEN OXIDES IN COMBUSTION EXHAUST GASES - A multi-stage selective catalytic reduction (SCR) unit ( | 12-04-2008 |
20080295320 | APPARATUS AND METHOD FOR THE INSTALLATION OF A PRE-ASSEMBLED STATOR CORE - The present invention comprises a method and apparatus for installing a stator core, or portions thereof, into a power generator frame | 12-04-2008 |
20080284262 | STATOR COIL WITH IMPROVED HEAT DISSIPATION - A stator coil includes a plurality of copper strands and a layer of high thermal conductivity polymer disposed adjacent at least one of the copper strands. The high thermal conductivity polymer includes a host polymer and a high thermal conductivity filler. The high thermal conductivity polymer improves heat transfer from the plurality copper strands. | 11-20-2008 |
20080262128 | Polymer Brushes - Polymer brushes ( | 10-23-2008 |
20080247636 | Method and System for Interactive Virtual Inspection of Modeled Objects - A method of using a Graphic User Interface (GUI) for interactive virtual inspection of modeled objects. The method includes acquiring a three-dimensional model of a modeled object and displaying a first view of the modeled object for a user to identify locations of interest on a surface of the modeled object visible within the first view. The user enters information to create a markup tag that annotates the location of interest, and the markup tag is automatically associated with the location of interest on the modeled object. A second view of the modeled object is displayed including the user identified location of interest and the markup tag. | 10-09-2008 |
20080247635 | Method of Coalescing Information About Inspected Objects - A method of coalescing information about inspected objects. The method includes acquiring an image set of an object to be inspected, the image set having a three-dimensional model of the object and a plurality of two-dimensional images of the object. A location of interest is identified on a surface of the modeled object and global coordinate points of the three-dimensional model are designated that characterize the location of interest of the modeled object. A markup tag annotating the location of interest is associate with the designated global coordinate points of the three-dimensional model, and the markup tag is conveyed when viewing any one of the plurality of two-dimensional images of the image set that have at least one image point that correlates to a corresponding designated global coordinate point of the three-dimensional model that characterize the location of interest. | 10-09-2008 |
20080239595 | ELECTRONIC GROUND DETECTION APPARATUS FOR USE ON GROUND DETECTOR RING OF POWER GENERATING SYSTEM - A ground detection apparatus for use in a power generating system including an excitation circuit and a driven rotatable shaft. A ground detector ring is disposed on the rotatable shaft of the power generating system. A ground detection transmitter is mounted on the ground detector ring and in electrical communication with the excitation circuit of the power generating system. The ground detection transmitter is utilized to detect ground faults in the excitation circuit of the power generating system and to send a signal associated with ground faults detected by the ground detection transmitter. A ground detection receiver is associated with a stationary portion of the power generation system and is in communication with the ground detection transmitter for receiving the signal associated with ground faults detected and sent by the ground detection transmitter. | 10-02-2008 |
20080236865 | ELECTRICAL-DISCHARGE-INHIBITING CONFORMABLE LAYER FOR USE IN INNER-COOLED COILS - A conformable layer ( | 10-02-2008 |
20080231844 | METHOD AND APPARATUS FOR CHECKING STATOR CORE ALIGNMENT - In one embodiment the present invention provides for a method for checking the alignment of a stator core that comprises placing a laser source | 09-25-2008 |
20080227648 | Winding for Use in High Temperature Superconducting Generator - A winding for use in a superconducting electric generator having a rotating rotor assembly surrounded by a non-rotating stator assembly is provided. The winding comprises at least one conductor structure associated with a component in the superconducting electric generator. The conductor structure comprises a plurality of conductive elements formed from a high temperature superconductive material. At least a portion of the conductive elements is arranged in a transposed relationship. A protective shell is positioned about the conductive elements and formed from a high strength alloy suitable for cryogenic temperatures. | 09-18-2008 |
20080210347 | Superalloy Component Welding at Ambient Temperature - A method for welding superalloy components at ambient temperature conditions while reducing the propensity of the superalloy material to crack as a result of the weld. A root pass region of the weld is formed using a filler material that exhibits ductility that is higher than that of the base superalloy material. The ductile material mitigates stress in the root region, thereby preventing the formation of cracks. A remaining portion of the weld is formed using a filler material that essentially matches the base superalloy material. The method may utilize a pre-weld heat treatment to grow a gamma prime precipitate phase in the superalloy material, a chill fixture to remove heat during welding, a relief cut to reduce stress in the root region, and a conventional post-weld heat treatment. | 09-04-2008 |