SIEMENS ENERGY, INC. Patent applications |
Patent application number | Title | Published |
20160123152 | AIR SEPARATOR FOR A TURBINE ENGINE - An air separator for a turbine engine is provided. The air separator includes an aft air separator member ( | 05-05-2016 |
20160115795 | TURBINE BLADE AIRFOIL AND TIP SHROUD - A turbine blade airfoil ( | 04-28-2016 |
20160114430 | REINFORCED CLADDING - A method for forming a reinforced cladding ( | 04-28-2016 |
20160108749 | TURBINE BLADE TIP SHROUD - A turbine blade tip shroud ( | 04-21-2016 |
20160102562 | COOLING ARRANGEMENT FOR GAS TURBINE BLADE PLATFORM - A gas turbine engine blade ( | 04-14-2016 |
20160102558 | GAS TURBINE BLADE CONFIGURATION - A gas turbine engine blade ( | 04-14-2016 |
20160084109 | GAS TURBINE RING SEGMENT COOLING APPARATUS - A gas turbine shroud ring segment assembly ( | 03-24-2016 |
20160084088 | STRESS RELIEVING FEATURE IN GAS TURBINE BLADE PLATFORM - A gas turbine engine blade ( | 03-24-2016 |
20160084087 | ROTOR IN A TURBINE ENGINE COUPLED TO PROVIDE INDIVIDUAL AND SEPARATE ACCESS TO RESPECTIVE ASSEMBLIES OF COMPRESSOR AND TURBINE DISKS - A rotor for a turbine engine. The rotor may include an assembly of axially-bolted compressor disks ( | 03-24-2016 |
20150375346 | COMPONENT REPAIR USING BRAZED SURFACE TEXTURED SUPERALLOY FOIL - A superalloy component such as a gas turbine engine blade ( | 12-31-2015 |
20150367456 | PRESINTERED PREFORM FOR REPAIR OF SUPERALLOY COMPONENT - A method of making pre-sintered preforms using a mixture of base superalloy particles and titanium-containing boron and silicon free braze alloy particles, such as for the repair of superalloy gas turbine engine components. Alloy particles as large as 2 mm provide reduced shrinkage when compared to prior art preforms. Braze material compositions disclosed herein are boron and silicon free and may have melting temperature ranges as low as 10° C., and they include no element not already present in the composition of the superalloy component. | 12-24-2015 |
20150352673 | COMPONENT REPAIR USING BRAZED SURFACE TEXTURED SUPERALLOY FOIL - A superalloy component such as a gas turbine engine blade ( | 12-10-2015 |
20150345796 | COMBUSTION TURBINE WITH SIAMESED WALL PAIRED COMBUSTOR HOUSINGS - A combustion turbine engine combustor section includes a plurality of annularly arrayed combustors housed within paired combustor portals of a combustor casing. Each combustor portal has a corresponding top hat cover having a peripheral flange. The paired combustor portals are formed in combustor housings having a figure eight-shaped sleeve wall planform. The paired adjoining combustor portals share a common Siamesed portion of the sleeve wall. A combustor portal mating surface is formed on an axial distal end of the sleeve wall, having a figure eight planform and defining a first array of fastener receiving apertures. A top hat cover retention bracket assembly having a composite planform conforming to the combustor portal mating surface planform and a second array of apertures that conform to the first array pattern apertures, is placed over the peripheral flanges of the paired combustor top hat covers and secured by top hat cover fasteners. | 12-03-2015 |
20150345792 | GAS TURBINE ENGINE COMBUSTOR TOP HAT COVER ATTACHMENT SYSTEM WITH LUGGED INTERLOCKING BACKING PLATE - Combustor top hat covers are attached to midframe combustor portals with a lugged backing plate that interlocks with mating recesses formed in the corresponding midframe combustor portal. Exemplary embodiments utilize twist lock engagement of backing plate ring lugs under projecting tabs formed over a lug raceway recess in the combustor portal mating surface. The top hat cover is in turn fastened to the combustor portal by fasteners that engage corresponding threaded apertures formed in the backing plate. | 12-03-2015 |
20150345504 | METHOD FOR FORMING A COATING MATRIX ON A SHAFT AND DISK ASSEMBLY FOR A TURBINE - A method for forming a coating matrix on a bore surface of a turbine disk wherein the coating matrix is applied at an interface between the disk and a turbine shaft. The coating matrix enhances thermal conductivity to increase heat transfer from the disk. The method includes providing a receiving surface on the bore surface. The receiving surface is then heated to melt the receiving surface. Next, at least one coating matrix layer is deposited on the receiving surface. The coating matrix layer includes a graphene layer. A pulsed laser system or a robot welding system may be used to melt the receiving section. | 12-03-2015 |
20150345324 | METHOD AND APPARATUS FOR MEASURING OPERATIONAL GAS TURBINE ENGINE HOUSING DISPLACEMENT AND TEMPERATURE BY A DISTRIBUTED FIBER OPTIC SENSING SYSTEM UTILIZING OPTICAL FREQUENCY DOMAIN REFLECTOMETRY - Operational gas turbine engine housing or casing dynamic strain, temporary or permanent displacement and/or temperature is measured by a distributed fiber optic sensing system (DFOSS) utilizing optical frequency domain reflectometry (OFDR) that is coupled to the turbine engine housing. The DFOSS/OFDR system measures localized variances in strain along the length of an optical fiber (OF), which are correlated with turbine engine housing displacement. Temperature influence on the measured localized strain variances is accounted for by obtaining temperature information from an another measurement system or by taking the same type OFDR measurements on unrestrained optical fiber (OF) and deriving compensated strain measurements that are not temperature influenced. The derived strain measurements along the DFOSS are correlated with housing displacement. Other embodiments include separate displacement measuring modules, each including DFOSS optical fibers, coupled along the engine housing. | 12-03-2015 |
20150343574 | STRUCTURAL BRAZE REPAIR OF SUPERALLOY COMPONENT - Boron and silicon free braze alloys useful for structural repairs of superalloy gas turbine engine components. The braze alloy composition may contain only elements that are contained in the superalloy material to be repaired, and may have melting temperature ranges as low as 10° C. to facilitate producing a high strength homogenized braze joint during a solution heat treatment of the superalloy substrate material. | 12-03-2015 |
20150343564 | METHOD FOR SELECTIVE LASER PROCESSING USING ELECTROSTATIC POWDER DEPOSITION - A method including: electrostatically adhering powder ( | 12-03-2015 |
20150341600 | FLEXIBLE TETHER POSITION TRACKING CAMERA INSPECTION SYSTEM FOR VISUAL INSPECTION OF OFF LINE INDUSTRIAL GAS TURBINES AND OTHER POWER GENERATION MACHINERY - A camera scope inspection system with a flexible, tether mounted camera head that is maneuverable in confined internal cavities of power generation machinery. A camera head position sensing system inferentially determines the three dimension (3D) position of the camera head within the inspected machinery. Camera head position data are correlated with camera image data by a controller. In this manner correlated internal inspection image data and corresponding position data are available for future analysis and image tracking. | 11-26-2015 |
20150323469 | RETAINING RING ONLINE INSPECTION APPARATUS AND METHOD - Inspecting a retaining ring of a dynamoelectric machine includes placing an optical device in a stationary component of the dynamoelectric machine and directing the optical device toward a radial view of the retaining ring. An image is obtained and transmitted of a circumferential portion of the retaining ring, using the optical device during rotation of the rotor. Identification is made of a location of one or more stress cracks forming and visible at the circumferential portion of the annular edge. Further, a structural condition is determined for at least one location on the retaining ring using a metric to identify a value of the metric exceeding a predetermined acceptable value of the metric. | 11-12-2015 |
20150323353 | FIBER OPTIC SENSING APPARATUS WITH AN IMPROVED FIBER-AFFIXING DEVICE - A fiber optic sensing apparatus that may be used to sense one or more conditions of an electromotive machine is provided. A housing ( | 11-12-2015 |
20150322817 | VIBRATION OPTIMIZED ROTOR AND A METHOD FOR PRODUCING A VIBRATION OPTIMIZED ROTOR - Disclosed is a method to minimize rotor vibration of a gas turbine. According to the method an air separator is attached to the rotor, an interference is determined between the air separator and a turbine disc of the rotor, and the interference is adjusted in the range of 0.020 and 0.060 inches. Further disclosed is rotor for a gas turbine in which an axial interference between two parts attached to the rotor are in a range of 0.20 to 0.060 inches. | 11-12-2015 |
20150321289 | LASER DEPOSITION OF METAL FOAM - A layer of superalloy metal foam ( | 11-12-2015 |
20150316606 | SELF LEARNING RADIO FREQUENCY MONITORING SYSTEM FOR IDENTIFYING AND LOCATING FAULTS IN ELECTRICAL DISTRIBUTION SYSTEMS - Electrical faults are detected in electrical distribution systems (EDS) by detection and location of radio frequency (RF) emissions generated by the fault with multiple time-synchronized radio frequency monitors (RFM) distributed about the EDS. The RFMs are coupled to a self-learning, electrical fault monitor (EFM) that characterizes and/or locates electrical faults based on operating state (OS) patterns learned from transmission of test signals generated within the EDS. RF emissions data samples are characterized as safe operation (SO) states or potential electrical faults by accessing a base of stored knowledge concerning fault emission characteristics and/or synchronized time of arrival at each RFM. Information in the base of stored knowledge is updated to include new EDS operating states (OS). Confidence level associations, location of new radio frequency emission patterns and whether those patterns are indicative of safe operating (SO) conditions or electrical faults are stored in the base of stored knowledge. | 11-05-2015 |
20150315090 | LASER GLAZING USING HOLLOW OBJECTS FOR SHRINKAGE COMPLIANCE - Hollow objects ( | 11-05-2015 |
20150314403 | ARRANGEMENT FOR LASER PROCESSING OF TURBINE COMPONENT - An arrangement ( | 11-05-2015 |
20150300179 | FORMING A SECONDARY STRUCTURE DIRECTLY ONTO A TURBINE BLADE - A process and apparatus for solid freeform fabrication and repair of components on existing bodies (such as turbine blades), the innovative process and apparatus as well as the resultant product having the following advantages: a) Can build on existing 3-D surfaces. Not limited to horizontal flat surfaces, b) Usable for metals that are difficult to weld. c) Robust process that is adaptable to new damage modes. d) No shielding of the melt pool by inert gas is needed. e) Wide range of powder sizes. | 10-22-2015 |
20150292742 | GAS TURBINE ENGINE COMBUSTOR BASKET WITH INVERTED PLATEFINS - A gas turbine engine combustor basket has nested outer and inner liners that are separated by a gap at their respective distal downstream ends for passage of cooling air between the liners. Radially inwardly projecting platefins formed on an inner circumferential surface of the outer liner maintain the cooling air passage gap. In some embodiments effusion cooling through holes are formed in the inner liner outer circumference, oriented in the air passage gap between the fins, so that cooling air passes through the effusion holes into the cooling air passage gap. | 10-15-2015 |
20150292476 | VORTEX GENERATORS ALIGNED WITH TRAILING EDGE FEATURES ON WIND TURBINE BLADE - A wind turbine blade ( | 10-15-2015 |
20150290747 | STRUCTURAL BRAZE FOR SUPERALLOY MATERIAL - Boron and silicon free braze alloys are useful for structural repair of superalloy gas turbine engine components. The braze alloy compositions include nickel, chromium, titanium, and at least one of zirconium and hafnium. All of the above elements are metallic and form ductile bonds within and across the braze interface when compared to non-metallic bonds of boron and silicon. | 10-15-2015 |
20150284264 | METHODS AND SYSTEMS FOR TREATING SPENT CAUSTIC AND REGENERATING MEDIA - Methods and systems for applying separation processes to a spent caustic stream are disclosed. Methods and systems for regenerating media utilized in spent caustic separation processes are disclosed. | 10-08-2015 |
20150280530 | FIBER OPTIC SENSING APPARATUS FOR DETECTING STATOR SLOT TEMPERATURES AND STATOR INCLUDING SUCH APPARATUS - A sensing apparatus ( | 10-01-2015 |
20150276226 | DUAL OUTLET NOZZLE FOR A SECONDARY FUEL STAGE OF A COMBUSTOR OF A GAS TURBINE ENGINE - A secondary fuel stage ( | 10-01-2015 |
20150275687 | LOCALIZED REPAIR OF SUPERALLOY COMPONENT - A method for repairing a damaged portion ( | 10-01-2015 |
20150275682 | SPRAYED HAYNES 230 LAYER TO INCREASE SPALLATION LIFE OF THERMAL BARRIER COATING ON A GAS TURBINE ENGINE COMPONENT - A technique for improving the thermal protection against oxidation for a component in a gas turbine engine, for example, blades, row 1 vanes and row 2 vanes. The technique includes spraying a thin layer of alloy 230 on a base substrate of the component at those locations on the component where thermal protection against oxidation is desired. A metal bond coat layer is then deposited on the alloy 230 layer and a thermal barrier coating is deposited on the bond coat layer. The chromium, molybdenum, iron and tungsten in alloy 230 provide superior oxidation resistance, and the addition of lanthanum in the alloy 230 helps tailor thermal expansion with the thermal barrier coating resulting in higher spallation life. | 10-01-2015 |
20150273605 | AUTOMATED CUTTING OF A CYLINDRICAL WORKPIECE - Disclosed is an automated cutting of a cylindrical workpiece. According to a method a cutting device is positioned, a motor is activated to rotate about an axis to cut the cylindrical element, and cutting the cylindrical element. Further disclosed is an apparatus and system to automate the cutting of a cylindrical workpiece. | 10-01-2015 |
20150267553 | METHOD FOR TRACKING TURBINE BLADE CREEP - A method for inspecting a turbine blade of a turbine. The method includes operating the turbine and providing a plurality of ablative material strips on the turbine blade. Each strip is fabricated from a common base material and is configured to ablate after exposure to a corresponding predetermined temperature for a corresponding predetermined time period Ablation of a strip indicates a corresponding amount of creep has occurred in the blade. In addition, the method includes visually inspecting the strips at predetermined intervals to determine whether one or more of the strips is ablated | 09-24-2015 |
20150260690 | METHOD AND SYSTEM FOR IMMERSION ULTRASOUND INSPECTION INCLUDING WITHIN DOWNWARDLY OPENING CAVITIES - Immersion ultrasonic NDE is performed within cavities of inanimate objects, having downwardly directed openings, such as for in situ inspection of steam inlet sleeves and steam inlet necks within steam turbine housings. A shaft assembly has one or more single angle or phased array ultrasonic probes that are affixed on an upstream or distal end. An inflatable bladder is affixed to the shaft on a proximal end of the shaft assembly downstream the ultrasonic probe(s). The shaft is inserted into the cavity opening, and the bladder is inflated to form a fluid tight seal against the cavity. Immersion fluid is introduced upstream the bladder in the volume occupied by the probes. Immersion ultrasonic inspection of the object is then performed. | 09-17-2015 |
20150252779 | WIND TURBINE BLADE WITH VISCOELASTIC DAMPING - A wind turbine blade ( | 09-10-2015 |
20150252688 | TURBINE AIRFOIL COOLING SYSTEM WITH COOLING SYSTEMS USING HIGH AND LOW PRESSURE COOLING FLUIDS - A turbine airfoil cooling system including a low pressure cooling system and a high pressure cooling system for a turbine airfoil of a gas turbine engine is disclosed. In at least one embodiment, the low pressure cooling system may be an ambient air cooling system, and the high pressure cooling system may be a compressor bleed air cooling system. In at least one embodiment, the compressor bleed air cooling system in communication with a high pressure subsystem that may be a snubber cooling system positioned within a snubber. A delivery system including a movable air supply tube may be used to separate the low and high pressure cooling subsystems. The delivery system may enable high pressure cooling air to be passed to the snubber cooling system separate from low pressure cooling fluid supplied by the low pressure cooling system to other portions of the turbine airfoil cooling system. | 09-10-2015 |
20150244344 | SELF-POWERED SENSING AND TRANSMITTING DEVICE AND METHOD OF FABRICATING THE SAME - A self-powered sensing and transmitting circuit ( | 08-27-2015 |
20150242440 | COMPUTERIZED METHOD FOR TRANSFORMING AN IMAGE FROM AN IMAGE-SEARCHABLE DOMAIN TO A PIXEL-SEARCHABLE DOMAIN - Computerized methodology for organizing and/or retrieving pixel data for rendering digital images In one embodiment, the method may include transforming ( | 08-27-2015 |
20150241303 | METHOD FOR INSPECTING A TURBINE ENGINE ROTOR WITH A THRU BOLT THREADS INSPECTION APPARATUS - Turbine engine rotor corresponding thru-bolts and disc cavities are inspected with a camera inspection system that includes one or both of a thru-bolt male threads inspection apparatus and a rotor disc cavity inspection apparatus. The thru-bolts threads inspection apparatus engages the male threads and advances along the bolt threads pattern, selectively capturing camera images at desired spatial positions along the threads pattern. The plural camera threads images are desirably combined to form a composite image of a desired portion of or the entire thru-bolt male threads profiles, which aids their inspection evaluation and provides an archived composite image of the profiles. | 08-27-2015 |
20150240984 | PIPE CRAWLER APPARATUS AND METHOD FOR INTERNAL PIPE INSPECTION - Steam turbine engine cross over pipe or other pipe internal inspection is performed with a selectively steerable pipe inspection crawler apparatus with a chassis having a longitudinal axis, with front and rear Mechanum wheels capable of independently-selected forward or rearward driven rotational direction, for selectively steering the apparatus within the pipe interior under control of a human-machine interface (HMI). The crawler apparatus has at least one inspection camera having a field of view, for capturing images of a pipe interior that is also under control of the HMI. Embodiments of the crawler apparatus include a selectively orientable inspection camera and/or a deployable bore scope that is selectively deployed and retracted from a descending section of the cross over pipe. | 08-27-2015 |
20150240657 | METHOD FOR INSPECTING A TURBINE ENGINE ROTOR WITH A ROTOR DISC CAVITY INSPECTION APPARATUS - Turbine engine rotor corresponding thru-bolts and disc cavities are inspected with a camera inspection system that includes one or both of a thru-bolt male threads inspection apparatus and a rotor disc cavity inspection apparatus. The disc cavity inspection scope apparatus is insertable in one or more of the desired rotor disc cavities and orients an attached inspection camera field of view generally transverse to the circumferential wall in the rotor disc that defines the cavity. Preferably inspection scope apparatus insertion into the disc cavities is performed with a motion control system that monitors spatial position of the camera field of view relative to the recess circumferential wall. The plural camera cavity circumferential wall images are desirably combined to form a composite image of a desired portion of or the entire disc cavity circumferential surface, which aids their inspection evaluation and provides an archived composite image of the surface. | 08-27-2015 |
20150240652 | TURBINE ABRADABLE LAYER WITH ASYMMETRIC RIDGES OR GROOVES - Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting asymmetric non-parallel walls or trapezoidal cross section ridges that reduce, redirect and/or block blade tip airflow leakage downstream into the grooves rather than from turbine blade airfoil high to low pressure sides. In some embodiments at least one angularly oriented first groove formed in the ridge plateau is adapted for angular orientation upstream a turbine blade rotation direction to resist blade tip airflow leakage and the ridges are separated by second grooves that are skewed relative to the respective ridge plateaus and the substrate that are also adapted for orientation upstream the turbine blade rotation direction to resist blade tip airflow leakage. | 08-27-2015 |
20150240644 | THERMAL SHIELDS FOR GAS TURBINE ROTOR - A turbomachine including a rotor having an axis and a plurality of disks positioned adjacent to each other in the axial direction, each disk including opposing axially facing surfaces and a circumferentially extending radially facing surface located between the axially facing surfaces. At least one row of blades is positioned on each of the disks, and the blades include an airfoil extending radially outward from the disk A non-segmented circumferentially continuous ring structure includes an outer rim defining a thermal barrier extending axially in overlapping relation over a portion of the radially facing surface of at least one disk, and extending to a location adjacent to a blade on the disk A compliant element is located between a radially inner circumferential portion of the ring structure and a flange structure that extends axially from an axially facing surface of the disk | 08-27-2015 |
20150239062 | INERTIA FRICTION DISK WELDING - A method of friction welding. A cutout ( | 08-27-2015 |
20150239043 | Cast Features for Location and Inspection - A method for casting an object ( | 08-27-2015 |
20150233582 | GAS FLOW PATH FOR A GAS TURBINE ENGINE - A duct arrangement in a can annular gas turbine engine. The gas turbine engine has a gas delivery structure for delivering gases from a plurality of combustors to an annular chamber that extends circumferentially and is oriented concentric to a gas turbine engine longitudinal axis for delivering the gas flow to a first row of blades A gas flow path is formed by the duct arrangement between a respective combustor and the annular chamber for conveying gases from each combustor to the first row of turbine blades The duct arrangement includes at least one straight section having a centerline that is misaligned with a centerline of the combustor. | 08-20-2015 |
20150228392 | MULTIDIRECTIONAL MAGNETIC PARTICLE INSPECTION SYSTEM - A magnetic particle inspection system for inspecting a plurality of articles The system includes a first magnetizing coil for generating a first magnetic field oriented in a first direction The system also includes a second magnetizing coil for generating a second magnetic field oriented in a second direction perpendicular to the first direction, wherein the first and second magnetizing coils are located in a common plane In addition, the system may include a mat having a plurality of drainage holes, wherein the first and second magnetizing coils are located in the mat and the first and second magnetizing coils are sized to inspect a plurality of articles Further, the system includes a power supply for supplying power for energizing the first and second magnetizing coils and a switching unit for switching current flow between the first and second magnetizing coils. | 08-13-2015 |
20150226929 | APPARATUS FOR MAKING UNIFORM OPTICAL FIBER BUNDLES IN POWER GENERATORS - A circular fiber hoop for supporting one or more fiber optic cables, especially fiber optic cables for an optical sensor provided within a pressurized enclosure of a power generator. The fiber hoop is a single piece member including a center mandrel positioned between opposing side guards. The fiber optic cable is wound around the mandrel between the side guards. An end of the fiber optic cable including the sensor is optically coupled through a union connector to another optical fiber, where the union connector is mounted to one of the side guards so that it is separated from the wound mass of the fiber cables The wound mass of the fiber cable on the mandrel is then enclosed in a suitable tape | 08-13-2015 |
20150226436 | FLASHBACK DETECTION IN GAS TURBINE ENGINES USING DISTRIBUTED SENSING - A distributed sensing system for detecting a flashback condition in a combustor for a gas turbine engine The distributed sensing system includes one or more strategically positioned fiber optic cables provided upstream of the combustion area in the combustor. The distributed sensing system employs Rayleigh backscattering and swept-wavelength interferometry to measure temperature and reliably identify the location of the flashback condition The fiber optic cable is specially fabricated to have a high temperature resistance suitable for those temperatures existing during flashback conditions. The fiber optic cable can be wrapped on an inside of a combustion basket or on an outside of the combustion basket, and in a serpentine manner or otherwise. | 08-13-2015 |
20150224607 | SUPERALLOY SOLID FREEFORM FABRICATION AND REPAIR WITH PREFORMS OF METAL AND FLUX - A preform ( | 08-13-2015 |
20150224603 | FILLER CLOTH FOR LASER CLADDING - A preform ( | 08-13-2015 |
20150221203 | GENERATOR MODULAR CONTINUOUS MONITORING SYSTEM WITH REMOTE ACCESS CAPABILITY - A monitoring system for electrical generators is disclosed The system continuously monitors sensor data from the generator and other electrical and mechanical equipment in a power plant, including data from sensors of different signal types, and data from existing control systems The monitoring system stores the data and analyzes it for both current conditions and time-based trends, and provides alarms for out-of-range conditions. The monitoring system also displays the data in an array of interface screens which make it easy for an operator to evaluate the performance of all of the systems in the power plant Remote access to the monitoring system from computers or mobile devices is also provided | 08-06-2015 |
20150218948 | TURBINE ENGINE BLADE REMOVAL APPARATUS AND METHOD - A turbine engine blade removal apparatus with a pair of opposed outwardly biased blocks are positioned proximal a blade root and corresponding rotor disc slot between opposed axial faces of the subject first rotor disc and an adjoining second rotor disc. The blocks are outwardly biased in abutting contact with first and second rotor disc axial faces, aligning an aperture of a guide bushing with an exposed axial face of the blade root, the guide bushing coupled to at least the first block. A punch is inserted in the guide bushing aperture so that a punch tip is in abutting relationship with the blade root axial face. An impact tool drives an opposite impact end of the punch, causing the punch to direct a relative driving force on the blade root, separating the blade root from the corresponding rotor disc slot. | 08-06-2015 |
20150212021 | APPARATUS AND METHOD FOR MONITORING AND QUANTIFYING PROGRESSION OF A STRUCTURAL ANOMALY IN A HIGH TEMPERATURE ENVIRONMENT OF A COMBUSTION TURBINE ENGINE - Apparatus and method for monitoring and quantifying progression of a structural anomaly, such as crack, over a surface of a component ( | 07-30-2015 |
20150199805 | METHOD OF DETERMINING THE LOCATION OF TIP TIMING SENSORS DURING OPERATION - A combination probe is positioned at a location in a stationary portion of a turbo machine that defines a gas flow path and is configured to detect a moving portion of the turbo machine within the gas flow path. The combination probe includes a tip timing sensor configured to sense when the moving portion is located proximate to the location of the probe, and an optical component configured to have a field of view that includes the moving portion when the moving portion is located proximate to the location of the probe. There is also an image capture device coupled to the optical component to capture an image of the field of view. The image can be used to determine the particular blade tip location within the field of view which is also the blade tip location sensed by the tip timing sensor. | 07-16-2015 |
20150198055 | GAS TURBINE INCLUDING SEALING BAND AND ANTI-ROTATION DEVICE - A turbine is provided comprising a plurality of stages, each stage comprising a rotatable disk and blades carried thereby, at least one pair of adjacent rotatable disks defining an annular gap therebetween and having respective opposing sealing band receiving slots aligned with the annular gap A sealing band is located in the opposing receiving slots to seal the annular gap Disk engagement structure is defined in the pair of adjacent rotatable disks. A clip member is coupled to the sealing band and engaged with the pair of adjacent rotatable disks through the disk engagement structure The clip member may have an aperture extending only partially through the clip member for alignment with a hole in the sealing band for engagement with a tool To improve weld geometry, the clip member may have angled surfaces and notched areas, and the sealing band may have chamfered edges. | 07-16-2015 |
20150198054 | ASSEMBLY FOR DIRECTING COMBUSTION GAS - An arrangement is provided for delivering gases from a plurality of combustors of a can-annular gas turbine combustion engine to a first row of turbine blades including a first row of turbine blades. The arrangement includes a gas path cylinder, a cone and an integrated exit piece (IEP) for each combustor. Each IEP comprises an inlet chamber for receiving a gas flow from a respective combustor, and includes a connection segment. The IEPs are connected together to define an annular chamber extending circumferentially and concentric to an engine longitudinal axis, for delivering the gas flow to the first row of blades. A radiused joint extends radially inward from a radially outer side of the inlet chamber to an outer boundary of the annular chamber, and a flared fillet extends radially inward from a radially inner side of the inlet chamber to an inner boundary of the annular chamber. | 07-16-2015 |
20150198050 | INTERNAL COOLING SYSTEM WITH CORRUGATED INSERT FORMING NEARWALL COOLING CHANNELS FOR AIRFOIL USABLE IN A GAS TURBINE ENGINE - An airfoil for a gas turbine engine in which the airfoil includes an internal cooling system formed from one or more midchord cooling channels with a corrugated insert positioned therein and creating nearwall leading edge, pressure side and suction side nearwall cooling channels. The corrugated insert may be formed from a wall that oscillates in a repeating pattern between peaks and valleys, such that the peaks are closer to an inner surface of the outer wall forming the generally elongated hollow airfoil The corrugated insert may work in concert with the rows of partition walls to create periodic impingement on the inner surface of the outer wall Such cooling system provides adequate cooling for use in environments in which few, if any, cooling holes are desired, such as in crude oil engine applications | 07-16-2015 |
20150197859 | MATERIAL DEPOSITION USING POWDER AND FOIL - The loss of aluminum content during the laser ( | 07-16-2015 |
20150196973 | APPARATUS FOR LASER PROCESSING OF HIDDEN SURFACES - A laser emitter ( | 07-16-2015 |
20150092039 | IN-SITU BLADE-MOUNTED OPTICAL CAMERA INSPECTION SYSTEM FOR TURBINE ENGINES - Turbine engine casing interiors are visually inspected in a fully assembled turbine casing by mounting an optical camera on a turbine blade that captures optical images, such as of the casing abradable surface. Optical images are recorded as the blade circumferentially sweeps the turbine casing when the turbine is operated in turning gear mode or manually rotated. Blade rotational position data are collected by a rotational position sensor. A data processing system correlates the captured optical images and rotational position data about the turbine casing circumference. This method and apparatus provide an accurate and cost effective solution for accessing a turbine casing interior. | 04-02-2015 |
20140360190 | STEAM TURBINE MOISTURE REMOVAL SYSTEM - A drain system ( | 12-11-2014 |
20140290368 | METHOD AND APPARATUS FOR REMOTE POSITION TRACKING OF AN INDUSTRIAL ULTRASOUND IMAGING PROBE - A freestanding ultrasonic probe or transducer position relative to the inspected object is remotely tracked with a wireless transmitter/receiver or an optically based positioning system. Either type of positioning system generates a time stamped or commonly clocked positional data set that are sent to a post data processing module. The post data processing module creates a 3-D model of the inspected object, including location and size of indications in the inspected object, utilizing the positional data and inspection data generated by an ultrasonic testing instrument coupled to the freestanding probe/transducer. | 10-02-2014 |
20140283612 | PHASED ARRAY ULTRASONIC BOLT INSPECTION APPARATUS AND METHOD - Ultrasonic bolt inspection apparatus and methods facilitate in situ as well as bench non-destructive evaluation (NDE) inspection of fastening bolt distal ends and their mating nuts. The apparatus is coupled to an exposed end of a fastener bolt head, its exposed thread tip or to a mating nut. The apparatus retains a phased array ultrasonic probe that generates inspection scan data and a rotational position encoder that generates rotational position data. The probe is coupled to an ultrasonic inspection system analyzer, which converts scan data into inspection data that characterizes possible defects in the inspected bolt. A system controller is coupled to the analyzer and the rotational position encoder, correlating rotation position data and inspection data, in order to identify location and characteristics of possible defects in the inspected bolt end. | 09-25-2014 |
20140272450 | NEAR EUTECTIC COMPOSITION NICKEL BASE SANDWICH BRAZE FOIL - A braze foil ( | 09-18-2014 |
20140251924 | TREATMENT OF SPENT CAUSTIC WASTE - Systems and methods are provided for the treatment of caustic wastewater. Specifically, systems and methods are provided for combining refinery spent caustic and ethylene spent caustic solutions and treating the combined spent caustic mixture using a wet air oxidation process. | 09-11-2014 |
20140251806 | WATER TREATMENT ARRANGEMENT FOR STEAM-ASSISTED OIL PRODUCTION OPERATION - A water processing arrangement ( | 09-11-2014 |
20140248512 | FUNCTIONAL BASED REPAIR OF SUPERALLOY COMPONENTS - A method of repairing or manufacturing a superalloy component ( | 09-04-2014 |
20140248133 | ACTIVE BYPASS FLOW CONTROL FOR A SEAL IN A GAS TURBINE ENGINE - An active bypass flow control system for controlling bypass compressed air based upon leakage flow of compressed air flowing past an outer balance seal between a stator and rotor of a first stage of a gas turbine in a gas turbine engine is disclosed. The active bypass flow control system is an adjustable system in which one or more metering devices may be used to control the flow of bypass compressed air as the flow of compressed air past the outer balance seal changes over time as the outer balance seal between the rim cavity and the cooling cavity wears In at least one embodiment, the metering device may include an annular ring having at least one metering orifice extending therethrough, whereby alignment of the metering orifice with the outlet may be adjustable to change a cross-sectional area of an opening of aligned portions of the outlet and the metering orifice | 09-04-2014 |
20140248132 | ACTIVE BYPASS FLOW CONTROL FOR A SEAL IN A GAS TURBINE ENGINE CROSS-REFERENCE TO RELATED APPLICATION - An active bypass flow control system for controlling bypass compressed air based upon leakage flow of compressed air flowing past an outer balance seal between a stator and rotor of a first stage of a gas turbine in a gas turbine engine is disclosed. The active bypass flow control system is an adjustable system in which one or more metering devices may be used to control the flow of bypass compressed air as the flow of compressed air past the outer balance seal changes over time as the outer balance seal between the rim cavity and the cooling cavity wears. In at least one embodiment, the metering device may include a valve formed from one or more pins movable between open and closed positions in which the one pin at least partially bisects the bypass channel to regulate flow. | 09-04-2014 |
20140241938 | PRECISION CASTING PROCESS - A ceramic casting vessel ( | 08-28-2014 |
20140237820 | Turbine Blade Insertion Tool - Turbine blade insertion tool ( | 08-28-2014 |
20140231356 | WATER TREATMENT APPARATUS INCORPORATING WALNUT SHELL FILTER MEDIA AND A DRAFT TUBE SYSTEM - The present invention relates generally to a system and method for treating wastewater in a filter media apparatus having a draft tube system. The filter media may be walnut shell media. | 08-21-2014 |
20140200853 | SYSTEM AND METHOD FOR IDENTIFICATION, GROUPING AND SIZING OF EMBEDDED FLAWS IN ROTOR COMPONENTS USING ULTRASONIC INSPECTION - A method and software system for flaw identification, grouping and sizing for fatigue life assessment for rotors used in turbines and generators. The method includes providing ultrasonic data of a plurality of rotor slices and providing volume reconstruction of the ultrasonic data. The method also includes providing in-slice identification, grouping and sizing of flaw indications in the rotor based on the volume reconstruction. Further, the method includes providing inter-slice identification, grouping and sizing of the flaw indications based on the in-slice flaw indications and providing flaw location and size information. The method can be used in both phased-array and A-scan inspections. | 07-17-2014 |
20140145546 | ELECTRICAL CONDUCTORS AND RELATED DEVICES - A method of spacing a plurality of electrical conductors for carrying electrical current in an electrical machine may include positioning between the electrical conductors an uncured spacer body. The uncured spacer body may include a curable material, and an activatable heat generating material mixed with the curable material. The method may further include activating the activatable heat generating material to heat the curable material to form a cured spacer to thereby space the electrical conductors in the electrical machine. | 05-29-2014 |
20140144008 | STATOR CORE MODULE, STATOR CORE ASSEMBLY AND PROCESS FOR ASSEMBLING A STATOR CORE ASSEMBLY - The present invention comprises a stator core module, stator core assembly and process for assembling a stator core assembly to replace existing stator cores in electric power generators. First and second stator core modules are aligned such that one end of a fastener assembly in the second stator core module is nested in a counter-bore of the first stator core module and one end of a fastener assembly in the first stator core is nested in a counter-bore of the second stator core module. | 05-29-2014 |
20140100798 | TURBINE BLADE FATIGUE LIFE ANALYSIS USING NON-CONTACT MEASUREMENT AND DYNAMICAL RESPONSE RECONSTRUCTION TECHNIQUES - A method dynamically reconstructing a stress and strain field of a turbine blade includes providing a set of response measurements from at least one location on a turbine blade, band-pass filtering the set of response measurements based on an upper frequency limit and a lower frequency limit, determining an upper envelope and a lower envelope of the set of response measurements from local minima and local maxima of the set of response measurements, calculating a candidate intrinsic mode function (IMF) from the upper envelope and the lower envelope of the set of response measurements, providing an N×N mode shape matrix for the turbine blade, where N is the number of degrees of freedom of the turbine blade, when the candidate IMF is an actual IMF, and calculating a response for another location on the turbine blade from the actual IMF and mode shapes in the mode shape matrix. | 04-10-2014 |
20140093415 | METHOD FOR REPAIRING A COMPONENT FOR USE IN A TURBINE ENGINE - A removed damaged portion of a fully consolidated turbine engine component is replaced with a powder coupon that includes powder particles that are at most partially sintered or are bonded together with a binder. A bonding agent is applied to the component and/or the powder coupon. The powder coupon is then positioned over the component and heat is applied to fully sinter the powder particles, thus causing the powder coupon to shrink onto the component. The heat also activates the bonding agent to bond the shrunken powder coupon to the component, but the heat does not sinter the material forming the fully consolidated component. | 04-03-2014 |
20140064326 | NOISE ROBUST TIME OF FLIGHT ESTIMATION FOR ACOUSTIC PYROMETRY - An acoustic signal traversing a hot gas is sampled at a source and a receiver and is represented in overlapping windows that maximize useable signal content. Samples in each window are processed to represented in different sparsified bins in the frequency domain. Determining a signal delay between the source and the receiver from a summation of maximum smoothed coherence transform cross-correlation values of different data windows wherein a sparseness of a mean smoothed coherence transform cross-correlation of windows is maximized. Determining a set of delay times wherein outliers are deleted to estimate a time of flight from which a temperature of the hot gas is calculated. | 03-06-2014 |
20140037526 | H2S CONVERSION TO SULFUR USING A REGENERATED IODINE SOLUTION - Systems and methods of removing sulfur from a gas stream comprising hydrogen sulfide (H | 02-06-2014 |
20130255937 | HIGH SPEED CEMENT BOND LOGGING AND INTERACTIVE TARGETED INTERVENTION - A method for cement bond logging and targeted intervention, including lowering a cylindrical n×m array of ultrasound (US) transducers into a well, firing the US transducers to transmit US signals into a well casing, converting reflected US signals received by the transducers into electronic form and transmit the converted signals to a control unit, analyzing the converted signals to detect holidays, if a holiday is detected, determining a position and angle of the holiday with respect to the transducers, and applying a high intensity focused ultrasound (HIFU) signal to the well casing to fill the holiday. | 10-03-2013 |
20130233800 | LOW CONCENTRATION WASTEWATER TREATMENT SYSTEM AND PROCESS - A low concentration wastewater treatment system is provided that includes a high flux adsorbent material treatment system integrated with a low flux adsorbent material biological regeneration reactor. The high flux adsorbent material treatment system includes one or more unit operations for mixing low concentration wastewater with adsorbent material that is fresh, recycled, or a combination of both, and for decanting a liquid effluent having a reduced level of contaminants. The adsorbent material with adsorbed contaminants is regenerated in a low flux adsorbent material biological regeneration reactor in which a biological reaction occurs, such as biological oxidation, wherein organic contaminants in the wastewater are metabolized generally into carbon dioxide and water. Excess biomass is removed from the adsorbent material, and the thus-regenerated adsorbent material is recycled to the high flux adsorbent material treatment system. | 09-12-2013 |
20130220921 | WASTEWATER TREATMENT PROCESS INCLUDING IRRADIATION OF PRIMARY SOLIDS - The present invention provides a method for treating wastewater in which the majority of solids and biological oxygen demand compounds are separated from the wastewater feed using a primary separation process, to produce a solids phase and a water phase. The solids phase is irradiated to reduce the level of pathogens such that it is safe to use as a soil substitute and/or additive so that the solids can thus be disposed of in an environmentally-friendly manner. In additional embodiments, the solids that have been disinfected by radiation are mixed with a suitable inert filler material to produce a soil substitute, fertilizer, compost, or other soil additive. The liquid phase is treated in a substantially smaller system than would be required for treating the full-strength wastewater that can include a suspended media biological regeneration reactor system. The liquid treatment system can include a high flux adsorbent material treatment system integrated with a low flux adsorbent material biological regeneration reactor. | 08-29-2013 |
20130206705 | pH CONTROL TO ENABLE HOMOGENEOUS CATALYTIC WET AIR OXIDATION - A system and method for the treatment of process streams is provided. A catalyst mediates a wet oxidation process at elevated temperatures and pressures for treating at least one undesirable constituent in an aqueous mixture. A catalyst may be selected for its solubility at a detected pH level of the aqueous mixture. Alternatively, a pH level of the aqueous mixture may be adjusted to solubilize a selected catalyst and/or maintain the selected catalyst in a soluble form. A controller in communication with a pH sensor may be configured to generate a control signal to adjust the pH level of the aqueous mixture in response to the pH sensor registering a pH level outside a predetermined pH solubility range for a selected catalyst. | 08-15-2013 |
20130191041 | INSULATION DEFECT DETECTION OF HIGH VOLTAGE GENERATOR STATOR CORE - In a general methodology for insulation defect identification in a generator core, a Chattock coil is used to measure magnetic potential difference between teeth. Physical knowledge and empirical knowledge is combined in a model to predict insulation damage location and severity. Measurements are taken at multiple excitation frequencies to solve for multiple characteristics of the defect. | 07-25-2013 |
20130191039 | METHOD AND SYSTEM OF DETERMINISTIC FATIGUE LIFE PREDICTION FOR ROTOR MATERIALS - A method of fatigue life prediction including: calculating a critical crack size of an object of interest; identifying a first flaw in ultrasound data of the object of interest; determining that the first flaw interacts with a second flaw, the first flaw is to be merged with the second flaw, or the first flaw is isolated; calculating an initial crack size based on the determination; and calculating an increase in the initial crack size due to fatigue and creep to determine a number of load cycles until the initial crack size reaches the critical crack size. | 07-25-2013 |
20130074946 | CAST MANIFOLD FOR DRY LOW NOx GAS TURBINE ENGINE - A casting ( | 03-28-2013 |
20130074501 | COMBUSTOR RESONATOR SECTION WITH AN INTERNAL THERMAL BARRIER COATING AND METHOD OF FABRICATING THE SAME - A combustor ( | 03-28-2013 |
20120128266 | Reconstruction of Phased Array Data - An image reconstruction method includes receiving volume data comprising a plurality of sampling points, determining a first conditioning of the sampling points suppressing low amplitudes and conserving maximum amplitudes, determining a second conditioning of the sampling points wherein an influence of a sampling point depends on its distance to a grid point in a sampling grid, determining a kernel comprising a plurality of weighting functions for the first conditioning and the second conditioning to determine an energy spread of each of the plurality of sampling points without determining a shape or size of the kernel, and outputting a reconstructed volume according to the energy spread of each of the plurality of sampling points. | 05-24-2012 |
20110109627 | Method and Apparatus for Three-Dimensional Visualization and Analysis for Automatic Non-Destructive Examination of a Solid Rotor using Ultrasonic Phased Array - A method and apparatus for three-dimensional visualization and analysis for automatic non-destructive examination of a solid Rotor using ultrasonic phased array is disclosed. Data is acquired by scanning a solid rotor with a phased array ultrasound transducer producing a plurality of two dimensional ultrasound scans. Each of a plurality of sample points of a plurality of two dimensional ultrasound scans are associated with a corresponding 3D image point of a regular grid. A kernel function for each of the plurality of sample points defining a size and shape of a kernel located at the corresponding image point is determined. A weight is assigned to each kernel which, in one embodiment, is based on the sample point value. A value for each image point of the regular 3D grid is determined based on kernels overlapping each image point. A three-dimensional volume representing the solid rotor is then visualized. | 05-12-2011 |
20100284822 | Turbine Airfoil with a Compliant Outer Wall - A turbine airfoil usable in a turbine engine with a cooling system and a compliant dual wall configuration configured to enable thermal expansion between inner and outer layers while eliminating stress formation in the outer layer is disclosed. The compliant dual wall configuration may be formed a dual wall formed from inner and outer layers separated by a support structure. The outer layer may be a compliant layer configured such that the outer layer may thermally expand and thereby reduce the stress within the outer layer. The outer layer may be formed from a nonplanar surface configured to thermally expand. In another embodiment, the outer layer may be planar and include a plurality of slots enabling unrestricted thermal expansion in a direction aligned with the outer layer. | 11-11-2010 |
20100284798 | Turbine Airfoil With Dual Wall Formed from Inner and Outer Layers Separated by a Compliant Structure - A turbine airfoil usable in a turbine engine with a cooling system and a compliant dual wall configuration configured to enable thermal expansion between inner and outer layers while eliminating stress formation is disclosed. The compliant dual wall configuration may be formed a dual wall formed from inner and outer layers separated by a compliant structure. The compliant structure may be configured such that the outer layer may thermally expand without limitation by the inner layer. The compliant structure may be formed from a plurality of pedestals positioned generally parallel with each other. The pedestals may include a first foot attached to a first end of the pedestal and extending in a first direction aligned with the outer layer, and may include a second foot attached to a second end of the pedestal and extending in a second direction aligned with the inner layer. | 11-11-2010 |
20100279072 | Gussets for Strengthening CMC Fillet Radii - A ceramic matrix composite (CMC) structure ( | 11-04-2010 |
20100257860 | Air Vent in Main Steam Duct of Steam Turbine - A power plant including a steam turbine, and a steam turbine exhaust duct configured to deliver uncontaminated fluid from the steam turbine to downstream components of the power plant. The steam turbine exhaust duct includes a steam turbine exhaust duct isolation valve selectively configured to prevent fluid communication between the steam turbine exhaust duct and the downstream components of the power plant, and a steam turbine exhaust duct vent with a steam turbine exhaust duct vent valve. The steam turbine exhaust duct vent is configured to deliver contaminated fluid from the steam turbine exhaust duct to a fluid sink upon opening of the exhaust duct vent valve. | 10-14-2010 |
20100239432 | Turbine Vane for a Gas Turbine Engine Having Serpentine Cooling Channels Within the Inner Endwall - A turbine vane for a gas turbine engine having an internal cooling system in fluid communication with cooling channels positioned in the inner endwall is disclosed. The cooling system in the inner endwall may include cooling channels extending outwardly from the leading edge, trailing edge, pressure side and suction side toward the edges of the inner endwall. The cooling channels may be serpentine cooling channels and may be two or more serpentine cooling channels coupled together in series. The cooling channels may exhaust cooling fluids from the inner endwall through a plurality of orifices on an outer surface facing the opposing endwall and on the sides surfaces of the endwall. The pressure side and suction side midchord modulus serpentine flow circuits may receive cooling fluids from one pass of an internal midchord cooling channel and may exhaust those cooling fluids into another pass of the midchord cooling channel. | 09-23-2010 |
20100239431 | Turbine Airfoil Cooling System with Dual Serpentine Cooling Chambers - A cooling system for a turbine airfoil of a turbine engine having dual serpentine cooling channels, an inward serpentine cooling channel and an outward serpentine cooling channel, positioned within the airfoil. The inward serpentine cooling channel may receive cooling fluids from a cooling supply system through the root and exhaust cooling fluids to the outward serpentine cooling channel at the leading edge. The outward serpentine cooling channel may pass the cooling fluids through the outward portion of the serpentine cooling channel and exhaust the cooling fluids through the trailing edge of the airfoil. Such configuration yields a better creep capability for the blade. | 09-23-2010 |
20100226790 | TURBINE BLADE LEADING EDGE TIP COOLING SYSTEM - A turbine blade for a turbine engine having a cooling system in the turbine blade formed from at least one leading edge cooling chamber for cooling the leading edge and for exhausting cooling fluids through a tip exhaust outlet. The leading edge cooling channel may include a second section that extends radially inward from the tip exhaust outlet and a first section that extends radially inward from the second section along the leading edge. The second section may be narrower than the first section and may direct cooling fluids to be exhausted from tip exhaust outlet skewed angle towards the suction side of the blade. As such, the leading edge cooling channel and tip exhaust outlet cooperate to exhaust the cooling fluids without forming a separation zone at the upstream side of the intersection between the leading edge cooling channel and the tip exhaust outlet. | 09-09-2010 |
20100226789 | TURBINE BLADE DUAL CHANNEL COOLING SYSTEM - A turbine blade having an internal cooling system with dual serpentine cooling channels in communication with tip cooling channels is disclosed. In at least one embodiment, the cooling system may include first and second tip cooling channels in communication with the first and second serpentine cooling channels, respectively. The first tip cooling channel may extend from the leading edge to the trailing edge and be formed from a first suction side tip cooling channel and a first pressure side tip cooling channel. The second tip cooling channel may extend from a midchord region toward the trailing edge and may be positioned between the pressure and suction sides such that the second tip cooling channel is positioned generally between the first suction side and pressure side tip cooling channels. The first and second tip cooling channels may exhaust cooling fluids through the trailing edge. | 09-09-2010 |
20100226788 | TURBINE BLADE WITH INCREMENTAL SERPENTINE COOLING CHANNELS BENEATH A THERMAL SKIN - A turbine blade having an internal cooling system with incremental serpentine cooling channels in near walls forming an outer surface of the turbine blade is disclosed. The turbine blade may be formed from an internal structural spar that is covered with a thermal skin. The incremental serpentine cooling channels may be cut into the outer surface of the spar to which the thermal skin may be attached. The incremental serpentine cooling channels may be formed from two or more serpentine cooling channels aligned along an axis that extends generally spanwise throughout the turbine blade. A row of incremental serpentine cooling channels may extend from a root to a tip of the blade, but a single incremental cooling channel does not. | 09-09-2010 |
20100226761 | Turbine Airfoil with an Internal Cooling System Having Enhanced Vortex Forming Turbulators - A turbine airfoil usable in a turbine engine and having at least one cooling system. At least a portion of the cooling system may include one or more cooling channels having a plurality of turbulators protruding from an inner surface and positioned generally nonorthogonal and nonparallel to a longitudinal axis of the airfoil cooling channel. The cooling channel may also include a plurality of vortex enhancers protruding from an inner surface forming the cooling channel and positioned nonparallel to the turbulators. In one embodiment, the vortex enhancers may be positioned generally orthogonal to the turbulators. The configuration of turbulators and vortex enhancers creates a higher internal convective cooling potential for the blade cooling passage, thereby generating a high rate of internal convective heat transfer and attendant improvement in overall cooling performance. This translates into a reduction in cooling fluid demand and better turbine performance. | 09-09-2010 |
20100226755 | Turbine Vane for a Gas Turbine Engine Having Serpentine Cooling Channels Within the Outer Wall - A turbine vane for a gas turbine engine having an outer wall containing a plurality of serpentine cooling channels. The serpentine cooling channels may be configured to receive cooling fluids from internal cooling fluids supply channels. The serpentine cooling channels may be positioned in the pressure side and suction side outer walls and configured such that a first pass is positioned radially outward from an internal chamber a greater distance than a second pass. As such, cooling fluids are first passed proximate to an outer surface where the fluids are heated and then passed proximate to an inner surface, thereby establishing a smaller thermal gradient than typically found in conventional turbine blade outer walls. | 09-09-2010 |
20100199672 | Condenser System - A method of substantially preventing contaminants from entering a condenser adapted for use within a steam generating system. A condenser is provided. Steam or a combination of water and steam is passed into the condenser, the condenser operating in a normal mode a pressure in a control area is equal to or greater than a predefined pressure and in a non-normal mode if the pressure in the control area is less than the predefined pressure. An inert gas is injected into the condenser if a pressure in the control area is less than a holding pressure, the holding pressure being equal to or greater than the predefined pressure. | 08-12-2010 |
20100199671 | Deaerator Apparatus in a Superatmospheric Condenser System - A power generating system comprises a condenser and a deaerator apparatus. The condenser condenses a working fluid into a condensate and operates at an internal pressure above ambient pressure during a normal operating mode. The deaerator apparatus uses steam to remove contaminants from the condensate to bring the condensate to a desirable purity. The deaerator apparatus is deactivated during a typical operating state of the power generating system such that the condensate bypasses the deaerator apparatus. The deaerator apparatus is activated during a non-typical operating state of the power generating system such that the condensate passes into the deaerator apparatus wherein contaminants can be removed from the condensate. The typical operating state of the power generating system occurs when the condensate comprises a desirable purity and the non-typical operating state of the power generating system occurs when the condensate comprises an undesirable purity. | 08-12-2010 |
20100199670 | Power Generation Plant Having Inert Gas Deaerator and Associated Methods - A power generation plant includes a steam turbine and an electrical generator driven thereby. A condenser is downstream from the steam turbine. Moreover, the power generation plant includes a steam source and an inert gas source. A deaerator downstream from the condenser and is operable to perform deaeration using the inert gas source and is also selectively operable to perform deaeration using the steam source. | 08-12-2010 |
20100180605 | Structural Attachment System for Transition Duct Outlet - A structural attachment system for the outlet of a transition duct includes a structural attachment member that has a step over portion with an outer flange at one end thereof and an inner flange at the other end thereof. The step over portion can project away from the inner and outer flanges and can define an open area. The step over portion can have a cross-section that is generally u-shaped, v-shaped, c-shaped, semi-circular, semi-oval, parabolic, or bowed. A portion of the outlet of a transition duct is received within the step over portion of the structural attachment member. Because of such arrangement, the structural attachment member is not constrained circumferentially to fitting in between two neighboring transition ducts. The structural attachment member can manage the thermal displacements that can occur between the transitions, rotor shaft cover and first row of blades during transient engine operation. | 07-22-2010 |
20100110451 | Coating Evaluation Process - System and method for evaluating coating thickness variations along a turbine blade contour. In one embodiment, applied to a first region extending 360 degrees about the blade and to a second region including an exposed reference surface, the first region includes a first surface over which the coating is formed and a second surface formed by the coating. The system provides a source of structured light positionable to cast patterns suitable for determination of coordinate position information along the surfaces. One or more imaging cameras are positionable to acquire image data based on the light patterns. A computer system processes image information to (1) characterize the first and second surfaces with respect to a coordinate along the reference surface; (2) compare coordinate data corresponding to the first surface with coordinate data corresponding to the second surface; and (3) determine thickness of the coating as a function of position. | 05-06-2010 |
20100078202 | Printed Circuit Board for Harsh Environments - A printed circuit board (PCB | 04-01-2010 |
20100077760 | Flex-Fuel Injector for Gas Turbines - A fuel injector ( | 04-01-2010 |
20100077719 | Modular Transvane Assembly - An arrangement for delivering gasses from can combustors of a can annular gas turbine combustion engine to a turbine first stage section including a first row of turbine blades, the arrangement including a flow-directing structure for each combustor, wherein each flow-directing structure includes a straight path and an annular chamber end, wherein the annular chamber ends together define an annular chamber for delivering the gas flow to the turbine first stage section, wherein gasses flow from respective combustors, through respective straight paths, and into the annular chamber as respective straight gas flows, and wherein the annular chamber is configured to unite the respective straight gas flows along respective shear planes to form a singular annular gas flow, and wherein the annular chamber is configured to impart circumferential motion to the singular annular gas flow before the singular annular gas flow exits the annular chamber to the first row of blades. | 04-01-2010 |
20100076703 | Method and Apparatus for Monitoring Blade Vibration With A Fiber Optic Ribbon Probe - A method and apparatus for monitoring blade vibrations in a turbine engine having blade tip target portions associated with blades. An illumination conduit including a plurality of optical fibers conveys light from a light source to a transmission end of the optical fibers where the light is focused to define an axially elongated projected image. The blade tip target portions pass through the projected image and reflect light to receptor ends of a plurality of optical fibers defining a detection conduit for conveying the reflected light to a processor. The transmission ends and receptor ends of the optical fibers are configured as a narrow rectangle to define a probe end for receiving reflected light at different axial locations along the probe end, and to detect blade passing events defined by passage of either or both a blade leading edge and a blade trailing edge. | 03-25-2010 |
20100075111 | Structure and Method for Forming Detailed Channels for Thin Walled Components Using Thermal Spraying - A coated substrate with a subsurface cooling channel having no corner disposed proximate a seam between the substrate and the coating. A method for forming such a structure, including forming a groove in a surface of a substrate, forming a preform having a cooperating portion and a protruding portion, inserting the cooperating portion of the preform into the groove, leaving the protruding portion of the preform protruding beyond the surface of the substrate, applying a layer of a coating material to the surface of the substrate and the protruding portion of the perform, and removing the preform, thereby creating a cooling channel. | 03-25-2010 |
20100074763 | Trailing Edge Cooling Slot Configuration for a Turbine Airfoil - A gas turbine engine hollow turbine airfoil having pressure and suction sidewalls extending chordwise between leading and the trailing edges. The trailing edge includes a pressure sidewall lip and a suction sidewall lip, and a breakout distance between the pressure sidewall lip and the suction sidewall lip. A cooling fluid channel extends spanwise through the airfoil for supplying a cooling fluid to the airfoil. Flow channels are provided extending chordwise between the cooling fluid channel and the suction sidewall lip and include a metering section, an internal diffusion section and a breakout slot. The interior diffusion section includes a spanwise dimension and a widthwise dimension perpendicular to the spanwise dimension, wherein the spanwise dimension continuously increases extending in the chordwise direction, and the widthwise dimension continuously decreases extending in the chordwise direction. | 03-25-2010 |
20100074762 | Trailing Edge Cooling for Turbine Blade Airfoil - A gas turbine engine hollow turbine airfoil having chordwise spaced apart leading and trailing edges, and widthwise spaced apart pressure and suction sidewalls extending chordwise between the leading edge and the trailing edge. A trailing edge rib extends from the trailing edge toward the leading edge, and forms a solid member between the pressure and suction sidewalls. A cooling fluid channel extends in the spanwise direction through the airfoil adjacent to the trailing edge rib. A plurality of fluid chambers are formed in the trailing edge rib. Film cooling holes extend from the fluid chambers to the pressure and suction sidewalls, and trailing edge discharge holes extend from the fluid chambers to the trailing edge. A metering hole is associated with each of the fluid chambers to define a flow restriction connecting the cooling fluid channel to a respective fluid chamber. | 03-25-2010 |
20100074735 | Thermal Shield at Casing Joint - A thermal shield for reducing thermal stress induced proximate to a first joint formed between adjacent engine casing components in a gas turbine engine. The thermal shield includes a cover structure for covering a radially inner portion of at least one of the engine casing components. The cover structure is disposed proximate to the first joint and attached to the respective engine casing component so as to limit exposure of a covered inner portion of the engine casing component to hot gases in an interior volume defined by the engine casing components. A thermally insulating layer is disposed between the cover structure and the engine casing component for effecting a reduced amount of heat transfer to the covered inner portion of the engine casing component from the hot gases in the interior volume defined by the engine casing components. | 03-25-2010 |
20100074734 | Turbine Seal Assembly - A seal assembly that limits gas leakage from a hot gas path to one or more disc cavities in a turbine engine. The seal assembly includes a seal apparatus that limits gas leakage from the hot gas path to a respective one of the disc cavities. The seal apparatus comprises a plurality of blade members rotatable with a blade structure. The blade members are associated with the blade structure and extend toward adjacent stationary components. Each blade member includes a leading edge and a trailing edge, the leading edge of each blade member being located circumferentially in front of the blade member's corresponding trailing edge in a direction of rotation of the turbine rotor. The blade members are arranged such that a space having a component in a circumferential direction is defined between adjacent circumferentially spaced blade members. | 03-25-2010 |
20100074733 | Ingestion Resistant Seal Assembly - A seal assembly limits gas leakage from a hot gas path to one or more disc cavities in a gas turbine engine. The seal assembly includes a seal apparatus associated with a blade structure including a row of airfoils. The seal apparatus includes an annular inner shroud associated with adjacent stationary components, a wing member, and a first wing flange. The wing member extends axially from the blade structure toward the annular inner shroud. The first wing flange extends radially outwardly from the wing member toward the annular inner shroud. A plurality of regions including one or more recirculation zones are defined between the blade structure and the annular inner shroud that recirculate working gas therein back toward the hot gas path. | 03-25-2010 |
20100074729 | Compressible Ceramic Seal - A stack of substantially parallel ceramic plates ( | 03-25-2010 |
20100074727 | Method and Apparatus for Monitoring Blade Vibration With An Imaging Fiber Optic Ribbon Probe - A method and apparatus for monitoring blade vibrations in a turbine engine having blade tip target portions associated with blades. An illumination conduit including a plurality of optical fibers conveys light from a light source to a transmission end of the optical fibers where the light is focused to define an axially elongated projected image. The blade tip target portions pass through the projected image and reflect light to a receptor array defined by receptor ends of a plurality of optical fibers forming an imaging conduit for conveying the reflected light to a sensor array. An imaging end of the imaging conduit radiates an image onto the sensor array that is identical to the reflected light image received at the receptor array to track tangential and axial movement of a predetermined point on the target portion. | 03-25-2010 |
20100073008 | Partial Discharge Coupler for Application on High Voltage Generator Bus Works - A partial discharge coupler for detecting partial discharges in a conductor includes a frequency dependent network, a differential amplifier and a frequency selective coupling component. The frequency dependent network includes a first filter component, a fuse component and a load component, typically coupled together in series with reference to a first ground. The first filter component filters the high voltage, low frequency alternating current signal carried by the conductor from the load component and passes high frequency partial discharge pulse signals to the load component. The frequency selective coupling component couples in series between the differential amplifier and the load component. The output of the differential amplifier is configured to provide an output that is isolated from the ground connection for communicating detected partial discharge signals to partial discharge test equipment. | 03-25-2010 |
20100071382 | Gas Turbine Transition Duct - A transition member between a combustion section and a turbine section in a gas turbine engine. The transition member includes a casing inner wall and a plurality of spanning members. The spanning members extend radially outwardly from a radially outer surface of the casing inner wall. Each of the spanning members included a slot formed therein. Each slot is in communication with a first aperture formed in the radially inner surface of the casing inner wall and a plurality of second apertures formed in an aft side of the spanning member for effecting a passage of the cooling fluid from a first cooling fluid channel to an inner volume defined within the radially inner surface of the casing inner wall. The slots include a component in the radial direction and a component in the axial direction such that the first aperture is not radially aligned with the second apertures. | 03-25-2010 |
20100071376 | Combustor Assembly in a Gas Turbine Engine - A combustor assembly in a gas turbine engine. The combustor assembly includes a combustor device coupled to a main engine casing, a first fuel injection system, a transition duct, and an intermediate duct. The combustor device includes a flow sleeve for receiving pressurized air and a liner disposed radially inwardly from the flow sleeve. The first fuel injection system provides fuel that is ignited with the pressurized air creating first working gases. The intermediate duct is disposed between the liner and the transition duct and defines a path for the first working gases to flow from the liner to the transition duct. An intermediate duct inlet portion is associated with a liner outlet and allows movement between the intermediate duct and the liner. An intermediate duct outlet portion is associated with a transition duct inlet section and allows movement between the intermediate duct and the transition duct. | 03-25-2010 |
20100068068 | Turbine Airfoil Cooling System with Diffusion Film Cooling Hole Having Flow Restriction Rib - A cooling system for a turbine airfoil of a turbine engine having at least one diffusion film cooling hole positioned in an outer wall defining the turbine airfoil is disclosed. The diffusion film cooling hole includes first and second sections. The first section may function as a metering section, and the second section may function as a diffusion section. The second section may include flow restriction ribs that direct the flow of cooling fluids in disproportionately larger amounts proximate to the downstream side of the diffusion film cooling hole. | 03-18-2010 |
20100068067 | Turbine Airfoil Cooling System with Divergent Film Cooling Hole - A cooling system for a turbine airfoil of a turbine engine having at least one divergent film cooling hole positioned in an outer wall defining the turbine airfoil is disclosed. The divergent film cooling hole includes a first section extending from an inner surface of the outer wall into the outer wall and a second section extending the first section and terminating at an outer surface of the outer wall. The divergent film cooling hole may provide a metering capability together with a divergent section that provides a larger film cooling hole breakout and footprint, which creates better film coverage and yields better cooling of the turbine airfoil. The divergent film cooling hole may provide a smooth transition, which allows the film cooling flow to diffuse better in the second section of the divergent film cooling hole. | 03-18-2010 |
20100068033 | Turbine Airfoil Cooling System with Curved Diffusion Film Cooling Hole - A cooling system for a turbine airfoil of a turbine engine having at least one diffusion film cooling hole positioned in an outer wall defining the turbine airfoil is disclosed. The diffusion film cooling hole includes a first sidewall having a first radius of curvature about an axis generally orthogonal to a centerline of cooling fluid flow through the diffusion film cooling hole and a second sidewall having a second radius of curvature about an axis generally orthogonal to the centerline of cooling fluid flow through the at least one diffusion film cooling hole. The radii of curvature of the first and second sidewalls are different such that the diffusion film cooling hole includes an ever increasing cross-sectional area moving from an inlet to an outlet, thereby diffusing and reducing the velocity of cooling fluids flowing there through. | 03-18-2010 |
20100068032 | Turbine Airfoil Cooling System with Diffusion Film Cooling Hole - A cooling system for a turbine airfoil of a turbine engine having at least one diffusion film cooling hole positioned in an outer wall defining the turbine airfoil is disclosed. The diffusion film cooling hole includes a first section extending from an inner surface of the outer wall into the outer wall, a second section extending the first section toward an outer wall, and a third section extending from the second section and terminating at an outer surface of the outer wall. The diffusion film cooling hole may provide a metering capability together with diffusion sections that provide a larger film cooling hole breakout and footprint, which create better film coverage and yield better cooling of the turbine airfoil. The diffusion film cooling hole may provide a smooth transition, which allows the film cooling flow to diffuse better in the second and third sections of the diffusion film cooling hole. | 03-18-2010 |
20100027584 | Thermocouple for Gas Turbine Environments - A thin-film thermocouple ( | 02-04-2010 |
20100021291 | Diffuser Apparatus in a Turbomachine - A diffuser apparatus in a turbomachine is provided comprising a diffuser structure and stabilizing structure. The diffuser structure includes inner and outer walls defining a flow passageway through which gases flow and diffuse such that kinetic energy is reduced and pressure is increased in the gases as they move through the passageway. The stabilizing structure stabilizes a separated gas recirculation zone. | 01-28-2010 |
20090266076 | Condensate Polisher Circuit - A power generating system including a working fluid circuit. The power generating system includes a condenser system in the working fluid circuit and a condensate polisher circuit. The condenser system receives a working fluid that includes steam or a combination of water and steam and condenses at least a portion of the working fluid into a condensate. The condensate has a temperature above a predetermined upper operating temperature. The condensate polisher circuit is branched off from the working fluid circuit and receives and treats said condensate from the working fluid circuit and returns treated condensate to the working fluid circuit. The condensate polisher circuit includes a heat exchanger that reduces the temperature of the condensate at least to the upper operating temperature and a condensate polisher that removes contaminants from the condensate to bring the condensate to a predetermined purity. | 10-29-2009 |
20090235516 | Method of Servicing a Power Generator - A method of servicing a stator frame of a power generator. The method includes removing a first stator core from a main housing of the stator frame, removing a plurality of first dove-tail shaped keybars that extend axially within and are coupled to a main support structure forming part of the main housing, and installing a plurality of second keybars in the main support structure. The second keybars are adapted to support a second stator core. Each of the second keybars has a generally rounded engagement surface and the second stator core includes recesses with shapes corresponding to the generally rounded engagement surfaces of the second keybars such that the second stator core can be securely supported in the main support structure by the second keybars. | 09-24-2009 |