Patent application number | Description | Published |
20130111393 | MODELING REPORTS DIRECTLY FROM DATA SOURCES | 05-02-2013 |
20130282696 | INTERACTIVE DATA EXPLORATION AND VISUALIZATION TOOL - A computer-implemented method for data visualization includes determining a query context for a user's search query, and retrieving relevant data for the query context. The method combines the relevant data with data that is filtered according to search parameters in the user's search query. The method further includes generating an interactive presentation to display the combined data from the perspective of the user's search query or from the perspectives of other entities. | 10-24-2013 |
20140046936 | System and Method for Data Modeling - A data modeling platform allows a user to enter a search request using natural language (e.g., typed or spoken). The search request may be semantically parsed to provide mapping to various database search elements. Pre-existing data models may be identified from the database search elements. One or more new data models may be created from the database search elements. The results represent candidate data models in response to the user's search request. | 02-13-2014 |
20140304308 | Interface Optimizing Model Based Upon Database Information - Embodiments relate to interfaces allowing a user to optimize a model which references and manipulates volumes of information present in an underlying database. An interface engine of an application layer, may communicate with the database engine of an underlying database layer, to provide a user with indicia of modeling performance. Thus for every modeling step, an interface engine could display performance indicia such as a number of database rows that are being referenced, and/or an amount of time consumed in retrieving the data from the database. This performance indicia, together with a structure of the model itself, can be processed by the interface engine through a repository of optimization recommendations. Recommendations from the repository may be published to the user, who is free to accept or reject them. Particular embodiments may leverage processing capacity of an in-memory database engine, to analyze database information gathered during modeling. | 10-09-2014 |
Patent application number | Description | Published |
20130319041 | NITROGEN-COOLED DYNAMOELECTRIC MACHINE SYSTEM AND RELATED METHOD - Various embodiments of the invention include systems and methods for cooling a dynamoelectric machine. In some embodiments, a system is disclosed including: at least one of a nitrogen separation unit (NSU) or an air separation unit (ASU) for extracting nitrogen from an inlet air source; a nitrogen expander fluidly connected with the at least one of the NSU or the ASU, the nitrogen expander for expanding the extracted nitrogen; and a dynamoelectric machine fluidly connected with the nitrogen expander, the dynamoelectric machine configured to receive the expanded nitrogen for cooling the dynamoelectric machine. | 12-05-2013 |
20140007553 | HOT WATER INJECTION FOR TURBOMACHINE - A turbomachine is provided and includes a combustor in which a first compressed air is combustible along with fuel and which is receptive of water. The water is provided to the combustor subsequent to the water being used to cool a second compressed air, and the water is used to cool the second compressed air prior to the second compressed air being used to atomize the fuel. | 01-09-2014 |
20140060057 | METHOD AND APPARATUS FOR HEATING LIQUID FUEL SUPPLIED TO A GAS TURBINE COMBUSTOR - A method of heating liquid fuel upstream of a combustor in a system where compressor discharge air is cooled before being supplied to fuel nozzles in the combustor includes the steps of passing the compressor discharge air through a heat exchanger in heat exchange relationship with the liquid fuel to heat the liquid fuel and cool the compressor discharge air; supplying the heated liquid fuel and the cooled compressor discharge air to the combustor. | 03-06-2014 |
20140090387 | FUEL HEATING SYSTEM FOR A POWER PLANT AND METHOD OF HEATING FUEL - A fuel heating system for a power plant includes an exhaust structure having an interior region for receiving an exhaust gas therein. Also included is a fluid injection arrangement comprising a first fluid duct for transferring a fluid, the first fluid duct extending at least partially throughout the interior region of the exhaust structure for heating the fluid. Further included is a heat exchanger for receiving the fluid and a liquid fuel, the fluid heating the liquid fuel during passage of the liquid fuel through the heat exchanger. | 04-03-2014 |
20140110092 | ATOMIZING AIR HEAT FOR ATTEMPERATION - An attemperation system and an atomizing air system are integrated for a combined cycle turbine including a gas turbine and a steam turbine. The atomizing air system receives compressor discharge air for fuel atomization. The atomizing air system includes an atomizing air cooler that serves to cool the compressor discharge air. A heat recovery steam generator receives exhaust from the gas turbine and generates steam for input to the steam turbine via an attemperation system. A feed water circuit draws feed water from the heat recovery steam generator and communicates in a heat exchange relationship with the atomizing air cooler to heat the feed water. The feed water circuit communicates the heated feed water to the attemperation system of the heat recovery steam generator. | 04-24-2014 |
20140123623 | GAS TURBOMACHINE SYSTEM INCLUDING AN INLET CHILLER CONDENSATE RECOVERY SYSTEM - A gas turbomachine system includes a compressor portion including an inlet portion, a turbine portion fluidically connected to, and mechanically linked with, the compressor portion, and a combustor assembly including at least one combustor fluidically connected to the turbine portion. An inlet system is fluidically connected to the inlet portion of the compressor portion. The inlet system includes an inlet chiller. An inlet chiller condensate recovery system is fluidically connected to the inlet system. The inlet chiller condensate recovery system includes an inlet fluidically connected to the inlet chiller and an outlet fluidically connected to one of the compressor portion and the combustor assembly. | 05-08-2014 |
20140130478 | GAS TURBOMACHINE INCLUDING A FUEL PRE-HEAT SYSTEM - A gas turbomachine includes a compressor portion, a turbine portion operatively connected to the compressor portion, a combustor assembly including at least one combustor fluidically connected to the turbine portion, and an accessory mechanically linked with and driven by the turbine portion. The gas turbomachine also includes a fuel pre-heat system including a fuel pre-heat element having a fuel circuit fluidically connected to the at least one combustor arranged in a heat exchange relationship with a heating medium circuit fluidically connected to at least one of the compressor portion, the turbine portion, and the accessory. | 05-15-2014 |
Patent application number | Description | Published |
20110085892 | VORTEX CHAMBERS FOR CLEARANCE FLOW CONTROL - An apparatus is provided and includes a first member with a flow diverting member extending from a surface thereof and a second member disposed proximate to the first member with a clearance gap area defined between a surface of the second member and a distal end of the flow diverting member such that a fluid path, along which fluid flows from an upstream section and through the clearance gap area, is formed between the surfaces of the first and second members. The second member is formed to define dual vortex chambers at the upstream section in which the fluid is directed to flow in vortex patterns prior to being permitted to flow through the clearance gap area. | 04-14-2011 |
20110085893 | COUNTOURED HONEYCOMB SEAL FOR A TURBOMACHINE - A turbomachine includes a housing having an inner surface, a compressor, a turbine and a rotary member including a plurality of blade members configured as part of one of the compressor and the turbine. Each of the plurality of blade members includes a base portion and a tip portion. The turbomachine also includes a honeycomb seal member mounted to the inner surface of the housing adjacent the rotary member. The honeycomb seal member includes a contoured surface having formed therein a deformation zone. The deformation zone includes an inlet zone and an outlet zone. The inlet zone is spaced a first distance from the tip portion of each of the plurality of blade members and the outlet zone is spaced a second distance from the tip portion of each of the plurality of blade members. The second distance being substantially equal to or less than the first distance. | 04-14-2011 |
20110103966 | FLOW BALANCING SLOT - A cover of an airfoil having opposing pressure and suction sides of a rotatable turbine stage to prevent fluid from crossover-flowing from a pressure side of a leading airfoil to a suction side of a trailing airfoil is provided. The cover includes pressure and suction side edge portions, one of which having a shape that is discontinuous relative to that of a complementary one of suction and pressure side edge portions of an aft cover of a corresponding one of a trailing and a leading airfoil, respectively. | 05-05-2011 |
20110158799 | RADIAL CHANNEL DIFFUSER FOR STEAM TURBINE EXHAUST HOOD - An exhaust hood for an axial steam turbine that includes a radial channel, downstream from the normal flow pattern. The radial channel guides the exhaust steam flow in upper half of the hood in the flow momentum direction. Due to this pattern of flow direction, vortex generation in upper exhaust hood is reduced and increased flow diffusion results. The geometric arrangement can eliminate the outer casing of the exhaust hood over the axial length of the turbine inner casing, allowing the turbine inner casing to be supported directly by a foundation for the steam turbine. | 06-30-2011 |
20110248452 | AXIALLY-ORIENTED CELLULAR SEAL STRUCTURE FOR TURBINE SHROUDS AND RELATED METHOD - A seal system between a row of buckets supported on a machine rotor and a surrounding stationary casing or stator includes a tip shroud secured at radially outer tips of each of the buckets, the tip shroud formed with a radially-projecting rail. A cellular seal structure is supported in the stationary stator in radial opposition to the tip shroud and the rail. The seal structure has an annular array of individual cells formed to provide continuous, substantially horizontal flow passages devoid of any radial obstruction along substantially an entire axial length dimension of the cellular seal structure to prevent flow about the tip shroud from turning radially inwardly. | 10-13-2011 |
20120043728 | TURBINE ENGINE SEALS - A seal is provided for preventing axial leakage through a radial gap between a stationary structure and a rotating structure. The radial gap is defined by an inner radial surface opposing an outer radial surface across the radial gap. The seal includes at least one land disposed on one of the inner radial surface and outer radial surface. At least one first tooth and at least one second tooth project from the other of the radial surfaces. The second tooth is shorter than the first tooth. At least one of the first tooth and second tooth, is configured to extend at an angle upstream. This angle is defined between a radial surface from which the first or second tooth projects and an upstream surface of the same tooth. The angle is less than or equal to about 80 degrees. | 02-23-2012 |
20120091662 | LABYRINTH SEAL SYSTEM - A labyrinth seal system is disclosed, including a stationary component having a plurality of radially inwardly projecting, axially spaced teeth extending therefrom; and a rotor having a plurality of radially outwardly projecting, axially spaced protrusions, each protrusion having a low pressure side and a high pressure side, wherein the low pressure side of at least one protrusion extends farther in a radial direction than the high pressure side. | 04-19-2012 |
20120121404 | Exhaust Hood Diffuser - The present application provides a diffuser for an exhaust hood of a steam turbine. The diffuser may include a first end adjacent to a last bucket and a second end downstream of a steam guide and adjacent to a bearing cone. An exhaust flow path extends therethrough. The second end may include an axial extension enlarging the exhaust flow path. | 05-17-2012 |
20120201650 | PASSIVE COOLING SYSTEM FOR A TURBOMACHINE - A turbomachine includes a housing having an outer surface and an inner surface that defines an interior portion. The housing includes a fluid plenum. A rotating member is arranged within the housing. The rotating member includes at least one bucket having a base portion and a tip portion. A stationary member is mounted to the inner surface of the housing adjacent the tip portion of the at least one bucket. At least one fluid passage passes through at least a portion of the stationary member. The at least one fluid passage includes a fluid inlet fluidly coupled to the fluid plenum and a fluid outlet exposed to the interior portion. The fluid outlet being configured and disposed to direct a flow of fluid toward the tip portion of the at least one bucket. | 08-09-2012 |
20130019600 | TURBINE EXHAUST ARRANGEMENT - An exhaust arrangement for a turbine is provided having an inner turbine casing, a condenser, an exhaust arrangement structure, and a bearing cone. The inner turbine casing includes a plurality of last stage buckets. A steam flow passes through the inner turbine casing and out of the plurality of last stage buckets. The condenser for receives the steam flow. The exhaust arrangement structure has a diffuser, a lower section and an upper section. The lower section has an exhaust section. The lower section receives the steam flow from the last stage buckets of the inner turbine casing through the diffuser and guides the steam flow out of the exhaust section in a direction generally towards the condenser. The upper section has a receiving section and a guiding section. | 01-24-2013 |
20130022444 | LOW PRESSURE TURBINE EXHAUST DIFFUSER WITH TURBULATORS - A turbine exhaust diffuser for use adjacent a last stage row of buckets fixed to a turbine rotor includes an annular inner diffuser ring and an annular outer diffuser ring defining a flow path for steam exiting a last stage row of buckets in a first substantially axial direction at a diffuser inlet, and turning substantially ninety degrees to a diffuser outlet. The outer diffuser ring has a curved steam guide surface extending between the diffuser inlet and the diffuser outlet including a first portion extending away from the diffuser inlet and a second portion extending to said diffuser outlet, the second portion shaped to extend beyond vertical and back toward the diffuser inlet so as to establish a flow component in a second opposite axial direction. The second portion is also provided with a plurality of turbulators to minimize flow separation along the steam guide surface. | 01-24-2013 |
20130064665 | LOW PRESSURE STEAM TURBINE INCLUDING PIVOTABLE NOZZLE - A low pressure steam turbine is disclosed including a rotor having: a rotor body; and a plurality of bucket stages disposed axially along the rotor body, the plurality of bucket stages including a last bucket stage; and a nozzle assembly at least partially surrounding the rotor, the nozzle assembly including a plurality of nozzle stages corresponding to the plurality of bucket stages, wherein a nozzle in a nozzle stage axially upstream of the last bucket stage is adjustable to modify a fluid flow within the last bucket stage during operation of the low pressure steam turbine. | 03-14-2013 |
20130091865 | EXHAUST GAS DIFFUSER - An exhaust gas diffuser is provided and includes a peripheral body, a center body, formed to define an interior and disposed within the peripheral body to define an annulus between the peripheral body and the center body through which a first fluid flows along a main flow direction, a plurality of first members, each of which is respectively coupled to the peripheral body and the center body, to support the center body within the peripheral body and a plurality of second members, each of which extends across the annulus from the peripheral body to the center body downstream from the plurality of the first members relative to the main flow direction, to transport a second fluid to the center body interior. The plurality of the second members is circumferentially clocked relative to the plurality of the first members. | 04-18-2013 |
20130167551 | TURBINE TO OPERATE AT PART-LOAD - A turbine includes a compressor to intake a fluid and to compress the fluid, a combustion chamber to heat the fluid from the compressor, a turbine section to rotate a shaft with the heated fluid from the combustion chamber, and a bypass circuit to generate a bypass flow by removing a portion of the fluid from the compressor, to heat the bypass flow, and to insert the bypass flow to the turbine section. | 07-04-2013 |
20130280050 | TURBINE VIBRATION REDUCTION SYSTEM - A turbine vibration reduction system includes a nozzle, a bucket in operable communication with the nozzle, and a structure having at least one opening configured to inject fluid into flow traveling past the nozzle and the bucket to disrupt formation of a vortex. | 10-24-2013 |
20130327061 | TURBOMACHINE BUCKET ASSEMBLY AND METHOD OF COOLING A TURBOMACHINE BUCKET ASSEMBLY - A turbomachine bucket assembly includes a rotor member including a body having a center portion and an outer edge portion joined by a web. The rotor member includes one or more cooling fluid conduit having a dimension, and an inlet arranged at the outer edge. A plurality of blades are provided on the rotor member and mechanically linked to the outer edge. Each of the plurality of blades includes an internal cooling passage that is fluidly connected to the one or more cooling fluid conduits. A cooling fluid control element is provided at each of the one or more cooling fluid conduits. The cooling fluid control element is configured and disposed to adjust the dimension of the one or more cooling fluid conduits to alter fluid flow into the plurality of blades. | 12-12-2013 |