Patent application number | Description | Published |
20140270108 | INTELLIGENT AUTOMATED AGENT AND INTERACTIVE VOICE RESPONSE FOR A CONTACT CENTER - A system for a contact center includes: a processor; an interactive voice response (IVR) node configured to engage in an incoming interaction from a customer to the contact center by presenting set scripts to the customer and receiving corresponding responses; an intelligent automated agent including an artificial intelligence engine; a call server node configured to route the interaction and the responses to one of a pool of live agents or to the automated agent; and a non-transitory storage device coupled to the processor and configured to store customer profile data built from previous interactions. The automated agent is further configured to retrieve a profile of the customer from the customer profile data during the interaction and to update the retrieved profile on the storage device to reflect the interaction. The artificial intelligence engine is configured to learn knowledge from the interaction and to apply the learned knowledge to future interactions. | 09-18-2014 |
20140270109 | CUSTOMER PORTAL OF AN INTELLIGENT AUTOMATED AGENT FOR A CONTACT CENTER - A customer portal of an intelligent automated agent for a contact center is provided. The customer portal is configured to run on a processor coupled to a non-transitory storage device. The customer portal includes a customer profile module configured to access a profile for a customer from a customer profile database stored on the storage device, and a customer emotion and mood detection module configured to detect emotions and moods of the customer during an interaction between the customer and the contact center. The intelligent automated agent is configured to run on the processor, take part in the interaction between the customer and the contact center, adjust its behavior in the interaction by factoring in the accessed profile for the customer and the detected emotions and moods of the customer during the interaction, and update the accessed profile on the storage device to reflect the interaction. | 09-18-2014 |
20140270146 | BACK OFFICE SERVICES OF AN INTELLIGENT AUTOMATED AGENT FOR A CONTACT CENTER - A back office services of an intelligent automated agent for a contact center is provided. The back office services is configured to run on a processor coupled to a non-transitory storage device. The back office services includes: a customer profile module configured to access a profile of a customer from a customer profile database stored on the storage device, the profile of the customer including interaction data from interactions involving the customer and the contact center, and analysis results from analyzing the interaction data between the interactions involving the customer and the contact center; and a content analysis module configured to generate new analysis results by performing the analyzing of the interaction data between consecutive interactions of the interactions involving the customer and the contact center, and update the analysis results of the profile of the customer on the storage device to reflect the new analysis results. | 09-18-2014 |
20140314225 | INTELLIGENT AUTOMATED AGENT FOR A CONTACT CENTER - A system for handling customer interactions with a contact center for an enterprise includes an intelligent automated agent that includes a processor, a non-transitory storage device configured to store customer profile data, and a memory. The memory has instructions stored thereon that, when executed by the processor, causes the processor to: run an artificial intelligence engine configured to learn knowledge about a customer from past interactions between the contact center and the customer, and to apply the learned knowledge to future interactions; and maintain the customer profile data on the storage device. The maintaining of the customer profile data includes retrieving the customer profile data at a beginning of a new interaction, using the retrieved customer profile data to decide how to handle the new interaction, and updating the customer profile data after completion of the new interaction to reflect the new interaction as one of the past interactions. | 10-23-2014 |
20150189085 | CUSTOMER PORTAL OF AN INTELLIGENT AUTOMATED AGENT FOR A CONTACT CENTER - A customer portal of an intelligent automated agent for a contact center is provided. The customer portal is configured to run on a processor coupled to a non-transitory storage device. The customer portal includes a customer profile module configured to access a profile for a customer from a customer profile database stored on the storage device, and a customer emotion and mood detection module configured to detect emotions and moods of the customer during an interaction between the customer and the contact center. The intelligent automated agent is configured to run on the processor, take part in the interaction between the customer and the contact center, adjust its behavior in the interaction by factoring in the accessed profile for the customer and the detected emotions and moods of the customer during the interaction, and update the accessed profile on the storage device to reflect the interaction. | 07-02-2015 |
Patent application number | Description | Published |
20090148305 | TURBINE BLADES AND METHODS OF MANUFACTURING - A turbine blade includes a convex suction side wall, a concave pressure side wall, a tip wall, an internal cooling circuit, and a plurality of tip edge channels. The tip wall is recessed from a first tip edge of the suction side wall and a second tip edge of the concave pressure side wall to define a suction side wall tip section and a pressure side wall tip section, and the suction side wall tip section is shorter than the pressure side wall tip section. The internal cooling circuit is formed at least partially between the convex suction side wall, the concave pressure side wall, and the tip wall. The plurality of tip edge channels formed through the first tip edge of the convex suction side wall extend to the internal cooling circuit. Methods of manufacturing turbine blades are also provided. | 06-11-2009 |
20090175733 | AIR COOLED TURBINE BLADES AND METHODS OF MANUFACTURING - An air-cooled turbine blade and methods of manufacturing the blade are provided. The blade includes a suction side flow circuit formed within its interior and defined at least by an interior surface of a convex suction side wall, a pressure side flow circuit formed within the blade interior and defined at least by an interior surface of a concave pressure side wall, and a center flow circuit including a first section and a second section, the first section disposed between the suction side flow circuit and the pressure side flow circuit, and the second section in flow communication with the first section and a plurality of openings of a leading edge wall and defined at least partially by an interior surface of the leading edge wall. | 07-09-2009 |
20100158700 | TURBINE BLADE ASSEMBLIES AND METHODS OF MANUFACTURING THE SAME - A turbine blade assembly includes an airfoil, a platform, and a first cover plate. A center flow path extends through the platform in communication with an internal cooling circuit of the airfoil, which extends from a first side of the platform. A second side of the platform is located opposite the platform from the first side. An edge of the platform extends between the first and second sides and, a first passage is formed between the first and second sides and includes a first inlet and a first outlet. The first passage extends from the center flow path toward the platform edge, and a first groove is formed on the second side of the platform and extends from the first outlet of the first passage toward the edge of the platform. The first cover plate is disposed over the second side of the platform covering the first groove. | 06-24-2010 |
20100284819 | TURBINE BLADES AND METHODS OF FORMING MODIFIED TURBINE BLADES AND TURBINE ROTORS - Turbine blades and methods of forming modified turbine blades and turbine rotors for use in an engine are provided. In an embodiment, by way of example only, a turbine blade includes a platform and an airfoil. The platform includes a surface configured to define a portion of a flowpath, and the surface includes an initial contour configured to plastically deform into an intended final contour after an initial exposure of the blade to an operation of the engine. The airfoil extends from the platform. | 11-11-2010 |
20120070307 | TURBINE BLADES, TURBINE ASSEMBLIES, AND METHODS OF MANUFACTURING TURBINE BLADES - A turbine blade includes a first side wall including a first tip edge, a second side wall opposite the first side wall and including a second tip edge, a tip wall between the first and second side walls, the tip wall recessed from the first tip edge of the first side wall and the second tip edge of the second side wall forming a coolant cavity, a tip recess cavity, a first parapet wall on the first side wall, and a second parapet wall on the second side wall, the coolant cavity defined by the tip wall, and the tip recess cavity defined by the tip wall, and the first and second parapet walls, a step formed between the first tip edge and the tip wall, a cooling hole through the first parapet wall, the step, and the tip wall, the cooling hole including an open and a closed channel section. | 03-22-2012 |
20120148406 | TURBINE ROTOR DISKS AND TURBINE ASSEMBLIES - A turbine rotor disk is provided. The turbine rotor disk includes a hub, a ring attached to the hub, the ring including a plurality of posts extending radially outwardly and disposed around a circumference of the ring, each post including a first radially-extending face, a second radially-extending face, and a blade attachment surface extending axially between the first and second radially-extending faces, a main cooling air feed channel formed in each post and extending from the first radially-extending face toward the second radially-extending face, and a plurality of ancillary jet openings formed in each post and extending from the main cooling air feed channel to the blade attachment surface. | 06-14-2012 |
20130051974 | GAS TURBINE ENGINES AND METHODS FOR COOLING COMPONENTS THEREOF WITH MID-IMPELLER BLEED COOLING AIR - Gas turbine engines and methods for cooling components thereof with mid-impeller bleed (MIB) cooling air having a pressure are provided. The gas turbine engine has a compressor comprising an impeller body and an impeller shroud at least partially surrounding the impeller body. The impeller shroud has a plurality of MIB openings disposed therein. At least one edge treatment is provided thereto. The edge treatment substantially preserves pressure of the cooling air during entrance into and discharge out of the MIB opening. The plurality of MIB openings may be extended MIB openings in a thickened impeller shroud. The centerline of the MIB openings may be oriented to be substantially aligned with an averaged local absolute flow velocity vector of the cooling air at the inlet section of the MIB opening in order to extract cooling air in a direction that has a vector component in a tangential, an axial, and a radial flow direction. | 02-28-2013 |
20130071254 | TURBINE BLADES AND METHODS OF FORMING MODIFIED TURBINE BLADES AND TURBINE ROTORS - Turbine blades and methods of forming modified turbine blades and turbine rotors for use in an engine are provided. In an embodiment, by way of example only, a turbine blade includes a platform and an airfoil. The platform includes a surface configured to define a portion of a flowpath, and the surface includes an initial contour configured to plastically deform into an intended final contour after an initial exposure of the blade to an operation of the engine. The airfoil extends from the platform. | 03-21-2013 |
20130280036 | AXIALLY-SPLIT RADIAL TURBINE - An axially-split radial turbine includes a forward rotor section and an aft rotor section being mechanically and abuttingly coupled to one another along an annular interface that resides within a plane generally orthogonal to a rotational axis of the axially-split radial turbine. The axially-split radial turbine can be provided as part of a gas turbine engine. | 10-24-2013 |
20140083116 | GAS TURBINE ENGINE COMPONENTS WITH BLADE TIP COOLING - A turbine rotor blade for a turbine section of an engine is provided. The rotor blade includes a platform and an airfoil extending from the platform into a mainstream gas path of the turbine section. The airfoil includes a pressure side wall, a suction side wall joined to the pressure side wall at a leading edge and a trailing edge, and a tip cap extending between the suction side wall and the pressure side wall. The rotor blade further includes an internal cooling circuit having a tip cap passage configured to deliver cooling air to the tip cap and a flow accelerator positioned within the tip cap passage of the internal cooling circuit. | 03-27-2014 |
20140161623 | TURBINE ENGINES WITH CERAMIC VANES AND METHODS FOR MANUFACTURING THE SAME - A vane assembly includes first and second annular metal rings configured to accept a compressed gas flow therebetween. The first and second annular rings each include a cutout portion. The assembly further includes a ceramic matrix composite vane configured as an airfoil having a blunt rounded nose and a flattened and tapered tail. A first radial end of the vane is rigidly disposed on the first annular ring and a second radial end of the vane is slidably disposed within the cutout portion of the second annular ring such that the vane is encompassed by the first and second annular rings. The vane includes a hollow through opening portion extending radially therethrough. Still further, the assembly includes a metallic elongated member disposed within and extending through the hollow portion of vane and through the cutout portion of the first annular ring. | 06-12-2014 |
20140321965 | TURBINE NOZZLES AND METHODS OF MANUFACTURING THE SAME - A turbine nozzle assembly includes an inner circumferential support platform, an outer circumferential support platform, and a plurality of airfoil vanes disposed between the inner circumferential support platform and the outer circumferential support platform. The turbine nozzle assembly further includes a plurality of impingement plates disposed along a radially outer surface of the outer circumferential support platform or a radially inner surface of the inner circumferential support platform, and a plurality of gap-maintaining features disposed between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates. Each gap-maintaining feature of the plurality of gap-maintaining features is provided at a height such that a cooling air flow space is maintained between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates. | 10-30-2014 |
20150078916 | TURBINE BLADES WITH TIP PORTIONS HAVING CONVERGING COOLING HOLES - A turbine rotor blade is provided with for a turbine section of an engine that includes a shroud surrounding the rotor blade. The rotor blade includes a platform and an airfoil extending from the platform into a mainstream gas path. The airfoil includes a pressure side wall, a suction side wall joined to the pressure side wall at a leading edge and a trailing edge, a tip cap extending between the suction side wall and the pressure side wall, a first squealer tip extension extending from the pressure side wall at a first angle relative to the pressure side wall, the first squealer tip extension defining a first cooling hole that converges between an inlet and an outlet; an internal cooling circuit configured to deliver cooling air to a gap between the pressure side squealer tip extension and the shroud via the first cooling hole. | 03-19-2015 |
20150082808 | GAS TURBINE ENGINES WITH TURBINE AIRFOIL COOLING - An airfoil for a gas turbine engine is provided. The airfoil includes a body with a leading edge, a trailing edge, a first side wall extending between the leading edge and the trailing edge, and a second side wall extending between the leading edge and the trailing edge. The body defines an interior cavity. The airfoil includes an interior wall disposed within the interior cavity of the body and extending between the first wall and the second wall to define a supply chamber and a leading edge chamber. The interior wall defines a cooling hole with a base portion and a locally extended portion to direct cooling air from the supply chamber to the leading edge chamber such that the cooling air impinges upon the leading edge. | 03-26-2015 |
20150159513 | BI-CAST TURBINE NOZZLES AND METHODS FOR COOLING SLIP JOINTS THEREIN - Bi-cast turbine nozzles and methods for cooling the same are provided. The bi-cast turbine nozzle comprises an endwall. A vane is coupled to the endwall. The vane comprises an end portion and a leading edge and a trailing edge interconnected by a pressure sidewall and a suction sidewall. A slip joint is provided between the end portion and the endwall. A plurality of cooling holes is defined through the endwall. The plurality of cooling holes is disposed adjacent the periphery of the slip joint along the pressure sidewall of the vane and in proximity to the leading edge of the vane. | 06-11-2015 |
20150300192 | GAS TURBINE ENGINE COMPONENTS HAVING SEALED STRESS RELIEF SLOTS AND METHODS FOR THE FABRICATION THEREOF - Embodiments of a gas turbine engine component having sealed stress relief slots are provided, as are embodiments of a gas turbine engine containing such a component and embodiments of a method for fabricating such a component. In one embodiment, the gas turbine engine includes a core gas flow path, a secondary cooling flow path, and a turbine nozzle or other gas turbine engine component. The component includes, in turn, a component body through which the core gas flow path extends, a radially-extending wall projecting from the component body and into the secondary cooling flow path, and one or more stress relief slots formed in the radially-extending wall. The stress relief slots are filled with a high temperature sealing material, which impedes leakage between the second cooling and core gas flow paths and which fractures to alleviate thermomechanical stress within the radially-extending wall during operation of the gas turbine engine. | 10-22-2015 |
20150337680 | TURBINE NOZZLES AND COOLING SYSTEMS FOR COOLING SLIP JOINTS THEREIN - Turbine nozzles and cooling systems for cooling slip joints therein are provided. The turbine nozzle has an endwall, a vane coupled to the endwall, a slip joint, and a plurality of airfoil quenching holes that cooperate with a plurality of endwall cooling holes. The vane comprises a leading edge and a trailing edge interconnected by a pressure sidewall and a suction sidewall and an end portion. The slip joint is between the end portion and the endwall. The airfoil quenching holes are defined through the pressure sidewall in the end portion. The endwall cooling holes are defined through the endwall along the pressure sidewall and in proximity to the leading edge. The airfoil quenching holes and endwall cooling holes are disposed adjacent the slip joint. | 11-26-2015 |
20150354461 | ENGINE SYSTEMS AND METHODS FOR REMOVING PARTICLES FROM TURBINE AIR - A cooling arrangement is provided for a gas turbine engine with a turbine section. The cooling arrangement includes a first conduit to receive cooling air that includes particles; a separator system coupled to the first conduit to receive the cooling air and configured to remove at least a portion of the particles to result in relatively clean cooling air and scavenge air including the portion of the particles; and a second conduit coupled to the separator system and configured to direct the relatively clean cooling air to the turbine section. | 12-10-2015 |
20160024948 | METHODS FOR MANUFACTURING A TURBINE NOZZLE WITH SINGLE CRYSTAL ALLOY NOZZLE SEGMENTS - Methods for manufacturing a turbine nozzle are provided. A plurality of nozzle segments is formed. Each nozzle segment comprises an endwall ring portion with at least one vane. The plurality of nozzle segments are connected to an annular endwall forming a segmented annular endwall concentric to the annular endwall with the at least one vane of each nozzle segment extending between the segmented annular endwall and the annular endwall. | 01-28-2016 |
Patent application number | Description | Published |
20090048224 | COMPOUNDS AND METHODS OF USE - Selected compounds are effective for treatment of pain and diseases, such as inflammation mediated diseases. The invention encompasses novel compounds, analogs, prodrugs and pharmaceutically acceptable derivatives thereof, pharmaceutical compositions and methods for prophylaxis and treatment of diseases and other maladies or conditions involving pain, inflammation, and the like. The subject invention also relates to processes for making such compounds as well as to intermediates useful in such processes. | 02-19-2009 |
20090054460 | Piperazine derivatives and methods of use - Selected compounds are effective for treatment of pain and diseases, such as inflammation mediated diseases. The invention encompasses novel compounds, analogs, prodrugs and pharmaceutically acceptable derivatives thereof, pharmaceutical compositions and methods for prophylaxis and treatment of diseases and other maladies or conditions involving pain, inflammation, and the like. The subject invention also relates to processes for making such compounds as well as to intermediates useful in such processes. | 02-26-2009 |
20090143355 | Substituted aryl-amine derivatives and methods of use - Selected amines are effective for prophylaxis and treatment of diseases, such as angiogenesis mediated diseases. The invention encompasses novel compounds of Formula I and II | 06-04-2009 |
20150141655 | METHOD FOR THE PREPARATION OF THIADIAZOLES - The present invention relates to processes for preparing protected glyceraldehydes, such as (hydroxy)methanesulfonates. In addition, the invention relates to thiadiazoles, particularly 3-diooxolanyl-thiadiazoles. | 05-21-2015 |