Patent application number | Description | Published |
20090232644 | CMC VANE INSULATOR AND METHOD OF USE - A method for assembling a gas or steam turbine is provided. The method includes providing an insulator and positioning the insulator between a vane support and a vane such that the insulator facilitates preventing hot gas migration into the vane, and such that during operation, hot gas is channeled from a high pressure side of the vane to a low pressure side of the vane. A vane assembly for a turbine rotor assembly is also provided. The vane assembly includes a vane support and an insulator including a projecting portion. The assembly also includes a vane. The insulator is coupled to the vane support such that the projecting portion is between the vane and a nozzle support strut to facilitate hot gas flow from a pressure side of the projecting portion to a suction side of the projecting portion. | 09-17-2009 |
20110289933 | Hybrid Prefilming Airblast, Prevaporizing, Lean-Premixing Dual-Fuel Nozzle for a Gas Turbine Combustor - A dual fuel nozzle for a gas turbine combustor includes a hub defining a fuel inlet and a plurality of liquid fuel jets disposed at a downstream end of the hub. The fuel jets are oriented to eject liquid fuel radially outward from the hub. An annular air passage includes a swirler that imparts swirl to air flowing in the annular air passage, and a splitter ring is disposed in the annular air passage and surrounds the plurality of liquid fuel jets. The nozzle allows liquid fuels to be injected into a swirling annular airstream and then atomized, dispersed and vaporized inside a lean premixing dual fuel nozzle for a gas turbine combustor. | 12-01-2011 |
20120015309 | METHOD FOR A COMBUSTOR NOZZLE - A method for supplying fuel to a combustor includes flowing a working fluid through a nozzle, injecting the fuel into the nozzle, and mixing the fuel with the working fluid to create a fuel and working fluid mixture. The method further includes swirling the fuel and working fluid mixture, sensing flame holding in the nozzle, and reducing the swirl in the fuel and working fluid mixture. A method for supplying a working fluid to a combustor includes flowing the working fluid through a nozzle and swirling the working fluid flowing through the nozzle. The method further includes sensing flame holding in the nozzle and reducing the swirl of the working fluid flowing through the nozzle. | 01-19-2012 |
20120085100 | Combustor with a Lean Pre-Nozzle Fuel Injection System - The present application provides for a combustor for combusting a flow of fuel and a flow of air. The combustor may include a number of fuel nozzles, a lean pre-nozzle fuel injection system positioned upstream of the fuel nozzles, and a premixing annulus positioned between the fuel nozzles and the lean pre-nozzle fuel injection system to premix the flow of fuel and the flow of air. | 04-12-2012 |
20140260271 | System Having a Multi-Tube Fuel Nozzle - A system including a plurality of multi-tube fuel nozzles each having a plurality of tubes extending in an axial direction, wherein each tube of the plurality of tubes includes an air inlet, a fuel inlet, and a fuel-air mixture outlet, a fuel nozzle housing including a first outer wall extending circumferentially about a central axis, wherein the plurality of multi-tube fuel nozzles are disposed in the fuel nozzle housing, an inlet flow conditioner removably coupled to a first end portion of the first outer wall, wherein the inlet flow conditioner includes a plurality of air openings, and an aft plate assembly removably coupled to a second end portion of the first outer wall, wherein the aft plate assembly includes an aft plate having a plurality of tube apertures, and the plurality of tubes extend to the plurality of tube apertures. | 09-18-2014 |
20140338344 | System Having a Multi-Tube Fuel Nozzle with a Fuel Nozzle Housing - A system including a plurality of multi-tube fuel nozzles each having a plurality of tubes extending in an axial direction, wherein each tube of the plurality of tubes includes an air inlet, a fuel inlet, and a fuel-air mixture outlet, and a fuel nozzle housing, including an outer wall extending circumferentially about a central axis, a plurality of radial walls extending from the outer wall inwardly toward the central axis, a plurality of fuel nozzle receptacles disposed within the outer wall, wherein the plurality of radial walls separate the plurality of fuel nozzle receptacles from one another, and the plurality of multi-tube fuel nozzles are disposed in the plurality of fuel nozzle receptacles a mounting structure including a plurality of radial support arms extending outwardly from the outer wall. | 11-20-2014 |
20140338354 | System Having a Multi-Tube Fuel Nozzle with an Inlet Flow Conditioner - A system including a multi-tube fuel nozzle, including a plurality of tubes extending in an axial direction relative to a central axis of the multi-tube fuel nozzle, wherein each tube of the plurality of tubes includes an air inlet, a fuel inlet, and a fuel-air mixture outlet; and an inlet flow conditioner, including a plate extending in a radial direction relative to the central axis of the multi-tube fuel nozzle; an outer wall extending circumferentially about the plate, wherein the outer wall is coupled to the plate; and a plurality of air openings in the plate, the outer wall, or a combination thereof, wherein the plurality of air openings are disposed upstream from the air inlets in the plurality of tubes. | 11-20-2014 |
20140338355 | System and Method for Sealing a Fuel Nozzle - A system including a multi-tube fuel nozzle, including a first plate having a first plurality of openings, a plurality of tubes extending through the first plurality of openings in the first plate, wherein each tube of the plurality of tubes includes an air inlet, a fuel inlet, and a fuel-air mixture outlet, and a resilient metallic seal disposed along the first plate about the plurality of tubes. | 11-20-2014 |
20140338356 | System Having a Multi-Tube Fuel Nozzle with an Aft Plate Assembly - A system including a first multi-tube fuel nozzle including a plurality of first tubes extending in an axial direction, wherein each first tube of the plurality of first tubes includes a first air inlet, a first fuel inlet, and a first fuel-air mixture outlet, a second multi-tube fuel nozzle including a plurality of second tubes extending in an axial direction, wherein each second tube of the plurality of second tubes includes a second air inlet, a second fuel inlet, and a second fuel-air mixture outlet, and an aft plate including a plurality of first tube apertures and a plurality of second tube apertures, wherein the plurality of first tubes extend to the plurality of first tube apertures, and the plurality of second tubes extend to the plurality of second tube apertures. | 11-20-2014 |
Patent application number | Description | Published |
20100078506 | CIRCUMFERENTIAL FUEL CIRCUIT DIVIDER - A fuel nozzle includes a hub with a plurality of output fuel holes arranged perimetrically around the hub. At least two plates located inside the hub define fuel flow passages between an input fuel flow and the output fuel holes. A plurality of enclosures is located between an inner surface of the hub and an outer one of the plates. Each enclosure is in fuel flow communication with first ones of the output fuel holes and the input fuel flow to define a first one of the passages. The two plates define a second one of the fuel flow passages which is in fuel flow communication with the input fuel flow and with second ones of the output fuel holes. | 04-01-2010 |
20100236247 | METHOD AND APPARATUS FOR DELIVERY OF A FUEL AND COMBUSTION AIR MIXTURE TO A GAS TURBINE ENGINE - A nozzle has combustion air passages extending from a first, upstream end to a second, downstream end. A fuel distribution manifold is associated with the first, upstream end of the nozzle. Combustion air passages correspond to, and align with the air passages in the nozzle. Fuel distribution grooves are formed in one end of the fuel distribution manifold disk and extend from a central opening to the air passages. A fuel circuit cover closes the fuel distribution grooves to define fuel passages that extend from the central opening to the combustion air passages. A fuel supply conduit communicates with the central opening and the fuel passages for delivery of fuel to the combustion air in the air passages. | 09-23-2010 |
20100275601 | TURBINE AIR FLOW CONDITIONER - A system includes an air flow conditioner configured to mount in an air chamber separated from a combustion chamber of a turbine combustor. The air flow conditioner comprises a perforated annular wall configured to direct an air flow in both an axial direction and a radial direction relative to an axis of the turbine combustor. In addition, the air flow conditioner is configured to uniformly supply the air flow into air inlets of one or more fuel nozzles. | 11-04-2010 |
20110005229 | LEAN DIRECT INJECTION FOR PREMIXED PILOT APPLICATION - Embodiments of this invention provide a premixed pilot assembly for use with a fuel nozzle for a turbine. The level of nitrogen oxide (NOx) emitted by the pilot is reduced by mixing the fuel and air fast, at the end of the pilot nozzle, thereby avoiding significant zones of rich fuel and air mixtures. The air is mixed with the fuel through the use of openings in a first cylinder and a second cylinder, one of which carries air and one of which carries pilot fuel. The openings can be configured as necessary to obtain a desired effect on the pilot. | 01-13-2011 |
20110094232 | APPARATUS FOR CONDITIONING AIRFLOW THROUGH A NOZZLE - A nozzle includes a center body and a shroud surrounding the center body to define an annular passage. An arcuate annular guide extending from a point radially inward of the shroud to a point radially outward of the shroud defines a first airflow between the arcuate annular guide and the shroud and a second airflow between the arcuate annular guide and the center body. | 04-28-2011 |
20110173983 | PREMIX FUEL NOZZLE INTERNAL FLOW PATH ENHANCEMENT - A nozzle for gas turbine includes a tubular nozzle body; and a plurality of hollow fuel injection pegs extending radially from the tubular nozzle body at a location between forward and aft ends of the tubular nozzle body; wherein each of the plurality of hollow fuel injection pegs has an external tear-drop cross-sectional shape, and a fuel passage in each of the hollow injection pegs has a substantially matching internal tear-drop cross-sectional shape. | 07-21-2011 |
20110247342 | SYSTEM AND METHOD FOR A COMBUSTOR NOZZLE - A nozzle includes a center body and a shroud circumferentially surrounding at least a portion of the center body to define an annular passage between the center body and the shroud. The nozzle further includes a bimetallic guide between the center body and the shroud. A method for supplying fuel to a combustor includes flowing a working fluid through a nozzle, injecting the fuel into the nozzle, and mixing the fuel with the working fluid to create a fuel and working fluid mixture. The method further includes swirling the fuel and working fluid mixture, sensing flame holding in the nozzle, and reducing the swirl in the fuel and working fluid mixture. | 10-13-2011 |
20120255310 | COMBUSTOR NOZZLE AND METHOD FOR SUPPLYING FUEL TO A COMBUSTOR - A combustor nozzle includes a center body and a shroud circumferentially surrounding at least a portion of the center body to define a passage between the center body and the shroud. A guide between the center body and the shroud can pivot with respect to the center body. A method for supplying fuel to a combustor includes flowing a working fluid through a nozzle at a mass flow rate and flowing a fuel through the nozzle. The method further includes sensing a flame holding event inside the nozzle and pivoting a guide inside the nozzle to increase the mass flow rate of the working fluid flowing through the nozzle. | 10-11-2012 |
20130025283 | SECTOR NOZZLE MOUNTING SYSTEMS - Systems are provided for mounting sector nozzles within gas turbine combustors. In one embodiment, a sector nozzle includes a nozzle portion configured to mix fuel and air to produce a fuel-air mixture and a shell coupled to the nozzle portion. The sector nozzle also includes a first longitudinal strut and a second longitudinal strut coupled to a first surface of the shell on opposite sides of a window within the first surface. A third longitudinal strut is coupled to a second surface of the shell, and the second surface is disposed opposite of the first surface. | 01-31-2013 |
20130025285 | SYSTEM FOR CONDITIONING AIR FLOW INTO A MULTI-NOZZLE ASSEMBLY - A system includes a turbine fuel nozzle assembly. The turbine fuel nozzle assembly includes a first fuel nozzle including a first air inlet and a second fuel nozzle including a second air inlet. The turbine fuel nozzle assembly also includes a first inlet flow conditioner disposed adjacent the first air inlet of the first fuel nozzle, wherein the first air inlet flow conditioner extends only partially around the first fuel nozzle. The turbine fuel nozzle further includes a second inlet flow conditioner disposed adjacent the second air inlet of the second fuel nozzle, wherein the second air inlet flow conditioner extends only partially around the second fuel nozzle, and the second inlet flow conditioner is separate from the first inlet flow conditioner. | 01-31-2013 |
20130061594 | TURNING GUIDE FOR COMBUSTION FUEL NOZZLE IN GAS TURBINE AND METHOD TO TURN FUEL FLOW ENTERING COMBUSTION CHAMBER - A fuel nozzle assembly for a gas turbine, the assembly including: a cylindrical center body; a cylindrical shroud coaxial with and extending around the center body, and a turning guide having an downstream edge extending in a passage between the center body and an inlet to the shroud, wherein the turning guide extends only partially around the center body. | 03-14-2013 |
20130067923 | COMBUSTOR AND METHOD FOR CONDITIONING FLOW THROUGH A COMBUSTOR - A combustor includes an end cover and a casing adjacent to the end cover, wherein the end cover and casing at least partially define a volume inside the combustor. The combustor further includes an end cap that extends radially across at least a portion of the combustor, at least one nozzle arranged in the end cap to provide fluid communication through the end cap, and means for conditioning flow through the volume. A method for conditioning flow through a combustor includes flowing a working fluid through a volume at least partially defined by an end cover, a casing, and an end cap that extends radially across at least a portion of the combustor and flowing the working fluid across an annular insert adjacent to the end cover. | 03-21-2013 |
20130101943 | COMBUSTOR AND METHOD FOR CONDITIONING FLOW THROUGH A COMBUSTOR - A combustor includes an end cap that extends radially across a portion of the combustor and includes an upstream surface axially separated from a downstream surface. A combustion chamber is downstream of the end cap. Premixer tubes extend from a premixer tube inlet proximate to the upstream surface through the downstream surface to provide fluid communication through the end cap and include means for conditioning flow through the plurality of premixer tubes. A method for conditioning flow through a combustor includes flowing a working fluid through a first and second set of premixer tubes that extend axially through an end cap, wherein the second set of premixer tubes includes means for conditioning flow through the second set of premixer tubes, and flowing a fuel through the first or second set of premixer tubes. | 04-25-2013 |
20130111909 | Combustion System Having A Venturi For Reducing Wakes In An Airflow - A combustion system is provided having a liner, a flow sleeve, a flow-obstructing element, and a venturi. The liner is disposed around a combustion region. The flow sleeve is disposed around the liner. The liner and the flow sleeve cooperate to create an air passage having an airflow located between the liner and the flow sleeve. The flow-obstructing element is disposed within the air passage, and generally obstructs the airflow in the air passage to create wakes in the airflow. The venturi is disposed downstream from the flow-obstructing element, and generally restricts and diffuses the airflow in the air passage to reduce wakes in the airflow. | 05-09-2013 |
20130192234 | BUNDLED MULTI-TUBE NOZZLE ASSEMBLY - A method for reducing emissions in a turbo machine is disclosed. The method includes providing fuel to a multi-tube nozzle and reducing the differences in the mass flow rate of fuel into each tube. An improved multi-tube nozzle is also disclosed. The nozzle includes an assembly that reduces the difference in the mass flow rate of fuel into each tube. | 08-01-2013 |
20140053571 | SEAL FOR A PERFORATED PLATE - A cooling circuit of a gas turbine passes an airflow through a combustor section that includes a plurality of mixing tubes for transporting a fuel/air mixture and a perforated plate including a plurality of impingement holes and a plurality of tube holes for accommodating the mixing tubes. The tube holes and the mixing tubes form a plurality of annulus areas between the perforated plate and the mixing tubes. The impingement holes and the annulus areas are configured to pass the airflow through the perforated plate. A flow management device modifies an effective size of the annulus areas to control a distribution of the airflow through the impingement holes and the annulus areas of the perforated plate to enhance cooling efficiency. | 02-27-2014 |
20140083110 | SEAL FOR FUEL DISTRIBUTION PLATE - A fuel flow passes through a micromixer section of a gas turbine that includes a plurality of mixing tubes for transporting a fuel/air mixture and a distribution plate including a plurality of distribution holes and a plurality of tube holes for accommodating the mixing tubes. Each of the mixing tubes includes a plurality of fuel holes through which fuel enters the mixing tubes. The tube holes and the mixing tubes form a plurality of annulus areas between the distribution plate and the mixing tubes. The distribution holes and the annulus areas are configured to pass the fuel flow through the distribution plate toward the fuel holes. A flow management device modifies an effective size of the annulus areas to control a distribution of the fuel flow through the distribution holes and the annulus areas of the distribution plate to provide a uniform fuel/air composition in each of the mixing tubes. | 03-27-2014 |
20140216041 | Variable Volume Combustor with Center Hub Fuel Staging - The present application and the resultant patent provide a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles and a fuel injection system for providing a flow of fuel to the micro-mixer fuel nozzles. The fuel injection system may include a center hub for providing the flow of fuel therethrough. The center hub may include a first supply circuit for a first micro-mixer fuel nozzle and a second supply circuit for a second micro-mixer fuel nozzle. | 08-07-2014 |
20140216054 | Variable Volume Combustor with Aerodynamic Support Struts - The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles and a fuel injection system for providing a flow of fuel to the micro-mixer fuel nozzles. The fuel injection system may include a number of support struts supporting the fuel nozzles and providing the flow of fuel therethrough. The support struts may include an aerodynamic contoured shape so as to distribute evenly a flow of air to the micro-mixer fuel nozzles. | 08-07-2014 |
20140366541 | SYSTEMS AND APPARATUS RELATING TO FUEL INJECTION IN GAS TURBINES - A gas turbine engine having a combustor that includes: an inner radial wall defining a first interior chamber and a second interior chamber, wherein the first interior chamber extends axially from an end cover to a primary fuel injector, and the second interior chamber extends axially from the primary fuel injector to the turbine; an outer radial wall formed about the inner radial wall so that a flow annulus is formed therebetween; upstream fuel nozzles jutting into the flow annulus from the outer radial wall. The upstream fuel nozzles may include non-uniform circumferential spacing about the inner radial wall. | 12-18-2014 |
20150107255 | TURBOMACHINE COMBUSTOR HAVING AN EXTERNALLY FUELED LATE LEAN INJECTION (LLI) SYSTEM - A turbomachine combustor assembly includes a combustor including a combustor body extending from a head end to a second end through a combustion zone. At least one injector is configured and disposed to introduce a first combustible fluid into the combustion zone at the head end of the combustor body. At least one late lean injector (LLI) is configured and disposed to introduce a second combustible fluid downstream of the first combustible fluid. An external fluid delivery system is fluidically connected to the at least one LLI. The external fluid delivery system includes at least one combustible fluid delivery conduit that extends from a first end fluidically connected to the LLI to a second end external to the turbomachine combustor assembly. The second end is configured and disposed to deliver the second combustible mixture to the LLI. | 04-23-2015 |
20150308345 | FUEL NOZZLE ASSEMBLY - A fuel nozzle assembly having an inlet region of a fuel nozzle base assembly that provides more uniform flow of fuel within the fuel nozzle assembly. The embodiments described herein provide fuel flow conditioning components that manage fuel uniformity within a fuel annulus and make more efficient use of allocated space, thereby overcoming spatial constraints imposed on the overall fuel nozzle assembly. | 10-29-2015 |
20160033133 | COMBUSTOR NOZZLES IN GAS TURBINE ENGINES - A micro-mixer nozzle for use in a combustor of a combustion turbine engine, the micro-mixer nozzle including: a fuel plenum defined by a shroud wall connecting a periphery of a forward tube sheet to a periphery of an aft tubesheet; a plurality of mixing tubes extending across the fuel plenum for mixing a supply of compressed air and fuel, each of the mixing tubes forming a passageway between an inlet formed through the forward tubesheet and an outlet formed through the aft tubesheet; and a wall mixing tube formed in the shroud wall. | 02-04-2016 |
Patent application number | Description | Published |
20080205445 | Optimizing TCP traffic via an SCTP association - In one embodiment, a method can include: (i) pre-configuring a stream control transmission protocol (SCTP) association; (ii) receiving a transmission control protocol (TCP) packet in a network device, where the TCP packet is intended for a destination node; (iii) encapsulating the TCP packet into an SCTP payload; and (iv) transmitting the SCTP payload across a wide area network (WAN). | 08-28-2008 |
20080250153 | STREAMING OF TEMPLATES AND DATA RECORDS IN INDIVIDUAL STREAMS USING A MULTISTREAM PROTOCOL - In one embodiment, a method includes determining a first template defining a data format for one or more first data records and a second template defining a data format for one or more second data records. The template may be needed to decode the information included in an associated data record. The first template is sent on a first stream of a multi-stream protocol in an ordered fashion, such as SCTP. The one or more first data records are also sent on the first stream in an ordered fashion and include first flow information for data sent through a network device. A second template is sent on a second stream using the multi-stream protocol in an ordered fashion. One or more second data records are sent on the second stream including second flow information for data sent through the network device. | 10-09-2008 |
20090196178 | Disconnected Transport Protocol Connectivity - In an embodiment, an existing transport protocol connection though a mobile device is recognized as having entered a state of disconnect. A lowest received sequence number is determined from received messages to be transmitted over a disconnected transport protocol connection. A disconnect acknowledgement message with a receive window of zero and a sequence number of one less than the lowest received sequence number is transmitted. The disconnect acknowledge message with a receive window of zero and a sequence number of one less than the lowest received sequence number is continued to be transmitted until the transport protocol connection exits the disconnect state to a connect state. | 08-06-2009 |
20120136944 | Method For Dynamic Discovery of Control Plane Resources and Services - An apparatus comprising a processor configured to discover one or more peer processors associated with a network component in a dynamic manner by detecting an announcement message from a peer processor, wherein the announcement message is multicast from the peer processor when the peer processor is added or activated on the network component. | 05-31-2012 |
20120137012 | Method for Dynamic On Demand Startup of a Process or Resource - An apparatus comprising a processor configured to startup a new process on a peer processor to off-load a load of a local process on the processor in a dynamic manner based on monitoring an amount of resources used by the processor, wherein the startup of the new process on the peer processor is initiated when the amount of resources used by the local process reaches a threshold. | 05-31-2012 |
20120177038 | Method for Group-Based Multicast with Non-Uniform Receivers - An apparatus comprising a proxy configured to couple to a sender and a receiver and to receive data from the sender at a first rate and forward the data to the receiver at a second rate that is less than the first rate. A method comprising detecting a reception speed for each of a plurality of receivers in a multicast group, assigning the receivers to a first group and a second group based on the reception speed of each of the receivers, wherein the first group has a reception speed that is faster than a reception speed of the second group, and sending multicast data intended for all of the receivers to the receivers in the first group and to a proxy at a first rate, wherein the proxy buffers the multicast data and sends the multicast data to the receivers in the second group at a second rate. | 07-12-2012 |
20120209989 | Method for Dynamic Migration of a Process or Services from One Control Plane Processor to Another - An apparatus comprising a processor configured to migrate load from a source process running on the processor to a target process running on a peer processor in a dynamic manner by monitoring an amount of resources used by the source process, wherein the load is migrated when the amount of resources utilized by the source process exceeds a threshold. Also disclosed is a network component comprising a first processor configured to select a source process to migrate a load from the first processor based on available resources on the first processor and the source process; and a second processor configured upon receiving a migration request from the first processor to one of select and start a target process to which to migrate the load based on available resources for the second processor and the target process. | 08-16-2012 |
20130132627 | System and Method for Implementing Locks Shared Between Kernel and User Space - An apparatus comprising one or more processors configured to implement a plurality of operations for an operating system (OS) platform including a kernel and a user application, one or more shared resource blocks by the kernel and the user application, and one or more shared locks by the kernel and the user application corresponding to the shared resource blocks, wherein the user application is configured to synchronize accesses to the shared resource blocks between a user thread and a kernel thread by directly accessing the locks without using a system call to the kernel. | 05-23-2013 |