Patent application number | Description | Published |
20100008179 | PRE-MIXING APPARATUS FOR A TURBINE ENGINE - A pre-mixing apparatus for a turbine engine includes a main body having an inlet portion, an outlet portion and an exterior wall that collectively establish at least one fluid delivery plenum, and a plurality of fluid delivery tubes extending through at least a portion of the at least one fluid delivery plenum. Each of the plurality of fluid delivery tubes includes at least one fluid delivery opening fluidly connected to the at least one fluid delivery plenum. With this arrangement, a first fluid is selectively delivered to the at least one fluid delivery plenum, passed through the at least one fluid delivery opening and mixed with a second fluid flowing through the plurality of fluid delivery tubes prior to being combusted in a combustion chamber of a turbine engine. | 01-14-2010 |
20100095676 | Multiple Tube Premixing Device - The present application provides a premixer for a combustor. The premixer may include a fuel plenum with a number of fuel tubes and a burner tube with a number of air tubes. The fuel tubes extend about the air tubes. | 04-22-2010 |
20100180564 | Systems and Methods for Mitigating a Flashback Condition in a Premixed Combustor - A method may mitigate a flashback condition in a gas turbine. The gas turbine may include a fuel nozzle. The method may include detecting the flashback condition in the fuel nozzle, and interrupting a flow of fuel to the fuel nozzle. | 07-22-2010 |
20100186413 | BUNDLED MULTI-TUBE NOZZLE FOR A TURBOMACHINE - A turbomachine includes a compressor, a combustor operatively connected to the compressor, an end cover mounted to the combustor, and an injection nozzle assembly operatively connected to the combustor. The injection nozzle assembly includes a cap member having a first surface that extends to a second surface. The cap member further includes a plurality of openings. A plurality of bundled mini-tube assemblies are detachably mounted in the plurality of openings in the cap member. Each of the plurality of bundled mini-tube assemblies includes a main body section having a first end section and a second end section. A fluid plenum is arranged within the main body section. A plurality of tubes extend between the first and second end sections. Each of the plurality of tubes is fluidly connected to the fluid plenum. | 07-29-2010 |
20100192581 | PREMIXED DIRECT INJECTION NOZZLE - A fuel/air mixing tube for use in a fuel/air mixing tube bundle is provided. The fuel/air mixing tube includes an outer tube wall extending axially along a tube axis between an inlet end and an exit end, the outer tube wall having a thickness extending between an inner tube surface having a inner diameter and an outer tube surface having an outer tube diameter. The tube further includes at least one fuel injection hole having a fuel injection hole diameter extending through the outer tube wall, the fuel injection hole having an injection angle relative to the tube axis. The invention provides good fuel air mixing with low combustion generated NOx and low flow pressure loss translating to a high gas turbine efficiency, that is durable, and resistant to flame holding and flash back. | 08-05-2010 |
20100218501 | PREMIXED DIRECT INJECTION DISK - A fuel/air mixing disk for use in a fuel/air mixing combustor assembly is provided. The disk includes a first face, a second face, and at least one fuel plenum disposed therebetween. A plurality of fuel/air mixing tubes extend through the pre-mixing disk, each mixing tube including an outer tube wall extending axially along a tube axis and in fluid communication with the at least one fuel plenum. At least a portion of the plurality of fuel/air mixing tubes further includes at least one fuel injection hole have a fuel injection hole diameter extending through said outer tube wall, the fuel injection hole having an injection angle relative to the tube axis. The invention provides good fuel air mixing with low combustion generated NOx and low flow pressure loss translating to a high gas turbine efficiency, that is durable, and resistant to flame holding and flash back. | 09-02-2010 |
20110005189 | Active Control of Flame Holding and Flashback in Turbine Combustor Fuel Nozzle - A system includes a turbine combustor fuel nozzle. The turbine combustor fuel nozzle includes a swirl vane. The turbine combustor fuel nozzle also includes an injection hole configured to inject fluid in a downstream region of the swirl vane. The injection of fluid in a downstream region of the swirl vane may be in response to detection of a condition indicative of a flame inside the turbine combustor fuel nozzle. | 01-13-2011 |
20120006030 | INJECTION NOZZLE FOR A TURBOMACHINE - A turbomachine includes a compressor, a combustor operatively connected to the compressor, an end cover mounted to the combustor, and an injection nozzle assembly operatively connected to the combustor. The injection nozzle assembly includes a first end portion that extends to a second end portion, and a plurality of tube elements provided at the second end portion. Each of the plurality of tube elements defining a fluid passage includes a body having a first end section that extends to a second end section. The second end section projects beyond the second end portion of the injection nozzle assembly. | 01-12-2012 |
20120031102 | TURBINE COMBUSTOR WITH FUEL NOZZLES HAVING INNER AND OUTER FUEL CIRCUITS - A combustor cap assembly for a turbine engine includes a combustor cap and a plurality of fuel nozzles mounted on the combustor cap. One or more of the fuel nozzles would include two separate fuel circuits which are individually controllable. The combustor cap assembly would be controlled so that individual fuel circuits of the fuel nozzles are operated or deliberately shut off to provide for physical separation between the flow of fuel delivered by adjacent fuel nozzles and/or so that adjacent fuel nozzles operate at different pressure differentials. Operating a combustor cap assembly in this fashion helps to reduce or eliminate the generation of undesirable and potentially harmful noise. | 02-09-2012 |
20120036856 | DIMPLED/GROOVED FACE ON A FUEL INJECTION NOZZLE BODY FOR FLAME STABILIZATION AND RELATED METHOD - A fuel injection head for a fuel nozzle used in a gas turbine combustor includes a substantially hollow body formed with an upstream end face, a downstream end face and a peripheral wall extending therebetween. A plurality of pre-mix tubes or passages extend axially through the hollow body with inlets at the upstream end face and outlets at the downstream end face. An exterior surface of the downstream end face is formed with three-dimensional surface features that increase a total surface area of the exterior surface as compared to a substantially flat, planar downstream end face. | 02-16-2012 |
20120055163 | FUEL INJECTION ASSEMBLY FOR USE IN TURBINE ENGINES AND METHOD OF ASSEMBLING SAME - A method for assembling a fuel injection assembly for use in a turbine engine is provided. The method includes providing at least one cap member that has at least one first opening extending at least partially through it and at least one second opening extending at least partially through it. The method includes coupling a plurality of tube assemblies within the turbine engine. Each tube assembly includes a plurality of tubes. Moreover, the method includes coupling an injection system to the cap member to enable a fluid from a fluid source to be discharged through the at least one second opening. This fluid provides a barrier between adjacent tube assemblies to facilitate reducing dynamic pressure oscillations within the fuel injection assembly during turbine engine operation. | 03-08-2012 |
20120058437 | APPARATUS AND METHOD FOR MIXING FUEL IN A GAS TURBINE NOZZLE - A nozzle includes a fuel plenum and an air plenum downstream of the fuel plenum. Fuel channels radially outward of an axial centerline of the nozzle include an inlet and an outlet downstream of the inlet. A fuel port in the fuel channels provides fluid communication between the fuel plenum and the fuel channels. An air port in the fuel channels downstream of the fuel port provides fluid communication between the air plenum and the fuel channels. A method for mixing fuel and air in a nozzle prior to combustion includes flowing fuel to a fuel plenum and flowing air to an air plenum downstream of the fuel plenum. The method further includes injecting fuel from the fuel plenum through fuel ports in fuel channels and injecting air from the air plenum through air ports in the fuel channels. | 03-08-2012 |
20120180487 | SYSTEM FOR FLOW CONTROL IN MULTI-TUBE FUEL NOZZLE - A system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle includes a fuel conduit, a fuel chamber coupled to the fuel conduit, and multiple tubes concentrically arranged in multiple rows about a central axis of the multi-tube fuel nozzle and extending through the fuel chamber to a downstream end portion of the multi-tube fuel nozzle. The multiple tubes include fluids flow and different flow control features including at least one of different fuel/air premixing ratios, different tube diameters, or different outlet distances relative to the downstream end portion. | 07-19-2012 |
20120180495 | SYSTEM AND METHOD FOR INJECTING FUEL - According to various embodiments, a system includes a staggered multi-nozzle assembly. The staggered multi-nozzle assembly includes a first fuel nozzle having a first axis and a first flow path extending to a first downstream end portion, wherein the first fuel nozzle has a first non-circular perimeter at the first downstream end portion. The staggered multi-nozzle assembly also includes a second fuel nozzle having a second axis and a second flow path extending to a second downstream end portion, wherein the first and second downstream end portions are axially offset from one another relative to the first and second axes. The staggered multi-nozzle assembly further includes a cap member disposed circumferentially about at least the first and second fuel nozzles to assemble the staggered multi-nozzle assembly. | 07-19-2012 |
20120192566 | FUEL INJECTION ASSEMBLY FOR USE IN TURBINE ENGINES AND METHOD OF ASSEMBLING SAME - A method for assembling a fuel injection assembly for use in a turbine engine is provided. The method includes providing a cap assembly that has at least one first opening extending at least partially through it and a plurality of second openings extending at least partially through it. Moreover, a plurality of tube assemblies are coupled within the cap assembly. Each tube assembly includes a plurality of tubes. Further, at least one injection system is coupled to the cap assembly to enable a fluid from a fluid source to be discharged through at least one of the plurality of second openings. The fluid flows between at least two adjacent tube assemblies to facilitate at least one of reducing a temperature within the cap assembly and reducing dynamic pressure oscillations within a combustor during operation of the turbine engine. | 08-02-2012 |
20120198812 | APPARATUS FOR MIXING FUEL IN A GAS TURBINE - A combustor nozzle includes an inlet surface and an outlet surface downstream from the inlet surface, wherein the outlet surface has an indented central portion. A plurality of fuel channels are arranged radially outward of the indented central portion, wherein the plurality of fuel channels extend through the outlet surface. | 08-09-2012 |
20120198856 | TURBINE COMBUSTOR CONFIGURED FOR HIGH-FREQUENCY DYNAMICS MITIGATION AND RELATED METHOD - A turbomachine combustor includes a combustion chamber; a plurality of micro-mixer nozzles mounted to an end cover of the combustion chamber, each including a fuel supply pipe affixed to a nozzle body located within the combustion chamber, wherein fuel from the supply pipe mixes with air in the nozzle body prior to discharge into the combustion chamber; and wherein at least some of the nozzle bodies of the plurality of micro-mixer nozzles have axial length dimensions that differ from axial length dimensions of other of the nozzle bodies. | 08-09-2012 |
20130045450 | SYSTEM AND METHOD FOR REDUCING COMBUSTION DYNAMICS IN A COMBUSTOR - A system for reducing combustion dynamics in a combustor includes an end cap that extends radially across the combustor and includes an upstream surface axially separated from a downstream surface. A combustion chamber is downstream of the end cap, and tubes extend from the upstream surface through the downstream surface. Each tube provides fluid communication through the end cap to the combustion chamber. The system further includes means for reducing combustion dynamics in the combustor. A method for reducing combustion dynamics in a combustor includes flowing a working fluid through tubes that extend axially through an end cap that extends radially across the combustor and obstructing at least a portion of the working fluid flowing through a first set of the tubes. | 02-21-2013 |
20130067926 | Multiple Tube Premixing Device - The present application provides a premixer for a combustor. The premixer may include a fuel plenum with a number of fuel tubes and a burner tube with a number of air tubes. The fuel tubes extend about the air tubes. | 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 |
20130104551 | FUEL INJECTION ASSEMBLY FOR USE IN TURBINE ENGINES AND METHOD OF ASSEMBLING SAME | 05-02-2013 |
20130104552 | FUEL NOZZLE ASSEMBLY FOR USE IN TURBINE ENGINES AND METHODS OF ASSEMBLING SAME | 05-02-2013 |
20130104556 | SYSTEM AND METHOD FOR REDUCING COMBUSTION DYNAMICS AND NOX IN A COMBUSTOR | 05-02-2013 |
20130174568 | COMBUSTOR AND METHOD FOR DISTRIBUTING FUEL IN THE COMBUSTOR - A combustor includes a tube bundle that extends radially across at least a portion of the combustor. The tube bundle includes an upstream surface axially separated from a downstream surface. A plurality of tubes extends from the upstream surface through the downstream surface, and each tube provides fluid communication through the tube bundle. A baffle extends axially inside the tube bundle between adjacent tubes. A method for distributing fuel in a combustor includes flowing a fuel into a fuel plenum defined at least in part by an upstream surface, a downstream surface, a shroud, and a plurality of tubes that extend from the upstream surface to the downstream surface. The method further includes impinging the fuel against a baffle that extends axially inside the fuel plenum between adjacent tubes. | 07-11-2013 |
20130199189 | FUEL INJECTION ASSEMBLY FOR USE IN TURBINE ENGINES AND METHOD OF ASSEMBLING SAME - A fuel injection assembly for use in a turbine engine is provided. The fuel injection assembly includes a plurality of tube assemblies wherein each of the plurality of tube assemblies includes a plurality of tubes. At least one injection system is coupled to at least one tube assembly of the plurality of tube assemblies. The injection system includes a fluid supply member that is positioned a predefined distance upstream from the tube assembly. The fluid supply member includes a first portion that includes at least one first opening for delivering fluid toward the tube assembly for reducing dynamic pressure oscillations within a combustor and/or reducing NOx emission within the combustor during operation of the turbine engine. | 08-08-2013 |
20130199190 | FUEL INJECTION ASSEMBLY FOR USE IN TURBINE ENGINES AND METHOD OF ASSEMBLING SAME - A fuel injection assembly for use in a turbine engine is provided. The fuel injection assembly includes a plurality of tube assemblies wherein each of the plurality of tube assemblies includes a plurality of tubes. At least one injection system is coupled to at least one tube assembly of the plurality of tube assemblies. The injection system includes a fuel delivery pipe and a fluid supply member coupled to the fuel delivery pipe, wherein the fluid supply member is positioned a predefined distance upstream from the tube assembly and includes at least one first portion having an annular end portion. The annular end portion includes at least one opening for delivering fluid toward the tube assembly for reducing dynamic pressure oscillations and/or reducing the temperature within a combustor during operation of the turbine engine. | 08-08-2013 |
20130219899 | ANNULAR PREMIXED PILOT IN FUEL NOZZLE - A combustor for a gas turbine engine has a head end portion that carries at least one fuel/air nozzle. Each fuel/air nozzle includes a premixed pilot nozzle having premix conduits that are configured with concentric axes that direct the fuel/air mixture axially from the premixed pilot nozzle. The premixed pilot nozzle can include an annular channel disposed radially outwardly from the premix and including air jets that direct air radially outwardly from the premix conduits. | 08-29-2013 |
20130227928 | FUEL NOZZLE ASSEMBLY FOR USE IN TURBINE ENGINES AND METHOD OF ASSEMBLING SAME - A fuel nozzle for use with a turbine engine is provided. The fuel nozzle includes a housing coupled to a combustor liner defining a combustion chamber. The housing is at least partially positioned within an air plenum and comprises an endwall that at least partially defines the air plenum. The fuel nozzle includes a plurality of mixing tubes extending through the housing for channeling a fuel to the combustion chamber, a cooling fluid plenum at least partially defined within the housing by the housing endwall, and a plurality of apertures defined within the housing endwall for channeling a cooling fluid from the cooling fluid plenum to the air plenum. | 09-05-2013 |
20130227953 | SYSTEM AND METHOD FOR REDUCING COMBUSTION DYNAMICS IN A COMBUSTOR - A system for reducing combustion dynamics in a combustor includes an end cap having an upstream surface axially separated from a downstream surface, and tube bundles extend from the upstream surface through the downstream surface. A divider inside a tube bundle defines a diluent passage that extends axially through the downstream surface, and a diluent supply in fluid communication with the divider provides diluent flow to the diluent passage. A method for reducing combustion dynamics in a combustor includes flowing a fuel through tube bundles, flowing a diluent through a diluent passage inside a tube bundle, wherein the diluent passage extends axially through at least a portion of the end cap into a combustion chamber, and forming a diluent barrier in the combustion chamber between the tube bundle and at least one other adjacent tube bundle. | 09-05-2013 |
20130227955 | SYSTEM AND METHOD FOR REDUCING COMBUSTION DYNAMICS IN A COMBUSTOR - A system for reducing combustion dynamics in a combustor includes an end cap having an upstream surface axially separated from a downstream surface, and tube bundles extend through the end cap. A diluent supply in fluid communication with the end cap provides diluent flow to the end cap. Diluent distributors circumferentially arranged inside at least one tube bundle extend downstream from the downstream surface and provide fluid communication for the diluent flow through the end cap. A method for reducing combustion dynamics in a combustor includes flowing fuel through tube bundles that extend axially through an end cap, flowing a diluent through diluent distributors into a combustion chamber, wherein the diluent distributors are circumferentially arranged inside at least one tube bundle and each diluent distributor extends downstream from the end cap, and forming a diluent barrier in the combustion chamber between at least one pair of adjacent tube bundles. | 09-05-2013 |
20130318977 | FUEL INJECTION ASSEMBLY FOR USE IN TURBINE ENGINES AND METHOD OF ASSEMBLING SAME - A fuel injection assembly for use in a turbine engine is provided. The fuel injection assembly includes an end cover, an endcap assembly, a fluid supply chamber, and a plurality of tube assemblies positioned at the endcap assembly. Each of the tube assemblies includes a housing having a fuel plenum and a cooling fluid plenum defined therein, the cooling fluid plenum downstream from the fuel plenum and separated therefrom by an intermediate wall, a plurality of tubes extending through the housing, each of the plurality of tubes in flow communication with the fluid supply chamber and a combustion chamber downstream from the tube assembly, and an aft plate at a downstream end of the cooling fluid plenum, the aft plate including at least one aperture defined therethrough. The fuel injection assembly further includes at least one fuel delivery pipe coupled to at least one of the plurality of tube assemblies. | 12-05-2013 |
20140144141 | PREMIXER WITH DILUENT FLUID AND FUEL TUBES HAVING CHEVRON OUTLETS - A premixer includes an air tube formed in a burner tube defining a longitudinal axis, and a coaxially disposed fuel tube with a turbulence enhancing chevron outlet. The fuel tube may include an exterior tube and an interior tube with the interior tube, the exterior tube or both having chevron outlets. The chevron outlets may be tapered and notched. | 05-29-2014 |
20140144152 | Premixer With Fuel Tubes Having Chevron Outlets - A premixer includes an air tube formed in a burner tube defining a longitudinal axis, and a coaxially disposed fuel tube with a turbulence enhancing chevron outlet. The fuel tube may include an exterior tube and an interior tube with the interior tube, the exterior tube or both having chevron outlets. The chevron outlets may be tapered and notched. | 05-29-2014 |
20140157779 | SYSTEM FOR REDUCING COMBUSTION DYNAMICS AND NOx IN A COMBUSTOR - A combustor includes an end cap that extends radially across at least a portion of the combustor. The end cap includes an upstream surface axially separated from a downstream surface. A plurality of tubes extend from the upstream surface through the downstream surface of the end cap to provide fluid communication through the end cap. Each tube in a first set of the plurality of tubes has an inlet proximate to the upstream surface and an outlet downstream from the downstream surface. Each outlet has a first portion that extends a different axial distance from the inlet than a second portion. | 06-12-2014 |
20140238025 | FUEL/AIR MIXING SYSTEM FOR FUEL NOZZLE - A system includes a fuel nozzle. The fuel nozzle includes a central hub with a first annular passage extending along a longitudinal axis of the fuel nozzle. A flow conditioner is disposed along the first annular passage. The flow conditioner includes at least one of a straightening vane, a mesh screen, or a multi-passage body having multiple passages generally parallel with the longitudinal axis. An outer shroud is disposed about the central hub to define a second annular passage extending along the longitudinal axis of the fuel nozzle. | 08-28-2014 |
20140238036 | FUEL/AIR MIXING SYSTEM FOR FUEL NOZZLE - A fuel nozzle includes an inner wall defining a central passage extending in an axial direction of the fuel nozzle, a hub wall surrounding the inner wall and defining a first annular passage, an outer wall surrounding the hub wall and defining a second annular passage, and a shroud surrounding the outer wall and defining a third annular passage. A swirler may receive air and direct the air into the first annular passage. The swirler includes at least one swirl vane extending from the shroud to the hub wall that has an air passage extending between the shroud and the hub wall. The air passage is coupled to the first annular passage and has a first width adjacent the shroud and a second width adjacent the hub wall. The second width is larger than the first width defining a diverging outlet into the first annular passage. | 08-28-2014 |