Patent application number | Description | Published |
20080264033 | METHODS AND SYSTEMS TO FACILITATE REDUCING NOx EMISSIONS IN COMBUSTION SYSTEMS - A method for assembling a gas turbine combustor system is provided. The method includes providing a combustion liner including a center axis, an outer wall, a first end, and a second end. The outer wall is orientated substantially parallel to the center axis. The method also includes coupling a transition piece to the liner second end. The transition piece includes an outer wall. The method further includes coupling a plurality of lean-direct injectors along at least one of the liner outer wall and the transition piece outer wall such that the injectors are spaced axially apart along the wall. | 10-30-2008 |
20080289314 | METHODS AND APPARATUS FOR OPERATING GAS TURBINE ENGINES - A fuel delivery system for a gas turbine engine includes one or more subsets of combustors, and at least two fuel manifolds including a fuel manifold coupled to each combustor subset and configured to deliver fuel to only the subset of combustors during a predetermined gas turbine engine operating mode. A gas turbine engine assembly including a fuel delivery system and a method of operating a gas turbine engine is also described herein. | 11-27-2008 |
20090007566 | NOx ADJUSTMENT METHOD FOR GAS TURBINE COMBUSTORS - A method for controlling NOx emissions from a gas turbine having a fuel adjustment system may include setting an outer nozzle fuel flow to achieve a desired level of combustion dynamics for at least one of a plurality of combustion chambers, determining a delta adjustment value for a center nozzle fuel flow that will result in a desired level of NOx emissions from the gas turbine, and adjusting the center nozzle fuel flow according to the determined delta adjustment value to obtain the desired level of NOx emissions from the gas turbine. | 01-08-2009 |
20090107105 | METHOD AND APPARATUS FOR COMBUSTING SYNGAS WITHIN A COMBUSTOR - A method for operating a combustor is provided. The method includes supplying a predetermined amount of a first gaseous fuel to the combustor, wherein the first gaseous fuel has a first Modified Wobbe Index (MWI) and a first fuel reactivity, and supplying a predetermined amount of a second gaseous fuel to the combustor, wherein the second gaseous fuel has a second MWI that is lower than the first MWI and a second fuel reactivity that is higher than the first fuel reactivity. The method also includes mixing the first and second gaseous fuels together to form a blended gaseous fuel, and injecting the blended gaseous fuel into the combustor. | 04-30-2009 |
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 |
20100024426 | Hybrid Fuel Nozzle - A hybrid fuel combustion nozzle for use with natural gas, syngas, or other types of fuels. The hybrid fuel combustion nozzle may include a natural gas system with a number of swozzle vanes and a syngas system with a number of co-annular fuel tubes. | 02-04-2010 |
20100050642 | MULTI-TUBE ARRANGEMENT FOR COMBUSTOR AND METHOD OF MAKING THE MULTI-TUBE ARRANGEMENT - A fuel injector tube includes a one piece, unitary, polygonal tube having an inlet end and an outlet end. The fuel injector tube further includes a fuel passage extending from the inlet end to the outlet end along a longitudinal axis of the polygonal tube, a plurality of air passages extending from the inlet end to the outlet end and surrounding the fuel passage, and a plurality of fuel holes. Each fuel hole connects an air passage with the fuel passage. The inlet end of the polygonal tube is formed into a fuel tube. A fuel injector includes a plurality of fuel injector tubes and a plate. The plurality of fuel tubes are connected to the plate adjacent the inlet ends of the plurality of fuel injector tubes. | 03-04-2010 |
20100084490 | Premixed Direct Injection Nozzle - An injection nozzle having a main body portion with an outer peripheral wall is disclosed. The nozzle includes a plurality of fuel/air mixing tubes disposed within the main body portion and a fuel flow passage fluidly connected to the plurality of fuel/air mixing tubes. Fuel and air are partially premixed inside the plurality of the tubes. A second body portion, having an outer peripheral wall extending between a first end and an opposite second end, is connected to the main body portion. The partially premixed fuel and air mixture from the first body portion gets further mixed inside the second body portion. The second body portion converges from the first end toward said second end. The second body portion also includes cooling passages that extend along all the walls around the second body to provide thermal damage resistance for occasional flame flash back into the second body. | 04-08-2010 |
20100089367 | FUEL NOZZLE ASSEMBLY - A fuel nozzle assembly is provided. The assembly includes an outer nozzle body having a first end and a second end and at least one inner nozzle tube having a first end and a second end. One of the nozzle body or nozzle tube includes a fuel plenum and a fuel passage extending therefrom, while the other of the nozzle body or nozzle tube includes a fuel injection hole slidably aligned with the fuel passage to form a fuel flow path therebetween at an interface between the body and the tube. The nozzle body and the nozzle tube are fixed against relative movement at the first ends of the nozzle body and nozzle tube, enabling the fuel flow path to close at the interface due to thermal growth after a flame enters the nozzle tube. | 04-15-2010 |
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 |
20100101229 | Flame Holding Tolerant Fuel and Air Premixer for a Gas Turbine Combustor - A fuel nozzle with active cooling is provided. It includes an outer peripheral wall, a nozzle center body concentrically disposed within the outer wall in a fuel and air pre-mixture. The fuel and air pre-mixture includes an air inlet, a fuel inlet and a premixing passage defined between the outer wall in the center body. A gas fuel flow passage is provided. A first cooling passage is included within the center body in a second cooling passage is defined between the center body and the outer wall. | 04-29-2010 |
20100115953 | Integrated Combustor and Stage 1 Nozzle in a Gas Turbine and Method - An integrated combustor and stage one nozzle in a gas turbine includes a combustion chamber that receives premixed fuel and air from at least one fuel nozzle group at separate axial locations. The combustion chamber includes a liner and a transition piece that deliver hot combustion gas to the turbine. The stage one nozzle, the liner and the transition piece are integrated into a single part. At least one of the axial locations of the one or more fuel nozzle groups includes a plurality of small scale mixing devices that concentrate heat release and reduce flame length. | 05-13-2010 |
20100170251 | LATE LEAN INJECTION WITH EXPANDED FUEL FLEXIBILITY - A gas turbine engine is provided and includes a fuel circuit, including multiple fuel circuit branches, a combustor having a first interior in which a first fuel supplied thereto by any one of the multiple fuel circuit branches is combustible, a turbine, a transition zone, including a second interior in which a second fuel supplied thereto by any one of the multiple fuel circuit branches, the second fuel including gas receivable by the fuel circuit from an external source, and the products of the combustion of the first fuel are combustible, the transition zone being disposed to fluidly couple the combustor and the turbine to one another, and a plurality of fuel injectors which supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages. | 07-08-2010 |
20100174466 | LATE LEAN INJECTION WITH ADJUSTABLE AIR SPLITS - A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, a turbine into which products of at least the combustion of the first fuel are receivable, a transition zone, including a second interior in which a second fuel and the products of the combustion of the first fuel are combustible, a plurality of fuel injectors which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages, a compressor, by which air is supplied to the first and second interiors for the combustion therein, and a control system configured to control relative amounts of the air to the first and second interiors and relative amounts of the first and second fuels supplied to the first and second interiors. | 07-08-2010 |
20100175380 | TRAVERSING FUEL NOZZLES IN CAP-LESS COMBUSTOR ASSEMBLY - A combustor includes a central fuel nozzle assembly and a plurality of outer fuel nozzle assemblies, each of the plurality of outer fuel nozzle assemblies having a center body and an outer shroud, the plurality of outer fuel nozzle assemblies being configured to abut one another in a surrounding relationship to the central cylinder such that no gaps are present between any two abutting ones of the plurality of outer fuel nozzle assemblies. One or more of the plurality of fuel nozzle assemblies may traverse axially back and forth according to embodiments of the invention. | 07-15-2010 |
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 |
20100180674 | Systems and Methods of Monitoring Acoustic Pressure to Detect a Flame Condition in a Gas Turbine - A method may detect a flashback condition in a fuel nozzle of a combustor. The method may include obtaining a current acoustic pressure signal from the combustor, analyzing the current acoustic pressure signal to determine current operating frequency information for the combustor, and indicating that the flashback condition exists based at least in part on the current operating frequency information. | 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 |
20100252652 | PREMIXING DIRECT INJECTOR - A fuel injection nozzle comprises a body member having an upstream wall opposing a downstream wall, a baffle member having an upstream surface and a downstream surface, a first chamber, a second chamber, a fuel inlet communicative with the first chamber operative to emit a first gas into the first chamber, and a plurality of mixing tubes, each of the mixing tubes having a tube inner surface, a tube outer surface, a first inlet communicative with an aperture in the upstream wall operative to receive a second gas, a second inlet communicative with the tube outer surface and the tube inner surface operative to translate the first gas into the mixing tube, a mixing portion operative to mix the first gas and the second gas, and an outlet communicative with an aperture in the downstream wall operative to emit the mixed first and second gasses. | 10-07-2010 |
20100326079 | METHOD AND SYSTEM TO REDUCE VANE SWIRL ANGLE IN A GAS TURBINE ENGINE - A fuel nozzle assembly includes a swirler assembly having an inlet end, an outlet end, a shroud inner surface and a hub outer surface. The inner surface has a first diameter adjacent to the inlet end and a second diameter adjacent to the outlet end defining a differential diameter ratio. A plurality of vanes are coupled to the swirler assembly and extend between the shroud inner surface and the hub outer surface. The vanes have a pair of opposing sidewalls joined at a leading edge and at an axially-spaced trailing edge, and a first height adjacent to the leading edge and a second height adjacent to the trailing edge. The first height and the second height define a differential height ratio, wherein the differential diameter ratio, the differential height ratio, or both are configured to provide convergent flow through the fuel nozzle. | 12-30-2010 |
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 |
20110179795 | INJECTOR WITH INTEGRATED RESONATOR - The system may include a turbine engine. The turbine engine may include a fuel nozzle. The fuel nozzle may include an air path. The fuel nozzle may also include a fuel path such that the fuel nozzle is in communication with a combustion zone of the turbine engine. Furthermore, the fuel nozzle may include a resonator. The resonator may be disposed in the fuel nozzle directly adjacent to the combustion zone. | 07-28-2011 |
20110185743 | Methods For Operating Gas Turbine Engines - Fuel is delivered in a gas turbine engine including a can annular combustor array that includes at least one combustor level subset within the array supplied by an independent fuel delivery system. Fuel is supplied only to one or more subsets during a first mode of operation. Fuel is supplied to the entire array of combustors during a second mode of operation. | 08-04-2011 |
20120096866 | FUEL NOZZLE FOR COMBUSTOR - A nozzle for a combustor is disclosed. The nozzle includes a center body, a burner tube provided around the center body and defining a fuel-air mixing passage therebetween, and an outer peripheral wall provided around the burner tube and defining an air flow passage therebetween. The nozzle further includes a nozzle tip connected to the center body. The nozzle tip includes a pilot fuel passage configured to deliver a flow of pilot fuel to a combustion zone, and a plurality of transfer passages. The plurality of transfer passages are configured to deliver a flow of air for combustion with the flow of pilot fuel in the combustion zone and further configured to deliver a flow of transfer fuel to the combustion zone. | 04-26-2012 |
20120110974 | LATE LEAN INJECTION WITH ADJUSTABLE AIR SPLITS - A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, a turbine into which products of at least the combustion of the first fuel are receivable, a transition zone, including a second interior in which a second fuel and the products of the combustion of the first fuel are combustible, a plurality of fuel injectors which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages, a compressor, by which air is supplied to the first and second interiors for the combustion therein, and a control system configured to control relative amounts of the air to the first and second interiors and relative amounts of the first and second fuels supplied to the first and second interiors. | 05-10-2012 |
20120198851 | TRAVERSING FUEL NOZZLES IN CAP-LESS COMBUSTOR ASSEMBLY - A combustor includes a central fuel nozzle assembly and a plurality of outer fuel nozzle assemblies, each of the plurality of outer fuel nozzle assemblies having a center body and an outer shroud, the plurality of outer fuel nozzle assemblies being configured to abut one another in a surrounding relationship to the central cylinder such that no gaps are present between any two abutting ones of the plurality of outer fuel nozzle assemblies. One or more of the plurality of fuel nozzle assemblies may traverse axially back and forth according to embodiments of the invention. | 08-09-2012 |
20120312024 | LATE LEAN INJECTION WITH ADJUSTABLE AIR SPLITS - A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, a turbine into which products of at least the combustion of the first fuel are receivable, a transition zone, including a second interior in which a second fuel and the products of the combustion of the first fuel are combustible, a plurality of fuel injectors which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages, a compressor, by which air is supplied to the first and second interiors for the combustion therein, and a control system configured to control relative amounts of the air to the first and second interiors and relative amounts of the first and second fuels supplied to the first and second interiors. | 12-13-2012 |
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 |
20130061593 | SYSTEM AND METHOD FOR CONTROLLING A COMBUSTOR ASSEMBLY - A system and method for controlling a combustor assembly are disclosed. The system includes a combustor assembly. The combustor assembly includes a combustor and a fuel nozzle assembly. The combustor includes a casing. The fuel nozzle assembly is positioned at least partially within the casing and includes a fuel nozzle. The fuel nozzle assembly further defines a head end. The system further includes a viewing device configured for capturing an image of at least a portion of the head end, and a processor communicatively coupled to the viewing device, the processor configured to compare the image to a standard image for the head end. | 03-14-2013 |
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 |
20130084534 | COMBUSTOR AND METHOD FOR SUPPLYING FUEL TO A COMBUSTOR - A combustor includes an end cap having upstream and downstream surfaces and a cap shield surrounding the upstream and downstream surfaces. First and second sets of premixer tubes extend from the upstream surface through the downstream surface. A first fuel conduit supplies fuel to the first set of premixer tubes. A casing circumferentially surrounds the cap shield to define an annular passage, and a second fuel conduit supplies fuel through the annular passage to the second set of premixer tubes. A method for supplying fuel to a combustor includes flowing a working fluid through first and second sets of premixer tubes, flowing a first fuel into the first set of premixer tubes, and flowing a second fuel through an annular passage surrounding the end cap and into the second set of premixer tubes. | 04-04-2013 |
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 |
20140137561 | SYSTEM AND METHOD FOR REDUCING MODAL COUPLING OF COMBUSTION DYNAMICS - A system for reducing modal coupling of combustion dynamics includes a plurality of combustors, and at least one fuel injector in each of the plurality of combustors. The system also includes structure for dithering a combustion instability frequency in at least one combustor in the plurality of combustors. A method for reducing modal coupling of combustion dynamics includes flowing a compressed working fluid at a temperature to a plurality of combustors and flowing a fuel to at least one fuel injector in each of the plurality of combustors. The method further includes dithering at least one of the temperature of the compressed working fluid flowing to the plurality of combustors or the fuel flow to the at least one fuel injector in at least one combustor in the plurality of combustors. | 05-22-2014 |
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 |
20140216048 | Variable Volume Combustor - The present application provides a variable volume combustor for use with a gas turbine engine. The variable volume combustor may include a liner, a number of micro-mixer fuel nozzles positioned within the liner, and a linear actuator so as to maneuver the micro-mixer fuel nozzles axially along the liner. | 08-07-2014 |
20140216051 | Variable Volume Combustor with an Air Bypass System - The present application provides a combustor for use with flow of fuel and a flow of air in a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles positioned within a liner and an air bypass system position about the liner. The air bypass system variably allows a bypass portion of the flow of air to bypass the micro-mixer fuel nozzles. | 08-07-2014 |