Entries |
Document | Title | Date |
20080229753 | METHODS AND APPARATUS TO FACILITATE DECREASING COMBUSTOR ACOUSTICS - A method for operating a gas turbine engine including a compressor and a combustor is provided. The method comprises channeling between about 0% to about 8% of the total airflow discharged from a compressor towards a pilot swirler coupled within the burner, wherein the burner includes a main swirler and an annular centerbody extending between the pilot and main swirlers, injecting a portion of the total fuel flow supplied to the burner through a plurality of apertures defined in a hollow pilot centerbody coupled within the pilot swirler, channeling the remaining airflow discharged from the compressor towards the main swirler, and injecting the remaining fuel flow supplied to the burner through at least one main swirler vane coupled within the main swirler, such that the portion of fuel is pre-mixed with a portion of the total airflow. | 09-25-2008 |
20080245075 | HOODED AIR/FUEL SWIRLER FOR A GAS TURBINE ENGINE - A gas turbine engine pilot assembly includes a swirler having high and low pressure sides. A hood at least partially encloses the swirler on the high pressure side. The hood is secured over the swirler, in one example. The hood includes an aperture creating a tortuous path from the high pressure side to the low pressure side through the swirler. The hood reduces the differential pressure across the swirler by reducing the velocity and pressure of the air before entering the swirler. In one example, the hood includes first and second spaced apart walls interconnected by a perimeter wall. The walls form a generally annular structure, in one example. At least one of the walls includes an array of apertures communicating with a cavity interiorly arranged within the walls upstream from the swirler. Air from the high pressure side flows through the apertures and is slowed before passing through the swirler and into a combustion chamber. | 10-09-2008 |
20080289341 | Combustor of Gas Turbine - A combustor | 11-27-2008 |
20090025394 | Method For Starting A Gas Turbine Equipped With A Gas Burner, And Axial Swirler For Said Burner - Method for starting a gas turbine equipped with a burner, which has an axial swirler for generating turbulence in a flow of comburent air, a secondary supply line of fuel gas, a main supply line of fuel gas arranged concentrically around the secondary line, and a pilot line of fuel gas; according to the method, the burner is ignited by firing a spark and feeding, towards said spark, comburent air and fuel gas which is synthesis gas | 01-29-2009 |
20090025395 | Swirler for Use in a Burner of a Gas Turbine Engine - Disclosed is a swirler for use in a burner of a gas turbine engine, the swirler comprising a plurality of vanes arranged in a circle, flow slots being defined between adjacent vanes in the circle, each flow slot having an inlet end and an outlet end, in use of the swirler a flow of fuel and air travelling along each flow slot from its inlet end to its outlet end such that the swirler provides a swirling mix of the fuel and air, at least one vane having an edge adjacent an inlet end of a flow slot configured to generate within the flow slot one or more flow vortices that extend along the slot thereby to enhance mixing of the fuel and air travelling along the slot. | 01-29-2009 |
20090031729 | FUEL INJECTION VALVE, COMBUSTOR USING THE FUEL INJECTION VALVE, AND FUEL INJECTION METHOD FOR THE FUEL INJECTION VALVE - A fuel injection valve is provided with a cylindrical injection valve main body in which one end is closed, and a fuel nozzle arranged on a center line of the main body and injecting a fuel. The main body has a plurality of air injection ports for injecting an air to an inner side in a tangential direction and forming a whirl flow in an inner portion in a circumferential direction of a cylinder portion of the main body, and the fuel nozzle has a fuel injection port injecting the fuel toward an inner peripheral surface of the main body. | 02-05-2009 |
20090038312 | MULTIPOINT INJECTOR FOR TURBOMACHINE - Multipoint injector for a turbomachine according to which any risk of fuel coking is eliminated. | 02-12-2009 |
20090049840 | OPTIMIZING AN ANTI-COKE FILM IN AN INJECTOR SYSTEM - The invention relates to the field of fuel injector systems. More particularly, the invention relates to an annular expansion ring centered on a main axis and suitable for being mounted on a fuel injector coaxial with said ring, the ring presenting holes that are distributed around said main axis and open out into its upstream face to enable air to pass towards the zone that is downstream from the ring. The ring includes a conical annular groove that converges downstream, that is open downstream, and that has the holes opening out into the upstream portion thereof, the axis of each of the holes making an angle relative to the main axis that is strictly greater than the angle between the generator line of the cone defining the annular groove and the main axis, such that the air exiting from the holes impacts against the inner wall of the annular groove, i.e. its wall that is closer to the main axis. | 02-26-2009 |
20090139242 | Burners for a gas-turbine engine - A burner for a gas-turbine engine has a frustoconical burner shell, at least two swirler arrangements, which are connected to the shell and are spaced apart around the circumference of the shell between its two ends, and a combustion chamber disposed downstream of a wider end of the shell. Each of the swirler arrangements includes an air swirler and a pre-combustion chamber disposed downstream of the air swirler, and a longitudinal axis of each swirler arrangement intersects a line parallel to, and spaced apart from, the longitudinal axis of the shell. The swirler arrangements are preferably connected to the shell at the same axial point. | 06-04-2009 |
20090158743 | Fuel distribution apparatus - A fuel distribution apparatus | 06-25-2009 |
20090255265 | SWIRLERS - A unitary swirler is disclosed, comprising a body having a swirler axis, and a plurality of vanes arranged in a circumferential direction around the swirler axis, wherein the swirler has a unitary construction. In one embodiment, the unitary swirler has a rim located coaxially with the swirler axis, and a wall extending between a portion of the rim and a portion of the hub. In another embodiment, the unitary swirler has an adaptor having a passage that is configured to direct a flow of air towards at least some of the plurality of vanes. | 10-15-2009 |
20090272117 | Burner - The invention relates to a burner, in particular a gas turbine burner, comprises: at least one swirler, the swirler having at least one air inlet opening, at least one air outlet opening positioned downstream to the air inlet opening and at least one swirler air passage extending from the at least one air inlet opening to the at least one air outlet opening which is delimited by swirler air passage walls, the air passage walls comprising downstream wall sections adjoining the at least one air outlet opening; and a fuel injection system which comprises fuel injection openings arranged in at least one swirler air passage wall so as to inject fuel into the swirler air passage; in which at least the downstream section of one air passage wall is corrugated. | 11-05-2009 |
20090277179 | SWIRLER PASSAGE AND BURNER FOR A GAS TURBINE ENGINE - A swirler passage is provided for mixing fuel and compressor air with at least two side walls; at least first and second conduits arranged inside at least one of the at least two side walls, the first conduit forming a fuel gas conduit and the second conduit forming an air conduit, the fuel gas conduit connected to a gas fuel supply and the air conduit connected to an air supply; a tube connected to the fuel gas conduit and entirely traversing the air conduit inside the side wall; a fluid passage connected to the air conduit and surrounding the tube; at least one fuel outlet opening of the tube arranged on the side wall; and at least one air outlet opening of the fluid passage arranged on the side wall and surrounding the fuel outlet opening. | 11-12-2009 |
20090301092 | Burners for a gas turbine engine - A burner for a gas-turbine engine including a swirler and a combustion chamber is provided. The swirler includes a plurality of vanes arranged in a circle, each adjacent pair of vanes defining a flow slot for the flow of air and fuel into the swirler, the air and fuel is mixed and supplied in swirling form to the combustion chamber. The swirler can also include a partitioning device which divides the flow of air along each flow slot into two air flows. One side of the partitioning device has a fuel-supply port for supplying fuel to one of the two air flows. The relevant air flow causes fuel supplied to the fuel-supply port to form a film of fuel over the relevant side of the partitioning device. The film leaves the relevant side of the partitioning device in a region of high shear between adjacent flows in the burner. | 12-10-2009 |
20090320484 | METHODS AND SYSTEMS TO FACILITATE REDUCING FLASHBACK/FLAME HOLDING IN COMBUSTION SYSTEMS - A method for assembling a premixing injector is provided. The method includes providing a centerbody including a center axis and a radially outer surface, and providing an inlet flow conditioner. The inlet flow conditioner includes a radially outer wall, a radially inner wall, and an end wall coupled substantially perpendicularly between the outer wall and the inner wall. Each of the outer wall and the end wall include a plurality of openings defined therein. The outer wall, the inner wall, and the end wall define a first passage therebetween. The method also includes coupling the inlet flow conditioner to the centerbody such that the inlet flow conditioner substantially circumscribes the centerbody, such that the inner wall is substantially parallel to the centerbody outer surface, and such that a second passage is defined between the centerbody outer surface and the inner wall. | 12-31-2009 |
20090320485 | Swirler for Use in a Burner of a Gas Turbine Engine - Disclosed is a swirler for use in a burner of a gas turbine engine, the swirler comprising a pluralkity of vanes arranged in a circle, flow slots being defined between adjacent vanes in a circle, each flow slot having an inlet end and an outlet end, in use of the swirler a flow of air and fuel traveling along each flow slot fom its inlet end to its outlet end such that the swirler provides a swirling mix of the air and fuel, at least one vane being configured to generate a flow vortex that extends from an edge of the vane adjacent an outlet end of a flow slot to within the swirling mix thereby to improve the mix of air and fuel in the swirling mix. | 12-31-2009 |
20100011772 | FUEL INJECTION SYSTEM - A fuel injection system is provided for a gas turbine, comprising a mains airblast fuel injector having an annular shape, and inner and outer mains swirlers for swirling air past the mains airblast fuel injector. The inner and outer mains swirlers are concentric with the mains airblast fuel injector and are located radially inwardly and radially outwardly of the mains airblast fuel injector, respectively. The mains airblast fuel injector and the inner and outer mains swirlers are so arranged as to produce a fuel spray stream which expands from the mains airblast fuel injector and has a double flame front. The double flame front comprises flame fronts on both the radially inner and radially outer surfaces of the fuel spray stream. | 01-21-2010 |
20100024427 | PRECISION COUNTER-SWIRL COMBUSTOR - A precision counter-swirl combustor that includes an annular combustor having a forward end, an aft end opposite the forward end, and an interior. The aft end being proximal to a gas turbine. The combustor further includes a fuel inlet and swirler operatively connected to the forward end and at least one air inlet. The air inlet is equipped with a chute that extends into the interior of said combustor. The combustor is secured to a fixed structure proximate the forward end of the combustor. | 02-04-2010 |
20100050647 | Swirler for a fuel injector - A swirler is provided for a fuel injector of a combustor of a gas turbine engine. The swirler is for directing an airflow into the combustor so as to atomise fuel exiting the fuel injector. The swirler has one or more passages for channelling the airflow. Each of the passages is configured to rotate the airflow channelled by that passage about a swirl axis of the swirler, such that on exiting the passage the airflow has an exit swirl angle and a direction of rotation relative to the swirl axis. The swirler is configured such that the exit swirl angle and/or the direction of rotation may be selectively varied. | 03-04-2010 |
20100050648 | COMBUSTOR AND THE METHOD OF FUEL SUPPLY AND CONVERTING FUEL NOZZLE - An object of this invention is to accelerate further mixing of a fuel and air independently of a flow rate of the fuel. | 03-04-2010 |
20100058767 | SWIRL ANGLE OF SECONDARY FUEL NOZZLE FOR TURBOMACHINE COMBUSTOR - A combustor includes a primary combustion chamber and a secondary combustion chamber, one or more primary nozzles disposed in the primary combustion chamber and providing fuel to the primary combustion chamber, a centerbody assembly, a venturi disposed downstream of the centerbody assembly, and a secondary fuel nozzle housed within the centerbody assembly and extending towards the venturi and providing fuel to the secondary combustion chamber. The secondary fuel nozzle includes a fuel passage and an air passage, and a swirler positioned around the fuel passage and having one or more vanes projecting radially within the air passage, each vane having a trailing edge arranged at a swirl angle relative to a longitudinal axis of the secondary fuel nozzle, the swirl angle is greater than 45°. | 03-11-2010 |
20100071378 | Alternately Swirling Mains in Lean Premixed Gas Turbine Combustors - A gas turbine combustor for producing hot gas by burning a fuel in compressed air comprising a combustor central axis and multiple main swirlers with respective swirler axes disposed about and parallel to the combustor central axis, each main swirler delivering an air fuel mixture flowing through it and about its swirler axis, wherein each swirler imparts rotation to the air fuel mixture flowing through it in a direction opposite that of adjacent swirlers. This combustor configuration reduces shear where the outer edges of adjacent flows meet, allowing for greater tuning of the combustion chamber and reduced NOx and CO emissions. | 03-25-2010 |
20100083663 | SYSTEM AND METHOD FOR AIR-FUEL MIXING IN GAS TURBINES - A system, in certain embodiments, includes includes a fuel nozzle for a turbine engine that includes a tapered central body located at an interior base of the fuel nozzle, an air swirler, and a fuel port in the tapered central body, separate from the air swirler. | 04-08-2010 |
20100107643 | TRIPLE SWIRL GAS TURBINE COMBUSTOR - Disclosed is a triple swirl gas turbine combustor using various fuels such as coal gas, DiMethyl Ether, and waste gas generated in an ironworks in a gas turbine. The triple swirl gas turbine combustor combusts three different fuels simultaneously or individually and various fuels such as LCV gas and HCV gas so that fuel flexibility can be improved. Swirl generated in a second swirler of the triple swirler is reversely jetted to increase a mixing degree of a fuel-air mixture and an intensity of a turbulent flow so that combustion efficiency can be increased, harmful exhaust gas can be reduced and vibration can be reduced. | 05-06-2010 |
20100107644 | COMBUSTION PRE-CHAMBER - A combustion pre-chamber including an upstream end and a downstream end is provided. The combustion pre-chamber includes a transition channel formed by a wall, the wall extending between the upstream end and the downstream end, and at least one flow trip arranged on the wall and tapering in height and width to the downstream end. Also provided are a burner assembly including a combustion pre-chamber, and a gas turbine engine. | 05-06-2010 |
20100115957 | Combustion Chamber for A Compact Lightweight Turbine - A turbine combustion chamber is provided with deflectors on the cold side generating vortices in a secondary gas flow into the chamber, thereby confining the flame front under variable operating conditions and cooling the chamber wall. | 05-13-2010 |
20100126176 | Dual swirler - A swirler arrangement for injecting a fluid into a tubular swirling chamber is provided. The swirler arrangement includes a first radial swirler device and a second radial swirler device. The swirler arrangement is fixed around an internal circulation zone of the tubular swirling chamber. The first radial swirler device includes first vanes, wherein the first vanes are formed to inject the fluid into the internal circulation zone with a first injecting angle. The second radial swirler device includes second vanes, wherein the second vanes are formed to inject the fluid into the internal circulation zone with a second injecting angle. The first injecting angle and the second injecting angle are defined by an angle between an injecting direction of the fluid and the tangential direction along the inner surface. A method of injecting a fluid into a tubular swirling chamber by the swirler arrangement is also provided. | 05-27-2010 |
20100132364 | FUEL NOZZLE DETACHABLE BURNER TUBE - A fuel nozzle for use with a combustion chamber defined within a gas turbine engine and a method for assembling the same are provided. The fuel nozzle includes a swirler assembly and a burner tube that is coupled to a support flange in a detachable manner such that an inner surface of the burner tube circumscribes an outer surface of the swirler assembly during fuel nozzle operation. | 06-03-2010 |
20100154426 | COMBUSTOR LINER WITH REVERSE FLOW FOR GAS TURBINE ENGINE - A combustor liner ( | 06-24-2010 |
20100162713 | COOLED FLAMEHOLDER SWIRL CUP - A combustor swirl cup includes coaxial inner and outer swirlers separated by a tubular centerbody. The centerbody includes a bypass inlet surrounding the inner swirler and diverges aft along a perforate inner nozzle to terminate at an annular flameholder. An impingement ring is spaced forward from the flameholder in flow communication with the bypass inlet for receiving cooling air therefrom to impingement cool the flameholder. | 07-01-2010 |
20100162714 | FUEL NOZZLE WITH SWIRLER VANES - A fuel nozzle for a gas turbine engine is provided having swirlers and a mounting device configured to mount the fuel nozzle to the inside of a combustor. In one embodiment the combustor has an interior surface formed to receive the mounting device of the fuel nozzle from within the combustor. The swirlers can be integrally formed in the fuel nozzle or can be separately attached, thus allowing the fuel nozzle to be mounted within the combustor having the relative placement of the swirlers already determined prior to installation. The fuel nozzle tip can be positioned a predetermined distance from the outlet of a swirler to reduce NOx emissions. | 07-01-2010 |
20100170255 | METHODS AND SYSTEMS TO ENHANCE FLAME HOLDING IN A GAS TURBINE ENGINE - A fuel nozzle including a swirler assembly that includes a shroud, a hub, and a plurality of vanes extending between the shroud and the hub. Each vane includes a pressure sidewall and an opposite suction sidewall coupled to the pressure sidewall at a leading edge and at a trailing edge. At least one suction side fuel injection orifice is formed adjacent to the leading edge and extends from a first fuel supply passage to the suction sidewall. A fuel injection angle is oriented with respect to the suction sidewall. The suction side fuel injection orifice is configured to discharge fuel outward from the suction sidewall. At least one pressure side fuel injection orifice extends from a second fuel supply passage to the pressure sidewall and is substantially parallel to the trailing edge. The pressure side fuel injection orifice is configured to discharge fuel tangentially from the trailing edge. | 07-08-2010 |
20100175382 | GAS TURBINE BURNER - The burner ( | 07-15-2010 |
20100205971 | Fuel nozzle having aerodynamically shaped helical turning vanes - A fuel nozzle for a gas turbine engine is disclosed which includes a nozzle body having a longitudinal axis, an elongated annular air passage defined within the nozzle body, and a plurality of circumferentially spaced apart axially extending swirl vanes disposed within the annular air passage, wherein each swirl vane has multiple joined leads and a variable thickness along the axial extent thereof. | 08-19-2010 |
20100242483 | COMBUSTOR FOR GAS TURBINE ENGINE - A gas turbine engine has a combustor module including an annular combustor having a liner assembly that defines an annular combustion chamber. The liner assembly includes an inner liner and an outer liner that circumscribes the inner liner. The inner liner has a plurality of first combustion air admission holes passing therethrough and the second liner has a plurality of second combustion air admission holes passing therethrough. Each of the first and the second combustion air admission holes has a swirler disposed therein. | 09-30-2010 |
20100242484 | APPARATUS AND METHOD FOR COOLING GAS TURBINE ENGINE COMBUSTORS - An apparatus and method fabricating a deflector-flare cone for a combustor is provided. The combustor includes an air swirler annular about a centerline axis of the combustor wherein the swirler includes an annular exit downstream of the swirler. The deflector-flare cone includes a single annular body including an engagement end configured to support the deflector-flare cone, an annular divergent portion extending downstream from the engagement end. The annular divergent portion includes a radially outer annular deflector portion and a radially inner annular flare cone portion that are separated by an annular gap extending between the deflector portion and the flare cone portion. The deflector-flare cone includes a plurality of cooling passages extending through the single annular body of the deflector-flare cone. The plurality of cooling passages are spaced circumferentially about the centerline axis and are configured to be coupled in flow communication with a cooling fluid source. | 09-30-2010 |
20100263383 | GAS TURBINE PREMIXER WITH INTERNAL COOLING - A system that includes a turbine fuel nozzle comprising an air-fuel premixer. The air-fuel premixed includes a swirl vane configured to swirl fuel and air in a downstream direction, wherein the swirl vane comprises an internal coolant path from a downstream end portion in an upstream direction through a substantial length of the swirl vane. | 10-21-2010 |
20100269507 | RADIAL LEAN DIRECT INJECTION BURNER - A burner for use in a gas turbine engine includes a burner tube having an inlet end and an outlet end; a plurality of air passages extending axially in the burner tube configured to convey air flows from the inlet end to the outlet end; a plurality of fuel passages extending axially along the burner tube and spaced around the plurality of air passage configured to convey fuel from the inlet end to the outlet end; and a radial air swirler provided at the outlet end configured to direct the air flows radially toward the outlet end and impart swirl to the air flows. The radial air swirler includes a plurality of vanes to direct and swirl the air flows and an end plate. The end plate includes a plurality of fuel injection holes to inject the fuel radially into the swirling air flows. A method of mixing air and fuel in a burner of a gas turbine is also provided. The burner includes a burner tube including an inlet end, an outlet end, a plurality of axial air passages, and a plurality of axial fuel passages. The method includes introducing an air flow into the air passages at the inlet end; introducing a fuel into fuel passages; swirling the air flow at the outlet end; and radially injecting the fuel into the swirling air flow. | 10-28-2010 |
20100269508 | COMBUSTION BURNER - A combustion burner | 10-28-2010 |
20100275604 | HIGH VOLUME FUEL NOZZLES FOR A TURBINE ENGINE - A fuel nozzle for a turbine engine is configured to deliver a large volume of a fuel which has a relatively low amount of energy per unit volume. The fuel nozzle includes a fuel swirler plate having fuel delivery apertures which are angled with respect to the flat surfaces of the swirler plate. A nozzle cap covers the end of the fuel nozzle to create a swirl chamber at the outlet end. The nozzle cap may include a plurality of air inlet apertures to allow the air to enter the swirl chamber. | 11-04-2010 |
20100275605 | Gas-Turbine Burner - A gas-turbine burner having a plurality of main swirl generators, each having an inlet flow opening formed by the main swirl generator edge, is provided. In order to achieve a uniform flow of combustion air through the main swirl generator, the gas-turbine burner has an inlet-flow guide means with a flow guide surface which runs from one of the inlet-flow openings to an adjacent inlet-flow opening, to which the main swirl generator edges which form the inlet-flow openings are connected, and the flow guide surface widens from there radially upwards. The main swirl generators are central-symmetrically arranged around a pilot burner and the flow guide surface runs radially outside the main swirl generators. | 11-04-2010 |
20100281872 | Airblown Syngas Fuel Nozzle With Diluent Openings - A fuel nozzle tip for use with a combustor and a method of assembling the fuel nozzle tip are provided. The fuel nozzle tip includes a fuel tube and an air collar coupled to the fuel tube. The fuel tube includes a first plurality of circumferentially-spaced fuel openings and a second plurality of circumferentially-spaced fuel openings. The fuel tube is configured to channel fuel into a mixing zone defined within the combustor. The air collar includes a plurality of circumferentially-spaced air openings configured to discharge air into the mixing zone. At least one of the plurality of air openings is oriented to facilitate generating a swirl number of greater than 0.6 within the mixing zone. | 11-11-2010 |
20100287939 | Flameless combustion systems for gas turbine engines - A flameless burner for a gas turbine engine includes a burner body having a longitudinal axis, an upstream section and a downstream section. The upstream section of the burner body defines a primary swirl generating chamber having air swirlers associated therewith. The primary swirl generating chamber is adapted and configured to receive compressor discharge air through the air swirlers. The strong swirl of the compressor discharge air forms a recirculation zone that entrains combustion product gases toward the burner body. Fuel injectors are operatively connected to the downstream section of the burner body for issuing fuel into the recirculated combustion product gases. | 11-18-2010 |
20100287940 | Burner of a gas turbine - The burner ( | 11-18-2010 |
20100293956 | TURBINE FUEL NOZZLE HAVING PREMIXER WITH AUXILIARY VANE - A fuel nozzle auxiliary vane comprising a vane mountable base comprising a fuel inlet, wherein the vane mountable base is configured to mount to a surface of a main vane disposed in an airflow path of a fuel nozzle. The fuel nozzle auxiliary vane also includes a body extending from the vane mountable base, wherein the body comprises a fuel passage that turns from the fuel inlet to a fuel outlet, and the fuel outlet has a fuel outlet direction generally crosswise to a fuel inlet direction through the fuel inlet. | 11-25-2010 |
20100307160 | Convex Pilot Cone - A gas turbine combustor is provided. The gas turbine combustor has a pilot nozzle having a pilot fuel injection port at a downstream end, in terms of the direction flow of a fuel, and lies on the axial centreline of the gas turbine combustor. It also has a main combustion zone, downstream of the pilot nozzle, and a pilot cone projecting from the vicinity of the pilot fuel injection port and having a diverged end adjacent to the main combustion zone, wherein a half angle of the pilot cone is increasing in the downstream direction. | 12-09-2010 |
20100307161 | FLEXURE SEAL FOR FUEL INJECTION NOZZLE - A nozzle includes an inlet at an upstream end of the nozzle, a discharge outlet at a downstream end of the nozzle, and a fluid delivery passage extending between the inlet and the discharge outlet. Exterior and interior walls of the nozzle have downstream tip ends that are relatively longitudinally movable at one or more interfaces. An internal insulating gap is interposed between the interior and exterior walls to insulate fuel from ambient temperature conditions exterior to the nozzle. One or more flexible seal structures internal to the nozzle isolate a portion of the insulating gap from any ambient fluid entering into the gap through the one or more interfaces while providing relative movement between interior and exterior walls of the nozzle. | 12-09-2010 |
20100313570 | GAS TURBINE COMBUSTOR - A gas turbine combustor is provided which can accomplish stable high-load combustion, high combustion efficiency, a low concentration of CO, and NOx in a small-sized combustion chamber. The gas turbine combustor includes an inner liner | 12-16-2010 |
20100319350 | Flashback Resistant Fuel Injection System - A fuel injector assembly includes a fuel injector that provides fuel to be mixed with air for ignition in a combustor. The fuel injector assembly includes a fuel shroud and a plurality of spanning members. The spanning members are spaced circumferentially on the fuel shroud between the fuel shroud and a base plate assembly, which supports the fuel injector assembly within the combustor. The spanning members space the fuel shroud from the base plate assembly such that an annular gap is formed therebetween. The gap permits a flow of purge air therethrough to be mixed with compressed air entering the fuel shroud and with fuel provided by the fuel injector. The spanning members comprise elongate members having upstream ends that are circumferentially offset from opposed downstream ends so that the spanning members provide tangential velocity to the purge air flowing through the annular gap. | 12-23-2010 |
20100319351 | GAS TURBINE COMBUSTOR - Provided is a gas turbine combustor capable of reducing the size of a low-temperature air layer of pilot air formed between a pilot flame and a premixed flame and of improving the flame stability of the premixed flame. A gas turbine combustor, which is provided with a pilot burner that is provided at the center portion of a combustor main body formed in a cylindrical shape to form a pilot flame, and a plurality of main burners arranged so as to surround the outer periphery of the pilot burner to form a premixed flame, includes, as the ignition improving part, a channel blocking member that reduces the size of the low-temperature air layer of the pilot air formed between the pilot flame and the premixed flame. | 12-23-2010 |
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 |
20100326080 | Acoustically Tuned Combustion for a Gas Turbine Engine - A fuel nozzle for a turbine engine has a central body member with a pilot, a surrounding barrel housing, a mixing duct and an air inlet duct. The fuel nozzle additionally has a main fuel injection device located between the air inlet duct and the mixing duct. The main fuel injection device is configured to introduce a flow of fuel into the barrel member to create a fuel/air mixture which is then premixed with a swirler. The fuel/air mixture then further mixes in the mixing duct and exits the nozzle into a combustor for combustion. The geometry of the fuel nozzle ensures that pressure waves from the combustor do not create a time varying fuel to air equivalence ratio in the flow through the nozzle that achieves a resonance with the pressure waves. | 12-30-2010 |
20110000216 | Gas turbine combustor - This invention provides a gas turbine combustor, which can enable only a swirler and a heat shield to be readily taken out from the combustor upon the exchange the swirler and the heat shield. The gas turbine combustor ( | 01-06-2011 |
20110005232 | AERODYNAMIC SWEPT VANES FOR FUEL INJECTORS - A fuel nozzle for a gas turbine engine includes a nozzle body having a longitudinal axis. An elongated annular air passage is defined within the nozzle body. A plurality of circumferentially spaced apart axially extending swirl vanes is disposed within the annular air passage. Each swirl vane has an axially swept cross-sectional profile along the radial extent thereof. | 01-13-2011 |
20110016868 | FUEL SPRAYING APPARATUS OF GAS TURBINE ENGINE - A fuel spraying apparatus of a gas turbine engine includes a first fuel spraying section configured to spray fuel for diffusion combustion and a second fuel spraying section configured to spray fuel for premixed combustion. The second fuel spraying section is disposed so as to surround the first fuel spraying section. The apparatus further includes an air curtain generating section disposed between the first fuel spraying section and the second fuel spraying section. The air curtain generating section is configured to generate an air curtain which defines an outer edge of a diffusion combustion area in a combustion chamber. | 01-27-2011 |
20110030376 | Gas injection in a burner - A burner including a gas injector for injecting fuel into the burner for a gas turbine engine is provided. The burner is provided with a quarl, which surrounds a combustion room, at least a first channel emerging into the combustion room for providing the combustion room with air mixed with fuel, a swirler for mixing the air and the fuel located at the inlet of the channel, at least one tube for the provision of fuel at an inlet of at least one channel, wherein the tube is provided with a plurality of diffuser holes distributed along the tube acting as gas injectors for effectively distributing fuel in a flow of air passing through the channel. | 02-10-2011 |
20110048023 | FUEL NOZZLE SWIRLER ASSEMBLY - A fuel nozzle air swirler assembly has a slotted cap to provide stress-relief. The stress-relief slits in the cap have an axial and a tangential component to impart a swirl to the air leaking therethrough in the same direction as that of the air exiting the swirler body. | 03-03-2011 |
20110072825 | AIR BLAST FUEL INJECTOR - An airblast fuel injector for the combustor of a gas turbine engine has, in order from radially inner to outer, a coaxial arrangement of an inner swirler passage, an annular fuel passage, an annular mid swirler passage, and an annular outer swirler passage. The fuel passage extends to a prefilming lip, and the inner and mid swirler passages swirl air past the prefilming lip so that fuel fed from the fuel passage to the prefilming lip is entrained by the swirling air into a fuel spray stream. The outer swirler passage has a convergent portion. The radially inward wall of said convergent portion is defined by a frustoconical separator element which separates the outer swirler passage from the mid swirler passage, the separator element converging in the direction of air flow to terminate in a lip at the mouths of the mid swirler passage and the outer swirler passage. | 03-31-2011 |
20110079014 | BURNER ARRANGEMENT, AND USE OF SUCH A BURNER ARRANGEMENT - A burner arrangement includes a tubular mixing tube extending along an axis and configured to mix fuel and air, the mixing tube opening into a combustion chamber in a direction of flow; and a film air ring disposed in the mixing tube and arranged concentrically to the axis, the film air ring configured to prevent a backfiring of the fuel disposed in the mixing tube and to generate or reinforce an air film near the wall, wherein the film air ring has at least one annular gap concentric to the axis and configured to inject air. | 04-07-2011 |
20110154825 | GAS TURBINE ENGINE HAVING DOME PANEL ASSEMBLY WITH BIFURCATED SWIRLER FLOW - Embodiments of the present invention include a unique gas turbine engine and a unique dome panel assembly for a gas turbine engine combustor. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines, gas turbine engine combustor systems and dome panel assemblies for gas turbine engine combustion system. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith. | 06-30-2011 |
20110162377 | TURBOMACHINE NOZZLE - A turbomachine includes a compressor, a turbine, a combustor operatively coupled to the compressor and the turbine, and an injection nozzle assembly mounted in the combustor. The injection nozzle assembly includes a swirler member provided with a hub portion having an internal surface. The injection nozzle assembly also includes a nozzle section, and a nozzle tip member fluidly coupled to the nozzle section and the swirler member. The nozzle tip member includes a body having a first end section that extends from the nozzle section to a second end section arranged in the hub portion of the swirler member. The nozzle tip member includes an external surface, and a discharge port. At least one of the external surface of the nozzle tip member and the internal surface of the swirler member hub portion is provided with a plurality of grooves. | 07-07-2011 |
20110232289 | Fuel Nozzle - A fuel nozzle including a nozzle tube and a nozzle outlet opening is provided. The nozzle tube is connected to a fuel feed line for feeding a fuel to the nozzle tube, wherein the fuel is fed from the nozzle outlet opening to an annular air stream surrounding the fuel nozzle, wherein a first nozzle tube section that extends up to the nozzle outlet opening is designed in a floral pattern in such a way that the fuel may be fed substantially coaxially into the air stream. | 09-29-2011 |
20110271683 | TURBOMACHINE INJECTION NOZZLE ASSEMBLY - A turbomachine includes a compressor, a turbine, a combustor operatively coupled to the compressor and the turbine, and an injection nozzle assembly mounted in the combustor. The injection nozzle assembly includes a swirler member for conditioning a fluid flow passing through the injection nozzle assembly. The swirler member includes a hub portion, a plurality of vanes that extend from the hub portion, and at least one flow conditioning band. The at least one flow conditioning band extends about the hub portion and between the plurality of vanes to provide a localized flow impediment within the injection nozzle assembly. | 11-10-2011 |
20120023951 | FUEL NOZZLE WITH AIR ADMISSION SHROUD - A fuel nozzle for a turbine engine includes an air admission shroud which admits a flow of air from an exterior of the fuel nozzle into an interior of the fuel nozzle at a position along the length of the fuel nozzle. A plurality of air admission apertures in the air admission shroud could be arranged to cause the air being admitted into the interior of the fuel nozzle to swirl around the interior of the fuel nozzle in a rotational fashion. If the fuel nozzle also includes swirler vanes located upstream of the air admission shroud, which also induce air within the fuel nozzle to swirl around the interior of the fuel nozzle in a rotational fashion, then the air admission apertures of the air admission shroud preferably cause the air admitted through the air admission shroud to swirl in a rotational direction which is opposite to the swirl induced by the swirler vanes. This helps to better mix the air and the fuel within the nozzle. | 02-02-2012 |
20120023952 | FUEL NOZZLE AND ASSEMBLY AND GAS TURBINE COMPRISING THE SAME - A nozzle for assemblies and gas turbines is provided. The nozzle exhibits destabilized flame holding characteristics, i.e., the nozzle is unable to stabilize flame up to an equivalence ratio of about 0.65. As a result, flame heat release is delayed resulting in lower peak flame temperatures and correspondingly lower NOx levels. Flame stabilization capability is retained for higher equivalence ratios to support operation of the combustor in other regions of the load range. | 02-02-2012 |
20120073302 | FUEL NOZZLE ASSEMBLY FOR GAS TURBINE SYSTEM - A fuel nozzle assembly is disclosed. The fuel nozzle assembly comprises an outer burner tube and an inner burner tube defining a pre-mixing annulus therebetween. The fuel nozzle assembly further comprises a swirler assembly, the swirler assembly comprising a plurality of swirler vanes disposed in an annular array about the inner burner tube and configured to interact with primary air upstream of the pre-mixing annulus. The fuel nozzle assembly further comprises an air injection feature configured to flow secondary air into the pre-mixing annulus downstream of the swirler assembly such that the secondary air flows in a generally linear path longitudinally with respect to the pre-mixing annulus and adjacent at least one of the outer burner tube and the inner burner tube. | 03-29-2012 |
20120096867 | Semi-Tubular Vane Air Swirler - A semi-tubular vane air swirler is provided. In one embodiment the air swirler is a deep drawn sheet metal component having a first and a second set of semi-tubular vanes formed therein. In one embodiment the semi-tubular air vanes include a first and a second portion formed by upsetting the sheet metal in opposing directions to create mirrored vane geometry, thereby doubling the open area of the vane. | 04-26-2012 |
20120137696 | AIR-STAGED DIFFUSION NOZZLE - In an air-staged diffusion nozzle for a gas turbine combustor, air is mixed with the gas fuel and expanded in a downstream burner tube. Introduction of air, passing downstream from the tip of the nozzle to the burner tube space forces hot gases away from and cools the nozzle tip. Air flow through an inner swirler or through cooling holes on the nozzle tip may be arranged to establish a cooling flow volume and direction that advantageously interacts with gas fuel-air flow from an outer swirler to improve fuel-air mixing in the burner tube, helping to reduce emissions and soot formation. | 06-07-2012 |
20120186258 | MIXER ASSEMBLY FOR A GAS TURBINE ENGINE - A mixer assembly for a gas turbine engine is provided, including a main mixer, and a pilot mixer having an annular housing in which a corner is formed between an aft portion of the housing and a bulkhead wall in which a corner recirculation zone is located to stabilize and anchor the flame of the pilot mixer. The pilot mixer can further include features to cool the annular housing, including in the area of the corner recirculation zone. | 07-26-2012 |
20120186259 | FUEL INJECTOR ASSEMBLY - A fuel injector assembly for a combustor is provided, including a fuel nozzle having an axial inflow swirler and one or more radial inflow swirlers spaced radially outward of the downstream end of the fuel nozzle and mounted to the combustor, wherein the airstreams produced by the swirlers airblast atomize fuel films produced by the fuel nozzle. | 07-26-2012 |
20130047619 | INJECTION NOZZLE ASSEMBLY FOR A GAS TURBOMACHINE - An injection nozzle assembly includes a nozzle body having an outer surface and an inner surface that defines a flow passage, and a center body arranged within the nozzle body and extending along the flow passage. The center body includes a first end that extends to a tip portion through an intermediate portion that defines a fluid passage. The intermediate portion includes a first outer dimension and the tip portion includes a second outer dimension that is distinct from the first outer dimension. The center body includes a plurality of grooves that extend axially along the tip portion. | 02-28-2013 |
20130047620 | CONICAL SWIRLER FOR FUEL INJECTORS AND COMBUSTOR DOMES AND METHODS OF MANUFACTURING THE SAME - A method of manufacturing gas and/or fuel swirlers for fuel injectors and combustor domes and cone-shaped swirlers so manufactured are disclosed. The disclosed conical swirlers feature cut-through slots on a cone-shaped body. The contour and spacing of the slots are configured and arranged to accommodate a wide range of requirements for fluid flow areas and swirl strengths. Preferably, the cone-shaped swirlers can be manufactured by wire EDM processing. More preferably, multiple cone-shaped swirlers can be manufactured simultaneously by nesting wirier blanks in a stack and wire EDM processing the stack as a unit. The cone-shaped pinwheel swirler fits well into various fuel injector heads, enabling the injectors to reduce the frontal surface area and flat area for minimal potential of carbon formation. | 02-28-2013 |
20130269351 | MICROMIXER ASSEMBLY OF A TURBINE SYSTEM AND METHOD OF ASSEMBLY - A micromixer assembly of a turbine system includes a plate having at least one aperture comprising a receiving diameter. Also included is at least one tube having an inlet and an outlet for receiving a flow and dispersing the flow to a combustor, wherein the at least one tube includes an inner diameter and an outer diameter, wherein the outer diameter is configured to fit within the receiving diameter of the at least one aperture, wherein the at least one tube is operably coupled at a location on the outer diameter to the receiving diameter of the at least one aperture by exerting a radial force on the inner diameter of the tube. | 10-17-2013 |
20130269352 | GAS-TURBINE BURNER - A gas-turbine burner having a plurality of main swirl generators which each have an inlet flow opening formed by the main swirl generator edge is provided. In order to achieve a uniform flow of combustion air through the main swirl generator, the gas-turbine burner has an inlet-flow guide means with a flow guide surface which runs from one of the inlet-flow openings to an adjacent inlet-flow opening, to which the main swirl generator edges which form the inlet-flow openings are connected, and the flow guide surface widens from there radially upwards. The main swirl generators are central-symmetrically arranged around a pilot burner and the flow guide surface runs radially outside the main swirl generators. | 10-17-2013 |
20130283805 | FUEL/AIR PREMIXING SYSTEM FOR TURBINE ENGINE - A system includes a fuel nozzle. The fuel nozzle includes a center body configured to receive a first portion of air and to deliver the air to a combustion region. The fuel nozzle also includes a swirler configured to receive a second portion of air and to deliver the air to the combustion region. The swirler includes an outer shroud wall, an inner hub wall, and a swirl vane. The swirl vane includes a radial swirl profile at a downstream edge of the swirl vane. The radial swirl profile includes a region extending from the outer shroud wall to a first transition point and a second region extending from the transition point to the inner hub wall. At least one of the first and second regions is substantially straight and at least one of the first and second regions is arcuate. | 10-31-2013 |
20140000263 | MULTI-PREMIXER FUEL NOZZLE SUPPORT SYSTEM | 01-02-2014 |
20140000264 | COMBUSTION BURNER | 01-02-2014 |
20140013764 | AXIAL SWIRLER FOR A GAS TURBINE BURNER - An axial swirler for a gas turbine burner includes a vane ring with a plurality of swirler vanes circumferentially distributed around a swirler axis. Each of the swirler vanes includes a trailing edge. In order to achieve a controlled distribution of the exit flow velocity profile and/or the fuel equivalence ratio in the radial direction. The trailing edge is discontinuous with the trailing edge having a discontinuity at a predetermined radius. | 01-16-2014 |
20140026580 | COMBUSTOR DOME AND HEAT-SHIELD ASSEMBLY - A combustor dome and heat-shield assembly comprises a heat-shield having a first opening therethrough. A swirler extends through the first opening and captures the heat-shield. A dome having a second opening therethrough and has an upstream side and a downstream side. The swirler extends through the second opening from the downstream side to the upstream side to capture the heat-shield on the downstream side, and a retaining clip engages the swirler to secure the swirler and the heat-shield on the dome. | 01-30-2014 |
20140060060 | BURNER ARRANGEMENT - The invention refers to burner arrangement for producing hot gases to be expanded in a gas turbine, including a burner inside a plenum, where the burner has means for fuel injection, means for air supply and means for generating an ignitable fuel/air mixture inside the burner, and a combustion chamber following downstream said burner having an outlet being fluidly connected to the gas turbine. The invention is characterized in that the means for air supply includes at least two separate flow passages, and that the one of the two flow passages is fed by a first supply pressure and the other flow passage is fed by a second supply pressure. | 03-06-2014 |
20140123655 | SWIRLER FOR GAS TURBINE ENGINE FUEL INJECTOR - A swirler for a gas turbine engine fuel injector comprises a swirler body extending from an upstream end to a downstream end. A fuel injector extends into the body, and has a downstream end for injecting fuel in a downstream direction. A first flow path directs air in a first circumferential direction about a central axis of the swirler body. A second flow path directs air to intermix with the air in the first flow path, and then to mix with fuel injected by the fuel injector. The first and second flow paths are positioned to inject air upstream of the downstream end of the fuel injector where fuel is injected. The first flow path is provided in a greater volume than the volume provided in the second flow path. The second flow path directs air at a location downstream of the first flow path. | 05-08-2014 |
20140245742 | AIR SWIRLERS - A swirler, such as for swirling air in a fuel injector of a gas turbine engine, includes a swirler body with opposed inlet and outlet ends with a swirler wall extending therebetween along a longitudinal axis. The inlet end of the swirler body defines an inlet opening. A plurality of swirl slots is defined through a portion of the swirler wall that converges toward the longitudinal axis in a direction from the inlet opening toward the outlet end of the swirler body. The swirl slots are radially off-set with respect to the longitudinal axis for imparting swirl on a flow passing from the inlet opening, through the swirl slots, and past the outlet end of the swirler body. | 09-04-2014 |
20140331679 | COMBUSTION BURNER - A combustion burner including a fuel nozzle, a burner tube that surrounds the fuel nozzle to form an air passage between the burner tube and the fuel nozzle, swirler vanes that are arranged in a circumferential direction on an external circumferential surface of the fuel nozzle, a liquid fuel injecting hole that is formed on the fuel nozzle, and from which a liquid fuel is injected to a vane pressure surface of each of the swirler vanes, and a cooling unit that cools a part of the vane pressure surface on which the liquid fuel hits. The cooling unit includes a multi-purpose injecting hole that is arranged on the vane pressure surface of each of the swirler vanes, and from which a gas fuel is injected during gas combustion, and water is injected to the vane pressure surface of the swirler vane during combustion of the liquid fuel. | 11-13-2014 |
20140331680 | COMBUSTION BURNER - A combustion burner including a fuel nozzle, a burner tube that surrounds the fuel nozzle to form an air passage between the burner tube and the fuel nozzle, swirler vanes that are arranged in a plurality of positions in a circumferential direction on an external circumferential surface of the fuel nozzle, each of which extends along an axial direction of the fuel nozzle, and gradually curves from upstream to downstream, a liquid fuel injecting hole that is formed on the fuel nozzle, and from which a liquid fuel is injected to a vane pressure surface of each of the swirler vanes, and a cooling unit that cools a part of the vane pressure surface on which the liquid fuel hits. The cooling unit injects a mixed fuel prepared by mixing water and the liquid fuel evenly from the liquid fuel injecting hole to the vane pressure surface of the swirler vane. | 11-13-2014 |
20150040569 | ANNULAR COMBUSTION CHAMBER FOR A TURBINE ENGINE - An annular combustion chamber including inner and outer walls forming surfaces of revolution that are connected together upstream by an annular chamber end wall having injection systems passing therethrough. Each injection system includes at least one swirler for producing a rotating stream of air downstream from a fuel injector, and a frustoconical bowl downstream from the swirler and formed with an annular row of air injection orifices, the outer wall having an annular row of primary dilution orifices. The orifices of the bowls are distributed and dimensioned such that sheets of air/fuel mixture present a local enlargement circumferentially intersecting an adjacent sheet of fuel upstream from the primary dilution orifices. | 02-12-2015 |
20150113993 | GAS TURBINE ENGINES HAVING FUEL INJECTOR SHROUDS WITH INTERIOR RIBS - A fuel injector assembly includes a fuel injector and a fuel injector shroud housing the fuel injector. The fuel injector includes a body and a nozzle coupled to the body. The fuel injector shroud includes a swirler device defining a center opening proximate to the nozzle of the fuel injector and a plurality of swirler holes surrounding the center opening, a body section with an air inlet configured to admit a flow of air into the fuel injector shroud and a dome section defining a mount for securing the swirler device to the body section, and at least one interior rib positioned on an interior surface of the dome section configured to direct the flow of air to the swirler holes of the swirler device such that the flow of air exiting through the swirler is mixed with the flow of fuel exiting the nozzle. | 04-30-2015 |
20150323185 | TURBINE ENGINE AND METHOD OF ASSEMBLING THEREOF - A turbine engine is provided. The turbine engine includes a compressor configured to discharge a flow of air at a first flow angle and a combustor coupled downstream from the compressor. The combustor is configured to combust the flow of air with fuel to form a flow of combustion gas discharged from the combustor at a second flow angle. The turbine engine also includes a turbine coupled downstream from the combustor. The turbine includes an inlet configured to receive the flow of combustion gas having a flow angle within a predetermined range, wherein the combustor is oriented such that the second flow angle is within the predetermined range. | 11-12-2015 |
20150330635 | COMBUSTION CHAMBER ARRANGEMENT - A combustion chamber arrangement comprises an annular combustion chamber arranged radially between an inner casing and an outer casing. The combustion chamber comprises a metering wall arranged upstream of an upstream wall and the upstream wall and the metering wall each have a plurality of circumferentially spaced apertures. Each aperture in the metering wall is aligned with a respective one of the apertures in the upstream wall. A fuel injector is arranged in each of the apertures in the upstream wall. An air swirler is aligned with a respective one of the fuel injectors. Each air swirler is arranged between the upstream wall and the metering wall. The metering wall has a plurality of metering holes arranged to provide a controlled supply of air to each of the air swirlers and the combustion chamber is secured to the inner casing by a mounting feature. | 11-19-2015 |
20160010864 | Gas Turbine Combustor | 01-14-2016 |
20160040599 | COMBUSTION SYSTEM, APPARATUS AND METHOD - Combustion systems for a gas turbine engines are provided. The combustion system is configured to provide a fuel-air mist to achieve light-off during high altitude start (e.g., at altitudes greater than 45,000 ft.) without flame out. The combustion system may also be configured to provide additional air to the combustion chamber at high altitude to facilitate flame propagation and second stage burn. | 02-11-2016 |
20160040881 | GAS TURBINE ENGINE COMBUSTOR - A swirler assembly for a gas turbine engine includes an outer annular injector which at least partially surrounds an inner injector and an air-assist atomizer upstream of said inner injector. | 02-11-2016 |
20160153660 | SWIRLER MOUNT INTERFACE FOR GAS TURBINE ENGINE COMBUSTOR | 06-02-2016 |
20160161122 | AIRBLAST NOZZLE WITH UPSTREAM FUEL DISTRIBUTION AND NEAR-EXIT SWIRL - A nozzle is provided including a nozzle body having an upstream end and a downstream end aligned about a central axis. A discharge portion is positioned adjacent the downstream end. A bore extends inwardly from the downstream end over the length of the discharge portion. An opening is formed in the nozzle body adjacent the discharge portion. The opening is fluidly connected to the bore to provide an interior air flow passage. A main fuel channel extends from the upstream end to the discharge portion. At least one fuel flow branch extends through the discharge portion between the bore and an outer surface of the nozzle body. The fuel flow branch is fluidly coupled to the main fuel conduit to provide a fuel flow passage. The outer air cap is positioned about the outer surface of the discharge portion of the nozzle body to form an exterior air flow passage. | 06-09-2016 |
20160169178 | COMBUSTION CHAMBER ASSEMBLY | 06-16-2016 |