Abstract: A swirler for creating a swirling fuel/air mix having vanes extending radially around a central axis of the swirler and positioned on an annular base. The swirler has mixing channels for mixing the fuel and the air. At least one mixing channel is defined by opposing walls of two adjacent vanes. At least one of the opposing walls includes a primary side injection opening for ejecting a stream of fuel into the mixing channel; and a secondary side injection opening which corresponds to the primary side injection opening and is for ejecting a jet of fuel into the mixing channel. The secondary side injection opening is positioned on the wall such that the jet from the secondary side injection opening creates turbulence, within the mixing channel, in the stream from the primary side injection opening. The turbulence increases mixing of fuel and air.

Abstract: A method for regulating jet wakes in a combustor including: directing compressed fluid into a passageway between a casing and a combustor liner; directing a combustion gas along a combustion zone; discharging a first portion of compressed fluid from the passageway into the combustion zone via a first through-hole which is disposed on a section of a combustor panel in a first circumferential row; and discharging a second portion of the compressed fluid from the passageway into the combustion zone via second through-holes, wherein the second through-holes are disposed on a section of the panel, spaced apart axially and circumferentially, and adjacent to the first through-hole, wherein the second through-holes include a first set of through-holes and a second set of through-holes, the first set of through-holes in a second row and the second set of through-holes in a third row, wherein the second and third rows extend circumferentially.

Abstract: A swirler with integrated damper may include a primary swirler vane having a primary air passage, a secondary swirler vane having a secondary air passage, and a damper within the primary swirler vane, the secondary swirler vane, or both the primary swirler vane and the secondary swirler vane. The damper may include a series of cavities. The damper is configured to absorb one or more frequencies present in an air flow through the primary air passage, the secondary air passage, or both the primary air passage and the secondary air passage.

Abstract: To achieve a reduction in waste heat loss of a fuel with improved efficiency in arrangement of a plurality of cavities, or manifold spaces. A multi-stage combustor includes a combustor liner configured to define a combustion chamber therein, a plurality of fuel nozzles configured to inject a fuel, and a manifold configured to distribute the fuel to the plurality of fuel nozzles. The manifold is disposed on a central axis of the combustor liner in a central axis extending direction. The manifold includes a casing and a plurality of partitions inserted in the casing so as to be arranged in a central axis direction of the combustor liner to define a plurality of cavities divided by the partitions. The plurality of cavities are layered in the central axis direction of the combustor liner inside of the casing, and are connected to the corresponding fuel nozzles.

Abstract: An assembly is provided for a turbine engine. This assembly includes a swirler and a fuel nozzle. The swirler is configured with an outer wall, an inner wall, an outer passage and an inner passage. The outer wall circumscribes the inner wall and extends axially along an axis to a distal outer wall end. The inner wall extends axially along the axis to a distal inner wall end that is axially recessed within the swirler from the distal outer wall end. The outer passage is formed by and radially between the inner wall and the outer wall. The inner passage is formed by and radially within the inner wall. The fuel nozzle projects into the inner passage. The fuel nozzle is configured with a plurality of orifices axially aligned with the inner wall and arranged circumferentially about the axis.

Abstract: A combustor includes a circumferential main combustion chamber and a plurality of air inlets, the plurality of air inlets dispersing air into the circumferential main combustion chamber. The combustor also includes at least one swirl-stabilized pilot burner, which disperses combustion gases into the circumferential main combustion chamber. The air inlets and the swirl-stabilized pilot burner are aligned at least partially in a radial direction and at least partially in a circumferential direction.

Abstract: A combustor for a turbomachine includes a head end, a liner at least partially defining a hot gas path, and a flow sleeve circumferentially surrounding at least a portion of the liner. The flow sleeve is spaced from the liner to form a cooling flow annulus therebetween. The cooling flow annulus is in direct fluid communication with a high pressure plenum, whereby air from the high pressure plenum flows into the cooling flow annulus and from the cooling flow annulus to the head end. The combustor further includes a first combustion zone and a second combustion zone downstream of the first combustion zone along the hot gas path. A plurality of fuel injectors are in fluid communication with the second combustion zone and are not in direct fluid communication with the high pressure plenum.

Abstract: A lean burn combustor includes a plurality of lean burn fuel injectors, each including a fuel feed arm and a lean burn fuel injector head with a lean burn fuel injector head tip, wherein the tip has a lean burn fuel injector head tip diameter, the lean burn fuel injector head including a pilot fuel injector and a main fuel injector, the main fuel injector being arranged coaxially and radially outwards of the pilot fuel injector; and a combustor chamber extending along an axial direction and including a radially inner annular wall, a radially outer annular wall, and a meter panel defining the size and shape of the combustor chamber, which includes a primary combustion zone with a primary combustion zone depth and a secondary combustion zone. A ratio of the primary combustion zone depth to the lean burn fuel injector head tip diameter is less than 2.4.

Abstract: A combustor includes a fuel supply unit defining on a radially inner side of an axis an inner peripheral side space into which inert gas is introduced and which is configured to supply the inert gas to a combustion cylinder, and defining on a radially outer side an outer peripheral side space into which the inert gas is introduced and which is configured to supply the inert gas to the combustion cylinder; an inner peripheral side oxygen supply unit that is configured to supply oxygen to the inner peripheral side space; an outer peripheral side oxygen supply unit that is configured to supply oxygen to the outer peripheral side space; and an adjustment unit that is configured to adjust the relative amounts of the oxygen supplied by the inner peripheral side oxygen supply unit and the oxygen supplied by the outer peripheral side oxygen supply unit.

Abstract: A method of igniting liquid fuel in a turbomachine combustor is provided. The method includes a step of initiating a flow of gaseous fuel from a gaseous fuel supply to a gaseous fuel nozzle. The method further includes a step of initiating a flow of liquid fuel from a liquid fuel supply to a primary liquid fuel cartridge. After initiating both the flow of gaseous fuel and the flow of liquid fuel, the method includes a step of igniting the flow of gaseous fuel and the flow of liquid fuel with an igniter. The method further includes a step of terminating the flow of gaseous fuel from the gaseous fuel supply to the gaseous fuel nozzle.

Abstract: A swirl mesh lean direct injection concept for distributed flame holding for low pollutant emissions and mitigation of combustion instability. The invention further relates to a new method for flame holding with least pressure drop and flame temperature, in gas turbine engine combustors, wherein the liner of the combustor is partially or fully replaced with a “swirl mesh”. The invention has lean direct injection for fuel distribution over several points in gas turbine combustors along with swirl arrangement for air injection which provides low pollutant emission and low combustion instability.

Abstract: A flow device for a combustor assembly defining a longitudinal axis around which the flow device is positioned is provided. The flow device includes a body extended around the longitudinal axis. The body includes a first wall and a second wall separated longitudinally from one another along the longitudinal axis. A fuel injector passage is defined through the body coaxial to the longitudinal axis. A plurality of vane walls is extended radially between the first wall and the second wall relative to the longitudinal axis. A radial flow passage is extended between the plurality of vane walls and the fuel injector passage.

Abstract: Integrated combustion nozzles and turbomachines are provided. An integrated combustion nozzle includes a unified head end coupled to a combustion liner. The unified head end includes a first fuel nozzle and a second fuel nozzle disposed at a forward end portion of the combustion liner. A fuel plenum is defined between the first fuel nozzle and the second fuel nozzle. A first liner portion extends from the first fuel nozzle and into an opening of a first wall of the combustion liner such that the first liner portion forms a continuous surface with the first wall. The unified head end further includes a second liner portion that extends from the second fuel nozzle and into an opening of a second wall of the combustion liner such that the second liner portion forms a continuous surface with the second wall.

Abstract: A nozzle, a combustor, and a gas turbine are capable of efficiently atomizing fuel. The nozzle includes an outer tube; a first inner tube installed in the outer tube and configured to form an air passage between the first inner tube and the outer tube; a second inner tube installed in the first inner tube and configured to form a main fuel passage between the first inner tube and the second inner tube and to form a pilot fuel passage within the second inner tube; and a splash plate configured to form a first space between the outer tube and the splash plate, the first space communicating with the main fuel passage and with the air passage, and to form an injection slot communicating with the first space, the splash plate having a front end and a diameter increasing toward the front end.

Abstract: A fuel injector for a combustor of a gas turbine engine is disclosed herein. The fuel injector includes a fuel stem assembly for receiving and distributing fuel and an injector head receiving fuel from the fuel stem assembly. The injector head can include an injector body, swirler vanes, a pilot assembly, passages, and fuel galleries. The pilot assembly can include pilot struts and a pilot tube. The swirler vanes and pilot struts can include passages to transport the pilot fuel from the fuel stem assembly to the pilot tube.

Abstract: A combustor a gas turbine engine includes an axial fuel injection system in communication with a combustion chamber, the axial fuel injection system operable to supply between about 10%-35% of a combustion airflow. A radial fuel injection system communicates with the combustion chamber downstream of the axial fuel injection system, where the radial fuel injection system is operable to supply between about 30%-60% of the combustion airflow. A multiple of dilution holes are in communication with a combustion chamber downstream of said radial fuel injection system, where the multiple of dilution holes are operable to supply between about 5%-20% of the combustion airflow.

Abstract: The combustor includes a nozzle casing, and combustion nozzles disposed at position spaced apart from each other in the nozzle casing and configured to mix fuel with compressed air and eject the mixture, Where each of the combustion nozzles includes, a nozzle shroud including an inlet through which the compressed air is drawn into the nozzle shroud, and an outlet through which the compressed air is discharged out of the nozzle shroud, an injection cylinder disposed in the nozzle shroud and configured to allow the fuel to be injected into the injection cylinder, and swirlers disposed on an outer circumferential surface of the injection cylinder, where the nozzle shroud includes a region having a constant diameter from the inlet to a predetermined distance along a longitudinal direction of the nozzle shroud.

Abstract: A method for staging premixers in a combustion system for a gas turbine having a compressor section and a turbine section. The method includes providing a plurality of burners each including premixers wherein compressed air from the compressor section is provided to the premixers. The method also includes providing a plurality of fuel circuits that deliver fuel to the premixers to provide premixed air and fuel used for combustion in the combustion system. In addition, the method includes associating premixers with each fuel circuit in accordance with a power of base two pattern. Further, the method includes activating or deactivating the premixers in stages by activating or deactivating an associated fuel circuit to deliver fuel or stop fuel delivery, respectively, to the premixers wherein a staging step size between consecutive stages is in accordance with a power of base two staging scheme.

Abstract: There is provided a gas turbine (1) including a compressor (2) that generates compressed air, a casing (5) into which the compressed air is introduced, a combustor (3) that generates a combustion gas, a turbine (4) that is driven by the combustion gas, a combustor cooling system (6) that has a sub-compressor (62), which is able to be operated independently of the compressor (2), and a heat exchanger (61), which extracts air in the casing (5) and causes the air to exchange heat after the sub-compressor (62) has increased a pressure of the air, and that introduces the air, which has exchanged heat, into a cooling passage (31) of a cylindrical body (30) of the combustor (3), and a combustor air introducing system that extracts air flowing in the combustor cooling system (6) and introduces the air into the combustor (3).

Abstract: A process includes manufacturing a gas turbine fuel injector body having a stub flange extending radially outward about a circumference of the gas turbine fuel injector body. The stub flange is sized to engage a stepped ledge along a central opening of a mounting flange. The central opening is sized to receive the gas turbine fuel injector body. A gas turbine fuel injector includes a gas turbine fuel injector body and a mounting flange. A method of mounting a gas turbine fuel injector includes placing a stub flange of a gas turbine fuel injector body between a surface of an injector boss and a stepped ledge of a mounting flange. The method also includes securing the gas turbine fuel injector to the injector boss with a plurality of bolts, each bolt extending through a mounting hole in the mounting flange and into a threaded hole in the injector boss.

Abstract: A method for controlling pilot-fuel/pilot-air ratio provided to a burner of a combustion system for altering its operating point. First, a value of a first parameter e.g. temperature, is checked, and if the value equals or exceeds a predetermined maximum limit of the first parameter that places the operating point in a first undesired region of operation, then a pilot-fuel/pilot-air ratio is altered such that the value of first parameter is moved to below the first parameter's predetermined maximum limit. Similarly, a value of a second parameter e.g., pressure, is checked, and if the value equals or exceeds a predetermined maximum limit of the second parameter that places the operating point in a second undesired region of operation, then again the pilot-fuel/pilot-air ratio is altered such that the value of second parameter is moved to below the second parameter's predetermined maximum limit. A combustion system operates according to the method.

Abstract: An annular combustion system includes a fuel nozzle, a panel fuel injector including a fuel plenum and at least one premixing channel therein, an inner liner having a hot side surface and a cool side surface and an outer liner having a hot side surface and a cool side surface. The inner liner, the outer liner and the panel fuel injector partially define a hot gas path downstream from the fuel nozzle. The inner liner and/or the outer liner define a plurality of micro-channel cooling passages which is disposed between the hot side surface and cool side surface of the inner liner. Each micro-channel cooling passage of the first plurality of micro-channel cooling passages is in fluid communication with an inlet hole defined along the cool side surface of the respective liner and an outlet hole.

Abstract: Disclosed herein are a nozzle capable of efficiently atomizing fuel, a combustor, and a gas turbine. The nozzle for the combustor includes a tube assembly including an air passage through which air moves, a main fuel passage disposed inside the air passage so that main fuel moves through the main fuel passage, and a pilot fuel passage disposed inside the main fuel passage so that pilot fuel moves through the pilot fuel passage as well as a nozzle tip configured to eject the pilot fuel and the main fuel, where the nozzle tip includes an injection passage coupled with the pilot fuel passage and a plurality of centrifugal flow chambers disposed outside the injection passage and communicating with the main fuel passage.

Abstract: A burner for producing a stabilized flame with an inertisation front upstream from the stabilized flame includes a swirl generator and an inlet device with a passage therethrough. The swirl generator swirls an inert process medium about a swirl axis in a flow direction and one or more openings in the inlet device provide one or more partial mass flows containing combustion educts. The inert process medium inhibits combustion of the combustion educts through the inertisation front to displace the stabilized flame from the one or more openings.

Abstract: Disclosed are a pilot fuel injector, and a fuel nozzle and a gas turbine having the same. The pilot fuel injector is mounted on the fuel nozzle to uniformize the flow of the introduced air and to enable uniform mixing with the fuel, so that a fuel mixed air having a high mixing rate is provided to the combustion chamber. The mixing rate of the fuel mixed air directed to the combustion chamber is increased, thereby suppressing the generation of nitrogen oxides and preventing the flame stagnation.

Abstract: The present disclosure is directed to an axial retention assembly for combustor components of a gas turbine engine. The axial retention assembly may include a combustor having a liner and a casing, with the casing including a flange spaced apart from the liner along an axial centerline of the combustor. Furthermore, the axial retention assembly may include a mounting plate having a first end removably coupled to the flange and a second end positioned inward from the casing in a radial direction. Moreover, the axial retention assembly may include a clamp removably coupled to the liner. Additionally, the axial retention assembly may include a tie rod coupled to the second end of the mounting plate and the clamp to reduce relative movement between the liner and the casing along the axial centerline.

Abstract: A fuel burner includes a tube extending from a first end to a second end and including a central passage and fluid directing structure for directing a mixture of air and combustible fuel radially through the tube. The fluid directing structure collectively defines a total flow area. A blocking member is axially movable within the central passage between a first condition blocking a first percentage of the total flow area and a second condition blocking a second percentage of the total flow area different from the first percentage to control the flow of the mixture of air and combustible fuel through the fluid directing structure from the first end to the second end of the tube to be ignited.

Abstract: A liner panel for use in a combustor of a gas turbine engine, the liner panel including a liner panel with a perimeter rail and a multiple of intermediate rails. A combustor for a gas turbine engine including a support shell and a multiple of liner panels mounted to the support shell via a multiple of studs, each of the multiple of liner panels having a multiple of intermediate rails to form a multiple of circumferential cavities.

Abstract: A combustor (3) includes a plurality of first burners extending along an axis (P) and arranged at intervals in the circumferential direction, a base plate (31) having support openings configured to support the plurality of first burners and a plurality of through-holes (34) through which base plate air flows toward a downstream side, a plurality of extension pipes supported by the base plate (31) to correspond to the first burners and configured to guide a pre-mixed gas ejected from the first burners toward the downstream side, and a base plate air guide section (35) configured to change a direction of at least some of the base plate air ejected from the through-holes (34) at a downstream side of the base plate (31).

Abstract: A combustion chamber of a turbomachine includes an annular outer casing and a flame tube connected to the outer casing. The flame tube includes an annular inner wall and an annular outer wall defining a first, radial portion at the inlet of the flame tube and a second, axial portion at the outlet of the flame tube. The first portion extends towards the second portion forming an elbow between the inlet and the outlet of the flame tube.

Abstract: A swirler for mixing fuel with air in a combustion engine includes a central axis, a swirler base with an upper surface, a central portion, a number of main swirler elements and a number of obstruction elements. The main swirler elements and the obstruction elements are located at the upper surface of the swirler base and are arranged around the central portion. The main swirler elements form a number of swirler slots configured for directing a fluid towards the central portion. Each swirler slot has a slot inlet and a slot outlet, wherein the slot outlet is located at a smaller radial distance from the central axis than the swirler inlet. Each obstruction element is located at a slot inlet and configured for forming a plurality of flow channels into the swirler slot.

Abstract: A combustion apparatus can avoid instability in combustion by controlling a pressure ratio of fuel mixed with air. The combustion apparatus includes a casing; a pilot nozzle disposed at the center of the casing and supplied with fuel by a pilot fuel supply pipe; and a plurality of main nozzles arranged around the pilot nozzle and supplied with fuel by a main fuel supply pipe, each main nozzle including a pair of parallel fuel channels each extending to a respective fuel spray position within the main nozzle. A gas turbine adopting the combustion apparatus includes a plurality of combustors, each combustor including the casing, pilot nozzle, and plurality of main nozzles, with each main nozzle having first and second fuel channels respectively extending to a fuel spray position of the corresponding fuel channel. A pilot manifold connects the respective pilot nozzles, and a main manifold connects the respective main nozzles.

Abstract: A burner for a gas turbine engine has a combustion chamber and a swirler adapted to guide a swirler air flow to the combustion chamber, wherein the swirler has a first wall confining the swirler air flow as well as a second wall confining the swirler air flow on the same side as and downstream with respect to the swirler air flow from the first wall and being displaced with respect to the first wall in a direction away from the swirler air flow so that a step being able to cause a flow separation of the swirler air flow is formed by the first wall and the second wall, wherein the second wall has a through hole in its surface adapted to inject a liquid fuel into the swirler air flow.

Abstract: A swirler is provided for a turbine engine. The swirler includes a swirler housing and a swirler nozzle that is attached to the housing. The housing defines a first inlet and a second inlet. The housing and the nozzle form an inner passage and an outer passage. The inner passage is radially within the nozzle and coupled with the first inlet. The outer passage is radially between the housing and the nozzle and coupled with the second inlet.

Abstract: An aft section structure of a jet engine with an axis is comprised of a casing defining a duct around the axis and opened axially fore and aft; a cone tapering aftward at a first angle with the axis and having a pointed end; guide vanes, each of the vanes radially extending from the cone to the casing and comprising a pressure side at a second angle with a plane containing the axis; spray bars, each of the spray bars extending radially within the duct and comprising trailing sides, each of the trailing sides being directed aftward at a third angle with a plane containing the axis; and flame holders, each of the flame holders extending radially within the duct and comprising one or more interior sides, each of the interior sides being directed aftward at a fourth angle with a plane containing the axis.

Abstract: A fuel injection system may comprise a mixer and a fuel injector disposed within the mixer. The mixer may comprise an outer housing with an exit port and a bluff body extending across the exit port of the outer housing. A flared surface of the mixer may match a contour of the bluff body.

Abstract: The gas turbine combustor and the operation method thereof are designed to minimize visualization of exhaust gas from the gas turbine upon switching of the gas turbine fuel from the oil fuel to the gas fuel. Upon switching of the combustion by the pilot burner from the oil burning to the gas burning, the gas fuel is supplied to the main burners so as to start the gas burning. Then the gas fuel is supplied to the pilot burner to start the gas burning.

Abstract: A combustor comprises an annular combustor chamber formed between the inner and outer liners. Fuel nozzles each have an end in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber, the fuel nozzles oriented to inject fuel in a fuel flow direction having an axial component relative to the central axis of the annular combustor chamber. A plurality of nozzle air holes are defined through the inner liner and the outer liner adjacent to and downstream of the fuel nozzles. The nozzle air holes are configured for high pressure air to be injected from an exterior of the liners through the nozzle air holes generally radially into the annular combustor chamber. A central axis of the nozzle air holes has a tangential component relative to the central axis of the annular combustor chamber.

Abstract: A fluid manifold including a manifold body having a first annular passage defined between a first wall of the manifold body and a second wall of the manifold body, wherein the second wall is radially inward from the first wall. A second annular passage is nested radially inward of the firsts annular passage, wherein the second annular passage is defined between the second wall of the manifold body and a third wall of the manifold body radially inward from the second wall of the manifold body.

Abstract: A method for the combustion of ammonia, wherein a first combustion chamber receives ammonia and hydrogen in controlled proportions, and an oxygen-containing gas. Combustion of the ammonia and hydrogen produces NH2 ions among other combustion products. A second combustion chamber receives the combustion products from the first combustion chamber and receives further ammonia and further hydrogen in controlled proportions, wherein combustion produces nitrogen oxides among other combustion products. A third combustion chamber receives the nitrogen oxides along with further ammonia and further hydrogen in further controlled proportions along with further oxygen-containing gas, such that the nitrogen oxides are combusted into nitrogen and water.

Abstract: An injector of a radial fuel injection system for a combustor of a gas turbine engine includes a swirler; and a fuel nozzle located within the swirler, the fuel nozzle located within the swirler, the fuel nozzle operable to provide a biased radial fuel distribution within the swirler. A method of controlling a fuel flow to a combustor of a gas turbine engine includes selectively controlling a biased radial fuel distribution within a swirler of a radial fuel injection system.

Abstract: A gas turbine facility of an embodiment includes: a combustor casing; a combustor provided in the combustor casing; a cylinder surrounding a periphery of the combustor and dividing a space between the combustor casing and the combustor; a turbine rotated by combustion gas exhausted from the combustor; a heat exchanger cooling the combustion gas exhausted from the turbine; a pipe through which a part of the combustion gas cooled in the heat exchanger passes in the heat exchanger to be heated, the pipe guiding the combustion gas heated in the heat exchanger into the cylinder; and a pipe guiding another part of the combustion gas cooled in the heat exchanger to a space between the combustor casing and the cylinder.

Abstract: A combustor a gas turbine engine includes an axial fuel injection system in communication with a combustion chamber, the axial fuel injection system operable to supply a first percentage of fuel and a radial fuel injection system that communicates with the combustion chamber downstream of the axial fuel injection system, the radial fuel injection system operable to supply a second percentage of fuel, the first percentage and the second percentage of fuel scheduled in response to an engine operating parameter.

Abstract: A nozzle assembly includes a fuel distributor for issuing a spray of fuel. A fuel conduit is in fluid communication with the fuel distributor and has a first end and a second end. The first end and/or the second end of the fuel conduit is operatively connected to the fuel distributor. The fuel conduit is configured to allow relative movement between the first end and the second end to accommodate dimensional variations of at least one of the nozzle assembly or a combustor. A nozzle system includes the nozzle assembly and a combustor wall having a nozzle inlet. The nozzle assembly is positioned adjacent to the nozzle inlet.

Abstract: An annular combustion system includes a fuel nozzle, a panel fuel injector including a fuel plenum and at least one premixing channel therein, an inner liner including an inner band radially spaced from an outer band and an inner flow annulus formed therebetween, and an outer liner radially spaced from the inner liner and comprising an inner band radially spaced from an outer band and an outer flow annulus formed therebetween. The fuel nozzle is positioned radially between the inner liner and the outer liner, and the panel fuel injector extends radially between the inner liner and the outer liner. At least one of the inner flow passage and the outer flow passage is in fluid communication with at least one of a premix air plenum, a cooling air cavity and a cooling air plenum defined within the panel fuel injector.

Abstract: A burner head for a burner defines a burner longitudinal axis along which the burner extends. The burner head includes a base body and at least one oxidant duct defining a duct longitudinal axis. The oxidant duct is arranged in the base body at a radial spacing to the burner longitudinal axis. A fuel duct body is inserted into the oxidant duct and at least one fuel nozzle is configured on the fuel duct body so as to open into the oxidant duct.

Abstract: A closed trapped vortex apparatus includes: a tubular structure having a structural wall, the structural wall forming a cavity within the tubular structure, the structural wall having a lower boundary wall forming a boundary between the cavity and a core flow passage; at least one driver hole passing through the structural wall; an ignition source communicating with the cavity; a fuel source communicating with the cavity; and a plurality of flame tubes extending through the lower boundary wall of the tubular structure at preselected locations so as to provide communication between the cavity and the core flow passage.

Abstract: A combustor with axially staged fuel injection includes a plurality of nozzle segments annularly arranged about a center fuel nozzle. Each nozzle segment includes a fuel plenum partially defined between a forward plate and an aft plate and a plurality of tubes that extends through the fuel plenum and the aft plate. A panel fuel injector extends axially downstream from the aft plate and includes an outer wall, an inner wall, a plurality of outlets defined along at least one of the outer wall and the inner wall and a plurality of premix channels defined between the outer wall and the inner wall. Each premix channel is in fluid communication with a fuel supply, a compressed air supply and a respective outlet of the plurality of outlets.

Abstract: An annular combustion chamber with an axis of revolution of a turbine engine delimited by coaxial inner and outer annular walls joined upstream by a substantially transverse bottom of the chamber, the chamber further comprising at least one annular deflector placed in the chamber and substantially parallel to the bottom of the chamber the bottom of the chamber having orifices designed to be passed through by the impact cooling air of the deflector and coming from upstream. The deflector is attached to the inner and outer walls in a sealed manner, and the cooling air of the deflector is discharged from the chamber through exhaust holes formed in the inner and outer walls.

Abstract: A combustor includes an inlet flow conditioner. The inlet flow conditioner includes a sleeve that circumferentially surrounds a portion of a fuel nozzle assembly and that extends from a forward end of a combustion liner to an inner surface of an end cover. The sleeve defines a plurality of apertures circumferentially spaced about the sleeve. A portion of the inner surface of the end cover and the sleeve define a head end volume of the combustor. An inlet to a premix passage of at least one fuel nozzle of the fuel nozzle assembly is disposed within and is in fluid communication with the head end volume.