Abstract: A low emissions combustion system with a plurality of tangential fuel injectors to introduce a fuel/air mixture at the combustor dome end of an annular combustion chamber in two spaced injector planes. Each of the spaced injector planes includes multiple tangential fuel injectors delivering premixed fuel and air into the annular combustor. A generally skirt-shaped flow control baffle extends from the tapered inner liner into the annular combustion chamber downstream of the fuel injector planes. A plurality of air dilution holes in the tapered inner liner underneath the flow control baffle introduce dilution air into the annular combustion chamber while another plurality of air dilution holes in the cylindrical outer liner introduces more dilution air downstream from the flow control baffle.

Abstract: A low emissions combustion system with a plurality of tangential fuel injectors to introduce a fuel/air mixture at the combustor dome end of an annular combustion chamber in two spaced injector planes. Each of the spaced injector planes includes multiple tangential fuel injectors delivering premixed fuel and air into the annular combustor. A generally skirt-shaped flow control baffle extends from the tapered inner liner into the annular combustion chamber downstream of the fuel injector planes. A plurality of air dilution holes in the tapered inner liner underneath the flow control baffle introduce dilution air into the annular combustion chamber while another plurality of air dilution holes in the cylindrical outer liner introduces more dilution air downstream from the flow control baffle.

Abstract: A mixer assembly for use in a combustion chamber of a gas turbine engine. The mixer assembly includes a mixer housing having a hollow interior, an inlet and an outlet. The housing delivers a mixture of fuel and air through the outlet to the combustion chamber for burning. The mixer assembly includes a fuel nozzle assembly mounted in the housing having a fuel passage adapted for connection to a fuel supply. The passage extends to an outlet port for delivering fuel from the passage to the hollow interior of the mixer housing. The nozzle assembly includes a plasma generator for generating at least one of a dissociated fuel and an ionized fuel from the fuel delivered through the nozzle outlet port to the hollow interior of the housing.

Abstract: A fuel injector nozzle for dispensing fuel in the combustion chamber of a gas turbine engine, includes an elongated, multi-layered, convoluted nozzle feed strip having an internal passage for directing fuel through the length of the strip from the inlet end to an outlet end; and a cylindrical, multi-layered fuel dispensing nozzle unitary with the feed strip and fluidly connected to the outlet end of the feed strip for dispensing the fuel. The multi-layered feed strip and nozzle allows complex porting of fuel circuits through the injector. The internal fluid passages through the feed strip and nozzle are formed by etching.

Abstract: In a combustion device (10), particularly for driving gas turbines, comprising a plurality of burners (12, . . . , 15) of identical thermal power output, which work parallel to an axis (28) into a common combustion chamber (11), an effective suppression of thermoacoustic combustion instabilities is achieved in a simple way in that the burners (12, . . . , 15) are designed differently from one another in such a way that the flames (24, . . . , 27) or flame fronts generated by them are positioned so as to be distributed along the axis (28).

Abstract: A fuel nozzle system for use in a combustor utilized in a combustion turbine for reducing nitrogen oxides and other pollutants including an annular fuel distribution manifold separately mounted away from a diffusion nozzle, said annular manifold having a plurality of fuel emitting passages or holes disposed along the downstream side of the manifold, said manifold being mounted in a position away from the diffuser nozzle body to allow air to stream around the manifold on all sides allowing for a thorough mixture of fuel and air around the annular manifold for better premixing in the combustion chamber. In an alternate embodiment, the diffusion nozzle is replaced by a pilot flame nozzle that is supplied with both air and fuel through a premix air and fuel chamber to a pilot flame nozzle which is used to sustain combustion in the secondary chamber. The use of a pilot flame nozzle that has a fuel and air mixture is believed to reduced NOx emissions.

Abstract: A premixer for an industrial type gas turbine engine wherein the premixer includes a diffuser ring assembly made up of annular concentric rings and upstream of the diffuser ring assembly in the airflow path is a corresponding fuel manifold ring assembly, each ring in the manifold ring assembly corresponding to a passageway formed between the diffuser rings, and each manifold ring includes a downstream channel for feeding the fuel to the air as the air passes by the ring.

Abstract: The invention refers to a combustion chamber device including a combustion chamber (2) and a set of burners (6) with an outlet opening (7) in the combustion chamber. Each burner includes members (10) for the supply of a flow of oxygen-containing gas, members (8) for the supply of fuel, and a space (9), which extends to the combustion chamber (2) for mixing of the fuel and the oxygen-containing gas. Each burner (6) is arranged to convey a substantially equally large flow of oxygen-containing gas through the burner to the combustion chamber. Each burner (6) is defined by at least one parameter including a characteristic length (a) of the space (9) along the longitudinal direction (x). At least the characteristic length (a) of at least one of the burners is selected in such a way that it deviates from the corresponding length (a) of another burner and in such a way that the influence of the oscillations which arise during operation of the combustion chamber device are reduced.

Abstract: A shaped charge engine includes an annular blast-forming chamber formed by joining inner and outer housings. A central through hole in the inner housing allows exhaust gases to exit. The outer housing comprises a generally round disk with an inner conical concave depression and through holes for the insertion of fuel and ignition. The blast chamber is preferably taper-conical in shape, wider at the base, and gradually decreasing in cross-sectional area as it rises to the apex. This construction forms a circular pinch point or throat toward the apex that produces a primary or first stage compression area. A secondary compression zone is created at the apex of the outer housing, just beyond the throat, producing hypersonic gases as generally opposing exhaust streams collide and are forced to exit the through hole in the inner housing. The shaped charge engine may be used in a variety of applications, including as a pulsed direct propulsion device, as a turbine driver, or in a wide array of tools and appliances.

Abstract: In a gas turbine having a plurality of hybrid burners, each of which has a pilot burner and a main burner, a different pilot fuel quantity is fed to the pilot burners as a function of the load on the gas turbine. This provides both stable operation of the gas turbine at low loads and effective suppression of combustion oscillations at high loads.

Abstract: A fuel control system for supplying metered quantities of fuel from a fuel supply (11), through a fuel pump (13), a metering valve (15) and a pressurizing valve (17) to a plurality of engine fuel manifolds (31a, 31b, 33) includes an ecology valve (43) for withdrawing fuel from the engine fuel manifolds (31a, 31b, 33) during cessation of engine operation and for returning fuel to the engine fuel manifolds (31a, 31b, 33) to be burned during normal engine operation. The ecology valve (43) includes a valve housing (44) having a plurality of ecology ports (50, 52, 54) adapted to be coupled to corresponding ones of the engine fuel manifolds (31a, 31b, 33) and a control port (46) adapted to be connected to a corresponding control port (45) of the fuel pressurizing valve (17).

Abstract: A three stage lean burn combustion chamber (28) comprises a primary combustion zone (36), a secondary combustion zone (40) and a tertiary combustion zone (44). Each of the combustion zones (36,40,44) is supplied with premixed fuel and air by respective fuel and air mixing ducts (76,78,80,92). The secondary fuel and air mixing duct (80) has passages (80A) and apertures (90A) at its downstream end to supply air and fuel into the secondary combustion zone (40) at a first position in the at least one combustion zone (40) and the secondary fuel and air mixing duct (80) has passages (80B) and apertures (90B) at its downstream end to supply air and fuel into the secondary combustion zone (40) at a second position in the secondary combustion zone (40) downstream from the first position. This axial distribution of fuel in the combustion zone (40) reduces the generation of harmful vibrations in the combustion chamber (28).

Abstract: A premixer for an industrial type gas turbine engine wherein the premixer includes a diffuser ring assembly made up of annular concentric rings and upstream of the diffuser ring assembly in the airflow path is a corresponding fuel manifold ring assembly, each ring in the manifold ring assembly corresponding to a passageway formed between the diffuser rings, and each manifold ring includes a downstream channel for feeding the fuel to the air as the air passes by the ring.

Abstract: A control system and method for controlling the split between premix fuel flow and pilot fuel flow to a combustor in a gas turbine engine so that an acceptable emissions are maintained. Engine speed and exhaust gas temperature are used to obtain a combustor pilot zone temperature that will result in the desired level of emissions. From this pilot zone temperature a desired split between premix fuel flow and pilot fuel flow is obtained and compared to the actual split to generate an error signal. The actual premix fuel flow and pilot fuel flow are then adjusted until the desired split and hence the desired emission levels are obtained.

Abstract: A nozzle configuration and control methodology adapted to provide a compact means for configuring and operating an industrial gas turbine on either gaseous or liquid fuel while utilizing fuel staging to achieve very low emissions. More specifically, the outer fuel nozzles are used for delivery of a portion of the premix gaseous fuel and all liquid fuel, but not diffusion gaseous fuel. Water injection for emissions control on liquid fuel and atomizing air for the liquid fuel are also supplied entirely by the outer fuel nozzles. The central fuel nozzle is thus used for the supply of both premix gaseous fuel and all diffusion gaseous fuel. The disclosed configuration reduces the number of required fluid passages thus simplifying the endcover structure while enabling fuel staging to achieve very low emissions on gaseous fuel.

Abstract: A combustor having liners made from ceramic matrix composite materials (CMC's) that are capable of withstanding higher temperatures than metallic liners. The ceramic matrix composite liners are used in conjunction with mating components that are manufactured from superalloy materials. To permit the use of a combustor having liners made from CMC materials in conjunction with metallic materials used for the mating forward cowls, and aft seals with attached seal retainer over the broad range of temperatures of a combustor, the combustor is designed to allow for the differential thermal expansion of the differing materials at their interfaces in a manner that does not introduce stresses into the liner as a result of thermal expansion and also balances the flow of cooling air as a result of the thermal expansion.

Abstract: A two-stage fuel nozzle assembly for a gas turbine engine. The primary combustion region is centrally positioned and includes a fuel injector that is surrounded by one or more swirl chambers to provide a fuel air mixture that is ignited to define a first stage combustion zone. A secondary combustion region is provided by an annular housing that surrounds the primary combustion region, and it includes a secondary fuel injector having a radially outwardly directed opening and surrounded by an annular ring that includes openings for providing a swirl chamber for the secondary combustion region. Cooling air is directed angularly between the primary and secondary combustion zones to delay intermixing and thereby allow more complete combustion of the respective zones prior to their coalescing further downstream. The primary combustion region is activated during idle and low engine power conditions and both the primary and secondary combustion regions are activated during high engine power conditions.

Abstract: A mixer assembly for use in a combustion chamber of a gas turbine engine. The assembly includes a pilot mixer and a main mixer. The pilot mixer includes an annular pilot housing having a hollow interior, a pilot fuel nozzle mounted in the housing adapted for dispensing droplets of fuel to the hollow interior of the pilot housing, and a plurality of concentrically mounted axial swirlers positioned upstream from the pilot fuel nozzle. Each of the swirlers has a plurality of vanes for swirling air traveling through the respective swirler to mix air and the droplets of fuel dispensed by the pilot fuel nozzle. The main mixer includes a main housing surrounding the pilot housing defining an annular cavity, a plurality of fuel injection ports for introducing fuel into the cavity, and a swirler positioned upstream from the plurality of fuel injection ports having a plurality of vanes for swirling air traveling through the swirler to mix air and the droplets of fuel dispensed by the fuel injection ports.

Abstract: Combustion air or a combustion air/fuel mixture is supplied in a flow to a combustion process of a burner. A swirl, which is non-uniform in the peripheral direction, is imposed on the flow. A flow duct, in which is arranged a swirl device for imposing the swirl, is used for the supply of the combustion air or the combustion air/fuel mixture. As such, combustion oxcillations are reduced.

Abstract: A three stage lean burn combustion chamber (28) comprises a primary combustion zone (36), a secondary combustion zone (40) and a tertiary combustion zone (44). Each of the combustion zones (36,40,44) is supplied with premixed fuel and air by respective fuel and air mixing ducts (76,78,80,92). Secondary fuel injectors (106) and two secondary fuel manifolds (105A, 105B) supply fuel into different circumferential sectors, halves, of the secondary fuel and air mixing duct (80). The secondary fuel manifolds (105A, 105B) have secondary fuel valves (107A,107B) which supply a greater proportion of fuel to the secondary fuel manifold (105A) than the secondary fuel manifold (105B) so that there is circumferential biasing of fuel in the secondary combustion zone (40). This circumferential biasing of fuel in the secondary combustion zone (40) reduces the generation of harmful pressure oscillations in the combustion chamber (28).

Abstract: A fuel injector nozzle for dispensing fuel in the combustion chamber of a gas turbine engine, includes an elongated, multi-layered, convoluted nozzle feed strip having an internal passage for directing fuel through the length of the strip from the inlet end to an outlet end; and a cylindrical, multi-layered fuel dispensing nozzle unitary with the feed strip and fluidly connected to the outlet end of the feed strip for dispensing the fuel. The multi-layered feed strip and nozzle allows complex porting of fuel circuits through the injector. The internal fluid passages through the feed strip and nozzle are formed by etching.

Abstract: A combustion chamber assembly (22) comprises a primary, a secondary and a tertiary fuel and air mixing ducts (54,78,98) to supply fuel and air to primary, secondary and tertiary combustion zones (40,42,44). Each of the primary, secondary and tertiary fuel and air mixing ducts (54,78,98) comprises a pair of axial flow swirlers (56,60,80,84,102,104) arranged coaxially to swirl the air in opposite directions and fuel injectors (62, 86,106) to supply fuel coaxially of the respective axial flow swirlers (56,60,80,84,102, 104). Valves (66,90) are provided to control the supply of air to the primary and the secondary fuel and air mixing ducts (54,78) respectively. A duct (122,116) is arranged to supply cooling air and dilution air to the combustion chamber (22). The amount of air supplied to the primary, secondary and tertiary fuel and air mixing ducts (54,78,98) and the duct (122,116) is measured.

Abstract: In a central portion of inner tube 28 of combustor 20, pilot fuel nozzle 22 and pilot cone 33 are arranged and main fuel nozzles 21 and main swirlers 32 therearound. Air intake portion (X-1) is provided with rectifier tube 11 for making air intake uniform. In air intake portion (X-2), air holes of appropriate number of pieces are provided in circumferential wall of the inner tube 28. In main swirler portion (X-3) and pilot cone portion (X-4), bolt joint of the main swirlers 32 is employed and optimized welded structure having less influence of thermal stress of the pilot swirler 33 is employed, respectively. Tail tube cooling portion (X-5) is provided with cooling structure having less influence of thermal stress to cool flange 71 portion of tail tube 24 uniformly. By the improvements in the portions (X-1) to (X-5), obstacles in attaining higher temperature in the combustor 20 is dissolved and combustor performance is enhanced.

Abstract: The present invention provides a premix fuel injector for use in gas turbine engines and in combustion systems having controllable pressure drops. The premix fuel injector comprises a premix chamber having an inlet for receiving a flow of pressurized air and having an exit. A venturi is coupled to the exit of the premix chamber and an inlet of a combustion chamber. Gaseous fuel is flowed into the premix chamber by a plurality of circumferentially disposed tubes extending into the premix chamber with each of said tubes having at least one hole for flowing a stream of the gaseous fuel.

Abstract: In a central portion of inner tube 28 of combustor 20, pilot fuel nozzle 22 and pilot cone 33 are arranged and main fuel nozzles 21 and main swirlers 32 therearound. Air intake portion (X-1) is provided with rectifier tube 11 for making air intake uniform. In air intake portion (X-2), air holes of appropriate number of pieces are provided in circumferential wall of the inner tube 28. In main swirler portion (X-3) and pilot cone portion (X-4), bolt joint of the main swirlers 32 is employed and optimized welded structure having less influence of thermal stress of the pilot swirler 33 is employed, respectively. Tail tube cooling portion (X-5) is provided with cooling structure having less influence of thermal stress to cool flange 71 portion of tail tube 24 uniformly. By the improvements in the portions (X-1) to (X-5), obstacles in attaining higher temperature in the combustor 20 is dissolved and combustor performance is enhanced.

Abstract: In a gas turbine having a plurality of hybrid burners, each of which has a pilot burner and a main burner, a different pilot fuel quantity is fed to the pilot burners as a function of the load on the gas turbine. This provides both stable operation of the gas turbine at low loads and effective suppression of combustion oscillations at high loads.

Abstract: A fuel nozzle system for use in a combustor utilized in a combustion turbine for reducing nitrogen oxides and other pollutants including an annular fuel distribution manifold separately mounted away from a diffusion nozzle, said annular manifold having a plurality of fuel emitting passages or holes disposed along the downstream side of the manifold, said manifold being mounted in a position away from the diffuser nozzle body to allow air to stream around the manifold on all sides allowing for a thorough mixture of fuel and air around the annular manifold for better premixing in the combustion chamber.

Abstract: A gas turbine fuel injection system of the lean direct injector type designed to reduce nitrous oxide (NOx) emissions is provided. The configuration includes a pilot fuel injector for injecting a pilot fuel stream, and a pilot swirler for providing a swirling pilot air stream to atomize and entrain the pilot fuel stream. A main airblast fuel injector is located concentrically about the pilot fuel injector, for injecting a main fuel stream concentrically about the pilot fuel stream. Inner and outer main swirlers provide a swirling main air stream to atomize and entrain the main fuel stream. An air splitter is located between the pilot swirler and the main swirler. The air splitter is so arranged and constructed as to divide the pilot air stream exiting the pilot swirler and the air splitter, from the main air stream exiting the inner main swirler, whereby a bifurcated recirculation zone is created.

Abstract: A three stage lean burn combustion chamber (28) comprises a primary combustion zone (36), a secondary combustion zone (40) and a tertiary combustion zone (44). Each of the combustion zones (36,40,44) is supplied with premixed fuel and air by respective fuel and air mixing ducts (76,78,80,92). The primary fuel and air mixing ducts (78,78) comprise first and second radial flow swirlers (60,62). The primary fuel injectors (64,66) inject fuel into the first and second swirlers (60,62). The primary fuel injectors (44,66) and the first and second swirlers (60,62) are arranged such the fuel to air ratio of the fuel and air flowing from the passages (61) of the first swirler (60) into the primary combustion zone (36) is different to the fuel to air ratio of the fuel and air flowing from the passages (65) of the second swirler (62) into the primary combustion zone (36).

Abstract: A fluid manifold (41) comprises two annular chambers (42 and 46) in flow series and having a barrier (45) therebetween. A fluid is fed into the first larger annular chamber (42) and circulates circumferential therethrough before being passed through a plurality of apertures (44) in the barrier (45) to the second smaller annular chamber (46). The fluid circulates circumferentially through the second chamber (46) in the opposite direction prior to its discharge through apertures (50) in a final barrier (48). The apertures (50) in the final barrier (48) decelerate the fluid discharging therefrom to enhance mixing of air with the fluid downstream of the manifold (41).

Abstract: A fuel-injection arrangement for a gas-turbine engine has distributed longitudinally along a pre-chamber portion of the combustion chamber a series of fuel-outlet holes configured such that a radial component of momentum of the fuel exiting the holes varies along the series of holes. To achieve this the holes are preferably differently sized along the trailing edge. Advantageously, the holes at the very upstream end of the pre-chamber portion have the smallest diameter, the size thereafter progressively increasing along the series. The size distribution may vary either continuously, or in stepped fashion. The direction of exit of the fuel from the outlets is preferably radial towards the central axis of the swirler. The variable-sized holes may be employed in a swirler upstream the main combustion chamber region and/or in an intermediate region between the swirler and the main chamber region.

Abstract: Assembly of the combustor dome in a gas turbine engine is facilitated by providing a self-fixturing configuration. The combustor dome assembly is made up of a dome plate having a plurality of swirler assemblies mounted therein. Each swirler assembly is provided with a locating pin that extends between the dome plate and the swirler assembly for positioning the swirler assembly with respect to the dome plate without the use of fixturing tools. Preferably, the swirler assembly includes a swirl cup and an outlet sleeve mounted in the dome plate. The locating pin is pressed into a hole formed in the swirl cup. One end of the pin is received in a slot formed in the dome plate, and the other end of the pin is received in a slot formed in the outlet sleeve. Thus, the locating pin sets the circumferential orientation of the swirler assembly in relation to the dome plate.

Abstract: A pre-mixing combustion chamber (8) for a gas turbine is disclosed which includes a main stage with at least one pre-mixing chamber and a combustion chamber fashioned at least partly dynamically balanced relative to its longitudinal axis with a main combustion zone (3) and an after-combustion zone (5) placed downstream, whereby the at least one pre-mixing chamber discharges into the combustion chamber in the region of the main combustion zone tangentially producing twisting action. The pre-mixing chamber also includes a pilot stage (4) with a pilot injection means, whereby the main combustion zone in the combustion chamber proceeds essentially coaxial to the after-combustion zone, and the pilot stage is arranged at that end of the combustion chamber remote from the after-combustion zone.

Abstract: Lean premixed combustion of a hydrocarbon fuel and air is combined with lean direct injection of hydrocarbon fuel and carrier fluid such as air or inert gas or a mixture of air and inert gas into a combustor downstream of the premixed reaction zone in order to achieve extremely low levels of emissions of oxides of nitrogen at the high combustor exit temperatures required by advanced heavy duty industrial gas turbines. One or more premixing fuel nozzles are used to supply a lean mixture of hydrocarbon fuel and air to the main or primary reaction zone of a gas turbine combustor. This lean fuel/air mixture has an adiabatic flame temperature below the temperature that would result in substantial thermal NOx formation.

Abstract: A premixing section for supplying a fuel-air mixture to a homogeneous combustion chamber includes a first fuel nozzle disposed along an axis, a second fuel nozzle disposed to surround the outer periphery of the first fuel nozzle, and a premixing/pre-evaporating chamber. The first fuel nozzle is a diffusion combustion type nozzle and supplies the fuel-air mixture from an air blast-type nozzle tip directly to the homogeneous combustion chamber. The second fuel nozzle is a premixing/pre-evaporating type nozzle and supplies the fuel-air mixture from an air blast-type nozzle tip to the premixing/pre-evaporating chamber, so that the fuel-air mixture promoted in mixing and evaporation in the premixing/pre-evaporating chamber, is supplied via a swirler to the homogeneous combustion chamber. With the above arrangement, the atomization of the fuel enhances the emission characteristics.

Abstract: A distributor for supplying burners of a gas turbine with fuel, air and coolant. Prior art distributors contain a combination of ring lines and tie lines, over which the fuel is distributed to individual burners. It is very complicated and expensive to replace defective components, and in some cases the entire apparatus has to be dismantled to do so. The distributor of the invention has two or more modules, depending on the number of burners, which are assembled from distributor units and regulating units in such a way that they can be taken apart again. For each burner, at least one regulating unit is provided, from which at least one supply line for the fuel, air and coolant extends to the burner.

Abstract: A lean-burn combustor for a gas-turbine engine has a radial inflow pre-mixing, pre-swirling burner with a central burner face which forms the upstream wall of a pre-chamber of the combustor. A circular recess is formed in the burner face, the recess having at least one pilot fuel injector for introducing pilot fuel tangentially into the recess, whereby the burner runs cooler and combustion characteristics are improved.

Abstract: A stem member for a gas turbine fuel nozzle includes inlet and outlet ends which are respectively adapted to be connected to a fuel adapter which is coupled to a fuel injector and a tip assembly having at least one spray orifice for atomizing fuel into a combustion chamber. The stem member further includes at least one slot which is sealed throughout the length thereof by a slot cover so as to define at least one fuel conduit for directing fuel flow from the inlet end to the outlet end of the stem member. An outer shield can be disposed outwardly of the stem member to protect and limit the transfer of heat from the surroundings to the stem member.

Abstract: A combustor assembly comprises a plurality of circumferentially arranged fuel nozzles, which fuel nozzles have a first end coupled to a combustion chamber and a second end attached to an endcover. The plurality of fuel nozzles define a central region therebetween. A baffle is disposed within the central region. The baffle has an upstream base portion adjacent the endcover and a contoured downstream portion having a width that is smaller with respect to a width of the upstream base portion so as to transition a recirculating flow into a downstream flow to minimize flashback occurrences within the central region.

Abstract: An annular premix section that reduces NO.sub.x and CO emissions of a gas turbine combustor by providing a more homogeneous fuel/air mixture for main stage combustion is provided. A gas turbine combustor according to the present invention includes a nozzle housing, a main fuel nozzle, and a main fuel swirler. A main combustion zone is located adjacent to the nozzle housing. The main fuel nozzle extends through the nozzle housing and is attached to a nozzle housing base. The tip of the main fuel nozzle is located downstream of the nozzle housing base. The main fuel swirler surrounds a portion of the main fuel nozzle, with a downstream end of the main fuel swirler located downstream of a main fuel injection port and upstream of the main fuel nozzle tip. The main fuel swirler is adapted to receive a flow of compressed air and to mix a fuel with the flow of compressed air to form a fuel/air mixture flow.

Abstract: A gas turbine combustor comprises: an outer casing; a combustor inner cylinder disposed inside the outer casing; a combustion chamber formed in the combustor inner cylinder; a pilot fuel injection unit disposed to a head side portion of the combustion chamber, the pilot fuel injection unit comprising a first premixing combustion nozzle unit, a diffusing combustion nozzle unit and a second premixing combustion nozzle unit, the first premixing combustion nozzle unit being arranged at a central portion of the head side portion of the combustion chamber, the diffusing combustion nozzle unit being arranged so as to coaxially surround an outside of the first premixing combustion nozzle unit and the second premixing combustion nozzle unit being arranged so as to coaxially surround an outside of the diffusing combustion nozzle unit, respectively; and a premixing combustion chamber disposed to an outlet side of the first premixing combustion nozzle unit so as to be communicated with the combustion chamber.

Abstract: The invention relates to a combustion chamber containing a number of aerohanical injectors mounted in the end of the chamber that connects the upstream end of two annular walls and which are supplied with fuel permanently during operation. The injectors are arranged in two concentric rows around the axis of symmetry and in pairs in longitudinal planes passing through the axis of symmetry. The injectors of the two rows are more or less equidistant from the outlet of the chamber and have axes directed toward the outlet. A carefully considered distribution of the primary holes, dilution holes and the air flow allows the emissions of oxides of nitrogen to be reduced.

Abstract: An apparatus is provided for suppressing flame/pressure pulsations in a furnace, in which a flame is surrounded by a gas shroud stream having a higher flow speed, whereby a ring vortex formation is stopped. In order for this gas shroud stream to be able to achieve smaller gas volumes, a screen is provided that surrounds the gas outlet openings and runs at a spacing around the burner, so that a flue gas recirculation area associated with the combustion chamber is separated from the outlet location of the gas shroud stream and thus the gas shroud stream itself.

Abstract: The burner arrangement for a gas turbine comprises at least one burner (2), which is arranged in the plenum of the gas turbine and leads with an inner injection space into a combustion chamber and to which compressed air is admitted on the outside from a compressor stage of the gas turbine. Furthermore, a fuel lance (9) for the alternative feeding of liquid and/or gaseous fuels is allocated to the burner (2), which fuel lance (9) has a central liquid-fuel tube (19) and a pilot gas tube (11) concentrically surrounding the liquid-fuel tube (19), the tubes (11, 19) ending in associated outlet openings (22, 23, 23a-c) in a lance head (12) at the tip of the fuel lance (9).

Abstract: A main stage fuel mixer that reduces NO.sub.x and CO emissions of a gas turbine combustor by providing a more homogeneous fuel/air mixture for main stage combustion is provided. A gas turbine combustor according to the present invention includes a nozzle housing having a nozzle housing base, a plurality of main nozzles, and a main stage fuel mixer. A main combustion zone is located adjacent to the nozzle housing. Each main nozzle extends through the nozzle housing and is attached to the nozzle housing base. The main stage fuel mixer has a plurality of inlets, each of which is adapted to receive a flow of gas, and an outlet adjacent to the main combustion zone. The main stage fuel mixer has a plurality of transition ducts, each associated with one inlet. Each transition duct provides fluid communication from the inlet associated with the transition duct to the outlet.

Abstract: A fuel mixer for a gas turbine combustor is provided. The fuel mixer has a substantially cylindrical body with a flared end and a tapered end. The flared end is adapted for receiving compressed air and for channeling the compressed air into the fuel mixer. The fuel mixer has a fuel/air mixing disk disposed within the body proximate the flared end. A disk axis of the fuel/air mixing disk is substantially parallel to the axis of the fuel mixer body. The fuel/air mixing disk has a plurality of holes parallel to the disk axis. The fuel/air mixer reduces NO.sub.x and CO emissions in a gas turbine combustor by providing more evenly distributed fuel/air mixtures without increasing the risk of flame holding or flashback.

Abstract: The fuel nozzle is configured with a fuel injector with a pair of coaxially mounted air swirlers utilized in an annular combustor of a gas turbine engine that is dimensioned to provide 70-90 percent of the mass airflow in the inner passage and the swirl angle of the inner swirler is 45.degree.-55.degree. and the outer swirler is 70.degree. and the L/D of the combustion hole location relative to the fuel injector is 0.6-0.7 which serve to produce an outer shear layer flame for improved lean blowout characteristics.

Abstract: The invention relates to a main-burner arrangement of a combustion chamber (5), in particular for a gas turbine, at least two main-burner groups (13.1, 13.2), each comprising at least one burner (13) of the same size and geometry being provided for the purpose of equipping the combustion chamber (5), and at least one main-burner group representing the normal main burner(s) (13.1), the normal main burner(s) (13.1) producing a homogeneous flame front in the combustion chamber (5), and the other main-burner group interfering as an interference burner or burners (13.2) with the homogeneity of the flame front in the combustion chamber (5). In this burner arrangement, the interference burner(s) (13.2) is/are arranged in the combustion chamber (5) so as to be inclined or axially displaced in relation to the normal main burner(s) (13.1). This interferes with the symmetry and homogeneity of the flame front. The power of the combustion chamber is increased and pressure pulsations can be avoided.

Abstract: A double annular combustor having concentrically disposed inner and outer annular combustors including an inner dome having an inner portion and an outer portion, an outer dome having an inner portion and an outer portion, wherein the outer dome inner portion is connected to the inner dome outer portion, and a substantially annular centerbody disposed between the inner dome and the outer dome. The centerbody includes a plurality of structurally independent arcuate segments, wherein each centerbody segment is retained in position via an interference fit between a first flange of such centerbody extending downstream and a hook in the inner dome outer portion and/or via a clamping fit of a second flange of the centerbody extending upstream to a flange of the inner dome outer portion.

Abstract: A multi-stage topping combustor unit having rich burn, and lean burn zones followed by a quench/dilution zone. Combustible fuel gas is supplied only to the rich burn zone, and an oxygen-containing air-flue gas mixture is supplied to all three zones in a fixed flow proportioning that establishes a desired temperature profile through the combustor unit that minimizes combustor NOx and CO emissions. The combustor unit casing is cooled by an augmented air and oxygen stream discharged into the rich burn zone only, or into both the rich and lean burn zones. The cooling air flow is regulated by a control device/valve that allows the cooling air flow, and hence the augmenting oxygen entering the rich burn zone or the rich and lean burn zones, to be reduced as the fuel gas flow/firing temperature is reduced.