Abstract: An improved fuel burner particularly adapted for domestic use and capable of burning fuels such as fuel oil and the like with extremely high efficiency and low pollutant output is comprised of a pair of identical spray heads, each including a spherical plenum onto which the fuel is flowed for atomization, the spray heads being disposed at the end of a flame tube which in turn is located within a blast tube, said spray heads further being disposed symmetrically with respect to the axis of both the flame tube and the blast tube and angularly disposed relative to each other whereby the spray output from the spray heads creates a turbulence within the flame tube such that the propagation of the flame front within the tube can be readily controlled and whereby the fuel may be readily ignited by a spark type of ignitor which is disposed centrally between the spray heads.

Abstract: A burner for hydrocarbon fuel, such as waste lubricating oil for internal combustion engines and the like, has a fuel line terminating in a discharge nozzle and connected to a source of the fuel. Arranged within the fuel line and terminating in a discharge outlet disposed substantially adjacent the discharge nozzle is a gas line connected to a source of a gas under pressure. The gas lifts and atomizes the fuel and causes same to discharge from the nozzle and into a combustion chamber. The latter is preferably formed by a burner can provided with one or more apertures in a sidewall thereof, and having a baffle disposed spaced from, but adjacent to, the discharge nozzle, which is disposed just inside the combustion chamber, for avoiding carbon buildup on the end of the nozzle.

Abstract: This invention relates to a new and novel method and apparatus for reacting nongaseous material with a gaseous reactant comprising introducing a first stream containing a nongaseous material into a reaction zone; simultaneously introducing a second stream containing a gaseous reactant into the reaction zone such that the gaseous reactant immediately contacts and reacts with the first stream thereby producing a gaseous product; forming a spiralling vortex within the reaction zone to cause substantial separation of gases, including the gaseous product, from the nongaseous material; forming and removing a third stream from the reaction zone containing the gaseous product which is substantially free of the nongaseous material before a major portion of the gaseous product can react with the nongaseous material; and forming and removing a fourth stream containing the nongaseous material from the reaction zone.

Abstract: A combustor assembly for an automotive gas turbine engine includes a continuously ignited, pilot flame tube supported on a combustor dome immediately downstream of an inlet fuel nozzle and air swirler assembly. The pilot flame tube has an air swirler and fuel nozzle supported on an interior bulkhead and air is supplied upstream of the bulkhead and through a double-walled porous tube assembly for cooling wall portions of the flame tube exposed to the flame front within the combustor and wall portions thereof exposed to a pilot flame formed within the flame tube.

Abstract: A heater of particular use in drying grain has a fluid fuel burner located axially in a housing through which air is drawn and a coaxial convergent guide ring downstream of the burner. One or more openings in the housing admit ambient air for mixing with the heated air downstream of the guide ring. The heater permits of supply of air at, for example, 5000 to 35000 ft.sup.3 /min at a temperature of 10.degree. F above ambient.

Abstract: A combustion chamber including an outer casing having a flame tube within it defining an annular space between them which receives air from the engine compressor. The flame tube has diametrically opposed pairs of air inlet ports through which air from the annular space flows substantially radially into the flame tube. A flow guide on the exterior of the flame tube is associated with each air inlet port. The upstream end of each flow guide is open to air from the compressor and the downstream end extends inwardly and downstream and partitions the upstream portion of its respective air inlet port from the annular space. A fuel tube extends into each flow guide. A curved baffle may extend radially inwardly at each air inlet port and define an arcuate louver between the baffle and the downstream edge of its respective air inlet port. Each air inlet port may have a square upstream portion merging into a circular downstream portion.

Abstract: Apparatus and methods are provided for reducing solid combustible particles by heat and abrasion to a condition in which they can be burned completely and without the production of objectionable solid particulates in the exhaust gases. Solid combustible particles are carried into an outer chamber of the device by a low pressure transport air stream, with additional air at high pressure and high velocity being introduced into the same chamber in a relation driving the solid particles rapidly and circularly within the outer chamber and about an inner chamber of the device. Impingement of the particles against one another and/or the walls of the outer chamber during such swirling motion, supplemented by partial oxidation of the combustibles, raises the temperature of the particles and comminutes or reduces their sizes to form a very highly combustible flowable aerosol mass which will burst into flame when contacted by a stream of secondary combustion air.

Abstract: A fuel burner adapted to produce a stable, non-contaminating blue flame throughout a broad operating range. The burner includes a combustion zone into which is directly fed the combustion air. Air-atomized liquid fuel is fed into the combustion zone through a Venturi whose constricted throat communicates by way of a feedback passage to the combustion zone, whereby the ejector effect produced by the atomized fuel passing through the Venturi causes a portion of the hot combustion gas generated in the combustion zone to be drawn into the throat to intermix with the atomized fuel therein, thereby pre-vaporizing the fuel to insure full combustion thereof.

Abstract: The invention concerns a method and apparatus for carrying out a reaction, particularly an exothermic one, between fluids, at a certain distance from the walls, the walls being protected from excessive heating. The apparatus comprises an external casing which is cylindrical or frustoconical, an internal perforated wall which is co-axial with the casing and which bounds the reaction chamber, an axial injection pipe for part of the reagents and a tangential feed pipe for another part of the reagents, the feed pipe imparting a symmetrical helical movement to them. The method is specially applied to the combustion of many different fluids, and the apparatus enables the heat liberated to be directed in a very flexible manner.

Abstract: Combustion apparatus for a gas turbine engine includes two separate combustion zones; one having a first air flow thereto defined by a plurality of holes in combustion apparatus liner; the second zone has air flow thereto through a second plurality of holes in the combustion apparatus liner. Parallel fuel injectors supply fuel into the respective zones and include a wide angle fuel flow nozzle that supplies fuel to the pilot zone of combustion and a narrow cone fuel injector that directs fuel through the pilot zone without combustion and into a downstream main combustion region where the fuel is then burned with air flow though the second plurality of holes to produce a staged combustion of air fuel in the combustion apparatus to achieve high combustion efficiency over a broad ange of fuel/air ratios as well as more uniform combustor outlet temperatures and low smoke output.

Abstract: A method for effecting combustion of carbonaceous fuel is operative to sustain the combustion at a predetermined rate or rates of total fuel demand, the fuel being distributed between two combustion stages to make up the required total feed rate. Thus one portion, usually about 20-70 percent, of the total fuel is fed to a thermal combustion stage. Sufficient air is supplied simultaneously to the thermal combustion stage, preferably about 125 to 185 percent of the stoichiometric amount of air, to effect substantially complete combustion of that portion of the fuel and produce a heated effluent. An additional amount of relatively cool air is mixed with this effluent, and the resulting cooled mixture continues through the mixing zone, the additional air being sufficient to inhibit preburning of the remaining portion of the fuel which is added downstream in the mixing zone.

Abstract: A liquid and/or gaseous fuel is burned in a tubular combustion chamber which has at least one baffle wall therein with a central aperture therethrough, comprises directing the fuel into the combustion chamber in a stream adjacent the baffle so as to cause it to flow through the aperture of the baffle and directing combustion air into the combustion chamber around and substantially parallel to the fuel stream so as to cause a portion of it to be directed against the baffle plate and whirl around adjacent the aperture and a further portion to pass directly through the aperture and into the whirling stream so as to provide a turbulent air stream which intermixes with the fuel both downstream and upstream of the baffle, igniting the fuel and air as it intermixes, and directing a separate combustion air stream into the intermixed fuel and combustion air on the opposite downstream side of the baffle.

Abstract: This invention refers to a burner for fluid fuels comprising an essentially cylindrical burner housing having an open end and a closed end, the open end being connectable to an exhaust pipe, a fuel supply means in the closed end in the longitudinal center axis of the housing, a combustion air supply passage in the peripheral wall of the housing, a tubular combustion chamber arranged co-axially within the housing, an annular space between said combustion chamber and the inner peripheral wall of the housing an annular space, said space being closed towards the open end of the housing, said air supply passage opening into said annular space.

Abstract: A combustor for use in a gas turbine engine is provided with a first wall defining a combustion zone; an outer casing partially defining a cooling plenum about the first wall; a second wall spaced apart from the first wall and defining together therewith a second plenum, the second wall bearing a plurality of perforations for passing fluid from the first plenum in impinging streams upon the first wall; and a plurality of ribs extending between the first and second walls and compartmentalizing the second plenum. The ribs add substantial stiffness to the combustor as well as providing for independently controlled cooling of the substantially isolated compartments formed thereby. The impinging streams provided by the perforations in the second wall substantially increase local fluid velocities and conductive heat transfer.

Abstract: A laser combustor apparatus for a chemical laser including an injector and transition manifold wherein the injector has a barrier area located between the oxidizer plenum and fuel plenum and a coolant area is located between the fuel plenum and a porous injector face plate, said barrier area and coolant area being connected by a restricted passage to control the pressure in the barrier area maintaining it higher than that in the oxidizer or fuel plenum. The combustor and manifold form a T-shape and have a liner fixed therein with a spaced relationship into which a diluent is placed for a purge thereof to keep combustion products from getting behind the liner.

Abstract: The metallic gas-burner of the invention comprises a central fire-tube constituting a mixing and combustion chamber into which is admitted a fuel-gas and a gaseous combustion agent from an annular air-box surrounding the fire-tube.The fuel-gas is supplied at a low pressure into the rear of the fire-tube and the gaseous combustion agent is distributed at a low pressure into the fire-tube, in the form of at least three main flows from the rear to the front of the tube, the second and third flows being provided in counter-rotation relationship.

Abstract: A steam generating apparatus which includes a novel gas burner and consisting of a pair of spaced coaxial cylinders, the outer of which is of considerably greater axial length than the inner and both of which are provided with apertures for admixing the gas with air. The inner cylinder functions as an integral pilot burner which is highly stable. The steam generating apparatus heats water to provide steam, heats it still further, then condenses the steam into liquid to assist in the formation of still more steam.

Abstract: A fuel burner diffuser comprises a frustoconical support fitted at its smaller diameter end to a fuel burner nozzle from which fuel is emitted in a conical stream. A plurality of series of gas jets are carried by and spiral about the support for introducing combustion-supporting gas into the fuel stream. The jets are mounted on the support in such manner that gas passing through the jets is substantially perpendicular to the longitudinal axis of the fuel stream so as to facilitate penetration of the fuel stream by the gas. Those jets which are substantially diametrically opposed to one another are circumferentially offset so as to avoid diametrical confrontation for the purpose of promoting better mixing of the fuel and gas. The cross sectional areas of the jets increase in a direction away from the fuel burner to enable a greater quantity of gas to be supplied to the fuel as the cross sectional area of the fuel stream increases.

Abstract: A simple and highly efficient fuel handling and combustion system and method are provided. The system includes preheating coils surrounding a perforated outer secondary air cylinder and a perforated inside fire control cone, in which combustion occurs. After flowing through the preheating coils, the fuel is compressed in at least one compression chamber before being released to the interior of the inside fire control cone through a spud orifice. Air mixes with the fuel only after the fuel is released from the spud. Substantially 100% combustion is achieved.

Abstract: New combustors, and methods of operating same, which produce lower emissions, particularly lower emissions of nitrogen oxides and CO. Means and methods are provided for supplying separate streams of air to primary and secondary combustion regions of a combustor, and expanding combustion products when passing same from said primary combustion region to said secondary combustion region. In preferred embodiments, unheated air can be used in said primary combustion region, and/or a second stream of air mixed with said combustion products during said expansion thereof.

Abstract: A combustion chamber with an evaporator that projects into the combustion zone of the flame tube and includes a coaxial channel and to which air and fuel are supplied separately; a deflection surface is thereby arranged at the end of the evaporator channel which deflects the fuel/air mixture on all sides essentially opposite to the main flow direction prevailing in the channel; an annular channel partly surrounding the evaporator channel adjoins the deflection surface which is in communication by way of discharge openings with a mixing zone disposed upstream of the combustion zone, as viewed in the main flow direction; the mixing zone is formed by an annular space between an outer wall of the evaporator and an intermediate wall of the flame tube, in which are arranged radial webs within a first and a second plane, whereby the discharge openings of the annular channel terminate between the radial webs.

Abstract: A multiple-jet orifice for the gas burner of a directly fired air heater of the non-premix type. The orifice openings are formed by radial slots in the periphery of a thin metal disc clamped between the end of a gas inlet pipe and a thicker metal disc member of special configuration. This specially configured disc member is larger in diameter than the gas inlet pipe and also larger in diameter than the slotted orifice disc. The portion of the member which is in contact with the slotted orifice disc is flat while the portion of the member larger than the slotted orifice disc is contoured outwardly in a convex manner. This convex surface by means of the Coanda effect causes the gas jets as emitted from the slotted orifice disc to flow into a conical shaped pattern and promotes the mixing of the gas with air and recirculated products of combustion.

Abstract: Laminated material comprises two spaced sheets, one having perforations and one being plain, the sheets being connected by heat conductive portions. Cooling fluid is passed through the perforations, impinges on the plain sheet and then passes between the sheets to discharge from the end of the laminate.

Abstract: A low emission combustion chamber in which vitiated products of combustion from a pilot burner are caused to swirl about the combustion chamber axis before fuel droplets are introduced into the vitiated, swirling combustion products for flash vaporization therein to produce a vaporized, swirling, vitiated fuel-air mixture so as to effect ignition lag until swirling combustion air can be mixed with the swirling mixture to molecularly premix the fuel and air and increase its oxygen content to reduce the ignition lag to effect autoignition at an equivalence ratio less than 1 so as to effect high-rate, lean burning in the primary combustion chamber.

Abstract: A fuel combustion apparatus of a double-shell construction in which the inner shell is composed of an upstream small-diameter section, a downstream large-diameter section, and a conically-shaped connecting section between the two sections of different diameters, all the sections being aligned and connected together on a common axis. Fuel injection valve and a first air supply port equipped with swirl blades surrounding the valve are provided at the upstream end of the small-diameter section of the inner shell. The cylindrical wall of the small-diameter section is not formed with any air supply port, but second air supply ports shrouded with scoops are formed in the cylindrical wall portion of the large-diameter section close to the small-diameter section. On the upstream side of the first air supply port is installed means for controlling the rate of air supply to the same port.

Abstract: Combustion chamber comprising a first combustion zone opening into a wider second combustion zone into which the combustion air is admitted through a practically frontal air entry comprising obstacles which impart a coefficient of blocking of about 60% to 80% to it. The first zone is supplied with air and fuel in substantially stoichiometric proportion in idling. At the other running rates, a supplementary fuel flow is injected into the chamber and burns in the second zone in the wake of the obstacles.

Abstract: A fuel combustor comprises a chamber with air and fuel inlets and a combination gas outlet. The fuel is supplied to a vaporization zone and fuel and air are mixed in a pair of mixing chambers each exemplified by a swirl can and the resultant mixture is directed into a combustion zone within the combustor. Combustion products are exhausted, for example, into a turbine inlet.Heat pipe means, in this case comprising a pair of heat pipes for each swirl can, are arranged each pipe with one end portion substantially in the combustion zone and the other end portion in the vaporization zone of its appropriate mixing chamber. By use of the heat pipe means some of the heat of combustion is carried back upstream into the swirl cans, to vaporize the fuel as it enters the vaporization zone in the swirl can, thereby improving vaporization and fuel mixing. Fewer pollutants are formed and complete combustion is assisted because of the improved fuel vaporization and better mixing.

Abstract: A variable flow air controller for a gas turbine engine combustor has a rotatable band including a first plurality of slots formed therein that overlie a plurality of primary air admission slots in the combustor wall circumferentially therearound and directed radially into a primary combustion zone. The slots are arranged to form an open junction therebetween which shifts axially along the combustor assembly upon rotation of the band thereby to control the point of admission of primary air into a combustion apparatus for completing combustion at preselected positions downstream of a liner dome in accordance with engine operation.

Abstract: A low emission combustion chamber in which vitiated products of combustion from a pilot burner are caused to swirl about the combustion chamber axis before fuel droplets are introduced into the vitiated, swirling combustion products for flash vaporization therein to produce a vaporized, swirling, vitiated fuel-air mixture so as to effect ignition lag until swirling combustion air can be mixed with the swirling mixture to molecularly premix the fuel and air and increase its oxygen content to reduce the ignition lag to effect autoignition at an equivalence ratio less than 1 so as to effect high-rate, lean burning in the primary combustion chamber.

Abstract: 1.

Abstract: A combustion chamber for gas turbine engines or power plants having devices for the gaseous processing of the fuel which is introduced therein, characterized by the combination of the following features:A. The fuel ejection cone of at least one fuel nozzle arranged upstream of the flame tube back wall of the combustion chamber extends exteriorly along the flame tube backwall, the latter of which is conically shaped in conformance with the ejection cone;B. The combustion chamber has an air infeed hood essentially encompassing at least partially the flame tube backwall as well as the fuel nozzle, forming an annular or ring channel narrowing in the direction of the downstream end of the flame tube backwall and which, by means of plurality of apertures located immediately behind the flame tube backwall in the side walls of the flame tube, is in communication with the interior of the flame tube.

Abstract: Integration of separate ceramic parts and metal parts to form a unified combustor is described. The flame holding portion and any other portion where air is introduced into the combustor are made of metal while insulated, imperforate ceramic construction is used for the balance of the combustor liner. In this manner the regions of high local stress are accommodated by cooled metal and the regions of uniform thermal stress are accommodated by resiliently-mounted thermally-insulated ceramic.

Abstract: A burner for heating an airstream is disposed in the airstream and has four identical walls which are secured together along their sides to form a tapered combustion chamber, the small end of which is located upstream. An axially extending gas pipe opens into the small upstream end of the combustion chamber and through this pipe a combustible gas enters the combustion chamber. Combustion air from the airstream enters the tapered chamber through apertures in the walls and the mixture so formed is ignited, resulting in a self-sustaining flame. A flame probe, which extends through the axial supply pipe and into the combustion chamber for a substantial distance, senses the flame regardless of whether it is high or low. The combustion chamber walls bulge inwardly intermediate there sides to insure that the combustion air reaches the center of the combustion chamber and mixes thoroughly with the combustible gas. A shroud surrounds the combustion chamber walls and has a metering inlet which opens upstream.

Abstract: NO.sub.x produced by combustion of nitrogen-containing fuels is reduced by a forced draft burner operating with below stoichiometric mixtures of air and fuel in a primary combustion chamber, combustion being completed by controlled injection of secondary air near the outlet of the chamber.

Abstract: NOx formation in a fixed geometry burner is minimized during steady state operation of a gas turbine engine by burning homogenous gaseous fuel and air mixtures in successive combustion stages of controlled duration and temperature determined by fuel to air ratios proximate the lean limit for combustion. When combustion is substantially complete in each stage NOx, formation is further inhibited by quenching the combustion temperature with comparatively cool air or the lean mixture for the next successive stage.Nox formation is effectively minimized during acceleration by supplying fuel to the combustion stages in sufficiently rich mixtures to consume all the available oxygen and to effect comparatively cool combustion temperatures.

Abstract: A hot gas generator for the production of hot combustion gases includes a cylindrical combustion chamber having an inner and an outer air conduit concentrically disposed thereabout. A fuel nozzle means is arranged at one longitudinal end of the cylindrical combustion chamber and an exhaust port is arranged at the other longitudinal end thereof. A baffle plate is disposed on the longitudinal end of the cylindrical combustion chamber on which the fuel nozzle means is arranged. Combustion air from a blower or the like flows through the outer air conduit into the inner conduit where it is heated by the cylindrical combustion chamber and then passes through openings in the baffle plate into the cylindrical combustion chamber.

Abstract: A combustor assembly includes a porous, laminated metal dome and an elongated tubular body portion disposed vertically within an air supply plenum. The dome and body portion are joined by a yieldable ring and a plurality of radially inwardly directed convolutions on one end of the body portion. A load support member is telescoped over the upper end of the dome and includes a tubular axial extension with a plurality of radially inwardly directed convolutions connected to the body portion and wherein the support member includes a plurality of radially outwardly directed spider arms extending from a support flange on the upper end of the support member secured to a fixed fuel nozzle pad whereby the porous laminated metal dome is supported for free flex movement with respect to the pad during combustor operation.

Abstract: New combustors, and methods of operating same, which produce lower emissions, particularly lower emissions of nitrogen oxide and CO, are provided. Means and methods are provided for supplying separate streams of air to first and second combustion regions of a combustor, and expanding combustion products when passing same from said first combustion region to said second combustion region. The combustors of the invention are characterized by the relatively small volume of said first combustion region as compared to the total volume of said first combustion region and said second combustion region; and methods and means provided for introducing first and second streams of air to said first and second regions, respectively. In some embodiments of the invention unheated air is used in the first combustion region. In other embodiments of the invention heated air is used in said first combustion region.

Abstract: New combustors, and methods of operating same, which produce lower emissions, particularly lower emissions of nitrogen oxides and CO, are provided. A first stream of air is introduced, either radially or axially, to a first combustion region of the combustor. A second stream of air is introduced tangentially into said first combustion region. A third stream of air is introduced tangentially into a second combustion region of the combustor. The amount of said first stream of air admitted to the first combustion region is varied in accordance with the fuel flow to said first combustion region.

Abstract: A porous laminated sheet adapted to be cooled by air flowing through the sheet from a rear face to a front face and to discharge the air through outlets in the front face at an angle to the normal to the surface. It is particularly adapted for use as a wall of a combustion liner. The sheet has a front layer with grooves leading to outlets from the front layer and has a rear layer defining channels from the exposed face of the rear layer into the grooves.

Abstract: A high velocity gaseous fuel burner has a casing with an inlet end into which air is blown to an outlet end in the form of a nozzle. Within the casing but circumferentially spaced therefrom is an elongated combustion tube into the rear end of which a main burner unit projects a fuel/air mixture. The outlet end of the tube reaches to or into the nozzle and the air blown through the casing passes over the combustion tube, some air passing into the tube through apertures in its wall. A boost burner unit may be mounted through the walls of the casing and tube to project a fuel/air mixture axially towards the casing nozzle to produce further combustion beyond the tube outlet. Valves are provided for controlling the flow of fuel and air to the two burner units jointly and/or separately.

Abstract: The combustion section of the gas turbine is comprised of an engine casing receiving compressor discharge air and housing a plurality of combustion chamber assemblies having removable inner center liners. The combustion chamber assemblies are comprised of an outer liner having an end wall in which fuel injectors are mounted and the removable inner center liner extending within the outer liner from the end wall to define an annular combustion chamber space adjacent the end wall.

Abstract: The disclosure of this invention relates to a gas turbine engine combustion chamber including a flame tube having holes closed by a filling of a material of lower melting point than the flame tube material so that if in operation the temperature of the tube exceeds that of the filling the latter melt and cooling air can enter the tube through the holes.

Abstract: A combustion liner for a gas turbine combustion apparatus has a wall of ceramic material. To minimize destructive thermal gradients in the ceramic material due to local cooling by air entering the liner through ports for combustion or dilution air, the walls of these ports are isolated from the entering air by a lining for the port, either a coating applied to the wall of the port or a metal or ceramic sleeve extending through the port.

Abstract: A combustion liner for a gas turbine combustion apparatus or the like has a head wall and a side wall extending downstream to an outlet for combustion products. A reaction zone is contained within the upstream end of the side wall and a dilution zone downstream. A barrier ring extends inwardly from the side wall to provide a constricted path between the zones. Combustion air is admitted from a cluster of nozzles in the head wall and a ring of nozzles extending forwardly from the side wall. Each nozzle in the head wall is axially aligned with one of the nozzles in the side wall so that air jets entering into the combustion zone through each such pair of nozzles impinge to create a high degree of turbulence. Fuel is jetted against a spatter plate in each nozzle in the head wall so that the fuel is atomized and entrained by the air flowing through the head wall air nozzle.

Abstract: A device for increasing combustion stability in a combustion chamber wherein the combustion chamber has a plurality of openings or apertures in the wall thereof, with each aperture having a swirl device therein to swirl gases passing through the apertures in either direction. A solid cylindrical wall extends around said combustion chamber to form a backing volume therebetween.

Abstract: In the use of combustion apparatus with hot gas turbines it is desirable to e able to efficiently burn fuel at widely ranging rates (pounds per hour) in accordance with varying demands on the turbine. The present invention proposes a combustor wherein stable combustion is achieved over a wide range of fuel flows. Combustion air is introduced as a circumferential swirl around the sprayed fuel to promote a high tangential velocity and low core velocity.

Abstract: A low emission combustion chamber in which vitiated products of combustion from a pilot burner are caused to swirl about the combustion chamber axis before fuel droplets are introduced into the vitiated, swirling combustion products for flash vaporization therein to produce a vaporized, swirling, vitiated fuel-air mixture so as to effect ignition lag until swirling combustion air can be mixed with the swirling mixture to molecularly premix the fuel and air and increase its oxygen content to reduce the ignition lag to effect autoignition at an equivalence ratio less than 1 so as to effect high-rate, lean burning in the primary combustion chamber.

Abstract: Apparatus for supplying air and fuel to a flame tube of a combustion chamber of a gas turbine engine which includes primary air supply ports for supplying air under high pressure toward the center of the flame tube and fuel tubes projecting into and opening at the primary supply ports for admitting fuel for entrainment by the primary air as it passes through the primary supply ports. In certain preferred embodiments, an annular member forms a supply port, as well as a mounting arrangement for fuel tube. Preferred embodiments also include deflector baffles or plates for preventing flow of fuel from the fuel tubes into portions of the air being supplied as secondary air to the combustion chamber.

Abstract: New combustors, and methods of operating same, which produce lower emissions, particularly lower emissions of nitrogen oxides.