Abstract: The combustion chamber is characterized by an annular-cylindrical space, which consists of two reaction chambers (8), arranged at the end, and a collision chamber (12) placed therebetween. The reaction chambers (8) are fitted at their face-sided ends with a number of burner elements (A, B), arranged axially parallel, their number depending on the output of the combustion chamber, which burner elements are in each case mirror-symmetrical to each other in relation to the central axis of the collision chamber (12). From the collision chamber (12), an annular mixing chamber (15) goes off to the turbine inlet (17). Each burner element (A, B) is provided with a twist member (6, 11), which in each case is orientated in opposed sense of rotation compared with the mirror-symmetrically arranged twist member.

Abstract: A combustor for a gas turbine engine. The combustor employs an array of fuel injectors arranged across and in the mouth plane of the combustor flame tube. Each injector has a baffle plate through which the injector nozzle projects, the baffle plate having axial holes for atomization air to intercept and atomize radial fuel jets from the injector nozzle. Cooling of the flame tube is performed by full coverage impingement and effusion without disturbing the cooling film by entry and penetration of transverse air jets. Flame stabilization is achieved under all required operating conditions by the radial-fuel/axial-air atomization in conjunction with the baffle plates. Comprehensive combustion mixing and dilution is achieved by the uniformly distributed supply of up to 90% of the total air supplied to the combustor around and through the baffle plates.

Abstract: A gas turbine engine has an annular combustor structure which includes a plurality of annularly displaced combustion zones. A fuel nozzle is positioned in each combustion zone for supplying fuel thereto. A swirler is supported on each of the fuel nozzles and includes a plurality of angularly-directed passages for causing a swirling action of the air entering the combustion chamber through the nozzles. The swirlers are associated in pairs, each of the swirlers of each pair including a tab extending radially outwardly. When air is supplied through the angularly-directed passages, the swirlers are urged in a direction which brings the tabs of each pair into engagement with each other and thereby limits further rotational movement of the swirlers.

Abstract: The fuel distributing and metering assembly provides separate multiple metered fuel flows from a common fuel reservoir by including a rotary valve having multiple valve metering slots for generating separate multiple fuel flows, a valve seat having multiple seat orifices relative to which the valve metering slots are moved for metering the multiple fuel flows, and multiple fuel discharge paths for conducting multiple fuel flows to each of a plurality of fuel injection devices. Each fuel discharge path to each fuel injection device includes multiple upstream transversely spaced discharge passages and multiple downstream discharge passages nested longitudinally one inside the other with the inner downstream discharge passage aligned beneath its associated upstream discharge passage and another downstream discharge passage therearound being transversely displaced relative to its associated upstream discharge passage.

Abstract: In a gas turbine apparatus of a premixed gas combustion type, a plurality of fuel supply systems are provided for supplying fuels to a combustion chamber of the gas turbine apparatus after the fuels are mixed with a high-pressure air, and the supply of fuels from the plurality of fuel supply systems is controlled according to programmed patterns which are predetermined for the fuel supply systems. According to a variation of the turbine load, the patterns of fuel supplies are executed in a transferred manner at a number of transfer points along a variation of the turbine load, with equal amounts of fuel reduced and increased stepwisely in the precedingly and subsequently executed patterns at each of the transfer points.

Abstract: A combustion chamber is defined by a wall having a closed end into which liquid fuel and oxidant are introduced and an open end through which exhaust gases flow. A baffle at the open end causes exhaust gas to flow adjacent the wall. Injector devices direct liquid fuel radially inwardly of the chamber between the closed and open ends. Unburnt fuel attached to the wall cools the walls and passes to the open end before being entrained by the exhaust gas flow through the baffle.

Abstract: In a combustion chamber having a flame tube therein at an annular gap from a housing of the chamber, a burner apparatus including at least one pilot burner near an end face of the flame tube for generating a pilot flame from natural gas and/or heating oil, an air supply channel surrounding the head of the pilot burner, a premixing device for natural gas in the form of a ring channel system surrounding the head including flow conduction walls defining an inflow cross section at an air inflow side of the ring channel system open toward the annular gap for conducting a majority of combustion air from the annular gap to a combustion zone developing downstream of the burner head in the flame tube, the combustion air having flow vectors with components entering the combustion zone in directions from parallel to the burner axis to an acute angle to the burner axis, the combustion air components having swirl components superimposed thereon tangentially relative to the burner axis acting as a swirl center, a multiplic

Abstract: The present invention relates to combustion apparatus for gas turbine engines.An annular combustion chamber of a gas turbine engine comprises an upstream wall formed from a single metal skin. The upstream wall has a plurality of equi-spaced apertures, and a convergent/divergent pot is positioned coaxially with each aperture and extends in an upstream direction therefrom. Each convergent/divergent pot has a radial swirler assembly positioned a its upstream end to supply air into the convergent/divergent pot. A fuel injector is aligned with each convergent/divergent pot and radial swirler assembly to supply fuel into the convergent/divergent pot. A plurality of annular air scoops extend in an upstream direction from the upstream wall, and each annular air scoop is positioned coaxially around a convergent/divergent pot to supply air to the radial swirler assembly. The downstream end of each convergent/divergent pot has apertures for supplying cooling air over the downstream face of the upstream wall.

Abstract: Combustion equipment e.g. for a gas turbine engine comprises an annular flame tube having air inlet openings fitted with respective air swirler devices surrounding respective fuel atomizers. Flare portions define an annular flare in which the atomizers and swirler devices are provided. To reduce the formation of a liquid fuel film on the wall of the flame tube, dividing means in the form of a smaller flare is provided for dividing the air flow through each of the swirler devices so as to create a fuel-free film of air adjacent the annular flare.

Abstract: A premixture of compressed air and gaseous fuel is supplied and conbusted into a head combustion chamber of a combustor for gas turbine and main combustion of lean, low flame temperature is carried out in a rear combustion chamber following the heat combustion chamber to prevent the formation of high flame temperature which tends to promote NOx generation.

Abstract: A low pressure loss injector element A is disclosed for the main combustion chamber of a rocket engine which includes a lox post (40) terminating in a cylindrical barrel (50). Received within the barrel (50) is a lox plug (46) which is threaded in the lox post and includes an interchangeable lox metering sieve (60) which meters the lox into an annular lox passage (56). A second annular gas passage (62) is coaxial with the annular lox passage (56). A cylindrical sleeve (64) surrounds the annular gas passage (62) and includes an interchangeable gas metering sieve (77) having metering orifices through which a hot gas passes into the annular passage (62). The jets which emerge from the annular lox passage and annular gas passage intersect at 80 which is recessed away from the combustion area. Thus, mixing and combustion stability are enhanced.

Abstract: Combustion equipment for a gas turbine engine operating on the pre-mix lean combustion bases comprises a flame tube having a plurality of alternately arranged main and pilot air ducts each having a respective fuel injector and receiving axially directed air from downstream of part span outlet guide vanes. The fuel and air in each duct are substantially pre-mixed before entry into the flame tube and the outlets of the pilot ducts direct the fuel and air mixture into the recirculation zone in a single vortex. At engine idle the air fuel ratio (AFR) is substantially stoichiometric to prevent the formation of unburnt hydrocarbons (UHC) and carbon monoxide (CO). As the engine accelerates the fuel flow to the pilot air ducts remains near constant so that the AFR in the re-circulation zone progressively weakens, and fuel is introduced into the main air ducts, the outlets of which direct the air fuel mixture into the flame tube with a substantial downstream component.

Abstract: A fuel supply method for a gas turbine combustor having first and second stage combustion chambers. The method comprises supplying the fuel from only first stage fuel supply from the start of the gas turbine until its low output range so as to operate only the first stage combustion chamber, supplying the fuel from both first and second stage fuel supply in a high output range of the gas turbine including its maximum output so as to operate both first and second stage combustion chambers. The method makes it possible to reduce NO.sub.x without deteriorating the combustion performance by step-wise supplying a predetermined flow rate of the fuel when the second stage fuel is to be supplied and at the same time, step-wise reducing the same quantity of the fuel that is being supplied from the first stage fuel supply.

Abstract: A catalytic combustor comprises a pilot zone having means to introduce fuel therein; upstream of said pilot zone and communicating therewith a catalytically supported thermal combustion zone comprising a plurality of catalytically supported thermal combustion sections each comprising a solid oxidation catalyst, means for introducing air into said section and means to introduce fuel into said section; and means to control the rate of fuel flow in each of the means to introduce fuel into a catalytically supported thermal combustion section and the means to introduce fuel into the pilot zone. The combustor is operated by staging the fuel supply in order to maximize the amount of combustion in the catalytically supported thermal combustion zone and minimize NOx emissions under all load conditions.

Abstract: A segmented, zoned fuel injection system for use within the entrance area of a combustor. The fuel injection system has a plurality of spray bars formed as part of closely-spaced apart segments. The spray bars are zoned to permit additional control of profile and flow rate of fuel injected into the combustor. This design permits radial profile control within the combustor, maintains higher efficiency at low fuel flows and easy replacement and/or maintenance of the components thereof.

Abstract: A swirler for use in combustion chambers in which the vanes of the swirler are partially unshrouded to improve the mixing of fuel and air.

Abstract: A gas turbine engine is provided with an improved fuel system that features a fuel manifold with a primary and secondary fuel flowpath circumventing a combustor section of the engine. The manifold is formed with a double-walled construction for the purpose of withstanding high temperatures or fires around the combustor section and, additionally, to provide a secondary flowpath for draining any fuel leakage from the manifold. The two walls of the manifold include an inner wall that encloses the primary fuel flowpath through the fuel system. A concentric outer wall encloses the inner wall and protects the primary fuel flowpath. The double-walled system is made possible with a unique manifold assembly utilizing double-walled manifold segments that interconnect fuel flowpaths through fuel injector base sections. When assembled, these parts connect together to form an integral double-walled fuel manifold assembly.

Abstract: A dual fuel injector for a gas turbine engine is arranged to maintain pre-determined air fuel ratios in adjacent upstream and downstream opposite handed vortices and to reduce the deposition of carbon on the injector. The injector comprises a central duct, a deflecting member, a first radially directed outlet, and a shroud which defines an annular duct, and a second radially directed outlet. The ducts receive a supply of compressed air and the central duct receives gaseous fuel from an annular nozzle and the annular duct receives liquid fuel from a set of nozzles.When the injector is operating on liquid fuel, the fuel and air mixture issues from the second outlet and compressed air flows from the first outlet and prevents migration of fuel between the two vortices, thereby maintaining a rich air fuel ratio in the upstream vortex which reduces the emissions of NOx. Also, the flow of air from the first outlet reduces the deposition of carbon from the liquid fuels on the deflecting member.

Abstract: 1. Combustion apparatus comprising a duct for containing a flow of air and including an air-fuel mixing device comprising an assembly of transversely spaced longeron members which extend along the duct and are inclined to the general direction of flow through the duct and to the walls of the duct so that a major portion of the flow through the duct will pass through the spaces between the longeron members, each longeron member having longitudinal edges adapted in operation to shed continuous vortices and a baffle extending across the upstream end of the longeron members and forming behind it a sheltered pilot combustion zone, and means adapted to generate pilot vortices of combustible mixture in the pilot zone, to cause each pilot vortex to divide, and to direct the divided portion of each pilot vortex to pass downstream along adjacent parts respectively of adjacent longeron members.

Abstract: A gas turbine combustor arrangement involves two combustion chambers separated by a necked down throat portion with provision for fuel introduction into each of the chambers. Initially, fuel is introduced into the first chamber and ignited. Thereafter, fuel is introduced into the second chamber until the total fuel flow to the combustor is at the desired rate. Burning in the first chamber is then extinguished by shifting fuel flow to the second chamber and after burning termination, the fuel distribution is reversed until a low emission operation is realized. Apparatus for carrying out the foregoing method and a high load ingition system is also disclosed.

Abstract: Improvement to the starting characteristics of an annular combustor for a gas turbine engine that employs dual fuel nozzles (primary and secondary fuel flow systems) by redistributing the total fuel admitted to the nozzles in an asymmetrical pattern to deliver the requisite amount of fuel to the igniter by the primary flow system feeding fuel to that igniter.

Abstract: An improved prechamber and fuel manifold structure for a gas turbine engine having a premixing-prevaporizing type combustor, the improvement residing in the provision of a prechamber having an internal cylindrical surface swept by swirling pressurized air passing through the prechamber from a plenum to the combustor and in the provision of a fuel manifold having a plurality of individual fuel conduits extending from a remote fuel supply pipe to a corresponding plurality of delivery heads in the prechamber. The delivery heads direct fuel generally tangent to the internal cylindrical surface to form a film for vaporization in the passing air and the length of the fuel conduits and the flow areas of the fuel conduits and the delivery heads are generally equal so that fuel flow in the fuel conduits is balanced and so that when the conduits are opened to atmospheric pressure at termination of combustion, purging of residual fuel to foreclose coking is rapid and complete.

Abstract: A method comprising injecting a primary fuel and air into a furnace to burn the fuel and form a first-stage combustion zone, the fuel being diluted with surrounding combustion gas and the air being supplied at a rate in excess of the stoichiometric rate required for the combustion of the fuel, and injecting a secondary fuel into the furnace around or downstream of the first-stage zone at a range approximately equal to the stoichiometric rate required for the consumption of the excess oxygen resulting from the combustion in the first-stage zone the fuel being diluted with surrounding combustion gas and to form a second-stage combustion zone around or downstream of the first-stage zone.

Abstract: A burner construction for low emission burners in which the primary fuel is injected with air in an annulus into the upstream end of the burners so as to cause a significant recirculation of the fuel and air mixture adjacent to the end cap, the secondary fuel is injected into the burner in a small angle spray at a point substantially spaced from the end cap and large combustion and/or dilution holes in the burner wall a small distance upstream of the secondary nozzle are sized to produce an additional recirculation in the primary fuel and air around the secondary nozzle with this additional recirculation in the direction opposite to the first recirculation.

Abstract: A combustion chamber of the type employing staged combustion principles is disclosed. Effective control of undesirable pollutants is sought over a wide range of operating power levels. A specific objective is to separate staged combustion zones without the penetration of structural apparatus into the chamber. Single site fuel injection is desired.Primary fuel premixing tubes (34) and secondary fuel premixing tubes (38) terminate at the front wall (32) of the combustion chamber (30). The primary fuel premixing tubes have highly angled discharge swirlers at the downstream ends thereof. The highly angled swirlers (66) cause the fuel/air mixture emanating therefrom to burn in close proximity to the front wall. The secondary fuel premixing tubes have lowly angled discharge swirlers, or no swirlers at all, so as to cause the effluent therefrom to penetrate the region at which primary combustion is taking place without significantly influencing the fuel/air ratio at the primary combustion site (P).

Abstract: Combustion apparatus of the premix/fuel lean type which employ jet induced circulation to inhibit the formation of atmospheric pollutants.

Abstract: A fuel distribution system for regulating split of fuel flow between a pilot nozzle system and a main nozzle system for a combustor includes a flow network for directing fuel from a main fuel metering valve into an unrestricted line to a small pilot nozzle orifice producing a fine fuel spray pattern at low fuel flow rates and further including a fuel splitter valve interposed between the outlet from the fuel metering valve and a fuel conduit connected to a main fuel nozzle of increased orifice size to atomize higher rates of fuel flow thereto and wherein the fuel splitter valve includes an electrically energizable component that receives a control signal of desired pilot fuel/air ratio generated by a controller in part utilizing a signal of total actual fuel flow and total actual air flow to produce the control signal to control operation of the splitter valve so as to regulate the amount of fuel flow to the main nozzle system in accordance with the control signal thereby to produce a residual flow of fuel to

Abstract: The invention relates to a fuel system for a gas turbine engine wherein an annular combustion chamber 10 has an annular series of pairs of first and second nozzles 15,16. In one mode of operation fuel is supplied only to the first nozzles 15. In another mode, fuel is supplied also to the second nozzles. The change has to be made during operation of the engine. If the first and second nozzles had separate supply manifolds, the manifold pertaining to the second nozzles would have to be primed and purged respectively when initiating and terminating the use of the second nozzles. To avoid this difficulty the first and second nozzles are supplied by a single manifold 12 and the second nozzles are controlled by individual valves 21 situated close to the latter nozzles and operated collectively by a fluid pressure supply 26,27.

Abstract: A counter flow combustor has a generally elongated hollow cylindrical outer casing or shell with a closure means at the upper end defining a head space and a generally elongated smaller hollow annular inner casing or combustion wall mounted therein in spaced relation to the outer casing to form an annular head space extension between the side walls of the outer casing and the inner casing which is continuous with the head space. The inner casing or combustion wall defines a primary combustion zone, and a secondary combustion zone in communication at one end with the primary combustion zone and at the end remote therefrom with the discharge outlet for delivering combustion gases from the combustor. An inlet assembly is mounted in said head space for mixing fuel and air and for delivering the same in proper ratio for combustion in said primary combustion zone and secondary combustion zone.

Abstract: Combustion chambers for gas turbine engines and, more particularly, an annular combustion chamber. The combustion chamber comprises a flame tube having a back wall through which several vaporizers project into the flame tube or combustion zone. Each vaporizer has a pipe section extending within the flame tube, fuel supply and also supply ports in communication with the pipe section, and at least one outlet port for supplying a vaporous fuel-air mixture from the pipe section to the flame tube. Outlet ports of adjacent vaporizers are arranged spaced-apart from and facing one another, whereby a zone of maximum turbulence is formed between the outlet ports.

Abstract: A combustor assembly having improved performance at low engine power operation and at altitude relight includes an annular combustion chamber, two fuel sources, and a premixing passageway having an outlet positioned adjacent either the inner and outer annular well of the combustion chamber. A perforated baffle is disposed across the outlet of the premixing passageway, the outlet being in gas communication with the combustion zone. In a preferred embodiment, for low power operation, such as for idle or for altitude relight, fuel from a first source is sprayed directly into the combustion zone. During this low power operation a localized stagnation region is created adjacent the fuel source which acts as a continuous ignition source for the combusting fuel-air mixture within the combustion zone. For high power operation such as takeoff, climb and cruise, fuel from a second source is injected into the premixing passageway where it is atomized by air entering the passageway from the compressor.

Abstract: A fuel injection system for low emission burners in which the primary fuel is delivered in an annular spray into the primary combustion zone; at high power operation, secondary fuel is injected additionally in a low angle axial spray to penetrate beyond the primary zone and into the secondary combustion zone downstream of the primary zone.

Abstract: A combustion apparatus for gas turbine engines particularly adapted to reduce emissions to meet automotive requirements. The fuel is laid on the wall of a cylindrical prechamber and evaporated from the wall by combustion air which is introduced through a swirler at the upstream end of the prechamber. The inner surface of the prechamber is artificially roughened by a grid of grooves to improve fuel evaporation. The fuel is laid on the wall from an annular manifold extending around the upstream end of the prechamber through tangential orifices leading from the manifold into the interior of the prechamber. More air enters through entrance ports distributed around the prechamber toward its downstream end. The resulting lean fuel-air mixture is delivered past an annular flow dam at the outlet of the prechamber into a domed combustor wall forming a combustion or reaction zone which is abruptly enlarged from the prechamber.

Abstract: A combustion chamber arrangement for a gas turbine engine which can be annular or can-annular, though the annular arrangement is preferred, comprises in the annular form, an annular combustion chamber having in its upstream end a plurality of primary air inlets with associated swirling means, such as a ring of swirl vanes and a plurality of fuel injectors located in fuel injector apertures, the fuel injectors and primary air inlets being arranged so that at least two primary air inlets are located between any two fuel injectors, the primary air all being swirled in one direction so that the fuel from one injector is sheared in opposing directions by the swirling primary air from adjacent primary air inlets. Little or no air enters the combustion chamber in the region of the fuel injectors and any air that does enter in that region is not swirled.

Abstract: A high-temperature combustor for burning low-BTU coal gas in a gas turbine is described. The combustor comprises a plurality of individual combustor chambers. Each combustor chamber has a main burning zone and a pilot burning zone. A pipe for the low-BTU coal gas is connected to the upstream end of the pilot burning zone; this pipe surrounds a liquid fuel source and is in turn surrounded by an air supply pipe; swirling means are provided between the liquid fuel source and the coal gas pipe and between the gas pipe and the air pipe. Additional preheated air is provided by counter-current coolant air in passages formed by a double wall arrangement of the walls of the main burning zone communicating with passages of a double wall arrangement of the pilot burning zone; this preheated air is turned at the upstream end of the pilot burning zone through swirlers to mix with the original gas and air input (and the liquid fuel input when used) to provide more efficient combustion.

Abstract: Combustion equipment designed to reduce smoke levels and the production of nitrogen oxides has a fuel burner mounted in the upstream wall of a combustion chamber, the fuel burner comprising a central duct partially surrounded by an annular duct, each of the ducts having an array of swirl vanes at their upstream ends and fuel inlet apertures downstream of the respective arrays of swirl vanes. The fuel supply to each of the ducts can be controlled to apportion the fuel flow between the two ducts in dependence of an engine parameter, such as speed, so that at low speeds a majority of the fuel is injected into the annular duct while at higher engine speeds, a majority of the fuel is injected into the central duct.

Abstract: An improved combustor for a gas turbine engine is disclosed. Techniques for reducing the level of noxious pollutants emitted by the combustor are developed. In one embodiment, a combination of serpentine geometried, fuel-mixing tubes discharging to the radially outward area of the combustor and an axially oriented, fuel-mixing tube near the center of the combustor are adapted to generate a strong centrifugal force field within the combustor by swirling the fuel/air mixtures flowing therethrough. The force field promotes rapid mixing and combustion within the chamber to reduce both the magnitude of the combustor temperature and the period of exposure of the medium gases to that temperature. The tube at the center of the combustor is adapted to swirl the medium flowing therefrom in a circumferential direction counter to the direction in which the medium from the serpentine geometried tubes is swirled.

Abstract: This invention concerns an improved combustion chamber comprising two concentric sheet metal cases forming a space into which air is admitted. The air passes from the space to the interior of the chamber in primary, secondary, annular, and tertiary air flows. The fuel coming from lateral nozzles forms a flame which is directed at first toward the closed end, then turned back by the secondary air flow. The external case comprises two walls between which a cooling flow circulates. The invention thereby achieves reduction in atmospheric pollution from exhaust gases.

Abstract: A turbojet combustor and method for controlling nitric oxide emissions is provided by employing successive combustion zones wherein after combustion of an initial portion of the fuel in a primary combustion zone, the combustion products of the primary zone are combined with the remaining portion of fuel and additional plenum air and burned in a secondary combustion zone under conditions that result in low nitric oxide emissions. Low nitric oxide emissions are achieved by a novel turbojet combustor arrangement which provides flame stability by allowing stable combustion, which usually result in large emissions of nitric oxide in a primary combustion zone, to be accompanied by low nitric oxide emissions resulting from controlled fuel-lean combustion, ignited by the emission products from the primary zone, in a secondary combustion zone at a lower combustion temperature resulting in low emissions of nitric oxide.

Abstract: A gas turbine engine combustor assembly of unique configuration has an outer wall made up of a plurality of axially extending multi-layered porous metal panels joined together at butt joints therebetween by a reinforcing and heat dissipation ring and a unique weld configuration to prevent thermal erosion of the ends of the porous metal panels at the butt joints; the combustor further including a unique inner wall made up of a plurality of like axially extending multi-layered porous metal panels joined at butt joints by a reinforcing and heat dissipation ring on the inner surface of the inner wall panels and an improved butt weld joint that prevents thermal erosion of the ends of the porous metal inner wall panels.

Abstract: A combustion apparatus for a gas turbine engine comprises a combustion chamber having primary and secondary combustion zones, a fuel injector having a series of primary fuel nozzles and a series of secondary fuel nozzles, and primary and secondary fuel and air duct means to direct fuel and air mixtures to the primary and secondary combustion zones respectively.

Abstract: A combustion chamber for a gas turbine is provided with a prechamber connected at the input end of the flame tube. The dimensions of the flame tube and prechamber, and the location of the air inlet openings are selected so that the flame in the flame tube flashes back and burns as a stable rich flame in the prechamber when the turbine is in a high-load condition. The result is a variation in the combustion properties of the chamber which reduces pollutant emission levels over a wide range of engine load conditions.