Abstract: A fuel/oxidizer pre-mixing combustion chamber for a turbojet engine is disclosed in which the pre-mixing device is incorporated into the upstream end wall structure of the combustion chamber. The upstream end portion of the combustion chamber, which is in communication with the oxidizer, has a plurality of generally radially extending, "V"-shaped members oriented such that the vertex of the "V" shape faces in an upstream direction. These members extend generally radially between the inner and outer walls which define the boundaries of the combustion chamber. The members define upstream edges and downstream edges which are axially the upstream edges. Fuel injectors extend radially inwardly between these members and are axially positioned between the locations of the upstream and downstream edges so as to spray fuel onto the adjacent sides of each of the members.

Abstract: A thrust augmentor heat shield for enclosing radially extending fuel pipes which can be attached to and removed from the outer duct wall from within the augmentor. The heat shield includes a hollow, elongate housing extending substantially entirely along the length of the fuel pipe, a nose projecting forwardly from the housing and received within a slot formed in the duct wall and a bolt for clamping the housing to the duct wall and urging the nose of the housing into the slot. The housing includes an opening between the outer duct wall and the diffuser wall for conveying cooling air radially inwardly along the housing, and openings along lateral sides of the housing in registry with the fuel discharge ports of the fuel tube. The housing includes a diffuser flowpath segment such that, when the housings are arranged in a spoke pattern, the segments form a continuous annular wall joined by splined connections.

Abstract: A premixed combustor for a gas turbine, comprises, a combustion chamber for burning a fuel with an air therein, at least two premixed fuel/air mixture outlets which are juxtaposed with each other, and through each of which a premixed fuel/air mixture flows out into the combustion chamber, and a flow deflection member arranged between the premixed fuel/air mixture outlets, urging the permixed fuel/air mixture from one of the premixed fuel/air mixture outlets to go away from another one of the premixed fuel/air mixture outlets, and terminating in the combustion chamber so that the premixed fuel/air mixture from the one of the premixed fuel/air mixture outlets is permitted to move toward the premixed fuel/air mixture flowing out from the another one of the premixed fuel/air mixture outlets after going away from the another one of the premixed fuel/air mixture outlets.

Abstract: First and second premixed burners having annular injection slots are concentrically adjacent and the injection slots are substantially aligned with each other in a longitudinal direction of the burners. A pilot burner is provided substantially in the center of the annular first premixed burner so that the injection slot of the pilot burner is substantially aligned with the injection slot of the first premixed burner in a longitudinal direction of the burner. A flame holder which forms a circulating flow of combusted gas Gh downstream of the flame holder is disposed at the downstream end of a boundary wall between the premixed burners so that the flame holder is co-used by the premixed burners. Flow rate adjusting means for adjusting the flow rate of fuel supplied to the first, second premixed burner and the pilot burner, respectively are provided. The fuel can be substantially uniformly mixed with a combustion gas. Reduction in NOx and stabilization of premixed flame can be achieved.

Abstract: A liquid fuel power plant (100) including an open-ended combustion chamber (102) and a first mechanism (110) for delivering a combustible liquid fuel to the combustion chamber (102). A second mechanism (118) is included for delivering compressed air to the combustion chamber (102) to provide a pressurized air-fuel mixture. A third mechanism (130) ignites the pressurized air-fuel mixture in the combustion chamber (102) and a fourth mechanism (134) is provided for extending the length of the combustion chamber (102) for decomposing the pressurized air-fuel mixture to provide an exhaust gas comprised of fundamental elements. Finally, a fifth mechanism (142) is provided for using the exhaust gas to perform useful work. The air inlet line (116) delivers compressed air from a turbocharger (118) which is preheated in an air passageway (128) and thereafter mixed with the fuel in the combustion chamber (102).

Abstract: A variable geometry flame trap device for use in an after-burner device of a gas turbine, which is not exposed to deformation forces during its use in the after-burner mode. This is achieved with a plurality of flame trap plate pairs (21), positioned downstream of the turbine at the outlet of a primary air flow duct (9) and mounted so as to pivot on a plurality of diffuser arms (19) located at the outlet of a secondary air flow duct (7), characterized in that the plates (21) of each pair are made from a composite material and in that they have a cam projecting from their facing faces (42), said two cams (43) bearing on one another.

Abstract: A combustor includes inner and outer arrays of generally Vee-shaped, radially extending, circumferentially spaced gutters canted in a circumferential direction relative to one another to produce isolated concentric counter-rotating circumferentially directed flows downstream of the gutters. A lean premixed combustion mode is used at baseload operations. At non-baseload operations, particularly low-load operating conditions, a diffusion combustion mode is employed by direct fuel injection into air supplied to one of the isolated flow fields, preferably the radially inner flow field, to produce a stabilized, locally hotter flame, resulting in higher combustion efficiency and lower emissions than otherwise using a lean premixed combustion mode at the non-baseload operating conditions.

Abstract: This invention relates to air staged premixed dry low NO.sub.x combustors of the type that are constructed of a premixing chamber, a centerbody plug premixed flame stabilizer and a venturi modulated flow split. Such structures of this type maintain very low flame temperatures and, ultimately, low NO.sub.x emissions while still providing adequate cooling for the combustor.

Abstract: A burner comprises at least one swirl member for mixing a fuel with an air previously to burning of the fuel, and at least one eddy generating device which is arranged in a flow of a mixture of the fuel and air to generate an eddy flow in the flow so that the eddy flow maintains a shape of a flame of the burned fuel. The at least one eddy generating device is arranged apart from a downstream end of the swirl member by a fixed sufficient distance so that the shape of the flame maintained by the eddy flow is prevented from moving toward the downstream end of the swirler member.

Abstract: A combustion assembly includes a combustor having inner and outer pilot liners, each being in the form of a lobed mixer having outer and inner cold and hot chutes. A plurality of carburetors are joined to a dome disposed at upstream ends of the liners for providing a pilot fuel/air mixture for generating pilot combustion gases in the hot chutes. A plurality of fuel spraybars are disposed downstream from the carburetors and are aligned radially with the cold chutes for selectively injecting main fuel into main airflow for generating a main fuel/air mixture ignitable by the pilot combustion gases. In a preferred and exemplary embodiment of the invention, lean combustion gases are obtained for reducing NO.sub.x emissions in a relatively short residence time.

Abstract: A gas turbine combustor is provided with a premixer in which an oxidant and fuel is mixed and caused to flow to the combustion zone past two or more arrays of convex members positioned transverse or canted to the flow. The convex members introduce turbulence and include a plurality of openings to introduce one or more additional fuels into the premixed oxidant and fuel flow. Parallel, annular and radial arrays, or combinations thereof, may be provided. The downstream array is V-shaped in cross section and provides flame holding capability while the upstream array principally provides additional mixing of fuel and oxidant.

Abstract: Shrouds 22, 24 are welded to support braces 20 near fuel spray ring 12. A splash shield 30 is secured to shroud 22 toward which fuel 16 is sprayed. It extends between braces protecting the shroud 22 from fuel impingement. Cracking of the structure at the shroud-brace interface is avoided.

Abstract: A combustor includes spaced outer and inner liners defining therebetween a combustion zone, and having a plurality of circumferentially spaced tubular domes disposed between forward ends thereof. Each of the domes includes an annular inlet for receiving pilot airflow, a swirler having a tubular ferrule and primary swirl vanes for receiving the pilot airflow, and an outlet disposed in flow communication with the combustion zone. A pilot fuel injector is disposed in each of the domes for injecting pilot fuel into the pilot airflow for generating a pilot fuel/air mixture dischargeable from the dome outlet. A plurality of main fuel spraybars inject main fuel into compressed airflow channeled between the domes and the outer and inner liners for generating a main fuel/air mixture dischargeable concentrically around the pilot fuel/air mixture.

Abstract: A carburetion and combustion system is provided in which the carburetor discharges a combustible fuel/air mixture in a rotating swirl from a plurality of nozzles at one end of a cylindrical combustion chamber, and discharges a rotating helical swirl of high-velocity compressor air concentrically surrounding the combustion mixture from a second set of nozzles. The high-velocity air swirl confines the flame propagation away from the combustible chamber walls and provides the walls with an insulating layer against the combustion heat.

Abstract: A V-shaped afterburner flameholder for a gas turbine engine has a plurality of rectangular tabs coextensive with and lying in the planes of the flameholder sidewalls. The tabs on opposing sidewalls alternate so as to introduce streamwise and spanwise (transverse) vortices in the flowing gas. The resultant streamwise vortices tend to reduce resonating vortex oscillations (screech) and the need for an acoustic liner to suppress such screech.

Abstract: A mounting arrangement for a composite material flameholder in teh reheat system of a gas turbine engine provides for a flameholder to be suspended from a flameholder bracket in the jet pipe by a means of pivotal mounting and to be restrained from movement by a leaf spring mounted trunnion attached between the bracket and the flameholder at a second mounting spaced a short distance away from the first. The resilience of the leaf spring allows movement in directions parallel to a line through the axes of the two mountings in order to accommodate differential thermal growth of the composite flameholders and their metallic supporting structure.

Abstract: A combustion assembly includes a combustor having inner and outer liners, and pilot stage and main stage combustion means disposed between the liners. A turbine nozzle is joined to downstream ends of the combustor inner and outer liners and the main stage combustion means is close-coupled to the turbine nozzle for obtaining short combustion residence time of main stage combustion gases for reducing NO.sub.x emissions. In a preferred and exemplary embodiment of the invention, the combustion assembly includes first and second pluralities of circumferentially spaced fuel injectors and air swirlers disposed radially outwardly of a plurality of circumferentially spaced hollow flameholders having fuel discharge holes. Pilot stage combustion is effected downstream of the first and second fuel injectors and swirlers, and main stage combustion is effected downstream of the flameholders.

Abstract: An afterburner flameholder for a gas turbine engine having a central diffuser cone, a generally cylindrical outer shell and fuel spray bars between the shell and cone defining an afterburner region is provided, which comprise an annular member with an asymmetric V-shaped cross section. The annular member is adapted to be secured to the engine in the afterburner region with the apex of the V facing upstream in the axial direction toward the fuel spray bars. The annular member has a first and second circular sidewall member each joined at one end forming an apex, the annular member in cross section has unequal length sidewall members. The difference in length between the distal ends of the first and second circular sidewall members is sufficient to cause spanwise vortices shed at the distal ends of the sidewall members to be out of phase when they meet downstream from the flameholder.

Abstract: In a combustion process streams of fuel, oxidant or combinations of fuel and oxidant pass simultaneously through a combustion region over opposite sides of a plate disposed therein having downstream extending convolutions which create pairs of large scale oppositely rotating vortices. These vortices cause the fuel and oxidant to mix rapidly with each other. A recirculation zone is disposed immediately downstream and adjacent the edge of the convoluted plate, and in one embodiment is created by a step-wise discontinuity in the flowpath. The mixing occurs without introducing large momentum losses and, when the mixture is ignited immediately downstream of the convoluted plate, the flame propagates with a larger than normal spreading angle.

Abstract: The uprating of existing jet engines increases the operating temperatures within the engines and also increases the tendency for flashback in some afterburner type engines. Afterburner type engines include a pilot fuel delivery pipe which is included between inner and outer annular members of a flameholder. Downstream from the pilot, partitions direct an ignited fuel/air mixture into the afterburner chamber. The afterburner flame is downstream from the flameholder, but under conditions of increased temperature the afterburner flame will tend to migrate upstream toward the flameholder. To avoid this tendency, the flameholder includes means for discharging gas which cools the flameholder metal itself while also decreasing the downstream air temperature, thereby decreasing the potential for flashback. In one embodiment, fuel and oxygen depleted turbine discharge gas are used to further decrease the tendency toward flashback.

Abstract: A gas turbine combustor including a first-stage combustion chamber being arranged to serve as a premix chamber for a second-stage combustion chamber and an auxiliary burner provided in the first-stage combustion chamber and arranged to effect, when fired, combustion and holding of a flame in the first-stage combustion chamber and to effect, when extinguished, feed a flame from the first-stage combustion chamber to the second-stage combustion chamber; and a method of driving the gas turbine combustor including a step of preparing the auxiliary burner in the first stage combustion chamber, the auxiliary burner being sparked when said combustion is fired, and causing the first-stage combustion camber to serve as the premixing chamber for the second-stage combustion chamber by extinguished the auxiliary burner.

Abstract: A combined fuel distribution and flameholding system (14) includes an improved spraybar (16) having a tapered portion (28) and a radially inwardly disposed tip portion (30). The tapered portion (28) is configured to provide a flow profile (26) diminishing with respect to inward radial displacement from the burner wall (32) for achieving a uniform blockage to free flow area ratio within the burner. The tip portion (30) creates a turbulent or pilot region (32) in the center of the burner, providing a local environment well suited for ignition and low load burner operation. The individual bars (16) are releasable (46) from the exterior of the burner for allowing longitudinal withdrawal of the entire spraybar (16) through a corresponding opening (48) in the burner wall (22).

Abstract: A radial flameholder (18) extends from the augmentor case (22) through an opening (30) in a coaxial liner (20) and into the hot exhaust gas stream (26). A portion of a cool, annular fan air stream (28) enters an upstream facing opening (34) and discharged radially inwardly adjacent the downstream edge (44) of the liner opening (30). The inner flow (42) of cool air protects the liner (20) downstream of the flameholder (18) by both cooling the liner (20) locally and by displacing the combustion reaction (32) attached to the flameholder (18).

Abstract: A low turbulence, close-coupled mounting structure for a flame holder disposed in an afterburner section of a gas turbine engine is provided. The afterburner section has a plurality of angularly spaced, radially extending fuel injection nozzles, with a fairing surrounding each nozzle to form open ended heat shields about the nozzles. A flame holder having a first cross-sectional configuration is disposed in recessed portions formed in the fairings surrounding the nozzles. The cross-sectional configuration of the recessed portions is configured to substantially conform to a portion of the cross-section of the flame holder such that the flame holder is recessed into the fairings when mounted thereon, thus eliminating outward projections at the connection of the flame holder and fairings. The flame holders are secured in the recessed portions by pins extending through aligned apertures in the skirts of the flame holder.

Abstract: A flow mixer and flame stabilizer structure for an afterburner of a turbofan engine is disclosed having a variable mixer to mix a portion of the cold flow with the hot flow gasses and which also forms a flame stabilizer for a secondary afterburner fuel injection manifold which injects fuel into the cold flow air during afterburner operation. The device forms a flame stabilizer around the secondary, annular fuel injection manifold and has a generally "U" shaped cross-section. One of the legs forming the "U" shape is fixed, while the opposite leg is movable so as to vary the downstream facing opening between the legs. The movable leg also blocks a portion of the cold flow duct to generate localized increases in pressure upstream of the stabilizer. An air scoop located in this upstream portion communicates with the primary afterburner flame stabilizer to direct pressurized air to cool the primary flame stabilizer.

Abstract: An integrated rocket ramjet in which initial acceleration of the rocket is achieved by a rocket fuel propellant and subsequent flight is sustained by a ramjet engine receiving air via a supersonic diffuser from an inlet disposed at the middle of the rocket. The flame for the ramjet combustion system is incorporated into the diffuser so that diffusion and combustion take place simultaneously. The combustion process continues within the space previously occupied by the rocket fuel propellant and the walls bounding this space are the outer casing of the rocket and are directly cooled by free stream air flowing past the rocket.

Abstract: A flameholder for a gas turbine engine includes a retainer plate on the igniter holder boss which protrudes from the flameholder gutter and extends through a clearance hole in the outer shroud. The retainer plate permits thermally induced growth of the parts but does not allow the fuel spray and air flow gap near the igniter to increase significantly, thus assuredly maintaining a sufficiently rich fuel/air mixture to promote ignition.

Abstract: A flameholder structure for a turbojet engine afterburner is disclosed in which a generally "V" shaped flameholder ring has a plurality of substantially radially extending fins attached to and extending radially outwardly from its outer surface. A portion of each of the fins is disposed at an angle to the gas flow so as to impart a cylindrical rotation to that portion of the flow passing over the fins. The cylindrical rotation of the flow increases the shear effect to thereby improve the stability of the flame front and increase the efficiency of the afterburner.

Abstract: This invention relates to a burner with low emission of polluting gases, comprising, in a conduit, an injector of fluid fuel which creates in the conduit, supplied with combustion-supporting air heated in an exchanger, a fuel/air mixture. The latter burns, creating a flame which clings to a stabilizer constituted for example by a hollow piece, of V-section, obturating a central part of the cross-section of the conduit. Downstream of this stabilizer there is placed an obstacle causing a local reduction follwed by a sudden increase in the cross-section of the conduit in order to promote oxidation of the carbon monoxide.

Abstract: The pilot section of a flameholder of an augmentor for a gas turbine engine is modified to improve the ignition and stability characteristics by judiciously locating aperture(s) or slot(s) in the pilot section wherein their orientation is critical so as to create a vortical flow field.

Abstract: A fuel spraybar (16) having an elongated, closed housing (26) discharges fuel from a plurality of openings (32) into an exhaust gas stream (12). A first fuel conduit (34) conducts liquid fuel through the housing (26) and into an annular volume (38) formed therebetween. The fuel, heated by contact with the housing (26) is vaporized in the annulus (38) for preferentially discharging liquid fuel (18) in an axial pilot zone (40) within the gas stream (12).

Abstract: An atmospheric gas burner assembly comprises a burner tube defining a multiplicity of gas outlet ports and an element reducing the flame temperature and, hence, the emission of oxides of nitrogen disposed above the burner tube in the flame area. To optimize the reduction of NO.sub.x emission without affecting permitted CO values and to render the values of reduction in NO.sub.x emissions largely independent of the geometry of the surrounding combustion chamber so as to obtain reproducible emission reduction values, the reducing element is constituted by a multiplicity of fins confining the flames in shafts extending therebetween, the fins extending perpendicularly above the tube and being distributed along the tube.

Abstract: An improved flameholder has a plurality of flameholder attachments removably mounted in cutouts in the downstream edge of a shroud of the flameholder. Each attachment includes a support plate which fits into one of the cutouts and a plurality of fan gutter flameholding elements rigidly mounted on the plate. A slip joint links the plate to the shroud and stiffeners which are fastened together connect each flameholding element to the shroud.

Abstract: An annular burner has an annular flame stabilizer of substantially V shaped cross-section containing a circular fuel injection manifold discharging in counterflow. The annular flame stabilizer is formed by two independent parts, each of these parts constituting one blade of the V cross-section. Pivotal support means are provided at the end of the separation wall of the flows in order to mount each of the parts of the annular stabilizer. The injection manifold is secured to the outer blade of the ring.

Abstract: A flameholder in an afterburner incorporates an improved mixer which includes a small duct for capturing a small percent of hot gas stream flow and routing the same outwardly along the gutter of the flameholder for producing a localized increase of the air temperature in the cool fan air stream flow. The mixer also includes a deflector plate for deflecting the hot gas exiting from the duct into the cool air stream flow.

Abstract: A combustion chamber for gas turbines, especially for motor vehicles, which includes a first reaction chamber, an outlet opening of which terminates in a second coaxially disposed reaction chamber. Each reaction chamber is associated with a premixing chamber provided with an air inlet and a fuel injection nozzle. An insert surrounds the first reaction chamber and its premixing chamber and projects into a flame tube. The flame tube encompasses the second reaction chamber and an outer wall of the insert forms with an inner wall of the flame tube an annular premixing chamber for the second reaction chamber. Several fuel injection nozzles are arranged in a zone of the air inlet of the second reaction chamber.

Abstract: A flameholder arrangement for a gas turbine combustor or the like includes a primary flameholder such as an elongated V-gutter extending across a main flow stream of gaseous components within the combustor. Vortices are shed by the trailing edges of the primary V-gutter flameholder and circulate in essentially two-dimension flow fields in planes normal to the elongated V-gutter to produce a downstream wake. In addition, a plurality of winglets are carried by the primary flameholder and are configured so as to shed vortices rotating about axes generally parallel to the main flow stream. More particularly, the winglets are carried by the outer surfaces of the V-gutter elongated walls, and lie in planes normal to the V-gutter walls and angled with respect to the flow stream. The resultant flow in the wake downstream of the V-gutter is three-dimensional for enhanced mixing of the gaseous components.

Abstract: A scroll-wound metallic cushioning bushing in a bore in a ceramic part permits pin-type connection between the ceramic part and a surrounding metal structure while cushioning against vibration and differential thermal loading which may otherwise destroy the relatively brittle ceramic material. In one embodiment, a scroll-wound cushioning bushing is employed in a trip baffle in a flameholder of an afterburner diffuser section wherein the pins holding the trip step in place are surrounded by the ceramic material and thus protected from the extreme heat found in a flameholder. In another embodiment of the invention, a large ceramic part is supported on a plurality of pins each passing through a cushioned bushing assembly which permits not only radial relative motion of pins and ceramic part, but also permits limited axial displacement and twisting.

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: An augmentor system for a gas turbine engine is drained of residual fuel after augmentor shutdown by means of a drain conduit connected to the augmentor fuel spray apparatus through a valve which opens upon augmentor shutdown. The outlet to the drain conduit is disposed within the flameholder. A pressure differential causes the residual fuel to flow from the spray apparatus into the drain conduit and thereupon into the flameholder, whereupon it is burned.

Abstract: A flameholder stabilization plate attaches to the lower part of a flameholding baffle disposed in an afterburner system of a turbofan engine. The plate includes extension tabs which extend laterally from a main body of the plate and block contact by cool fuel droplets entrained in a cold fan air stream flow with the baffle. The tabs disperse some large droplets into smaller ones which flow to a recirculation flame zone behind the baffle where a leaner fuel-air mixture is formed. Other large droplets of fuel are directed by the tabs to combustion zones at lateral sides of the baffle where a richer fuel-air mixture is formed. The leaner mixture in the recirculation zone will result in a more stable flame which, in turn, will more efficiently burn the richer mixture of fuel in the lateral combustion zones.

Abstract: The outermost gutter of a reheat system has an extended outer wall to two or three times the length of the inner wall of the outermost gutter. This causes a single vortex to develop instead of the usual two vortices giving an increased basic burning stability.The outer wall also protects the jet pipe from excess heat.

Abstract: A gas turbine engine comprises an annular combustion chamber (13) intended for low nitrogen oxide emission. The chamber has a pre-mixing section (20) in which an air-fuel mixture is brought to a significant degree of vaporization before issuing through a grill (22) at the end of the pre-mixing section into a main section (21) of the chamber. Pilot sections (18,19) at opposite sides of the pre-mixing section have outlets (28,29) through which burning mixture from the pilot sections is discharged into main section (21). The grill (22) defines openings (35) through which the fresh mixture from the pre-mixing section (20) is discharged across the outlets (28,29) of the pilot sections (18,19) to mix with and become ignited by the burning mixture.The pre-mixing section (20) is an annular duct (33) having walls (15,16) which extend in the direction of the axis of the chamber and are straight in that direction though slightly convergent. The arrangement favors vaporization in the duct without auto-ignition.

Abstract: A gaseous fuel injector for a gas turbine engine, designed to burn gaseous fuels having a wide range of calorific values, includes a fuel nozzle attached to the engine casing and downstream fuel and air inlet means separate from the nozzle, attached to the head of the flame tube. The fuel and air inlet means comprise an outer annular passage containing a row of swirl vanes, through which compressed air from the engine compressor is arranged to flow, and an inner annular passage through which gaseous fuel and compressed air are arranged to flow, the inner annular passage decreasing in cross-sectional area in the direction of flow to prevent the flow of combustion products back into the injector. The nozzle and fuel and air inlet means, which is relatively large, are separate from each other so that the fuel nozzle can be removed and replaced through a relatively small opening in the engine casing.

Abstract: A combustion chamber for a gas turbine, in particular for motor vehicles, with an atomizer nozzle for the fuel fed to a pre-chamber, in which the inlet cross section for the primary air is changed by the longitudinal movement of a deflection member extending through the inlet opening of the combustion chamber. The deflection member serves as a flame holder for the stabilization of the combustion in the primary air zone while the air-atomizing nozzle is constructed ring-shaped and is provided with swirl slots in such a manner that the mixture of the fuel and of the atomizing air enters as an annular jet the primary air inlet channel, impinges approximately perpendicularly onto the primary air flow, penetrates the same and uniformly mixes with the same on its way to the inlet into the primary zone. The quantity of the primary air to be supplied is thereby automatically adjustable.

Abstract: Combustion systems which employ such features as rotary cup fuel atomizers and the latter in conjunction with CIVIC combustion to enhance flame performance, to produce efficient combustion over a wide operating range, and to eliminate the problems typically encountered in liquid fueled combustors, especially as they are scaled down in size. Innovations that can advantageously be employed in combustors operated on other fuels are also disclosed.

Abstract: In order to prevent the accumulation of carbon on the pintle of a gas turbine engine fuel burner, the pintle has a hollow base and inlet holes so that a small mass flow of compressor delivery air can enter the hollow base and flow over its interior surface.

Abstract: The invention concerns a fuel distribution device in a high velocity gase flow. The device consists of two coaxial, toric injection manifolds placed in close proximity with respect to each other, pierced by small diameter uniformly distributed orifices and arranged to introduce fuel into the flow. The orifices in the manifold located downstream with respect to the direction of the flow of gases, are arranged on the face turned upstream of the manifold, in a circular row coaxial with it.It is the object of the invention to reduce the drag induced in the flow by the devices presently in use, while improving the distribution of the fuel; it finds particularly advantageous applications in the afterburner ducts of gas turbine engines.

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 method and apparatus are described for controlling the mixing of two fluids in which an active element is driven to induce, in the vicinity of the beginning of the mixing region, oscillations of the two fluids about an axis substantially normal to the mixing region flow axis.The active element may be driven by an external drive, or by the kinetic energy in the fluids. Several applications of the invention are described including promoting combustion in jet engines, suppressing audible jet noise, and increasing the output of ejector pumps or thrust augmentors.