Abstract: A flame holder for an augmentor includes geometry to produce large radial variations in heat release to prevent coupling with modes within the exhaust duct that produce combustor screech. A surface of the flame holder varies axially in a radial direction to produce a radial phase variation in heat released from the flame holder. The radially changing surface produces radially non-uniform and unsteady heat release that does not couple with acoustic modes within the exhaust duct.

Abstract: A trapped vortex combustor. The trapped vortex combustor is configured for receiving a lean premixed gaseous fuel and oxidant stream, where the fuel includes hydrogen gas. The trapped vortex combustor is configured to receive the lean premixed fuel and oxidant stream at a velocity which significantly exceeds combustion flame speed in a selected lean premixed fuel and oxidant mixture. The combustor is configured to operate at relatively high bulk fluid velocities while maintaining stable combustion, and low NOx emissions. The combustor is useful in gas turbines in a process of burning synfuels, as it offers the opportunity to avoid use of diluent gas to reduce combustion temperatures. The combustor also offers the possibility of avoiding the use of selected catalytic reaction units for removal of oxides of nitrogen from combustion gases exiting a gas turbine.

Abstract: A single stage combustor for a gas turbine having an annular array of outer fuel nozzles arranged about a center axis of the combustor; a center fuel nozzle aligned with the center axis, wherein the center fuel nozzle is substantially smaller than each of the outer fuel nozzles, wherein the combustor includes a pre-mix operating mode in which the center nozzle receives a fuel rich air-fuel mixture.

Abstract: A gas turbine combustor comprises a premixed combustion burner disposed on the periphery of a pilot burner, an approximately cylindrical combustor liner disposed on the downstream side of the premixed combustion burner, which defines a combustion chamber in the liner. The gas turbine combustor is characterized by further comprising flame stabilizers radially disposed at the exit of the premixed combustion burner, and a fuel injection means with which the pilot burner is provided injects at least one of gas fuel and liquid fuel, in which a plurality of air nozzles are provided which are located outside the pilot burner and inside the premixed combustion burner, and which spout out air into the combustion chamber. Adequate combustion can be accomplished with a combustor which is capable of using gas fuel and liquid fuel, and at the same time, NOx can be reduced.

Abstract: A combustion chamber (5) for a gas turbine is adapted for flameless oxidation of fuels. This circulation flow has an internal space (9) in which a large-volume circulation flow is established. To this end, the combustion chamber supplies a hot exhaust stream to the introduced air, the mass flow rate of which exceeds the fresh air stream. The fresh air and the fuel are fed to the combustion chamber in the same direction, roughly parallel to the wall.

Abstract: A trapped vortex combustor for gas turbine engines. An annular combustor housing is provided having a plurality of inlet centerbodies disposed along a helical axis. The inlet centerbodies include a leading edge structure, opposing sidewalls, a pressurizable cavity, and a rear wall. Inlet centerbodies cooperate with adjacent structure and an aft bluff body to define a trapped vortex cavity combustion chamber for mixing an inlet fluid and burning fuel to form hot combustion gases. Mixing is enhanced by utilizing struts adjacent to the rear wall to create eddies in the fluid flow, and by injecting fuel and/or air in opposition to swirl created by the bulk fluid flow. Hot combustion gases are utilized in a turbine for extraction of kinetic energy, or in heat exchange equipment for recovery of thermal energy. High combustion efficiencies and less than 10 ppm emissions of oxides of nitrogen and of carbon monoxide are achieved.

Abstract: A flow controller is disposed between a preburner section in a diffuser and prior to the main fuel injector and catalytic sections in a turbine combustor. The flow from the burner section is typically not uniform in temperature and velocity and the flow splitter renders the flow substantially uniform at the fuel injector and catalyst inlet. The flow splitter comprises substantially equal mass annular flow areas defined by a first outer frustoconical element and the diffuser wall, a second element defining with the first element a second annular area and a central bluff disk defining with the second element the interior annular area. Vanes are provided on the flow splitter to enhance turbulent flow and substantially preclude swirling flow. As a result, flow uniformity at the catalyst inlet and main fuel injection is achieved.

Abstract: A gas turbine engine augmentor nozzle has an inlet for connection to an augmentor fuel conduit and an outlet for expelling a spray of fuel. A passageway between the inlet and outlet is at least partially bounded by outlet end surface portions diverging from each other. The nozzle may be used as a replacement for a non-divergent nozzle and may reorient a fuel jet centerline toward radial.

Abstract: A turbine engine has a centerbody within a gas flowpath and a downstream tailcone and a pilot at an upstream end of the tailcone. A flameholder is positioned in the flowpath outboard of the centerbody. The pilot has a first surface diverging in a downstream direction.

Abstract: A pilotless catalytic combustor (10) including a basket (12) having a central axis (14) and a central core region (16) disposed along a portion of the central axis. Catalytic combustion modules (18) are circumferentially disposed about the central axis radially outward of the central core region for receiving a fuel flow (20) and a first portion of an oxidizer flow (22), and discharge a partially oxidized fuel/oxidizer mixture (24) at respective exit ends (26). A base plate (30) is positioned in the central core region upstream of the exit ends of the catalytic combustion modules, the baseplate defining a recirculation zone (32) near the respective exit ends for stabilizing oxidation in the burnout zone. A method of staged fueling for a pilotless catalytic combustor includes providing fuel to at least one of the modules during start up and progressively providing fuel to other modules as a load on the turbine engine is increased.

Abstract: An afterburner apparatus that utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel into an oxidant. The swirl generator converts an oxidant flow into a turbulent, three-dimensional flowfield into which the fuel is introduced. The swirl generator effects a toroidal outer recirculation zone and a central recirculation zone, which is positioned within the outer recirculation zone. These recirculation zones are configured in a backward-flowing manner that carries heat and combustion byproducts upstream where they are employed to continuously ignite a combustible fuel/oxidizer mixture in adjacent shear layers. The recirculation zones accelerate flame propagation to allow afterburning to be completed in a relatively short length.

Abstract: An annular combustor has an annular inner shell, an annular outer shell and a dome end wall connecting the inner shell with the outer shell. A dam is positioned between the dome end wall and the exit end and extends radially from at least one of the inner shell and the outer shell to provide a reduced flow area passageway within the combustion chamber.

Abstract: A pilot nozzle of a gas turbine combustor comprises a first structure, provided near a main nozzle of a combustor that injects fuel oil, having a flow channel for a fuel gas and an outlet for the fuel gas. The first structure diffusion-injecting the fuel gas obliquely forward through the outlet to maintain a flame and to aid ignition of the fuel oil injected from the main nozzle. There is further provided a second structure which circulates in whirls a combustion gas generated due to the combustion of the fuel gas.

Abstract: The invention relates to a method for combustion of fuels of arbitrary state of aggregation, which are burnt with air, possibly with the addition of water, and a reactor therefore, which is intended to optimize the combustion method. A solid, liquid and/or gaseous fuel, possibly water and/or an oxidizing agent are introduced into a reaction chamber (2) in its axial direction under high pressure, the amount of injected pressurized air corresponding to the amount of air necessary for the complete combustion, and the introduced mixture is led to a deflection surface (7) in the interior of the reaction chamber (2), whereby it is atomized, sublimates and/or evaporates and burns explosively, before it can reach the wall or the bottom of the reaction chamber (2).

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

Abstract: A ported, premixed extendable burner provides increased turndown capability relative to conventional burners. The burner has an adjustable flameholder sleeve which can be extended and retracted relative to a flameholder, to increase and decrease the available flameholder area. The burner is suitable for use in modulated heating applications and other applications where high turndown ratios are desired.

Abstract: A carbureted flameholder (30) with optial cooling is provided for a bypass turbojet-engine. The flameholder (30) comprises a body (34) which extends radially into the primary flow. The body (34) is formed by a V-dihedral having two outer plates (35, 36) which intersect at a common ridge apex (37). An air tube (38) is mounted between the two outer plates (35, 36) and at least one fuel conduit (44, 45) is disposed to the rear of the air tube (38). The overall cross-section of the air tube (38) is approximately triangular and the air tube (38) includes a transverse downstream wall that is curved to define a trough (42) in which the fuel conduit (44, 45) is located. The air tube (38) includes orifices (41, 46) directed against the dihedral plates (35, 36) and the fuel conduit (44, 45) to cool them. The fuel conduit includes a nozzle injector (46) directed downstream towards the afterburner chamber (23).

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

Abstract: A pulverized fuel combustion burner includes a pulverized fuel and air mixture conduit. A pulverized fuel rich/lean separator is disposed at the axial center of the conduit so that a high concentration mixture is formed at an outer peripheral portion of the conduit and a low concentration mixture is formed at a central portion of the conduit. The pulverized fuel rich/lean separator has a cross-sectional shape which gradually enlarges in the flow direction at an angle to the flow direction. It becomes parallel to the flow direction downstream of the enlarging portion, and terminates in a flat surface that is perpendicular to the axis of the separator. A passage extends through the pulverized fuel rich/lean separator along the axis.

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

Abstract: A gas turbine combustor has a premixing burner for jetting out a premixed gas of fuel and air. A stabilizer forms a circulation of combustion gas generated by combustion of the premixed gas at the downstream side of the stabilizer to stabilize flame formed by the combustion of the premixed gas. Before the operation of the combustor, a relationship between a temperature of the stabilizer and combustion conditions of the premixed gas is checked. Thereafter during operation of the combustor, the temperature of the stabilizer is measured during combustion and the combustion conditions are checked according to only the measured temperature of the stabilizer and the aforesaid relationship. The stabilizer has a heat receiving surface at the most downstream side thereof. The temperature of a portion of the stabilizer around the heat receiving surfaces measured to allow an accurate assessment of the combustion conditions.

Abstract: This is to claim the invention of the twin-plate flameholders that can be applied to the afterburner and reheater of the jet engines as well as the industrial burners and incinerators. The claimed flameholder features a certain overlap between the two plates and a slit at the overlap portion. It turns out that a small portion of the air and fuel flows through the slit between the two plates will result in significant modification in the aerodynamic flow structure and local fuel distribution to enhance the capability of flameholding. Hence the performance of the claimed FLAMEHOLDER is much better than the conventional ones in terms of the combustion efficiency, flame ignition and blowout limits, and operation range of the combustion devices. The inclined angle of the twin-plate flameholder can be adjusted by a turning mechanism, this provides the benefit to adjust the inclined angle of the twin-plate flameholders under different operation conditions.

Abstract: An ultra-low NOx gas turbine combustor having a dual fuel capability. The combustor has a plurality of venturis in flow communication with a corresponding number of fuel lances such that fuel injected from each lance into a corresponding venturi is mixed with high velocity air also flowing into the venturis. A vee-gutter flame holder is positioned downstream of the array of venturis for holding a combustion flame within the combustor at stable conditions. Due to the high velocities of the air-fuel mixture in the vicinity of the flame-holder, as a result of the fuel-air mixing in the venturis, destructive flash back conditions are obviated. A stable flame within the combustor provides for minimum acoustic disturbance and low overall pressure losses within the combustor provide for high operating efficiency levels of the turbine apparatus. Burning of the fuel in air at lean mixtures allows for minimal operation of a conventional pilot nozzle assembly so as to reduce the undesirable formation of NOx.

Abstract: A low emissions combustion system for a gas turbine engine, including a generally annular combustor with a plurality of tangential fuel injectors to introduce a fuel/air mixture. The annular combustor includes a skirt shaped flow control baffle from the inner liner and air dilution holes in the inner liner underneath the flow control baffle and also in the cylindrical outer liner. The fuel injectors extend through the recuperator housing and into the combustor through an angled tube and then through a tangential guide in the cylindrical outer liner of the combustor housing. The fuel injectors generally comprise an elongated injector tube with the outer end including a coupler having at least one fuel inlet tube. Compressed combustion air is provided to the interior of the elongated injector tube from either holes or slits therein which receive compressed air from the angled tube around the fuel injector which is open to the space between the recuperator housing and the combustor.

Abstract: A combustor structure is described which comprises a cavity defined in the combustor for trapping a vortex of fuel, air and hot combustion products to stabilize the flame, the cavity being formed in any suitable way such as being defined between two or more bluff bodies in tandem, or in a wall of the combustor, or in the combustor liner, and wherein fuel and air are injected directly into the fuel/air recirculation zone defined by the trapped vortex.

Abstract: A burner for combustion of a pulverized coal mixture having two kinds of rich and lean concentration has a height of a burner panel reduced and the overall burner simplified. A rich/lean separator (10, 20, 30) is provided within a pulverized coal conduit (2) so that a high concentration mixture is formed in an outer peripheral portion and a low concentration mixture is formed in a central portion within a single pulverized coal conduit. Thus, a rich mixture burner and a lean mixture burner, which have been conventionally provided separately, may be formed into a single burner. Recirculation of air is accelerated by a cutaway slit (20d, 30d) provided in a central portion of the rich/lean separator to make the air flow rate distribution uniform in a pulverized coal nozzle. Also, a duct and an air blow box for the combustion air to be supplied to the pulverized coal flame are not integrally formed continuous in the height direction, but are divided into a plurality of discontinuous units.

Abstract: A liner for a gas turbine engine combustor is disclosed having a non-linear cavity section, wherein air and fuel injected therein form a trapped vortex for igniting and stabilizing a flame in the combustor. The cavity section, which is substantially rectangular in shape, has an aft wall, a forward wall, and an intermediate wall connected at one end to the aft wall and at the other end to the forward wall. A plurality of passages are provided in the aft wall for injecting fuel therethrough and a plurality of air passages are provided in the aft wall surrounding each fuel passage for injecting air therethrough. Cooling holes are also provided in the aft wall, the forward wall, and the intermediate wall for reinforcing the fuel/air vortex flow in the cavity section.

Abstract: This invention is a twin-plate flameholder for an afterburner and reheater of jet engines as well as for industrial burners and incinerators. The flameholder features two plates with a certain overlap and a slit at the overlap portion. A small portion of the air and fuel flows through the slit between the two plates and results in a significant modification in the aerodynamic flow structure and local fuel distribution to enhances the capability of flameholding. Hence the performance of the flameholder is much better than conventional ones in terms of combustion efficiency, flame ignition, blowout limits, and operation range of the combustion devices. The inclined angle of the twin-plate flameholder can be adjusted by a turning mechanism to adjust the inclined angle of the twin-plate flameholder under different operation conditions. Furthermore, a series of the twin-plate flameholders can be linked together with a control mechanism so that these flameholders can be rotated in the same or opposite direction.

Abstract: An afterburner 20 for a gas turbine engine 10 has a fuel spray ring 24a for injecting fuel into the afterburner, a flameholder gutter 34a for stabilizing combustion of a fuel-air mixture flowing through the afterburner, and an ignitor 35 for initiating combustion and includes an enclosure 50 attached to the gutter. The enclosure has radially inner and outer walls 52, 54 and circumferentially spaced apart webs 60, 62 extending between the walls to define a radially and circumferentially bounded chamber 64. Each web has a forward opening 72 and an aft opening 74 so that a portion of the spray ring and a portion of the gutter are embraced by the enclosure. The enclosure is ideally circumferentially aligned with the ignitor and regulates the fuel-air ratio within and in the vicinity of the chamber to ensure reliable lighting of the afterburner and flawless advancement to full afterburning operation.

Abstract: This invention relates to low NOx combustor burners of the type that employ an irregular edge at the edge of the center hub of the combustor burner. Such structures of this type, generally, reduce the strength of combustion instabilities by disrupting the coherent vortices shed from the center hub section of the burner.

Abstract: The present invention has an object to provide a gas turbine combustor which is able to effect stable combustion in a wide range of fuel flow rate. A burner 1 is provided with fuel nozzles 31 and 32. When a fuel flow rate is small, diffusion flame is formed with fuel supplied from the nozzle 31 with a ring-shaped flame stabilizer 11. Next, fuel is supplied from the nozzle 32 to mix with air, reach to the flame stabilizer 11 and be held by the diffusion flame already formed, whereby stable premixed flames are formed in the flame stabilizer 11 from a range of low fuel air ratio. Further, when flame is propagated from the burner 1 to the burner 2, a fuel air ratio at the outer periphery side of the burner 1 is locally raised by the fuel supplied from the nozzle 31, whereby the combustion stability can be raised in a wide range of fuel flow rate and propagation of flame to adjacent burners becomes easy.

Abstract: A combustor for a gas turbine having primary and secondary combustion zones. The combustor has primary gas fuel spray pegs for supplying a lean mixture of gaseous fuel to the primary combustion zone via a first annular pre-mixing passage and secondary fuel spray bars for supplying a lean mixture of fuel to the secondary combustion zone via a second annular pre-mixing passage. The fuel spray bars are aerodynamically shaped and a row of fuel discharge ports are formed on opposing sides of the spray bar. A pair of mixing fins project outwardly from the spray bar sides. The fins create turbulence in the air flow that ensures adequate mixing of the fuel and air. The fins have sufficient height and are displaced sufficiently far from the fuel discharge ports so that although the turbulence has not dissipated by the time the air flow reaches the fuel discharge ports, the zone of recirculation located downstream from the fins does not extend to the fuel discharge ports.

Abstract: A gas turbine combustor is provides with a stabilizer at a downstream side of a premixing device for premixing and supplying fuel and air into a combustion chamber. The stabilizer has a cylindrical part extending axially from an upstream end thereof to a downstream end and a stabilizing part at the downstream end of the cylindrical part for stabilizing a flame, and the stabilizer is mounted on an inside of the combustor by a plurality of members arranged annularly and secured to the inside of the combustor at their ends, each of the members having a part slidably inserted in an opening of the cylindrical part so as to restrict the stabilizer to move axially while allowing deformation of the stabilizer and another part supporting the upstream end of the cylindrical part so as to restrict radial movement of the stabilizer.

Abstract: A combustor for a gas turbine engine is disclosed which is able to operate efficiently at inlet air flows having a high subsonic Mach Number. The combustor has an outer liner and an inner liner spaced therefrom, wherein a combustion chamber is defined therebetween. A dome inlet module is provided which is in flow communication with compressed air flow from a compressor upstream thereof. The dome inlet module has an outer member fixed to the outer liner and an inner member fixed to the inner liner, wherein a flow passage is defined by the outer and inner members for the compressed air flow to flow freely from a compressor to the combustion chamber. Fuel atomizers are then utilized to inject fuel into the flow passage so that the fuel is mixed with the compressed air stream to form a fuel/air mixture which enters the combustion chamber.

Abstract: A combustor for burning the untreated exhaust of an internal combustion engine heats and burns the exhaust prior to release into the atmosphere, or prior to introduction into a downstream treatment system such as a catalytic converter. The combustor defines a novel, passive flame holder in combination with an igniter, whereby the exhaust continues to burn, without assist, once ignited. Managed air injection may be employed. The combustor is configured to fit within standard exhaust systems with a minimum of modification to the overall exhaust assembly. The combustor is particularly useful in cold start conditions for increasing the temperature of the exhaust to catalytic converter operating temperatures and for use in small engine applications where exhaust has heretofore been released untreated.

Abstract: A plurality of turbulence promotors (11) are arranged on a surface of a stabilizer (11) comprising a stabilizer portion (14) contacting combustion gas and support portion (15) for rectifying flow except for a heat receiving surface (13) contacting with combustion gas to promote heat transfer from the stabilizer to an air fuel flow. The distance between the turbulence promotor closest to the heat receiving surface (13) and the heat receiving surface is at least 4 times the height of said turbulence promotor to prevent back fire due to provision of the turbulence promotor.

Abstract: This invention is an improved catalyst structure and its use in highly exothermic processes like catalytic combustion. This improved catalyst structure employs integral heat exchange in an array of longitudinally disposed adjacent reaction passage-ways or channels, which are either catalyst-coated or catalyst-free, wherein the configuration of the catalyst-coated channels differs from the non-catalyst channels such that, when applied in exothermic reaction processes, such as catalytic combustion, the desired reaction is promoted in the catalytic channels and substantially limited in the non-catalyst channels. The invention further comprises an improved reaction system and process for combustion of a fuel wherein catalytic combustion using a catalyst structure employing integral heat exchange, preferably the improved structures of the invention, affords a partially-combusted, gaseous product which is passed to a homogeneous combustion zone where complete combustion is promoted by means of a flameholder.

Abstract: A flameholder is disclosed for use in an afterburner of an aircraft gas turbine engine. The flameholder comprises at least one annular ring and a plurality of open ended slots around the forward end of the ring with the open end of each slot open through the forward edge of the ring for accepting a plurality of fuel spraybars. One particular embodiment provides two or more sub-pluralities of slots having two or more differing axial lengths to accommodate different axially spaced sub-pluralities of spraybars such as primary and pilot spraybars. A fastening means is provided for attaching the annular ring to the outer engine casing and is accessible through the exhaust nozzle of the engine. One embodiment provides a fastening means with an anti-rotation means on a connecting link into which a bolt head may be slipped and held from rotating during torquing of a nut.

Abstract: Combustion-induced instabilities are minimized in gas turbine combustors with a plurality of flameholders disposed on the center hub of each fuel nozzle. The flameholders are streamlined bluffbodies oriented at an angle with respect to the longitudinal axis of the center hub which roughly matches the swirl angle of the fuel nozzle swirl vanes. The flameholders have streamlined upstream faces and flat downstream faces. The flat faces are preferably flush with the bluff end of the center hub. The flameholders, which are equally spaced about the circumference of the center hub, preferably block about 30-50% of the annular cross-sectional area in each burner. Thus, an array of additional flame sheets is produced in each burner without destroying the swirl. These additional flame sheets effectively increase early fuel consumption so that heat release in the main combustion chamber is decreased, thereby reducing combustion instabilities.

Abstract: A fuel injection system for a gas turbine engine combustion chamber is disclosed having a sleeve defining a passageway extending along a longitudinal axis of a combustion zone, a first fuel injector orifice to inject fuel into the passageway, and second fuel injector holes arranged in a plurality of substantially linear arrays extending radially from the sleeve and angularly equidistantly spaced from each other, the second fuel injection holes located in a plane extending substantially perpendicular to the longitudinal axis of the combustion chamber such that the plane is located axially between an upstream end wall of the combustion chamber and the downstream end of the sleeve.

Abstract: A gas turbine combustor suppresses the generation of NOx by mixing a fuel and air homogeneously. A pilot nozzle is provided at the center of the gas turbine combustor. A plurality of main nozzles surround the pilot nozzle. A diverging cone projects from the vicinity of the injection port of the pilot nozzle such that the flame from the main nozzles is sustained by the pilot nozzle and NOx is suppressed. The main nozzles can be provided upstream of the injection port of the pilot nozzle in which case an annular premixing nozzle having a throttled exit end is disposed downstream of the main nozzles. The main nozzle may also be in the form of a fuel nozzle having a plurality of tubes, a gaseous fuel being injected through one of the tubes, and liquid fuel being injected into the annular premixing nozzle through the other of the tubes so that the liquid fuel is atomized to mix the fuel and air homogeneously.

Abstract: An afterburner for a turbofan engine is disclosed having a plurality of connecting arms connecting the inner wall to the outer wall wherein each of the connecting arms defines an air chamber, an inlet communicating with the main air bypass passageway and a plurality of outlets communicating with the afterburner chamber. The plurality of connecting arms are distributed generally radially about the longitudinal axis of the engine and serve to distribute a portion of the bypass air into the afterburner chamber. The bypass air is further distributed into the afterburner chamber through a plurality of flame holders extending radially inwardly from the outer wall towards the longitudinal axis. Each of the flame holders also defines an air chamber, an inlet communicating with the main air bypass passageway and a plurality of air outlets. The flame holders may also be distributed in a radial array about the longitudinal axis and are interposed between adjacent connecting arms.

Abstract: A cooled ignition flameholder assembly includes a first heat shield having first and second spaced apart chambers. A fuel spraybar is disposed inside the first chamber, and a hollow baffle is disposed inside the second chamber. A second heat shield is joined to the first heat shield for closing the second chamber with the baffle therein. The baffle includes an inlet for receiving cooling air which is discharged through a plurality of outlet holes for impingement cooling the first and second heat shields. An ignition bulb is disposed adjacent to the second chamber and receives an igniter tip and a fuel injector tip for initiating combustion.

Abstract: A cooled flameholder assembly includes a first heat shield having first and second spaced apart chambers. A fuel spraybar is disposed inside the first chamber, and a hollow baffle is disposed inside the second chamber. A second heat shield is joined to the first heat shield for closing the second chamber with the baffle therein. The baffle includes an inlet for receiving cooling air which is discharged through a plurality of outlet holes for impingement cooling the first and second heat shields.

Abstract: An improved flameholder for a thrust augmentation combustor includes a toroidal pilot gutter and inner and outer radial gutters, all having U-shaped cross-section and formed from a single piece of metal. The one-piece formation enables design improvements and variations which were not possible in the multiple piece construction of the prior art.

Abstract: An integral, one-piece afterburner structure for a turbojet engine is disclosed which is formed of composite material. The afterburner structure has an outer casing formed as a body of revolution about a central axis, an inner casing also formed as a body of revolution about the central axis, which casings are integrally joined by a plurality of connecting arms extending between the inner and outer casing. The connecting arms are also formed of a composite material and are integrally molded with both the inner and outer casings. The afterburner structure also has a plurality of secondary support arms formed of composite material which extend either from the outer, or the inner casing in a generally radial direction relative to the central axis. Integrally formed with the plurality of secondary support arms is at least one annular flameholder ring which extends around the central axis and is supported by the secondary support arms.

Abstract: An afterburner assembly is disclosed in which the flameholder ring is for by plurality of flameholder ring segments, each segment being integrally formed with a generally radially extending arm. The flameholder ring segments extend beyond each opposite sides of the arm. The arm and flameholder ring segments are attached to the casing of the afterburner by a support element which is pivotally attached to the arm and fixedly attached to the afterburner casing. The distal end of the arm slidably contacts the casing defining the opposite side of the afterburner duct to enable the arm to slide relative to the casing to allow for differential thermal expansion of the respective elements. When each of the arm/flameholder ring segments are attached to the afterburner casing, the flameholder ring segments form a generally annular flameholder ring.

Abstract: A flight vehicle scramjet combustor. The combustor, in its "2-D" and annular embodiments, has two spaced-apart, generally opposing, and longitudinally extending walls. One wall includes a generally aft-facing step having a first section and an interconnected second section, a forward wall portion attached to the first section, and an aft wall portion attached to the second section. The second section includes a fuel injector discharge orifice having a fuel discharge axis which is aligned generally perpendicular to the second section and which projects both generally towards the other wall and longitudinally aft. The combustor has a cylindrical embodiment which includes a cylindrical wall having a step and fuel injector discharge orifice similar those of the "2-D" and annular combustor embodiments.

Abstract: A combustor comprises a passage area changing mechanism which relatively moves a flame holder relative to a premixed combustion nozzle in an axial direction so that the area of passage for premixed gas between an injection edge of the premixed combustion nozzle and a peripheral edge of the flame holder can be changed. Stable combustion can be maintained over a wide load range and reduction in NOx can be achieved.

Abstract: This invention involves an improved technique for the modulation of waste an actively controlled compact waste incinerator afterburner. This improved technique utilizes acoustic driving to affect indirect modulation of waste flow velocities. The waste surrogate gases are modulated indirectly by periodic entrainment created by the roll-up of the main air vortex as well as indirect acoustic excitation of secondary air injection. One of the main advantages of this new configuration is the acoustic drivers used to phase inject the waste into the vortex for proper combustion are not in direct contact with the hot waste and therefore can be less expensive and more durable over the long term.