Abstract: A multilayer heat sink including a heat-receiving layer, a channel layer including cooling micropaths extending and directing a fluid in a direction orthogonal to a stacking direction, an orifice layer including jet orifices configured to jet the fluid into the cooling micropaths, and drain orifices configured to drain the fluid from the cooling micropaths, a header layer including a peripheral wall and a baffle, and a bottom layer, wherein the baffle includes parallel plates disposed parallel to each other, and end plates configured to alternately close an opening at an end and an opening at an opposite end of the parallel plates, and the orifice layer, the bottom layer, the baffle, and the peripheral wall define a supply channel to guide the fluid from a fluid inlet to the jet orifices and a drain channel to guide the fluid from the drain orifices to a fluid outlet.

Abstract: A liner for a combustor in a gas turbine engine and a related method. The liner includes a liner body having a cold side and a hot side. The liner includes a dilution passage having a concatenated geometry extending through the liner body. The concatenated geometry has a plurality of discrete dilution holes, an annular slot, and a plurality of dilution inserts. The dilution passage is configured (i) to integrate a first dilution air flow flowing through the dilution passage from the cold side to the hot side and a second dilution air flow flowing through the dilution passage from the cold side to the hot side into an integrated dilution air flow, and (ii) to inject the integrated dilution air flow into a core primary combustion zone of the combustor to attain a predetermined combustion state of the combustor.

Abstract: A liner for a combustor in a gas turbine engine. The liner includes a liner body having a cold side and a hot side. The liner includes a dilution passage having a concatenated geometry extending through the liner body. The concatenated geometry has a plurality of discrete dilution holes, an annular slot, and a fence concatenated with the plurality of discrete dilution holes. The dilution passage is configured (i) to integrate a first dilution air flow flowing through the plurality of discrete dilution holes from the cold side to the hot side and a second dilution air flow flowing through the annular slot from the cold side to the hot side into an integrated dilution air flow, and (ii) to inject the integrated dilution air flow into a core primary combustion zone of the combustor to attain a predetermined combustion state of the combustor.

Abstract: Disclosed herein are systems, apparatuses, and methods for using a sensed combustion zone temperature to continuously control combustion of a first (main) gas within an enclosed combustor. The combustor is in fluid communication with a first gas line carrying the first gas, a second gas line independent of the first gas line carrying a second (assist) gas having a higher heating value than the first gas, and air dampers providing draft or assist air. The first gas may be vapors from a production source or tank. A computer control system monitors the combustion zone temperature of the enclosed combustor as sensed by a sensor in electronic communication with the computer control system and controls the combustion zone temperature by changing a condition of a first gas line valve of the first gas line, a second gas line valve of the second gas line, and the air dampers.

Abstract: The present subject matter relates to a smoke tube boiler including: a mix chamber, a heat exchanger, a firing rod assembly, a sealing means, and an air-cooled cooling means and a water-cooled cooling means.

Abstract: A crankcase ventilation system comprises a housing defining an internal volume structured to receive a. rotating air/oil separator element. The housing has a housing inlet structured to receive a fluid and a housing outlet defined tangentially in a sidewall of the housing which is structured to allow the fluid to exit the housing. An outlet conduit is fluidly coupled to housing outlet. The outlet conduit comprises an outlet conduit first portion axially aligned with the housing outlet, and an outlet conduit second portion positioned downstream of the outlet, conduit first, portion. A swirl breaking structure is positioned in at least one of an outlet conduit inlet and the outlet conduit second portion. The swirl breaking structure is configured to disrupt swirling flow of the fluid into the outlet conduit so as to reduce a pressure drop experienced by the fluid as the fluid flows from the housing into the outlet conduit.

Abstract: A turbofan gas turbine engine configured to reduce hotspots within combustors. The engine includes an axis and a combustor that is circumferentially disposed about the axis. The combustor includes an annular combustor liner that includes a front portion and a rear portion. The annular combustor liner is joined to an annular combustor dome via front portion and defines a chamber and a nozzle is mounted within the annular combustor dome and is configured to inject fuel into a plurality of swirlers. At least one or more dilution openings is circumferentially distributed around the liner such that a region is fluidly connected through the annular combustor liner to the chamber. Each one of the pluralities of dilution openings includes an opening and a radial support wall that is positioned aft of the opening such that the radial support wall extends into the chamber.

Abstract: A gas turbine engine that includes a combustor configured for efficient combustion of fuel for the generation of combustion gases. The engine includes an annular combustor that includes an annular wall that defines a channel configured to conduct hot combustion gases along a flow-path of combustion gases. The annular wall has an exterior first surface and an interior second surface. A plurality of dilution holes is defined through the wall. Each dilution hole is defined by a dilution hole surface that extends between an entry end and an exit end. The entry end is defined by the first surface and the exit end is defined by the second surface such that the dilution hole has a convergent and then divergent cross-sectional profile. The entry end has a first geometric shape and the exit end has a second geometric shape that is different than the second geometric shape.

Abstract: The invention relates to a premixing method for premixing fuel with air prior to the combustion of a fuel/air mixture to allow burners to be operated at high output and with a good load variation range with stable and reliable operation and low NOx emissions. The method comprises: a) creating a rich fuel/air mixture with a fuel/air ratio above an ignitable fuel/air ratio, b) supplying air to the rich fuel/air mixture to obtain an ignitable fuel/air mixture, and c) swirling the ignitable fuel/air mixture obtained in step a) or b). The invention further relates to a premixing device for performing the method.

Abstract: A combustion chamber assembly group, and a mounting method therefor, includes a combustion chamber for an engine that includes a curved combustion chamber wall extending along two spatial directions, and a combustion chamber shingle affixed at an inner side of the combustion chamber wall and having a shingle edge defining the outer contour of the shingle. For an at least sectional abutment of the shingle edge at the combustion chamber wall with a minimum clamping force in an operational state of the engine, the shingle is mounted to the combustion chamber wall in a mounting state in which the shingle at least at one section of the shingle edge has a curvature with respect to at least one of the spatial directions that differs from the curvature of the combustion chamber wall with respect to this spatial direction.

Abstract: A burner including a burner tube including a side wall, a first longitudinal end configured for receiving a fuel mixture flow, a closed second longitudinal end, a chamber defined by the interior flow space of the burner tube, the cross-sectional area of the burner tube is larger at the first longitudinal end than the cross-sectional area of the burner tube at the second longitudinal end; and a plate disposed on the first longitudinal end, isolating the chamber from a space upstream of the chamber, the plate further includes a plurality of openings disposed in a spiral format on the plate and a plurality of baffles, each baffle coupled to one of the plurality of openings of the plate, each of the plurality of baffles is configured to direct a portion of the fuel mixture flow through one of the openings from the space upstream of the chamber into the chamber.

Abstract: A burner head that constitutes a combustion chamber for an exhaust gas processing apparatus by being attached to an upper portion of a combustion chamber main body is provided. The burner head includes a chassis which has a cylindrical portion having a lower opening and in which a fastening module for removably fastening to the combustion chamber main body is provided, a fuel nozzle that blows fuel into the cylindrical portion, a combustion supporting gas nozzle that blows combustion supporting gas into the cylindrical portion, a processing gas nozzle that blows processing gas into the cylindrical portion, and a pilot burner that ignites the fuel and/or the combustion supporting gas.

Abstract: A liner panel for use in a combustor of a gas turbine engine, the liner panel includes a radiused edge blended into a hot side of the linear panel. A combustor for a gas turbine engine including a liner panel mounted to a support shell via a multiple of studs, the liner panel including a radiused edge blended into a hot side of the linear panel, the hot side including a thermal barrier coating. A method of manufacturing including casting a radiused edge blended into a hot side of a linear panel; and applying a thermal barrier coating to the hot side of the liner panel.

Abstract: A heat shield assembly for an engine case of a gas turbine engine may include a heat shield and a support lock. The heat shield may have an annular shape. The heat shield may define an aperture extending through the heat shield. The support lock may have a tab extending radially outward from a distal surface of the support lock. The aperture in the heat shield may be configured to retain the tab of the support lock.

Abstract: A solid fuel boiler burner has a rotary combustion chamber mounted in casing. The casing is connected by hooks to a gearwheel. The gearwheel is mounted rotationally between a pair of cage bearings. The gearwheel and a compensating and pressure plate have openings for a inflow of air from a blower chamber through an adjustable screen. The adjustable screen controls a ratio of primary to secondary air. A worm feeder delivers fuel to the combustion chamber through an outlet thereof. The worm feeder has an axially placed aeration duct therein.

Abstract: A component for a gas turbine engine includes a substrate with a substrate aperture and a coating on the substrate that extends a length of the substrate aperture. A liner assembly for a gas turbine engine includes a hot sheet with a multiple of apertures and a coating on the hot sheet that extends a length of each of the multiple of apertures. A method of forming an aperture to provide film cooling in a component of a gas turbine engine, includes forming a multiple of substrate apertures in a substrate. Each of the multiple of substrate apertures defines a substrate inner periphery. A coating is applied on the substrate after forming the multiple of substrate apertures to define a coating inner periphery at least partially within each of the multiple of substrate apertures. The coating inner periphery is smaller than the substrate inner periphery.

Abstract: A combustor adapted for use in a gas turbine engine is disclosed. The combustor includes a metallic case forming a cavity and a ceramic liner arranged in the cavity of the metallic case. The ceramic liner defines a combustion chamber in which fuel is burned during operation of a gas turbine engine. The ceramic liner is located in the metallic case using a plurality of cross key connectors.

Abstract: An assembly is provided for a turbine engine. A combustor wall of the turbine engine assembly includes a shell, a heat shield and an annular body engaged with the shell and the heat shield. The annular body extends through the combustor wall. The annular body at least partially defines a quench aperture along a centerline through the combustor wall. The annular body also at least partially defines a cooling aperture in fluid communication with the quench aperture. At least a portion of the cooling aperture extends radially outward from the quench aperture relative to the centerline.

Abstract: A dual wall component for use in a gas turbine engine and a method for making the same are disclosed herein. The dual wall component includes an inner support wall and an outer shield wall that extends around the inner support wall to act as a heat shield for the inner support wall.

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular body. The annular body extends through the combustor wall and at least partially defines a quench aperture along a centerline through the combustor wall. The shell defines a first cooling aperture radially outwards of the annular body relative to the centerline and is configured to direct air to impinge against a portion of the annular body between the heat shield and the shell.

Abstract: A combustor arrangement for a gas turbine includes a first burner, a first combustion chamber, a mixer for admixing a dilution gas to the gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. These elements of the combustor arrangement are arranged in a row to form a flow path extending between the first combustion chamber and the second burner. The arrangement includes a central lance body in the flow path, extending from the first burner into the second burner, which lance body includes at least one air duct for providing air for the mixer, wherein the air is injected into the combustor through air supply elements.

Abstract: The invention refers to a sequential combustor arrangement including a first burner, a first combustion chamber, a mixer for admixing a dilution gas to the hot gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. The mixer includes a plurality of injection pipes pointing inwards from the side walls of the mixer for admixing the dilution gas to cool the hot flue gases leaving the first combustion chamber with a low pressure drop. The disclosure further refers to a method for operating a gas turbine with such a combustor arrangement.

Abstract: A heat shield for a combustor includes a ring shaped body including a central opening defining a radially inner edge of the ring shaped body. The ring shaped body is at least partially made of a ceramic material. The heat shield includes a shaped portion designed to enhance an interference fit.

Abstract: A method and apparatus for a burner adapted to heat a furnace or other environment of use. In particular, a burner for providing a fuel gas in combination with an oxidant to effect controlled reaction of the fuel gas in a manner to reduce NOx emissions is described. Combustion of the fuel gas is shifted from the burner combustor to a location outside the burner once the temperature within the furnace/radiant tube has reached a sufficient level to complete combustion of the fuel gas.

Abstract: A combustor assembly for a gas turbine engine is provided. The combustor assembly generally includes an annular dome and a liner. The liner at least partially defines a combustion chamber and includes the forward end received within a slot defined by the annular dome. Additionally, a heat shield is provided. The heat shield includes an end also received within the slot defined by the annular dome. A mounting assembly attaches the forward end of the liner and the end of the heat shield to the annular dome, such that the forward end of the liner and the end of the heat shield are co-mounted within the slot defined by the annular dome.

Abstract: A self-cooled orifice structure that may be for a combustor of a gas turbine engine, and may further be a dilution hole structure, includes a hot side panel, a cold side panel spaced from the hot side panel, and a continuous inner wall extending between the hot and cold side panels and defining an orifice having a centerline and communicating axially through the hot and cold side panels. A plurality of end walls of the structure are in a cooling cavity that is defined in-part by the hot and cold side panels and the inner wall. Each end wall extends between and are engaged to the hot and cold side panels and are circumferentially spaced from the next adjacent end wall. A plurality of inlet apertures extend through the cold side panel and are in fluid communication with the cavity, and each one of the plurality of inlet apertures are proximate to a first side of a respective one of the plurality of end walls.

Abstract: The present invention discloses a novel apparatus and way for directing a supply of compressed air into a fuel nozzle assembly for mixing with a fuel source. The apparatus comprises a fuel nozzle assembly having a plurality of coaxial tubes and radially-extending swirler vanes for directing a supply of fuel to a mixing tube. Compressed air is directed to flow in a primarily axial direction by passing through a hemispherically-shaped dome portion at an air inlet region of the fuel nozzle assembly. The hemispherically-shaped dome includes a plurality of openings for directing air into the fuel nozzle assembly in a direction having a radial and axial component.

Abstract: A system includes a multi-tube fuel nozzle of a turbine combustor. The multi-tube fuel nozzle includes a support structure defining an interior volume configured to receive an air flow; a plurality of mixing tubes disposed within the interior volume, wherein each of the plurality of mixing tubes comprises a respective fuel injector; and an outer annular wall configured to direct an air flow from an annulus between a liner and a flow sleeve of the turbine combustor at least partially radially inward into the interior volume through an air inlet and toward the plurality of mixing tubes, wherein the outer annular wall at least partially defines an air flow passage extending from the annulus to the interior volume.

Abstract: A fuel combustion system comprises a discharge nozzle with concentric fuel and air orifices. A fuel conduit is coupled to each fuel orifice for supplying liquid fuel thereto. An air conduit is coupled to each air orifice for supplying air thereto. The fuel and the pressurized air only mixing with one another, upon being discharged from the respective fuel and air orifices, to form a fuel mixture. A supplemental air source supplies supplement air to facilitate combustion. An air deflector sleeve at least partially surrounds and accommodates the at least one discharge nozzle and a cylindrical blast tube surrounding the air deflector sleeve and an outlet end of the cylindrical blast tube supports a flame retention head. The flame retention head redirects the supplement air radially inward, through openings in the air deflector sleeve and the flame retention head, to assist with combustion of the fuel mixture.

Abstract: An insert element for closing an opening inside a wall of a hot gas path component of a gas turbine includes a plate like body with an opening sided surface. The surface provides at least one first area which projects beyond at least one second area of said surface which surrounds the at least one first area frame-like. The at least one first area is encompassed by a circumferential edge corresponding in form and size to the opening such that the circumferential edge and the opening contour limit a gap at least in some areas, while the at least one second area contacts directly or indirectly the wall of the hot gas path component at a rear side facing away from the hot gas path. The plate like body provides at least a first functional layer-system, providing at least one layer made of heat resistant material, defining the first area of the surface (S).

Abstract: The gaseous fuel-fired can combustor for a gas turbine include a generally cylindrical housing, and a generally cylindrical liner disposed coaxially within the housing to define with the housing a radial outer flow passage for combustion air, the-liner also defining inner combustion and a dilution zone, the dilution zone being axially distant a closed housing end relative to the combustion zone. A fuel/air mixing apparatus disposed at the closed housing end includes a plurality of swirl vanes defining passages each having constant cross-section flow areas along the vanes, and an increasing aspect ratio from the passage inlet to the outlet. An impingement cooling sleeve coaxially disposed in the combustion air passage between the housing and the liner cools the portion of the liner defining the combustion zone.

Abstract: A combustion chamber of a gas turbine with an outer combustion chamber wall and with tiles attached to the inner side of said wall or to a combustion chamber of the single-wall design, wherein the combustion chamber has in a center area, relative to the flow direction, a slot extending around the circumference of the combustion chamber and dividing the outer combustion chamber wall and the tiles for the supply of mixing air.

Abstract: A combustor component of a gas turbine engine including a heat shield panel. The heat shield panel a defines microcircuit flow path within a thickness of said heat shield panel.

Abstract: A combustor apparatus is provided, comprising a mixing arrangement for mixing a carbonaceous fuel with enriched oxygen and a working fluid to form a fuel mixture. A combustion chamber is at least partially defined by a porous perimetric transpiration member, at least partially surrounded by a pressure containment member. The combustion chamber has longitudinally spaced apart inlet and outlet portions. The fuel mixture is received by the inlet portion for combustion within the combustion chamber at a combustion temperature to form a combustion product. The combustion chamber directs the combustion product longitudinally toward the outlet portion.

Abstract: A combustor having wake air injection is provided. The combustor includes a fuel nozzle, first and second vessels formed and disposed to define a flow path along which a first fluid flows in first and second opposite directions toward the fuel nozzle, a vane disposed in the flow path and an injector to inject a second fluid into wake formed by an obstruction disposed in the flow path upstream from the vane.

Abstract: A transition piece of a combustor that sends high temperature combustion gas to a turbine includes a cylindrical body wall and cooling air passages. The passages are formed in the body wall so as to extend in an axial direction thereof, and each of the passages has cooling air inlet ports opened at an outer circumferential surface of the transition piece and cooling air outlet ports opened at an inner circumferential surface of the transition piece. The cooling air outlet ports form a plurality of lines in a direction oblique with respect to the axial direction of the body wall. A first distance between a first line of the cooling air outlet ports and a second line of the cooling air outlet ports adjacent to the first line is larger than a second distance between the cooling air outlet ports adjacent to each other.

Abstract: A cooling arrangement for a surface of a wall in a gas turbine engine, the wall having a plurality of effusion holes each with an outlet onto the surface for supplying an effusion flow to the surface and an inlet, the inlets of the effusion holes being arranged at the peripheries of groups tessellated on an opposing surface of the wall, each inlet being located on the peripheries of three groups. The arrangement comprises a second wall spaced apart from the opposing surface having impingement orifices each for directing a flow of air in use to a respective impingement location on the opposing surface, each group having a centrally positioned impingement location.

Abstract: An air-fuel burner includes a heat-transfer tube, an air-fuel mixing chamber, and an air-fuel nozzle. The air-fuel nozzle is coupled to the air-fuel chamber to communicate a combustible air-fuel mixture into a combustion chamber defined between the air-fuel nozzle and the heat-transfer tube. The combustible air-fuel mixture, when ignited, establishes a flame in the combustion chamber to produce heat which is transferred through heat-transfer tube to an adjacent medium external to the heat-transfer tube.

Abstract: A burner includes a generally cylindrical casing (1) and a burner head (2) mounted within the casing, the burner head including one or more vanes (9) rotatably mounted on the head and rotatable about the head to sweep through a region between the burner head (2) and the casing (1). The vanes (9) each include one or more gas outlets for introducing gas into an air flow through the region.

Abstract: A high speed burner having very low polluting emissions, suitable for the process for heat treatment furnaces of a load in free atmosphere. The burner is capable of creating a compact and lean flame with the peculiarity of keeping the NOx emissions at very low levels at any chamber temperature and at any excess combustion air. The burner requires a single inlet for the comburent air and a single inlet for the combustible gas.

Abstract: A flame tube for a liquid fuel burner is disclosed. The liquid fuel burner includes a fuel atomizer directing atomized fuel into the flame tube and an igniter disposed within the flame tube to ignite the atomized fuel. The flame tube comprises an outer wall and an inner wall disposed about the outer wall to define an air passage therebetween. At a discharge end of the flame tube, the outer and inner walls are conjoined to form an annular surface, the annular surface being perforated. Preferably, the annular surface is perforated in an evenly distributed pattern.

Abstract: A gas-fired air conditioning furnace has a cavity burner configured to combust an air-fuel mixture at least partially within an interior space of the cavity burner. A method of operating a gas-fired furnace by flowing an air-fuel mixture into a cavity burner through a perforated wall of the cavity burner, combusting at least a portion of the air-fuel mixture within an interior space of the cavity burner, and flowing at least partially combusted air-fuel mixture into a heat exchanger. A gas-fired air conditioning device has a cavity burner that has a cylindrically shaped body and a cap on a first end of the body, each of the body and the cap being perforated. The device has a cylindrically shaped heat exchanger inlet tube and the cavity burner is at least partially concentrically received within the heat exchanger inlet tube.

Abstract: A burner for fabricating an optical fiber preform, which can suppress the adhesion and deposition of glass particles to the front end of the burner without enlarging the burner diameter, is provided. The burner has a first tube, a second tube and a third tube coaxially arranged and define a glass raw material gas port, a sealing gas port, and a burnable gas port by the front end portions thereof, and a plurality of small diameter nozzles arranged between the second tube and the third tube, each of the nozzles arranged on a concentric circle relative to the glass raw material gas port and defines a combustion assisting gas port by the front end portion thereof, the front end portion of the second tube protrudes ahead of that of the first tube, and the front end portion of the third tube protrudes ahead of those of the second tube and each of the nozzles.

Abstract: A combustor having wake air injection is provided. The combustor includes a fuel nozzle, first and second vessels formed and disposed to define a flow path along which a first fluid flows in first and second opposite directions toward the fuel nozzle, a vane disposed in the flow path and an injector to inject a second fluid into wake formed by an obstruction disposed in the flow path upstream from the vane.

Abstract: The present invention provides a gas burner (10) including: a distributor means (50) having at least one distribution chamber to distribute an air gas mixture around said distributor (50), said burner (10) including a plurality of flame ports (70) through which said gas mixture can pass and be ignited; at least one injector (39) associated with said distributor (50), said at least one injector (39) being positioned to inject gas into said at least distribution chamber via a venture formed of a vertically directed passage and transition port (64) and at least one venturi extension extending away from said transition port (64).

Abstract: A combustor assembly that includes a casing that includes a plenum, a combustor liner positioned within the plenum and defining a combustion chamber there within, and a transition piece that includes a forward portion that is coupled to the combustion liner and an aft portion that extends from the forward portion. The aft portion includes a transition piece frame. The transition piece frame includes an upstream surface, a downstream surface, and a radially inner surface extending between the upstream and downstream surfaces. The radially inner surface includes a leading edge that extends between the radially inner surface and the upstream surface. A plurality of first cooling passages extend from the upstream surface to the downstream surface. Each of the first cooling passages is oriented obliquely with respect to the leading edge from the upstream surface towards the downstream surface.

Abstract: A combustor nozzle includes a downstream surface having an axial centerline. A plurality of passages extend through the downstream surface and provide fluid communication through the downstream surface. A plurality of slits are included in the downstream surface, and each slit connects to at least two passages. A method for modifying a combustor nozzle includes machining a plurality of slits in a downstream side of a body. The method further includes connecting each slit to at least two passages that pass through the body.

Abstract: A system, in one embodiment, includes a turbine engine. The turbine engine includes a combustor that includes a hollow annular wall having a combustor liner. The turbine engine also includes first flow path in a first direction through the hollow annular wall. The turbine engine further includes a second flow path in a second direction that is opposite the first direction through the hollow annular wall. The second flow path may include one or more film holes configured to supply a cooling film to a downstream end portion of the combustor liner.

Abstract: Apparatus for enhancing combustion of an undesired chemical to minimize the formation of smoke during operation of a flare stack for the discharge of a flare feedstream includes a plurality of high-pressure air nozzles spaced apart below and around the periphery of the stack outlet. Each nozzle is directed toward the stack outlet and in the direction of the feedstream's movement. High-pressure air from the nozzles forms a plurality of high-velocity air jets to produce a moving air mass that draws additional atmospheric air into the air mass moving toward the stack outlet to enhance combustion of the flare feedstream. Analytical means determine the stoichiometric oxygen requirements, and an air-flow valve controls the flow rate of the high-pressure air to the nozzles.

Abstract: A premix burner with staged liquid fuel supply is described having at least two partial cone shells which on the radial side form the boundary of a swirl chamber which axialwards conically widens, which partial cone shells are arranged in a partially overlapping manner, the center axes of the partial cone shells of which extend with offset effect in relation to each another, and the mutually overlapping partial cone shell sections of which enclose in each case an air inlet slot which extends tangentially to the swirl chamber, with a burner lance which projects axialwards into the swirl chamber, which lance provides means for feed of liquid fuel into the swirl chamber, and also with further means for feed of liquid fuel which are provided in the region of the air inlet slots.