Burner for automobiles

Abstract

The present invention relates to a burner (42) for an exhaust pipe (26) capable of being traversed by exhaust gases of an internal combustion engine (12) of a motor vehicle, comprising a combustion chamber (58) in which a mixture comprising air and liquid fuel is ignited and thereby burned, and an inner swirl chamber (62) capable of being traversed by a first portion of the air, the inner swirl chamber having a first swirl generating device (115) capable of inducing a vortex flow of the first portion of the air, and a first outlet opening (64) capable of being traversed by the first portion of the air flowing through the inner swirl chamber (62), through which the first portion of the air can be discharged from the inner swirl chamber (62).

Description

[Technical Field]

[0001] The present invention relates to a burner for an exhaust pipe that can be traversed by exhaust gases of an internal combustion engine of a motor vehicle. [Background technology]

[0002] From the prior art in general and from the production of mass-produced vehicles in particular, motor vehicles are known which have an internal combustion engine and an exhaust system, also called an exhaust pipe. The respective exhaust pipe can be passed through by the exhaust gases of the internal combustion engine, also called an internal combustion engine. In some operating states or situations of the respective internal combustion engine, a high temperature of the exhaust gases may be desirable, for example in order to quickly heat up and / or keep at a high temperature an exhaust gas aftertreatment device arranged in the exhaust pipe, but in such operating states or situations the temperature of the exhaust gases is insufficiently high.

[0003] Patent Document 1 discloses a burner for an exhaust pipe traversed by exhaust gas from an internal combustion engine of a motor vehicle, having a combustion chamber for igniting and burning a mixture containing air and liquid fuel. The burner has an inner swirl chamber traversed by a first portion of air and causing a vortex flow of the first portion of air. The inner swirl chamber has a first outlet opening through which the first portion of air can be discharged from the inner swirl chamber. Liquid fuel can be injected into the inner swirl chamber by an injection element. A second swirl chamber circumferentially surrounds the inner swirl chamber over at least one length region. The second swirl chamber is traversed by the second portion of air and causes a vortex flow of the second portion of air. The second swirl chamber has a second outlet opening through which the second portion of air, the first portion of air, and the liquid fuel can be introduced from the inner swirl chamber into the combustion chamber. [Prior art documents] [Patent documents]

[0004] [Patent Document 1] German Patent No. 3729861 Summary of the Invention [Problem to be solved by the invention]

[0005] The object of the present invention is to provide a burner for the exhaust pipe of a motor vehicle, which makes it possible to carry out a particularly favorable mixture pretreatment. [Means for solving the problem]

[0006] This problem is solved by a burner with the features of claim 1 and by a motor vehicle with the features of claim 10. Advantageous embodiments according to expedient developments of the invention are set forth in the further claims.

[0007] A first aspect of the present invention relates to a burner for an exhaust pipe that can be traversed by exhaust gases from an internal combustion engine of a motor vehicle, also known as an internal combustion engine. This means that a motor vehicle, which may preferably be configured as a motor vehicle, most preferably as a passenger car, has an internal combustion engine and an exhaust pipe in its fully manufactured state and can be driven by the internal combustion engine. During combustion operation of the internal combustion engine, a combustion process takes place in the internal combustion engine, particularly in at least one or more combustion chambers of the internal combustion engine, resulting in exhaust gases from the internal combustion engine. These exhaust gases exit the respective combustion chambers and flow into the exhaust pipe, which can then traverse the exhaust pipe, also known as an exhaust system. At least one component, such as an exhaust gas aftertreatment element, for aftertreatment of the exhaust gases can be arranged in the exhaust pipe. The exhaust gas aftertreatment element can be, for example, a catalytic converter, particularly an SCR catalytic converter, whereby selective catalytic reduction (SCR) can be catalytically supported and / or initiated by the SCR catalytic converter. In selective catalytic reduction, nitrogen oxides that may be present in the exhaust gas are at least partially removed from the exhaust gas by reacting them with ammonia to form nitrogen and water during the selective catalytic reduction. The ammonia is provided, for example, by a particularly liquid reducing agent. Furthermore, the exhaust gas aftertreatment component can be or include a particulate filter, in particular a diesel particulate filter, by means of which particles, in particular soot particles, contained in the exhaust gas can be filtered from the exhaust gas.

[0008] The burner has a combustion chamber in which a mixture containing air and liquid fuel can be ignited and burned. In particular, the combustion of the mixture in the combustion chamber produces burner exhaust gas, also called burner exhaust gas. The burner exhaust gas can, for example, exit the combustion chamber and enter the exhaust pipe, particularly at an inlet located upstream of the components, for example, in the direction of flow of the exhaust gas from the internal combustion engine through the exhaust pipe. As a result, the burner exhaust gas can, for example, flow through the components and thereby heat them. It is also conceivable that the burner exhaust gas exits the combustion chamber and enters the exhaust pipe, thereby mixing with the exhaust gas from the internal combustion engine flowing through the exhaust pipe and / or with the gas flowing through the exhaust pipe, thereby heating the exhaust gas or gases from the internal combustion engine. In other words, a particularly high temperature of the exhaust gas or gases from the internal combustion engine, also called the exhaust gas temperature, can be achieved. Because the exhaust gas or gases flow past the components, the high exhaust gas temperature can heat the components. Thus, for example, exhaust gases from the combustion chamber are introduced into the exhaust pipe at the aforementioned introduction points and are thus introduced into the exhaust gases or gases flowing through the exhaust pipe. For example, an ignition device, particularly an electrically operable ignition device, is arranged in the combustion chamber, by means of which at least one ignition spark can be provided, i.e., generated, for ignition of the mixture, for example, in the combustion chamber and / or using electrical energy or current. The ignition device is, for example, a glow plug or a spark plug.

[0009] The burner preferably has an inner swirl chamber through which the first portion of air forming the air-fuel mixture can flow and which generates a swirling flow of the first portion of air, and is therefore arranged upstream of the combustion chamber as seen in the direction of flow of the first portion of air flowing through the inner swirl chamber. The inner swirl chamber has, in particular, exactly one first outlet opening through which the first portion of air flowing through the first outlet opening can be discharged from the inner swirl chamber and, for example, introduced into the combustion chamber. The requirement that the inner swirl chamber induces or is capable of inducing a vortex flow of the first portion of air flowing through it is understood in particular to mean that the first portion of air flows vortically through the swirl chamber, i.e., flows vortically through at least one length region of the swirl chamber, and / or that the first portion of air only has a vortex flow in at least a first flow region arranged downstream of and outside the inner swirl chamber, for example in a combustion chamber. It is particularly conceivable that the first portion of air vortexes out of the inner swirl chamber via a first outlet opening and / or vortexes into the combustion chamber, so that the first portion of air has its vortex flow at least in the combustion chamber.

[0010] The burner further comprises an injection element, in particular an injection element, having at least one or exactly one outlet opening through which a liquid fuel can flow. The outlet opening is arranged in the inner swirl chamber, so that the injection element, in particular the injection element or the passage of the injection element through which the liquid fuel can be penetrated, communicates with the inner swirl chamber via the outlet opening. The injection element allows the fuel flowing through the outlet opening to be injected, in particular injected, in particular directly into the inner swirl chamber via the outlet opening, so that the first outlet opening can also be penetrated by the liquid fuel that leaves the injection element via the outlet opening, in particular is ejected, and is thereby injected, in particular directly, into the inner swirl chamber. This means, in particular, that a first portion of the air and the fuel can flow through the first outlet opening along a common first flow direction and thereby exit the inner swirl chamber.

[0011] The burner further includes an outer swirl chamber that surrounds at least one length of the inner swirl chamber, and preferably also the first outlet opening, in the circumferential direction of the inner swirl chamber, particularly completely. For example, the circumferential direction of the inner swirl chamber extends around the aforementioned first flow direction, which coincides with the axial direction of the inner swirl chamber and thus of the first outlet opening. Preferably, the inner swirl chamber is intended to terminate at the first outlet opening or its end in the direction of flow of the first portion through the first outlet opening, and thus in the axial direction of the inner swirl chamber and thus of the first outlet opening. The outer swirl chamber can be passed through by the second portion of air and is configured to generate a swirling flow of the second portion of air. This is understood in particular to mean that the second portion of air flows within the outer swirl chamber, i.e., flows vortex-like through at least one partial region or length of the outer swirl chamber, and / or has a vortex-like flow in a second flow region, for example, corresponding to the first flow region mentioned above and arranged downstream of the outer swirl chamber as seen in the direction of flow of the second portion of air flowing through the outer swirl chamber; the second flow region may, for example, be arranged outside the outer swirl chamber and, for example, inside the combustion chamber. It is also conceivable that the first flow region mentioned above is arranged outside the outer swirl chamber. In other words, it is conceivable that the second portion of air vortex-like exits the outer swirl chamber and / or vortex-like enters the combustion chamber; preferably, therefore, the second portion of air has a vortex-like flow at least within the combustion chamber.

[0012] The outer swirl chamber has, for example, in particular just one second outlet opening, through which the second portion of air flowing through the outer swirl chamber, the fuel flowing through the first outlet opening, and the first portion of air flowing through the inner swirl chamber and the first outlet opening can flow, for example, arranged downstream of the first outlet opening in the flow direction of the portions and the fuel, through which the second portion of air can be discharged from the outer swirl chamber and the portion of air and the fuel can be introduced into the combustion chamber. In particular, the portion of air and the fuel can flow through the second outlet opening along a second flow direction and thus enter the combustion chamber via the second outlet opening, for example, the second flow direction extending parallel to or coinciding with the first flow direction. Furthermore, it is preferably intended that the second flow direction extends in the axial direction of the outer swirl chamber and thus coincides with the axial direction of the outer swirl chamber, and thus preferably that the axial direction of the inner swirl chamber corresponds to the axial direction of the outer swirl chamber, or vice versa. In other words, it is preferably intended that the axial direction of the inner swirl chamber coincides with the axial direction of the outer swirl chamber, or vice versa. The respective radial directions of the respective swirl chambers extend perpendicular to the respective axial directions of the respective swirl chambers. For example, the second outlet openings are arranged downstream of the first outlet openings along the respective flow directions, i.e., in the flow directions of the respective air portions and the fuel, and preferably the outer swirl chamber surrounds the first outlet opening, so that, for example, the first outlet opening is arranged in the outer swirl chamber. In particular, it is conceivable that the outer swirl chamber terminates at the second outlet opening, particularly at its end, in the flow direction of the second air portion flowing through the second outlet opening.

[0013] For example, to generate a respective vortex flow, each vortex chamber can have at least one or more vortex generators, by means of which the respective vortex flow can be generated or is generated. In particular, each vortex generator is arranged in each vortex chamber. In particular, the vortex generator can be, for example, a guide vane, by means of which, for example, the respective portion, i.e., the respective air forming the respective portion, is turned at least once or exactly once, in particular by at least or exactly 70 degrees, in particular by approximately 90 degrees, i.e., for example, by 70 to 90 degrees. In particular, a vortex flow is understood to mean a flow that extends vortically or at least substantially spirally or helically around the respective axial direction of the respective vortex chamber or of the respective outlet opening. In particular, the respective axial direction of the respective outlet opening extends perpendicular to the plane in which the respective outlet opening extends. In this case, for example, the respective axial direction of the respective outlet opening coincides with the respective axial direction of the respective vortex chamber. Each outlet opening is also called, for example, a respective nozzle, although its cross section, which can be pierced by each portion of air, does not necessarily have to be tapered along the respective flow direction. Thus, for example, the second outlet opening is also called an outer nozzle or second nozzle, and the first outlet opening is also called, for example, an inner nozzle or first nozzle.

[0014] The respective vortex flows generated allow the air to be mixed with the liquid fuel particularly favorably, even over a particularly short mixing path, particularly in the combustion chamber, thereby achieving a particularly favorable mixture preparation, i.e., a particularly favorable mixture formation. In particular, the fuel can first be mixed particularly well with the first portion of the air, particularly in the inner swirl chamber, due to the vortex flow of the first portion in the inner swirl chamber. Furthermore, the fuel, and for example the first portion already mixed with the fuel, can be mixed particularly favorably with the second portion of the air, particularly in the outer swirl chamber and / or the combustion chamber, because the second portion of the air also has a favorable vortex flow. Overall, the vortex flow allows a particularly favorable mixing of the air portions with the fuel, thereby achieving a favorable mixture preparation.

[0015] The inner swirl chamber has a first inner vortex generator, which can be used to generate a first vortex flow of the first portion of air. Furthermore, the outer swirl chamber has a second outer vortex generator, which can be used to generate a second vortex flow of the second portion of air. For example, the vortex generator constitutes a vortex generating device or is a structural part of a vortex generating device of a burner. It is particularly conceivable that the vortex generating devices are configured integrally with each other or formed by an integral component. For example, the first vortex generating device preferably has at least one or more first vortex generators, preferably first guide vanes, which can be used to guide, deflect, or redirect the air or the first portion of air in such a way that a vortex flow of the first portion of air can be generated, i.e., generated. Alternatively or additionally, the second vortex generating device may have at least one or more second vortex generators, preferably second guide vanes, by means of which the air or the second portion of the air may be guided, redirected or deflected in such a way that a second vortex flow of the second portion of air can be generated, i.e. generated. Preferably, the vortex generators of each vortex generating device are intended to be arranged consecutively in the circumferential direction of the respective vortex chamber, in particular extending about the respective axial direction of the respective vortex chamber, and / or spaced apart from one another.

[0016] In order to carry out the particularly preferred pretreatment, also called mixture pretreatment, or mixture formation, and thus to be able to heat the components particularly quickly and efficiently and / or keep them at a high temperature, the burner further comprises a separating wall with at least one length section that is arranged or extends upstream of the swirl generator, as seen in the direction of flow of the air portions through the swirl chamber, i.e., as seen in the direction of flow of the air through the swirl chamber. The separating wall and thus the length section are preferably constructed as a solid body. The separating wall separates the inner air supply chamber, which is associated with the inner swirl chamber and is arranged upstream of the first vortex generating device in the direction of flow of the first portion of air flowing through the inner swirl chamber and is capable of supplying the first portion of air to the inner swirl chamber, from the outer air supply chamber, which is associated with the outer swirl chamber and is arranged upstream of the second vortex generating device in the direction of flow of the second portion of air flowing through the outer swirl chamber, is fluidly connected to the outer air supply chamber via the overflow opening, and is preferably in particular permanently connected to the outer air supply chamber, and which surrounds the inner air supply chamber in the circumferential direction of the respective swirl chamber, in particular completely. The outer air supply chamber is thus delimited in the radial direction of the respective swirl chamber, in particular directly, by the separating wall, in particular by the outer circumferential outer surface of the separating wall, for example, the outer air supply chamber is delimited in the radial direction of the respective swirl chamber, in particular directly, by a component of the burner which is configured or functions as a chamber element, in particular configured as a solid body, in particular by the inner circumferential outer surface of the chamber element, while the inner air supply chamber is delimited in the radial direction of the respective swirl chamber, in particular directly, by the separating wall, in particular by the inner circumferential outer surface of the separating wall.

[0017] The burner further has a supply passage through which air can flow, in particular directly communicating with the outer air supply chamber, and through which air can be introduced into the outer air supply chamber. From or starting from the outer air supply passage, a second portion of air can be transferred and introduced into the inner air supply chamber through the overflow opening, thereby dividing the air introduced into the outer air supply chamber into portions. In other words, part of the air introduced into the outer air supply chamber through the supply passage flows through the overflow opening and can thereby flow from the outer air supply chamber into the inner air supply chamber, becoming part of the first portion of air. The air remaining in the outer air supply chamber and flowing from there into the outer swirl chamber becomes the second portion of air. In this way, the separating wall allows the air to be divided into portions and supplied to the respective swirl chambers in a particularly favorable manner, thereby allowing the air to be mixed with the fuel in a particularly favorable manner. In this case, it is intended in particular that the radial direction of each swirl chamber extends perpendicular to the axial direction of the respective swirl chamber, and that the respective axial direction of each swirl chamber preferably coincides with the respective flow direction in which the air or the respective part of the air flows through the respective swirl chamber or the respective outlet opening.

[0018] Each air supply chamber is, for example, a respective pre-chamber, or the air supply chambers as a whole form a pre-chamber, which allows a particularly favorable division of the air into portions and, as a result, a particularly good mixing of the air with the fuel, thereby ensuring a particularly favorable pre-treatment of the air-fuel mixture and thereby allowing a particularly efficient and therefore fuel-saving operation of the burner.

[0019] In another embodiment of the invention, the injection element has at least one, or just one, or several outlet openings through which fuel can flow. Via each outlet opening, fuel can be discharged from the injection element, in particular can be ejected from an injection element, for example configured or functioning as an injection element. By discharging liquid fuel from the injection element, the fuel discharged from the injection element and thereby provided by the injection element can be injected, in particular injected, into the inner swirl chamber.

[0020] It is particularly advantageous here if the injection element, i.e. the fuel passage of the injection element, also simply called the passage, through which the liquid fuel can flow, communicates directly with the inner air supply chamber via the outlet opening.

[0021] Since the outer air supply chamber surrounds the inner air supply chamber, and since the air supply chambers are fluidly connected to one another via the overflow openings, and since the supply passages in particular lead directly to the outer air supply chamber, the air supply chambers are arranged in particular serially, i.e., connected in series with one another, in the direction of air flow from the supply passages through the air supply chambers towards and into the vortex chamber, with the inner air supply chamber being arranged in particular downstream of the outer air supply chamber. In other words, the inner air supply chamber receives a supply of air or a first portion of the air from the outer air supply chamber via the overflow openings, thereby enabling a particularly advantageous air division.

[0022] For example, the overflow openings and the supply channels, in particular the passage openings of the supply channels which communicate in particular directly with the outer air supply chamber via the passage openings, are intended to be arranged at least partially, in particular at least substantially or completely, at the same height in the circumferential direction of the respective air supply chamber, so that, for example, the supply channels or passage openings are at least partially, in particular at least substantially or completely, overlapped or covered by the overflow openings towards the inside in the radial direction of the respective air supply chamber, the circumferential direction of the respective air supply chamber running around the respective axial direction of the respective air supply chamber, which axial direction coincides with the respective axial direction of the respective swirl chamber.

[0023] In order to achieve particularly favorable mixture pretreatment, another embodiment of the invention provides for guide bodies to be arranged in the inner air supply chamber, in particular in the axial direction of the respective air supply chamber or swirl chamber, facing the injection element, which guide bodies are arranged between the first swirl generators in the radial direction of the inner swirl chamber and therefore in the radial direction of the outer swirl chamber, i.e. in the radial direction of the respective air supply chamber. This particularly means that, for example, the first swirl generators are arranged in the circumferential direction of the inner air supply chamber and therefore in the circumferential direction of the first swirl chamber, and therefore in particular in the circumferential direction of the guide body, in particular evenly distributed around its circumference. In other words, for example, the first swirl generators are adjacent to one another in the circumferential direction of the guide body, and therefore in the circumferential direction of the respective swirl chamber and in the circumferential direction of the respective air supply chamber. The guide bodies, i.e., the guide surfaces of the guide bodies, which in particular face the injection element in the axial direction of the respective air supply chamber and thus in the axial direction of the respective swirl chamber, are preferably convexly curved toward the injection element and are arranged at least partially upstream of the first swirl generator. The guide bodies, in particular the guide surfaces, are preferably arranged rotationally symmetrically with respect to the axial direction of the respective air supply chamber and thus in the axial direction of the respective swirl chamber. This allows the air, i.e., the first portion of the air, to flow in the axial direction of the respective swirl chamber and impinge on one or more guide bodies or guide surfaces and be guided or directed by the guide bodies in a particularly favorable manner, in particular toward the first swirl generator. In this way, the guide bodies enable a particularly flow-friendly air guidance, which in turn enables a particularly favorable mixture pre-treatment.

[0024] Another embodiment is characterized in that the first outlet opening, in the flow direction of the first portion of the air flowing through the first outlet opening, ends at a precisely processed end edge, which end edge is formed by an atomizing lip, in particular configured as a solid, which tapers up to the end edge in the flow direction of the first portion of the air flowing through the first outlet opening and ends at the end edge.

[0025] In other words, in order to enable a component configured as, for example, an exhaust gas aftertreatment device or an exhaust gas aftertreatment system, to be heated particularly quickly and effectively, especially when the exhaust gases of an internal combustion engine have only low temperatures, the first outlet opening (first or inner nozzle) can be designed to be precisely shaped in the flow direction of the first portion of air flowing through the first outlet opening and thus terminate in a sharp or knife-edge edge, which is preferably formed by an atomizing lip that tapers toward and terminates at the edge in the flow direction of the first portion of air flowing through the first outlet opening and thus in the flow direction of the fuel flowing through the first flow opening. This means that the atomizing lip has a taper that tapers toward the first flow direction, and therefore in particular toward the combustion chamber, and in particular terminates only at the edge. This, and in particular the precise machining of the end edge, results in a sharply tapered portion or atomizing lip, or in other words, the atomizing lip ends in a sharp edge, which allows particularly favorable mixture preparation to be carried out.

[0026] For example, an air-fuel mixture is burned in the combustion chamber to form a flame, and the vortex flow allows the fuel to be mixed with the air favorably, and in particular the flame in the combustion chamber to be stabilized favorably due to the vortex flow. For this purpose, the vortex flow can be used to generate combustion-induced vortex breakdown. For example, the air flowing into the combustion chamber is redirected in each vortex chamber by approximately 70 degrees or approximately 90 degrees, particularly within the range of 70 to 90 degrees, which can be achieved, for example, by a respective vortex generator. The inner and outer vortex chambers form a single vortex chamber, also referred to as a total vortex chamber, which is divided into the inner and outer vortex chambers in the present invention. The inner and outer vortex chambers are preferably separated from each other by a separating wall, preferably formed as a solid, particularly in the radial direction of the respective vortex chamber. In this case, the separating wall can surround at least the aforementioned length of the inner swirl chamber, particularly completely, in the circumferential direction of the inner swirl chamber, extending around the axial direction of the inner swirl chamber. For example, the separating wall can define at least the length of the inner swirl chamber, particularly directly radially outward from the inner swirl chamber. Furthermore, it is also conceivable that at least one second length of the outer swirl chamber can be defined, particularly directly radially inward from the outer swirl chamber, by the separating wall. In this case, it is particularly conceivable that the length of each swirl chamber can be arranged at the same axial height of the respective swirl chamber. During operation of the burner, the outer swirl chamber is circulated exclusively by air, i.e., only by the second portion of air, while the inner swirl chamber is circulated exclusively by air, i.e., by the first portion, and by liquid fuel. In this way, desirable mixing of the first portion of air with the fuel can be achieved already in the inner swirl chamber. The injection element, in particular the injection element, may be an injection nozzle, the outlet opening of which is arranged, for example, in or on the surface of the front or end face of the injection element, the front or end face of the injection element extending in a front or end plane that extends perpendicular to the axial direction of the respective swirl chamber.It is further conceivable that the injection element is configured as a lance, for example, having a longitudinal extension coinciding with the axial direction of the respective swirl chamber or the respective outlet opening. In this case, the lance has, for example, at least one or exactly one outlet opening, which may be configured as at least two or exactly two holes, in particular as cross holes. The outlet opening has a through-flow direction along which the fuel can flow through the outlet opening. In particular, if the injection element is configured as an injection nozzle, the through-flow direction of the outlet opening extends parallel to the axial direction of the respective swirl chamber or the respective axial direction of the respective swirl chamber or the respective outlet opening. In particular, if the injection element is configured as a lance, the through-flow direction extends obliquely or preferably perpendicular to the axial direction of the respective swirl chamber or the respective outlet opening.

[0027] In particular, it is conceivable that at least the inner swirl chamber is formed by a component, in particular formed as a solid, which also forms the atomizing lip and thus the end edge. In particular, the inner circumferential outer surface of this component defines the inner vortex in the radial direction of the inner swirl chamber toward the outside. In this case, for example, this component, in particular its inner circumferential outer surface, is or functions as a film attachment between the individual swirl chambers and thus between the respective vortex-like, or swirled, flows, also called air flows. In particular, it is conceivable that the inner circumferential outer surface or the film attachment is formed by or has the above-mentioned separating wall. In this case, the fuel, in particular injected by the injection element, which flows through the outlet opening and thereby leaves the injection element, is applied to the film attachment, in particular as a film, also called a fuel film, on the inner circumferential outer surface, or is sprayed onto the film attachment between the two swirled air flows. Due to the centrifugal force resulting from the vortex flow of the first portion of air, the fuel that leaves the injection element, particularly being ejected and thus injected, particularly directly into the inner swirl chamber, i.e., nozzle-injected, adheres to the film attachment area, particularly on the inner circumferential outer surface, particularly as the aforementioned film, and flows downstream toward the first outlet opening, also called the nozzle opening, and thus toward the end edge. That is, the fuel is applied to the atomizing lip and carried or transported to the end edge. According to the present invention, the first outlet opening terminates in a knife-sharp end edge, which, due to the tapering described above, has or does not provide a small area, so that excessively large droplets of fuel do not form at the end edge. Due to the inventive design of the atomizing lip, and particularly the end edge, only very small droplets of fuel separate at the end edge. In other words, the fuel film generates particularly small, i.e., minute droplets at the edge, which separate from the atomizing lip or component at the edge and have a correspondingly large surface area, resulting in a particularly soot-free combustion of the mixture in the combustion chamber.This allows for the generation of very small fuel droplets without the need for expensively generated high fuel injection pressures and without the need for cost-intensive injection elements, which in turn allows for particularly low burner costs. On the other hand, the generation of particularly small fuel droplets also allows for very low burner outputs. The present invention is based in particular on the finding that conventional burners have excessively high pressure losses and are therefore unsuitable for low outputs, and therefore have drawbacks in terms of fuel consumption. The problems and drawbacks mentioned above can only be avoided by the present invention, which in turn allows for particularly low fuel consumption. Whenever an injection element is mentioned below, this is understood to mean the injection element.

[0028] When referring below to gases flowing through an exhaust pipe, this is understood to mean the exhaust gases of the internal combustion engines mentioned above or the gases mentioned above, unless otherwise specified. The mentioned introduction points into which the burner exhaust gases can be introduced into the exhaust pipe or the gases are conceivably arranged in the direction of flow of the gases through the exhaust pipe downstream or upstream of an oxidation catalyst device, for example configured as a diesel oxidation catalyst. The oxidation catalyst device is configured in particular to oxidize unburned hydrocarbons (HC) that may be present in the exhaust gas and / or to oxidize carbon monoxide (CO) that may be present in the exhaust gas, in particular to carbon dioxide.

[0029] In order to generate particularly small droplets of fuel by the end edge, in one embodiment of the invention, it is intended that the end edge be precisely machined. The requirement that the end edge be precisely, in particular mechanically machined, is understood to mean, in particular, that the end edge is not, for example, randomly configured or has an arbitrarily intended machining, but rather that the end edge is or is machined precisely, and thus, in particular mechanically, as desired within the scope of the manufacture of the burner.

[0030] Another embodiment is characterized in that the end edges are turned, i.e. turned and / or ground, and thus precisely machined, so that they can be used to generate particularly small fuel droplets.

[0031] In order to be able to achieve a particularly efficient operation and, as a result, a particularly good mixture pre-treatment, in another embodiment of the invention it is provided that at least one length region of the injection element is surrounded, in particular completely, in the circumferential direction of the injection element, and thus in the circumferential direction of the respective swirl chamber and in the circumferential direction of the respective air supply chamber, by a cooling jacket which can be passed through by a cooling fluid for cooling the injection element.

[0032] It is particularly preferred that the cooling fluid is a cooling liquid, which ensures particularly good heat transfer. The cooling liquid preferably contains at least, in particular at least substantially or entirely, water, which ensures particularly good cooling.

[0033] In another particularly preferred embodiment of the invention, the burner is intended to have an ignition device, in particular electrically operable, by means of which the mixture in the combustion chamber can be ignited and thus burned. The ignition device is, for example, configured to provide, i.e., generate, in the ignition chamber, at least one ignition spark, in particular by means of electrical energy or current, by which the mixture in the combustion chamber is ignited. The ignition device is, for example, configured as a glow plug, spark plug, or glow pin.

[0034] In order to achieve particularly efficient operation of the burner and thus particularly favorable mixture pretreatment, it is particularly preferred that the ignition device have at least one cooling rib for cooling the ignition device, which extends radially outward from the body of the ignition device. In particular, the ignition device may be provided with a plurality of cooling ribs for cooling the ignition device, which extend radially outward from the body of the ignition device and are spaced apart in the longitudinal direction of the body. The radial direction of the ignition device, and thus of the body, runs perpendicular to the longitudinal direction of the body and thus of the entire ignition device. The cooling ribs provide a particularly large surface, through which heat can be removed from the ignition device in a particularly favorable manner. To achieve particularly favorable cooling of the ignition device and thus particularly favorable operation of the burner, in another embodiment of the invention, each cooling rib has a plurality of through-openings, through which air can flow.

[0035] Finally, it is particularly preferred that the burner has at least one closing element that is movable, particularly translationally, relative to the outlet openings and, for example, relative to the aforementioned components, for example, pivotable, particularly solid, between at least one closed position in which at least one of the outlet openings is fluidly blocked and at least one open position in which the at least one outlet opening is free. In other words, in the closed position, the closing element blocks the at least one outlet opening, so that particles and gases, in particular from the combustion chamber, cannot penetrate into or through the at least one outlet opening. However, in the open position, the closing element frees the at least one outlet opening, so that air can flow through the at least one outlet opening. The closing element prevents gases, such as exhaust gases from the combustion chamber, and / or particles from the combustion chamber from penetrating the at least one outlet opening and thus into the swirl chamber, thereby preventing adverse effects on the mixture pretreatment that could be caused by such particles or gases.

[0036] In another particularly preferred embodiment of the invention, the vortex flow of the first portion of air, particularly in the inner vortex chamber, is intended to be opposite to the vortex flow of the second portion, particularly in the outer vortex chamber. In other words, each vortex chamber is preferably configured to generate vortex flows of the respective portions of air in opposite directions relative to one another. Thus, for example, a first of the respective vortex flows extends in a first rotational direction when viewed along the respective axial direction of the respective vortex chamber during operation of the burner or during the above-mentioned operation. In other words, for example, the first vortex flow has a first rotational direction when viewed along the axial direction of the respective vortex chamber. The second vortex flow has a second rotational direction opposite to the first rotational direction when viewed along the axial direction of the respective vortex chamber. In other words, the second vortex flow extends in a second rotational direction opposite to the first rotational direction when viewed along the axial direction of the respective vortex chamber. This allows a particularly favorable mixture preparation to be carried out, whereby the components can be heated and / or kept at high temperatures quickly and efficiently, i.e. with low fuel consumption.

[0037] To achieve particularly favorable mixture pre-treatment and thus particularly efficient burner operation, another embodiment of the invention provides that the smallest flow cross-section of the second outlet opening, through which the second portion of air can flow, is defined or formed entirely radially inwardly by the end edge of the respective outlet opening and thus of the respective swirl chamber. In other words, the second outlet opening has its smallest flow cross-section at the end edge.

[0038] In another particularly preferred embodiment of the invention, the outer swirl chamber and thus the second outlet opening are formed by a component that may be configured separately, in particular integrally, from the aforementioned components. It is particularly conceivable that the aforementioned components, in particular integrally, may be arranged within the component. It is then preferably provided that a recirculation prevention plate that projects radially outward from at least one partial region of the component extends radially away from the respective outlet opening and thus from the respective swirl chamber. It is conceivable that this partial region is arranged upstream of the recirculation prevention plate, i.e., on the back side of the recirculation prevention plate, with its back side facing the respective swirl chamber. For example, at least one first region of the combustion chamber, in which the recirculation prevention plate is arranged, is thereby at least partially separated from a second region of the combustion chamber by the recirculation prevention plate. In particular, the anti-recirculation plate can be configured to extend around the axial direction of the outlet opening, in the circumferential direction of the outlet opening and thus of the swirl chamber, or around the outlet opening. The anti-recirculation plate can prevent the air-fuel mixture, especially after being discharged from the second outlet opening, from returning to the combustion chamber, i.e., counter to the flow direction of the fuel and air through the second outlet opening, thereby preventing excessive swirl formation in the combustion chamber. For this purpose, the anti-recirculation plate is preferably configured to extend in an imaginary plane that extends perpendicular to the flow direction and thus perpendicular to the axial direction of the outlet opening or swirl chamber. In this way, a particularly efficient operation of the burner can be achieved.

[0039] In order to avoid excessive backflow of the air-fuel mixture in the combustion chamber and thus excessive swirl formation in the combustion chamber and thus to enable particularly efficient operation of the burner, in another embodiment of the invention it is provided that the second outlet opening, in the flow direction of the air portion flowing through the second outlet opening and thus in the flow direction of the fuel through the second outlet opening, ends in an imaginary plane extending perpendicular to the flow direction of the air portion flowing through the second outlet opening, or in the above-mentioned imaginary plane, on which the recirculation prevention plate is arranged. In this way, the recirculation prevention plate is not offset in the opposite direction with respect to the second flow direction, in particular with respect to its end, but rather the second outlet opening, in particular its end, and the recirculation prevention plate are preferably located in a common imaginary plane, which reliably prevents excessive swirl formation.

[0040] It has proven particularly advantageous here if the anti-recirculation plate is constructed integrally with the component, as this makes it possible to reliably avoid excessive vortex formation, thereby enabling particularly efficient burner operation in a particularly cost-effective manner.

[0041] Finally, it is particularly preferred if the combustion chamber has a plurality of exhaust openings that are spaced apart from one another and separated from one another by respective wall sections that are preferably solid, and that are preferably integral with one another. For example, the wall sections are formed by perforated plates or perforated panels. Via the exhaust openings, the burner exhaust gases resulting from the combustion of the air-fuel mixture can be discharged from the combustion chamber and thus introduced into the exhaust pipe.

[0042] The following describes the start-up of the burner. During a cold start of the burner, high temperatures and, therefore, high air movement in the respective swirl chambers have not yet occurred. This condition usually does not allow ignition, or at least makes ignition difficult. To achieve particularly fast and efficient start-up of the burner, even when the internal combustion engine is running and / or in low ambient conditions, the mixture in the combustion chamber must be ignitable, i.e., an ignitable mixture must be present. This can be achieved by fuel or by so-called pre-dosing of the fuel. For this purpose, for example, first, during a set or settable period of time, which may be, for example, between 2 and 6 seconds, fuel is delivered by a fuel pump into the inner swirl chamber, in particular through an injection element, and is thereby pre-dosed. In particular, the ignition device remains deactivated during this period, i.e., the ignition device does not provide an ignition spark during this period. Only after this time period has elapsed is the ignition device switched on, i.e., activated, and the actual air and fuel supply begins. In other words, it is intended that, for example, no air is supplied to the swirl chamber during this time period. This pre-dosing results in the formation of a particularly rich mixture, which, despite the large droplets, provides a large fuel surface suitable for ignition due to its particularly large mass.

[0043] The preferred cooling of the ignition device, for example, configured as a spark plug, can be achieved, for example, by a rib with a hole, especially a bore, especially made of aluminum, which can be arranged or provided on the thread of the ignition device, also called a spark plug thread, especially configured as an external thread. Alternatively or additionally, a particularly eccentric air supply, i.e., an at least substantially eccentric supply of each portion of air, to each swirl chamber or to at least one of the swirl chambers, can be provided. The fuel pumps mentioned above can be frequency-controlled and / or have a piston and spring to prevent backflow of exhaust gases. This can avoid the use of non-return valves and create particularly small dead volumes. It is particularly conceivable for the membrane attachment or the inner swirl chamber to have a Venturi nozzle, for example, on the surface or in the narrowest flow cross section of which the injection element is arranged. The injection element, especially the lance, can have preferably several, especially more than two, particularly small outlet openings. The penetration direction, for example, forms a jet angle with the axial direction of the inner swirl chamber. In other words, for example, fuel flows through the outlet opening while forming a fuel jet, and thus exits the injection element via the outlet opening, with the fuel jet, in particular with its longitudinal axis, coinciding with the penetration direction. By appropriately selecting or adjusting the jet angle, particularly favorable mixture preparation can be achieved. Alternatively or additionally, an afterburner or reburning function is conceivable, for example, to generate a particularly high burner power, in particular a burner power of more than 8 kilowatts. The burner has a rated power, which may be, for example, 8 kilowatts, and the afterburner function allows for at least temporarily higher burner power than the rated power. This allows for particularly high gas temperatures, for example, of at least 600 degrees Celsius or more, and thus for example, components configured as particle filters, to be heated to particularly high temperatures of at least 600 degrees Celsius or more.

[0044] A second aspect of the invention relates to a motor vehicle, in particular configured as a motor vehicle, very preferably as a passenger car, comprising at least one burner according to the first aspect of the invention.

[0045] Further advantages, features and details of the present invention will become apparent from the following description based on preferred embodiments and drawings. The features and combinations of features mentioned in the above description and the following description of the figures and / or shown only in the figures can be used not only in the respective combinations presented, but also in other combinations or alone without departing from the scope of the present invention. [Brief explanation of the drawings]

[0046] [Figure 1] 1 is a schematic diagram showing a drive system of a motor vehicle having an internal combustion engine, an exhaust pipe, and a burner; [Figure 2] 1 is a schematic vertical cross-sectional view showing a first embodiment of a burner. [Figure 3] 1 is a schematic longitudinal sectional view partially illustrating a burner according to a first embodiment. [Figure 4] 1 is a schematic longitudinal cross-sectional view showing components of a burner according to a first embodiment; FIG. [Figure 5] FIG. 4 is a schematic vertical cross-sectional view showing a second embodiment of the burner. [Figure 6] FIG. 10 is a schematic perspective rear view partially illustrating a third embodiment of the burner. [Figure 7] FIG. 10 is a schematic vertical cross-sectional view showing a burner according to a third embodiment. [Figure 8] FIG. 2 is a schematic perspective view, partially in section, showing a vortex generating device of the burner; [Figure 9] FIG. 2 is a schematic perspective view showing a vortex generating device. [Figure 10] FIG. 1 is a schematic front view of a closure device. [Figure 11]FIG. 10 is a schematic longitudinal sectional view partially illustrating a fourth embodiment of the burner. [Figure 12] FIG. 10 is a schematic longitudinal sectional view partially illustrating a fifth embodiment of the burner. [Figure 13] FIG. 10 is a schematic longitudinal sectional view partially showing a sixth embodiment of the burner. [Figure 14] FIG. 10 is a schematic longitudinal sectional view partially illustrating a seventh embodiment of the burner. [Figure 15] FIG. 2 is a schematic partial cross-sectional side view showing an injection member of a burner. [Figure 16] FIG. 2 is a block diagram illustrating the operation of a burner. [Figure 17] FIG. 2 is a schematic cross-sectional view showing a fuel pump for delivering fuel to a burner. [Figure 18] FIG. 2 is a schematic cross-sectional perspective view showing a vortex generating device of a burner. [Figure 19] FIG. 2 is a schematic vertical cross-sectional view showing a burner. [Figure 20] FIG. 2 is a schematic side view showing a burner ignition device. [Figure 21] FIG. 2 is a schematic front view showing the ignition device. [Figure 22] FIG. 2 is a schematic vertical cross-sectional view partially showing the ignition device. [Figure 23] FIG. 4 is a schematic cross-sectional view partially illustrating a burner according to a second embodiment. DETAILED DESCRIPTION OF THE INVENTION

[0047] 2, 5, 7 and 14 serve to explain the background of the present invention.

[0048] In the drawings, identical or functionally identical elements are designated by the same reference numbers.

[0049] FIG. 1 shows a schematic diagram of a drive train 10 for a motor vehicle, preferably configured as a power vehicle, particularly a passenger car. This means that a motor vehicle configured as a land vehicle includes the drive train 10 in its fully manufactured state and can be driven by the drive train 10. The drive train 10 includes an internal combustion engine 12, also referred to as an internal combustion engine, having an engine block 14, also referred to as an engine housing. The internal combustion engine 12 further includes cylinders 16, particularly formed or defined directly by the engine block 14. During combustion operation of the internal combustion engine 12, respective combustion processes take place in the cylinders 16, from which exhaust gases of the internal combustion engine 12 are generated. For this purpose, a particularly liquid power fuel is injected, particularly by direct injection, into each cylinder 16 during each working stroke of the internal combustion engine 12. The internal combustion engine 12 can be configured as a diesel engine, and therefore the power fuel is preferably diesel fuel. A tank 18, also referred to as a power fuel tank, is provided, which can contain or has contained the power fuel. Each cylinder 16 is assigned, for example, a respective injector, by means of which fuel can be injected, in particular directly injected, into each cylinder 16. A low-pressure pump 20 delivers fuel from a tank 18 to a high-pressure pump 22, by means of which the fuel is delivered to the injectors or to a fuel distribution member, also called a rail or common rail, common to each injector. The injectors can be supplied with fuel by the fuel distribution member common to each injector, from which fuel can be injected, in particular directly injected, into each cylinder 16.

[0050] In this case, the drive unit 10 includes an intake manifold 24 through which fresh air can flow, by means of which the fresh air flowing through the intake manifold 24 is guided towards and into the cylinders 16. The fresh air forms a fuel-air mixture, which includes fresh air and fuel, and which is ignited and thereby burned in each cylinder 16 during each working stroke. In particular, the fuel-air mixture is ignited by autoignition. The ignition and combustion of the fuel-air mixture produces exhaust gases from the internal combustion engine 12, which are also referred to as engine exhaust gases.

[0051] In this case, the drive unit 10 has an exhaust line 26 through which the exhaust gases from the cylinders 16 can flow. The drive unit 10 also includes an exhaust-gas turbocharger 28 having a compressor 30 arranged in the intake line 24 and a turbine 32 arranged in the exhaust line 26. The exhaust gases can leave the cylinders 16, enter the exhaust line 26, and continue to flow through the exhaust line 26. The turbine 32 can be driven by the exhaust gases flowing through the exhaust line 26. The compressor 30 can be driven by the turbine 32, in particular via a shaft 34 of the exhaust-gas turbocharger 28. By driving the compressor 30, the compressor 30 compresses the fresh air flowing through the intake line 24. A number of components 36a-d are arranged in the exhaust line 26, each configured as an exhaust-gas aftertreatment device, i.e., exhaust-gas aftertreatment components for aftertreatment of the exhaust gases. In the flow direction of the exhaust gases of the internal combustion engine 12 through the exhaust pipe 26, the components 36a-d are arranged in succession and are thus connected in series or in series with one another. Component 36a is, for example, an oxidation catalyst, in particular a diesel oxidation catalyst (DOC). Component 36b may also be a nitrogen oxide storage catalyst (NSK). Component 36b may be an SCR catalyst, also simply called SCR. Component 36c may be a particulate filter, in particular a diesel particulate filter (DPF). Component 36d may, for example, have a second SCR catalyst and / or an ammonia slip catalyst (ASC).

[0052] A motor vehicle has a structure configured as a unitary body that forms or defines an interior space of the vehicle, also known as a passenger cell or safety cell. A person can ride in the interior space during each travel of the vehicle. For example, the structure forms or defines an engine compartment, in which an internal combustion engine 12 is arranged. For example, an exhaust gas turbocharger 28 is also arranged in the engine compartment. Furthermore, the structure has a floor, also known as a main floor, by which the interior space is at least partially, particularly at least substantially, or entirely defined downward in the vehicle height direction. For example, components 36a, b, and c are arranged in the engine compartment, whereby components 36a, b, and c form a so-called hot end or form components of a so-called hot end. In particular, the hot end can be directly flange-connected to the turbine 32. Component 36d is arranged, for example, outside the engine compartment and, in this case, below the floor in the vehicle height direction, whereby component 36d forms a so-called cold end or is a component of a so-called cold end.

[0053] The drive system 10 includes a metering device 38, by means of which a reducing agent, particularly a liquid, can be injected into the exhaust pipe 26 at the inlet point E1, for example, into the exhaust gas flowing through the exhaust pipe 26. The reducing agent is preferably an aqueous urea solution that can react with nitrogen oxides that may be present in the exhaust gas to produce ammonia, which is then selectively reduced to water and nitrogen. The selective catalytic reduction can be catalyzed and / or supported by an SCR catalyst. As can be seen from FIG. 1, the inlet point E1 is located upstream of the component 36b and downstream of the component 36a, as viewed in the direction of exhaust gas flow through the exhaust pipe 26. The exhaust pipe 26 preferably includes a mixing chamber 40, in which the reducing agent injected into the exhaust gas at the inlet point E1 can be mixed with the exhaust gas.

[0054] The drive system 10, and thus the motor vehicle, further includes a burner 42, by means of which components 36b, c, and d arranged downstream of the burner 42 in the direction of exhaust gas flow through the exhaust pipe 26 can be quickly and effectively heated and / or maintained at high temperatures, as will be explained in more detail below. The burner 42 combusts the mixture, particularly forming a flame 44 and particularly providing burner exhaust gas, which can be or is introduced into the exhaust pipe 26 at an inlet point E2. This means that the burner 42 is arranged at the inlet point E2, so to speak. In the embodiment shown in FIG. 1, the inlet point E2 is arranged upstream of the components 36b, c, and d and downstream of the component 36a. In other words, in the embodiment shown in FIG. 1, the burner 42 is arranged upstream of the components 36b, c, and d and downstream of the component 36a. Alternatively, it is also conceivable to arrange the burner 42 or the inlet point E2 upstream of the component 36a, and in particular downstream of the turbine 32. The aforementioned mixture to be burned in or by the burner 42 comprises air and liquid fuel. In the embodiment shown in FIG. 1, this fuel is a power fuel, and / or at least one portion of the air supplied to the burner 42 and used to form the mixture can come from the intake manifold 24, for example. For this purpose, a power fuel supply line 46 is provided that is fluidly connected to the burner 42 on the one hand and is fluidly connected or connectable to a power fuel line 48 on the other hand. The power fuel line 48 can be traversed by the power fuel flowing from the tank 18 to the injector or to the power fuel distribution element. In particular, the power fuel supply path 46 is fluidly connected to the power fuel pipe 48 at a first connection point V1, which is located downstream of the low-pressure pump 20 and upstream of the high-pressure pump 22 in the flow direction of the power fuel from the tank 18 to the power fuel distribution member or respective injectors. At the connection point V1, at least a portion of the liquid power fuel flowing through the power fuel pipe 48 can be branched off from the power fuel pipe 48 and introduced into the power fuel supply path 46.The power fuel introduced into the power fuel supply line 46 can flow through the power fuel supply line 46 and is introduced as fuel, in particular, to the burner 42 by means of the power fuel supply line 46. A first valve member 50 is arranged in the power fuel supply line 46, by means of which the amount of fuel to flow through the power fuel supply line 46 and thus be supplied to the burner 42 can be adjusted. An electronic computing device 52, also referred to as a control device, is provided here, by means of which the valve member 50 is controlled, so that the amount of fuel to be supplied to the burner 42 through the power fuel supply line 46 by the control device via the valve member 50 can be adjusted, in particular limited.

[0055] Furthermore, an air supply line 54 is provided, via which air for forming the mixture can be or is supplied to the burner. This means that the air for forming the mixture can flow through the air supply line 54. A pump 56, also called an air pump, is arranged in the air supply line 54, using which air can be pumped through the air supply line 54 and thus to the burner 42. For example, the low-pressure pump 20, also called a low-pressure power fuel pump, is also called a fuel pump, using which fuel can be pumped through the power fuel supply line 46 and thus to the burner 42.

[0056] It is clear that the air supply line 54 is fluidly connected to the intake manifold 24 at the second connection point V2. In this way, for example, at connection point V2, at least a portion of the fresh air flowing through the intake manifold 24 can be branched off and introduced into the air supply line 54. The fresh air introduced into the air supply line 54 can flow through the air supply line 54 as air and can be introduced via the air supply line 54 towards, and in particular into, the burner 42. A second valve element 55 is arranged in the air supply line 54, by means of which the amount of air flowing through the air supply line 54 and thus through the burner 42, which is used to form the mixture, can be adjusted. The control device is configured, for example, to control the valve element 55 so that the amount of air flowing through the air supply line 54 and thus supplied to the burner 42, which is used to form the mixture, can be adjusted, in particular controlled, by the control device via the valve element 55.

[0057] 2 shows a schematic cross-sectional view of a first embodiment of the burner 42. The burner 42 has a combustion chamber 58 in which a mixture comprising air supplied to the burner 42 and liquid fuel supplied to the burner 42 is ignited and thereby combusted, i.e., ignited and thereby combusted during operation of the burner 42. For this purpose, an ignition device 60, for example configured as a spark plug or glow plug or glow pin, is provided, by means of which at least an ignition spark can be generated in the combustion chamber 58, in particular with the aid of electrical energy or electric current. The ignition spark ignites and combusts the mixture in the combustion chamber 58, in particular while providing the burner exhaust gases and / or the flame 44. The burner exhaust gas or flame 44 can rapidly and effectively heat and / or keep at a high temperature, for example, the exhaust gas flowing through the exhaust pipe 26, and thereby the heated and / or kept at a high temperature exhaust gas flowing through components 36b, c and d can rapidly and effectively heat and / or keep at a high temperature, for example, at least component 36b.

[0058] The burner 42 has an inner swirl chamber 62 through which a first portion of the air supplied to the burner 42 can flow, generating a swirling first flow of the first portion of the air. This is understood in particular as the first portion of the air flowing swirl-like through at least one first partial region of the swirl chamber 62 and / or exiting the swirl chamber 62 in a swirling manner and / or flowing swirl-like within the combustion chamber 58. The inner swirl chamber 62 in particular has exactly one first outlet opening 64 through which the first portion of the air can flow along a first through-direction of the outlet opening 64 and thus along a first flow direction that coincides with the first through-direction. Via the first outlet opening 64, the first portion of the air can be discharged from the inner swirl chamber 62. This means that the first portion of the air can flow out of the inner swirl chamber 62 via the first outlet opening 64. Burner 42 further includes an injection member in the form of an injection member 66 having a passageway 68 through which liquid fuel can flow to be supplied to burner 42 .

[0059] In the first embodiment, the injection member 66 is configured as a lance, also referred to as a power fuel lance. The passage 68, and thus the injection member 66, has at least one outlet opening 70 through which the liquid fuel flowing through the passage 68 can pass. As can be seen from FIG. 2 , in the first embodiment, the passage 68, and thus the injection member 66, has at least two, or even exactly two, outlet openings 70 configured, for example, as bores. The outlet openings 70 are circumferentially ... The respective second through-directions of the respective outlet openings 70 correspond to respective second flow directions, through which fuel can flow through the respective outlet openings 70. It is clear that fuel can be ejected from the injection element 66 via the respective outlet openings 70, forming respective fuel jets 72, and thereby, in particular, directly into the inner swirl chamber 62. For example, the respective fuel jets 72, whose longitudinal axes coincide with the respective second through-directions or respective second flow directions, are at least substantially conically shaped. Furthermore, for example, the injection element 66, and thus the passage 68 in this example, has a longitudinal direction or longitudinal extension that extends parallel to the first through-direction, and thus extends parallel to the first flow direction, in particular, coincides with the first through-direction or first flow direction. As is further clear from FIG. 2 , the first through-direction or first flow direction coincides with the axial direction of the outlet openings 64 and the axial direction of the inner swirl chamber 62. In this case, the respective second penetration directions or respective second flow directions extend perpendicular to the first penetration direction and thus the first flow direction and to the axial direction of the vortex chamber 62 and the outlet opening 64, or extend obliquely, as in this example.

[0060] The swirl chamber 62 is formed or defined at least in part, in particular at least substantially, and thus more than half or even entirely, by a preferably integrally configured component 74 of the burner 42, whereby the component 74 also forms or defines the outlet opening 64.

[0061] Furthermore, the burner 42 has an outer swirl chamber 76 that surrounds at least one length region, and in this example also the first outlet opening 64, in a circumferential direction of the swirl chamber 62, extending around the axial direction of the swirl chamber 62, in particular completely. The component 74 here has a separating wall 78 arranged between the swirl chambers 62 and 76 in the radial direction of the swirl chamber 62, the radial direction of which extends perpendicular to the axial direction of the swirl chamber 62. The swirl chambers 62 and 76 are thereby separated from one another by the separating wall 78 in the radial direction of the swirl chamber 62. The axial direction of the swirl chamber 62 coincides with the axial direction of the swirl chamber 76, and thus the radial direction of the swirl chamber 62 coincides with the radial direction of the swirl chamber 76. The outer swirl chamber 76 can be passed through by a second portion of the air supplied to the burner 42 and is configured to generate a second swirling flow of the second portion of air. This means that the second portion of air flows swirl-wise through the swirl chamber 76 and / or flows swirl-wise out of the swirl chamber 76 and / or flows swirl-wise in the combustion chamber 58. In particular, it is intended that each portion of air has a swirl-like flow in the combustion chamber 58, i.e., proceeds swirl-wise in the combustion chamber 58. The outer swirl chamber 76 has, in particular, exactly one second outlet opening 80 through which the second portion of air flowing through the outer swirl chamber 76 can flow, in particular along a third flow direction, and the third through-direction through which the second portion of air flowing through the swirl chamber 76 can flow corresponds to the axial direction of the swirl chamber 76 and thus to the axial direction of the swirl chamber 62 in this example. The third through-direction corresponds to the third flow direction in which the second portion of air flowing through the outer swirl chamber 76 flows or can flow through the outlet opening 80. This means in particular that the first penetration direction coincides with the third penetration direction and that the first flow direction coincides with the third flow direction, so that in this example the first flow direction, the third flow direction, the first penetration direction and the third penetration direction coincide with the axial direction of the swirl chamber 62 and the axial direction of the swirl chamber 76. In the flow direction of the air portions, the second outlet opening 80 is arranged downstream of the outlet opening 64, here in particular in series with the outlet opening 64, so that the outlet opening 80 can be traversed by the second air portion, the first air portion and the fuel.In particular, the first portion of the air is mixed with the fuel already in the swirl chamber 62, in particular due to the vortex-like first flow, forming in particular a partial mixture. This partial mixture flows through the outlet opening 64 and can therefore leave the swirl chamber 62 and subsequently flow through the outlet opening 80, in particular due to the preferred vortex-like second flow, whereby the mixture is particularly preferably pre-treated, i.e. the partial mixture is particularly preferably mixed with the second portion.

[0062] It is clear that the swirl chamber 76 is at least partially, in particular at least substantially, and thus at least more than half or even entirely, defined radially inward of the respective swirl chamber 62 to 76 by the component 74, in particular by the separating wall 78. Radially outward of the respective swirl chamber 62 to 76, the swirl chamber 76 is at least partially, in particular at least substantially or entirely, defined by a component 82, which in this example is configured separately from the component 74. Here, the component 74 is at least partially, in particular at least substantially, arranged within the component 82. The outlet opening 80 is defined or formed, for example, by the component 82 and partly by the component 74, in particular in terms of the smallest or minimum flow cross-sectional area of ​​the outlet opening 80 through which the second portion of air can flow.

[0063] 3, the first outlet opening 64 is intended to be precisely machined, in particular mechanically, in the direction of flow of the first portion of air through the first outlet opening 64, and thus in the direction of flow of the fuel through the first outlet opening 64, so as to terminate in a knife-sharp end edge K which extends all the way around the outlet opening 64, for example in the circumferential direction of the outlet opening 64, which extends about the axial direction of the outlet opening 64 and coincides with the axial direction of the respective swirl chamber 62 to 76. The knife-sharp end edge K is formed in this example by an atomizing lip 84 formed by the component 74. The atomizing lip 84 tapers in the direction of flow of the first portion of air through the first outlet opening 64, and thus in the direction of flow of the fuel through the first outlet opening 64, up to and ends at an end edge K. For example, the end edge K can be ground and / or turned, thereby being appropriately machined. For example, the fuel is injected toward the component 74, in particular toward the inner circumferential outer surface 86 of the component 74, forming the fuel jet 72, in particular so that a fuel film, also simply referred to as a film, is formed by the fuel on the component 74, in particular on the inner circumferential outer surface 86. It is particularly clear here that the inner swirl chamber 62 is formed radially outward of the inner swirl chamber 62, in particular directly, by the inner circumferential outer surface 86. The first vortex flows, and in particular the centrifugal forces resulting from the first vortex flows, carry the fuel film along the inner circumferential outer surface 86 to the end edge K, where the fuel separates from the end edge K, thereby generating particularly fine droplets of fuel from the fuel or fuel film. In this way, the component 74 is, so to speak, a film attachment point between the respective vortex flows, or functions as a film attachment point. The respective droplets jointly form a particularly large surface area of ​​fuel, which allows particularly effective burner operation even at low burner power, and no expensive pumps or expensive high-pressure generators are required to generate the small, and therefore fine, droplets of fuel.In this case, the smallest flow cross section of the second outlet opening 80 through which the second partial air can flow is bounded or formed radially inwardly all over by the end edge K of the respective outlet opening 64 to 80.

[0064] Furthermore, the burner 42 has a recirculation prevention plate 88, which in the first embodiment is arranged downstream of the outlet opening 80 and downstream of the component 82 in the flow direction of the portions flowing through the outlet opening 80 and in the flow direction of the fuel flowing through the outlet opening 80. In this case, the recirculation prevention plate 88 has a throughflow opening 90 arranged correspondingly downstream of the outlet opening 80 and thus through which the air portions and fuel from the swirl chambers 62 and 76 can flow. Starting from the throughflow opening 90, and in particular from the outlet opening 80, and thereby from the component 82, in particular from its end, the recirculation prevention plate 88 extends away from the axial direction of the respective swirl chamber 62 to 76 outward, so that the recirculation prevention plate 88 projects outward from at least one partial region T of the component 82 in the radial direction of the respective swirl chamber 62 to 76. For example, the first portion T1 of the combustion chamber 58 is thereby at least partially separated from the second portion T2 of the combustion chamber 58 by the recirculation prevention plate 88. The recirculation prevention plate 88 prevents excessive flow of the mixture flowing through the through-flow openings 90 into the combustion chamber 58, in particular into portion T2, from returning towards the component 82 or back into portion T1, thereby enabling a favorable mixture preparation to be achieved.

[0065] 2, for example, the swirl chambers 62 and 76 are supplied with air or air portions via a feed chamber 92 common to the swirl chambers 62 and 76. Here, the feed chamber 92 is arranged upstream of the swirl chambers 62 and 76 in the direction of flow of the air portions through the swirl chambers 62 and 76. This means that the air is first introduced into the feed chamber 92 via the air feed channel 54. The air introduced into the feed chamber 92 can flow through the feed chamber 92 on its way to and into the swirl chambers 62 and 76, being divided in particular by the component 74 into first and second portions. The air flowing through the air feed channel 54 can, for example, leave the air feed channel 54 and enter the feed chamber 92 along a feed direction that extends obliquely and / or tangentially to the axial direction of the respective swirl chambers 62 and 76 and thus to their respective longitudinal axes.

[0066] FIG. 4 shows the component 74, also referred to as the film attachment, in a schematic longitudinal section. It can be seen that at least one portion TB of the outer swirl chamber 76 is formed by the component 74. Here, the component 74 comprises a first vortex generator 94 of the inner swirl chamber 62 and a second vortex generator 96 of the outer swirl chamber 76. The vortex generator 94 generates a first vortex flow of a first portion of the air, while the vortex generator 96 generates a second vortex flow of a second portion of the air. The inner torus of the inner swirl chamber 62 is specifically designated K1 in FIG. 4, and the outer torus of the outer swirl chamber 76 is specifically designated K2 in FIG. 4. The vortex generator 94 is arranged in an air passage LK1 of the swirl chamber 62, which is specifically entirely bounded by the component 74. In particular, the air passage LK1 is defined by the component 74 radially outward and inward of the respective swirl chamber 62-76. The swirl generator 96 is arranged in the second air passage LK2 of the swirl chamber 76, which is defined entirely, and in particular axially outward and inward of the respective swirl chamber 62-76, by the component 74. For example, the swirl generators 94 and 96 are also formed by the component 74. In this case, a first portion of air can flow through the air passage LK1, and a second portion of air can flow through the air passage LK2, whereby the swirl generator 94 generates or induces a first vortex flow, and the swirl generator 96 generates or induces a second vortex flow. The outer diameter of the air passage LK1, also referred to as the air guide, is designated Di here, and the outer diameter of the air passage LK2, also referred to as the air guide, is designated Da in FIG. 4.

[0067] 2 to 4, the outlet openings 64 and 80, also called nozzles, are both aligned in the axial direction. This means that the partial mixture from the inner swirl chamber 62 flows at least substantially axially into the combustion chamber 58. Furthermore, a second portion of the air from the outer swirl chamber 76 also flows at least substantially axially into the combustion chamber 58, entraining the finely dispersed fuel from the film deposit as small droplets at the end edge K, in particular at its separation point, into the combustion chamber 58. The smallest or narrowest flow cross section of the outer nozzle, i.e., of the outlet opening 80, is located at the separation point, i.e., at the end edge K, of the inner nozzle, i.e., of the outlet opening 64.

[0068] Preferably, the nozzles or outlet openings 64 and 80 are intended to have the following size or surface ratios: Preferably, the outlet opening 64 (inner nozzle) has a diameter, in particular an inner diameter, that is 10 to 20 percent of Di. Furthermore, preferably, the outer nozzle or outlet opening 80 is intended to have a diameter, in particular an inner diameter, that is, for example, 10 to 35 percent of Da. The inner and outer tori may have the same area, i.e., both occupy 50 percent of the total torus. In other words, preferably, the air passage LK1 has a first torus and the air passage LK2 has a second torus, and these tori are preferably of equal size.

[0069] 5 shows a schematic cross-sectional view of a second embodiment of the burner 42. In the first embodiment, for example, the element 82 and the anti-recirculation plate 88 are intended to be separate components that are at least indirectly, in particular directly, connected to one another. In the second embodiment, the anti-recirculation plate 88 is intended to be integral with the element 82. The anti-recirculation plate 88 has the advantage that, after the air-fuel mixture leaves the outer nozzle or outlet opening 80 and enters the combustion chamber 58, it can flow backwards towards the element 82, which could cause swirls. The anti-recirculation plate 88, also referred to simply as plate, preferably has a diameter, in particular an outer diameter, at least equal to Di.

[0070] FIG. 6 partially illustrates a third embodiment of the burner 42 in a schematic perspective view. In this third embodiment, the combustion chamber 58 has a plurality of through-flow openings 98 spaced apart from one another and separated from one another, particularly in the radial direction of each vortex chamber 62-76, by respective wall sections W, each of which is formed as a solid body. Via the through-flow openings 98, the burner exhaust gases or flames 44 can be discharged from the combustion chamber 58 and introduced into the exhaust pipe 26. In this example, the wall sections W are integral with one another, for example, as a solid, one-piece perforated plate 100. To be precise, eight through-flow openings 98 are preferably provided. As can be seen from FIG. 2, it is conceivable in principle for the combustion chamber 58 to have just one large, undivided discharge opening 102, through which the burner exhaust gases or flames 44 can be discharged from the combustion chamber 58 and introduced into the exhaust pipe 26. In contrast, in the third embodiment, a plurality of through-flow openings 98 are provided, separated from one another by a distance, so that the discharge opening 102 is effectively subdivided or divided by the wall region W into a plurality of through-flow openings 98. The through-flow openings 98 are uniformly distributed in a circumferential direction extending around the axial direction of the respective swirl chamber 62-76, and it is clear that they are arranged in particular along a circle whose center is located in the axial direction of the respective swirl chamber 62-76. Thus, in the third embodiment, instead of one large outlet opening in the form of a large discharge opening 102, a plurality of outlet openings in the form of through-flow openings 98 are provided, particularly at individual locations, in order to enable favorable recirculation in the combustion chamber 58. In this case, it is preferable to use a perforated plate, such as a perforated plate 100, which has a plurality of relatively small openings, for example in the form of through-flow openings 98, rather than a reduced outlet opening. The number of through-flow openings 98 is, for example, in the range from 3 to 9. The through-flow openings 98 have similar, or at least substantially equal, flow-through or discharge surfaces through which the burner exhaust gases or flame 44 can flow.The throughflow surfaces of these throughflow openings 98, or of all throughflow openings, together result in a total throughflow surface, also referred to as the total discharge surface, which is, for example, 0.8 to 1.8 times larger than that of a single centrally located opening, such as the discharge opening 102. Instead of a central outlet opening, for example with a diameter of 25 millimeters and therefore an area of ​​491 square millimeters, it may be preferable, depending on the flow conditions in the exhaust pipe 26, to implement six smaller openings, each with a diameter of 10.5 millimeters, thereby implementing a total discharge surface of 520 square millimeters.

[0071] FIG. 7 shows a schematic longitudinal section of a third embodiment of the burner 42, which is provided with a perforated plate 100, also referred to as a perforated plate. The preferred recirculation in the combustion chamber 58, as mentioned above, is indicated by arrows 104 in FIG. 7. Furthermore, FIG. 7 shows a vortex of the mixture, designated by reference number 106, which arises from the respective vortices of the air portions in the combustion chamber 58. The vortex of the air portions, and thus the vortex of the mixture 106, is achieved in particular by the vortex generators 94 and 96, and in particular by the tangential air supply via the air supply channel 54. Each vortex generator 94-96 is preferably configured as an air guide vane, rather than as, for example, a quarter-spherical thin plate structure, so that the respective vortex can be particularly favorably generated or induced. The vortex flow of the air portions, and the resulting vortex flow 106 of the mixture in the combustion chamber 58, prevents the flame 44 from being extinguished in the combustion chamber 58, optimizes the mixing of fuel and air in the combustion chamber 58, and causes vortex breakdown to stabilize the flame 44. Recirculation in the combustion chamber 58, indicated by arrows 104, can be carried out in particular by the use of perforated plates and the resulting reduction in the discharge cross section, through which the flame 44 or the burner exhaust gases can be discharged from the combustion chamber 58 and introduced into the exhaust pipe 26. A reduction in the discharge cross section is understood, for example, to mean that the total discharge surface of the individual through-flow openings 98 is smaller than the area of ​​the succession of large discharge openings 102. The preferred recirculation within the combustion chamber 58, as indicated by arrow 104, results in improved mixing of the air and motive fuel within the combustion chamber 58 and a longer residence time for the burning mixture within the combustion chamber 58, thereby avoiding excessive emissions of unburned hydrocarbons (HC) as the flame 44 or burner exhaust gas exits the combustion chamber 58 into the exhaust pipe 26 and enabling particularly high temperatures at the discharge of the flame 44 or burner exhaust gas.

[0072] In particular, the recirculation provides a recirculation zone and vortex breakdown, thereby enabling an extra long residence time of the flame 44 within the combustion chamber 58 .

[0073] FIG. 8 shows a schematic, partially cross-sectional perspective view of a vortex-generating device 107, which may be formed, for example, by a structural part of component 74 or by component 74. This vortex-generating device 107 includes a vortex generator 94 for the inner vortex chamber 62 and a vortex generator 96 for the outer vortex chamber 76. As can be particularly clearly seen from FIG. 8, the vortex generators 96, and preferably also the vortex generators 94, are configured as air guide vanes, which may be flow-facilitatingly configured, in particular shaped. This avoids excessive pressure losses, particularly compared to spherical vortex generators. The number of outer vortex generators 94 is, for example, in the range from 6 to 11. Alternatively or additionally, the number of outer vortex generators 96 is, for example, in the range from 8 to 14. Each air passage LK1-LK2 in which the vortex generators 94-96 are arranged has, for example, a respective area, for example, at least 20 percent and at most 70 percent of which is covered by the respective vortex generators arranged in the air passage LK1-LK2. A particularly preferred axial shielding of at least 20 percent and at most 70 percent of the respective area is thus intended. The respective radius of each air guide vane can extend from at least 40 percent of Di to infinity, whereby each air guide vane can be configured linearly. It is particularly conceivable that each air guide vane forms, with the respective radial direction of each swirl chamber 62-76, a respective angle α, for example, in the range of 10 degrees to 45 degrees. The radius of each air guide vane, also referred to simply as a vane, is designated R in FIG. 8. The swirl generators 94 to 96 are preferably configured to redirect the portion of the air flowing through the respective air passage LK1 to LK2, i.e. the air flowing through the respective air passage LK1 to LK2 and thus forming the respective portion, in particular by 70 to 90 degrees relative to the strict or pure axial direction of the respective swirl chamber 62 to 76. In order to achieve particularly preferred mixture pre-treatment, the air guide vanes of the inner and outer swirl chambers 62 and 76 can be configured in opposite directions.In other words, the outer vortex generator 96 of the outer vortex chamber 76 and the inner vortex generator 94 of the inner vortex chamber 62 may be configured to create or induce vortical flows of the respective portions of air in opposite or counter-directional vortex flows, so that, for example, one flow is counterclockwise and the second flow is clockwise, or vice versa.

[0074] The vortex generating device 107 has in particular a central through opening 108 which is penetrated by the injection member 66. In other words, the injection member 66 passes through the through opening 108 and enters the inner vortex chamber 62.

[0075] 10 shows a schematic front view of the closing device 110, which in this example is configured as an iris diaphragm or in the manner of an iris diaphragm. When the burner 42 is not operating, it may be advantageous to shield the air and fuel lines, i.e., for example, the air supply line 54 and / or the fuel supply line 46 and / or the swirl chambers 62 and 76, and thereby for example the outlet opening 64 and / or the outlet opening 80, to prevent exhaust gases from the internal combustion engine 12 from entering the air supply line 54, the fuel supply line 46, the supply chamber 92, the swirl chambers 62, and / or the swirl chambers 76. It is also conceivable to shield the combustion chamber 58 or at least one length of the combustion chamber 58 to prevent exhaust gases from the internal combustion engine 12 from entering the combustion chamber 58 from the exhaust pipe 26 or into a partial region or length thereof. For this purpose, the closing device 110 can be used, which can be arranged, for example, in the combustion chamber 58 or downstream of the combustion chamber 58. The closing element 112 of the closing device 110, which is movable in the manner of an iris diaphragm, allows the opening cross-section 114, which is defined, in particular directly, by the closing element 112 and through which, for example, the flame 44 or burner exhaust gases can flow, to be changed, i.e., variably adjusted, so that, for example, the opening cross-section 114 can be adjusted depending on the load, in particular controlled or regulated. It is thus conceivable to close at least one partial region of the combustion chamber 58 with the closing device 110. Alternatively or additionally, for example, the outlet opening 80 can be closed with the first closing device 110. Alternatively or additionally, for example, the outlet opening 80 can be closed with the second closing device 110. This has the advantage, among other things, that the air supply and the power fuel supply can be closed simultaneously with a small valve. In this case, an air valve downstream of the pump 56 is also not necessary, since this prevents exhaust gases from entering the pump 56. A much larger exhaust gas flap after the combustion chamber 58 or after its discharge, against which the hot exhaust gases impinge, can also be dispensed with.

[0076] In particular, the opening cross section 114 can be considered to be an opening cross section or a discharge cross section of the combustion chamber 58 through which the flame 44 or the burner exhaust gases can be discharged from the combustion chamber 58 and introduced into the exhaust pipe 26. The tapering of the opening cross section, which is necessary, necessary, or implemented to increase the flow velocity of the flame 44 or the burner exhaust gases from the combustion chamber 58, especially by a corresponding movement of the closing element 112 in the manner of an iris diaphragm, can be implemented in a manner that is favorable for the flow. Therefore, instead of a flat closing plate bore, a tapered outlet with an angle of 30 to 70 degrees to the horizontal, as is implemented, for example, in aircraft drives by segments and / or tapers, can be implemented. This can be done with a fixed geometry or variably, as in aircraft drives with individual segments that can be opened and closed, for example in propulsion nozzles, or by a slidably arranged discharge taper that can slide in the axial direction of the respective swirl chamber 62-76.

[0077] FIG. 11 partially illustrates a burner 42 according to a fourth embodiment in a schematic cross-sectional view. As can be seen particularly well in FIG. 11 and also clearly seen in FIGS. 2 and 7, the combustion chamber 58 is formed or defined by a chamber member 116, which is particularly solidly configured. In particular, the combustion chamber 58, whose axial direction coincides with the axial direction of each of the swirl chambers 62 to 76, is defined, in particular directly, by an inner circumferential outer surface 118 of the chamber member 116 along a radial direction extending parallel to the radial direction of each of the swirl chambers 62 to 76. The chamber member 116 may be configured as a single unit. In the fourth embodiment, the chamber member 116 is configured, for example, to have two chamber sections 120 and 122 that are configured as a single unit, or the chamber sections 120 and 122 are separate components that are joined together. In this case, the inner circumferential outer surface 118 is formed by the chamber section 122. The chamber portions 120 and 122 are nested such that at least one length of the chamber portion 120 surrounds at least one length of the chamber portion 122 in a circumferential direction of the combustion chamber 58 extending in the axial direction of the combustion chamber 58, in particular completely around the circumference, and the at least one length of the chamber portion 120 is spaced apart from the length of the chamber portion 122 in a radial direction of the combustion chamber 58, in particular forming an intermediate space 124. The intermediate space 124 is arranged between the chamber portions 120 and 122 in the radial direction of the combustion chamber 58, and is formed between the chamber portions 120 and 122, for example as an air gap. It is further apparent that a continuous or uninterrupted discharge opening 102 is formed or defined by the chamber portion 122 in a circumferential direction of the combustion chamber 58, in particular completely around the circumference of the combustion chamber 58. In the first embodiment shown in Figure 2, the discharge opening 102 is not subdivided, i.e., there are no components that subdivide the discharge opening 102 into multiple flow-through openings that are separated from each other and spaced apart from each other.7, a perforated plate 100, also called a perforated plate, is arranged at the discharge opening 102, thereby dividing or segmenting the otherwise uninterrupted, i.e., continuous, discharge opening 102 into a plurality of spaced-apart, separated through-flow openings 98 formed in the perforated plate 100. The flame 44 or the burner exhaust gases can exit the combustion chamber 58 along a fourth flow direction extending in the axial direction of the combustion chamber 58, i.e., parallel to or coincident with the axial direction of the combustion chamber 58, and can thereby flow through the discharge opening 102 or the respective through-flow opening 98, the fourth flow direction coinciding with the first, second, and third flow directions. It is clear that the discharge opening 102 tapers in the flow direction of the burner exhaust gases flowing through the discharge opening 102, i.e., along the fourth flow direction. To this end, the chamber member 116, and in particular the chamber portion 120, has a length region L1 that is defined around the discharge opening 102 in the circumferential direction of the combustion chamber 58, in particular all the way around, and that tapers in the direction of flow of the burner exhaust gases through the discharge opening 102. In other words, the length region L1, and thus the discharge opening 102, is tapered in the direction of flow of the burner exhaust gases through the discharge opening 102, i.e., conically or frustoconically configured. Since the burner exhaust gases or flames 44 exit the combustion chamber 58 through the discharge opening 102, the discharge opening 102 is configured at or forms the discharge of the combustion chamber 58, which in the fourth embodiment is tapered at its discharge, i.e., has a taper formed by the length region L1. The discharge opening 102 preferably has an internal diameter of 34 mm. In other words, it is intended that the smallest or narrowest inner diameter of the discharge opening 102 through which the burner exhaust gas can flow is preferably 43 mm.

[0078] At least the length regions of the chamber sections 120 and 122 are nested and spaced apart from one another in the radial direction of the combustion chamber 58, forming an intermediate space 124 that is filled, for example, with air and configured as an air gap, thereby creating a double wall of the combustion chamber 58 or chamber member 116, whereby the combustion chamber 58 is insulated by the intermediate space 124, i.e., by an air gap. In the following, with particular reference to the outer diameter Da shown in FIG. 4 of the film attachment of the outer air passage LK2 of the outer swirl chamber 76, the air passage LK2 in which the outer vortex generator 96 is arranged and thus the outer diameter Da is formed in particular entirely by the film attachment, i.e., by the component 74. With reference to FIG. 11 and the outer diameter Da, the combustion chamber 58, particularly upstream of the tapered section or upstream of the length region L1, preferably has an inner diameter d1 that is 1.0 to 3.0 times Da. Furthermore, it is contemplated that the minimum inner diameter d2 of the discharge opening 102 is preferably 0.7 to 2.3 times Da, where the minimum inner diameter d2 of the discharge opening 102 is also referred to as the discharge diameter. The relatively small discharge diameter of the discharge opening 102 maintains the discharge velocity of the burner exhaust gas and reduces the influence of the exhaust gases of the internal combustion engine 12, also referred to as the engine exhaust, on the flame 44, also referred to as the burner flame. The length l1 of the combustion chamber 58 extending in the axial direction of the combustion chamber 58 is preferably 1.5 to 4.0 times Da, particularly excluding the secondary air injection section. With the secondary air injection section, it is contemplated that the length l1 of the combustion chamber is preferably 2.0 to 5.5 times Da.

[0079] Instead of a continuous discharge opening 102, it is conceivable to use a plurality of spaced-apart through-flow openings 98. In other words, it is conceivable to divide the continuous, and thus uninterrupted, discharge opening 102 into a plurality of spaced-apart, separated through-flow openings 98, the number of which is preferably in the range of 3 to 9. Each through-flow opening 98 has an area, also referred to as a discharge surface or through-flow surface, and the sum of the areas of all through-flow openings 98 is preferably similar to the discharge surface of the continuous discharge opening 102, i.e., similar to the area of ​​the discharge opening 102. The sum of the areas of the through-flow openings 98 is also referred to as a total discharge surface. The through-flow openings 98 are configured, for example, as bores. It is conceivable that the sum of the areas of all through-flow openings 98, i.e., the total discharge surface, is 0.8 to 1.8 times the area of ​​the continuous, uninterrupted discharge openings 102 of the combustion chamber 58. In particular, it is conceivable that the perforated plate 100 is arranged at the discharge opening 102 or at the length L1. With regard to the exhaust gases of the internal combustion engine 12, also referred to as engine exhaust gases, it may be preferable to use deflectors, in particular deflectors and / or perforated elements, in particular perforated plates, where a perforated element is understood to be an element, in particular of solid construction, having a plurality of spaced apart holes, in particular separated from one another by respective walls, through which gases, such as burner exhaust gases or engine exhaust gases, can flow. For example, in order to prevent the engine exhaust gases from excessively adversely affecting and destabilizing the flame 44 in the combustion chamber 58, it is preferable to provide a deflector, such as a deflector plate, before the combustion chamber 58, i.e., upstream of the combustion chamber 58, so that the engine exhaust gases cannot or only very little can enter the combustion chamber 58 in the direction opposite to the flow direction of the flame 44 or burner exhaust gases, in particular, from the combustion chamber 58 into the exhaust pipe 26. Thus, it is preferably intended that the deflector is arranged in the exhaust pipe 26 upstream of the combustion chamber 58 in the flow direction of the engine exhaust gases, ie upstream of the inlet point E2.The geometry of the deflection element can be determined depending on how the combustion chamber 58 is arranged relative to the exhaust pipe 26, i.e., relative to the exhaust gas passage of the exhaust pipe 26. Exhaust gas passage can be understood as meaning that the burner exhaust gases or flames 44 flow into the exhaust gas passage from the combustion chamber 58, particularly along the fourth flow direction, particularly at the inlet point E2. The geometry of the deflection element is preferably adapted individually.

[0080] Furthermore, as explained above, a closure device 110 or other type of closure device is preferably arranged at the discharge of the combustion chamber 58. This can be understood in particular as follows: the closure device 110 can be arranged, for example, in the length region L1 or in the discharge opening 102, so that the flow cross-section through which the burner exhaust gases or flames 44 can flow, and through which the burner exhaust gases or flames 44 can be discharged from the combustion chamber 58, in particular at the inlet point E2, and introduced into the exhaust pipe 26, in particular into the exhaust gas channel, is defined by the closure device 110, in particular by the closure element 112, and can be changed, i.e., adjusted, accordingly by the closure device 110. Such an adjustable flow cross-section is in particular the opening cross-section 114.

[0081] In this case, the closing device 110 can be arranged in the chamber section 122 and thus in the discharge opening 102, or the closing device 110 or another closing device can be arranged downstream of the combustion chamber 58, i.e., downstream of the chamber section 122, and thus directly following the combustion chamber 58 or the chamber section 122, i.e., downstream of the discharge opening 102 itself. In the fourth embodiment, the tapering of the discharge opening 102, implemented by the length section L1, i.e., by the above-mentioned taper, leads to an increase in the flow velocity of the burner exhaust gases, and the tapering of the discharge section of the combustion chamber 58 can be implemented in a flow-favorable manner. In this example, the taper formed by the length section L1 preferably has an angle, also referred to as the taper angle, of 30° to 70° relative to the axial direction of the combustion chamber 58, in particular as shown by the dashed line 126 in FIG. 11 . In the fourth embodiment, the taper is configured as a fixed geometry, so that the taper, i.e., the taper angle, is fixed, i.e., cannot be changed. However, it is also conceivable to configure the taper variable, in particular with regard to its taper angle, as in, for example, an aircraft drive, in particular by individual segments that can be opened and closed, i.e., pivoted relative to the chamber part 122, in particular, as in, for example, a propulsion nozzle in an aircraft drive, thereby making the taper or the taper angle adjustable, i.e., variable. Alternatively or additionally, it is conceivable that the taper or its taper angle can be varied by a slidably arranged discharge taper and / or that the longitudinal axis of the discharge taper coincides with, for example, the axial direction of the combustion chamber 58 and / or that is slidable in the axial direction of the combustion chamber 58, in particular relative to the chamber part 116, preferably arranged coaxially with the combustion chamber 58 and tapering in the flow direction of the burner exhaust gases through the discharge opening 102. The requirement that the discharge taper be arranged coaxially with the combustion chamber 58 is understood in particular to mean that the axial direction of the discharge taper, i.e., its longitudinal axis, coincides with the axial direction of the combustion chamber 58.The sliding of the discharge taper in the axial direction of the combustion chamber 58 relative to the chamber element 116 makes it possible to change the flow cross section that can be traversed by the burner exhaust gases, for example, through which the burner exhaust gases can be discharged from the combustion chamber 58 and introduced into the exhaust gas channel. The discharge taper is particularly diagrammatically shown in FIG. 11 and designated by the reference numeral 128. The direction of movement, which runs parallel to the axial direction of the combustion chamber 58 or coincides with the axial direction of the combustion chamber 58 and along which the discharge taper 128 can translate, in particular slide, relative to the chamber element 116, is shown in FIG. 11 by a double arrow 130. It is clear that the flow cross section that can be traversed by the burner exhaust gases is defined, in particular directly, by the chamber element 116 in the radial direction of the combustion chamber 58 both outwardly and inwardly by the discharge taper 128, in that the flow cross section is configured in the form of a ring or an annular surface. The discharge taper portion 128 tapers in the flow direction of the burner exhaust gas flowing through the discharge opening 102 or the flow cross section, so that the flow cross section is changed by sliding the discharge taper portion 128 relative to the chamber member 116 along the direction of movement.

[0082] Figure 12 shows, in a schematic cross-sectional view, part of a fifth embodiment of burner 42. In particular, part of component 74 and part of component 82 are clearly visible, as in Figure 3. When burner 42 is not in operation, the air and power fuel lines, i.e., preferably outlet openings 64 and 68, are preferably closed to prevent engine exhaust gases from entering swirl chambers 62 and 76. For this purpose, it is conceivable to arrange a closing device 110 at the outlet opening 64 and / or at the outlet opening 80, respectively, or to arrange the closing device 110 downstream of the outlet opening 80 and thereby directly adjacent to it, so that, for example, a first flow cross section through which the first portion of air and the fuel can flow, in particular the outlet opening 64, and / or a second flow cross section through which the portions of air and the fuel can flow, in particular the outlet opening 80, or a third flow cross section through which the portions of air and the fuel can flow and which is arranged downstream of the outlet opening 80 and directly adjacent to it, can be varied or adjusted by the closing device 110. The first, second and third flow cross sections are, for example, opening cross sections 114, i.e., opening cross sections 114 of an opening having opening cross sections 114, the flow cross section (opening cross section 114) and thus the area of ​​which can be adjusted by the closing element 112, in particular in the manner of an iris diaphragm. In this way, the first, second and third flow cross sections can be adjusted, in particular load-dependently, and in particular controlled or regulated. For example, it is conceivable to close only both outlet openings 64 and 80, also called discharge nozzles, by the closing device 110 or by another further closing device, i.e. to reduce the first, second and third flow cross sections to zero.

[0083] Another closure device may be, for example, a closure element, designated 132, also referred to as a closure plug, which is particularly schematically shown in FIG. 12 . The closure element 132 is, for example, translationally movable relative to the component 82, particularly in the axial direction of the respective swirl chamber 62 or 76, and relative to the component 74, particularly between at least one closed position and at least one open position shown in FIG. 12 . In the closed position, the outlet openings 64 and 80 are closed and thus fluidically sealed by the closure element 132, particularly while the burner 42 is deactivated. Engine exhaust gases from the exhaust pipe 26 are thereby unable to flow through the outlet openings 64 and 80. In the open position, the closure element 132 opens the outlet openings 64 and 80, particularly while the burner 42 is operating. It is clear that the outlet openings 64 and 80 can be simultaneously closed or are closed by the closure element 132, which may be configured, for example, as a small plug, particularly when the closure element 132 is in the closed position. In that case, an air valve, such as valve element 55, is not necessary downstream of pump 56, since closing element 132 prevents engine exhaust gases from flowing from exhaust pipe 26 through air supply line 54. In other words, closing element 132 or closing device 110 prevents engine exhaust gases from entering pump 56 from exhaust pipe 26. A much larger exhaust gas flap downstream of combustion chamber 58, i.e. after the discharge, which is loaded with hot exhaust gases, can also be omitted.

[0084] The air gap insulation of the combustion chamber 58 is described in detail below. Since the outer wall of the combustion chamber 58 becomes very hot, even incandescent, especially during full-load operation, the air gap insulation ensures particularly safe operation. Furthermore, the air gap insulation also reduces heat loss. Preferably, the thermal insulation surrounds the combustion chamber 58 in a circumferential direction extending around the axial direction of the combustion chamber 58, particularly completely. In this example, an air gap insulation, i.e., an air gap, is provided as such insulation. The intermediate space 124, formed as an air gap in this example, preferably has a width extending in the radial direction of the combustion chamber 58, particularly a gap width, which is preferably 6% to 25% of Da. In particular, this width can be in the range of 1.5 mm to 6 mm. It is clear that the chamber member 116 is a double-walled, air-gap-insulated tube. In other words, the chamber portions 120 and 122 are double-walled, thereby forming an air-gap insulated pipe. Preferably, an insulating member configured separately from the chamber member 116 (air-gap insulated pipe) is intended to surround the air-gap insulated pipe (chamber member 116), i.e., at least one length region of the chamber member 116 extending in the axial direction of the combustion chamber 58, particularly completely around the circumference of the combustion chamber 58. This insulating member is preferably an insulating mat. The insulating member is preferably formed of at least mineral wool and / or thin plate, thereby enabling particularly favorable insulation of the combustion chamber 58.

[0085] Possible mounting positions for the combustion chamber 58 or the burner 42 are described below. As explained above, the mixture in the combustion chamber 58 is too lean to combust when heat or thermal energy is released. The thermal energy can be used to efficiently and effectively heat and / or maintain at a high temperature, for example, at least the component 36b. Alternatively or additionally, the component 36c, which may be configured as a particle filter, can be heated. The heating of the particle filter can, for example, initiate or perform regeneration of the particle filter. To optimally utilize the thermal energy of the burner 42, the inlet E2 is preferably located as close as possible to the components to be heated or maintained at a high temperature, such as the components 36b and / or 36c. This minimizes heat losses. However, to ensure a favorable mixing of the burner exhaust gas and the engine exhaust gas, a minimum distance for mixing the engine exhaust gas and the burner exhaust gas should be provided. This minimum distance extends, in particular in the direction of flow of the engine exhaust gas through the exhaust pipe 26, from the burner 42 or the inlet point E2 to the component to be heated or kept at a high temperature, such as component 36b, in particular to its inlet. In particular, this minimum distance is the minimum distance of the mixing chamber 40. Therefore, the inlet point E2 cannot be positioned immediately before the inlet point of component 36b. It is particularly preferred that the distance between the inlet point E2 and the component 36b, in particular the component immediately following the inlet point E2 in the direction of flow of the exhaust gas through the exhaust pipe 26, in the direction of flow of the exhaust gas through the exhaust pipe 26, be at least 5 to 8 times Da, and at most 30 times Da. The requirement that component 36b immediately follows inlet point E2 in the flow direction of the exhaust gas (engine exhaust gas) flowing through the exhaust pipe 26 is understood to mean that no other exhaust gas aftertreatment components are arranged between inlet point E2 and component 36b in the flow direction of the exhaust gas flowing through the exhaust pipe 26.Alternatively or additionally, the diameter, particularly the inner diameter, of the exhaust gas passage in which the inlet point E2 is located preferably expands conically to at least six times Da, particularly before the exhaust gases enter the component 36b, particularly after the discharge from the combustion chamber 58. In particular, if the component 36b is a catalyst, particularly the above-mentioned SCR catalyst, the component 36b has a substrate. Accordingly, the above-mentioned distances preferably refer to distances extending between the inlet point E2 and the substrate of the catalyst, particularly in the flow direction of the exhaust gases through the exhaust pipe 26. Accordingly, it is preferred that the inner diameter of the exhaust gas passage expands to at least six times Da after the discharge from the combustion chamber 58, i.e., starting from the inlet point E2, before the exhaust gases (engine exhaust gases or burner exhaust gases) impinge on the substrate.

[0086] As can be seen from FIG. 2 , the ignition device 60, which may be configured as, for example, a spark plug, glow plug, or glow pin, has a thread 134, particularly configured as an external thread, by means of which the ignition device 60 is at least indirectly screwed to the chamber member 116 and thereby held therein. To ensure sufficient cooling of the ignition device 60, i.e., to ensure favorable heat dissipation from the ignition device 60, the thread 134 of the ignition device 60, also referred to as the spark plug thread, is preferably provided with cooling ribs. The number of cooling ribs is preferably in the range of 1 to 7. For example, the cooling ribs have a thickness in the range of 2 to 4 mm. Furthermore, it is conceivable that each cooling rib has a diameter, particularly an outer diameter, of 20 to 80 mm. Additionally, to ensure favorable heat dissipation, each cooling rib preferably has an opening, particularly configured as a bore, in the periphery of the ignition device 60, i.e., to the ambient air, in the number of openings in the range of 3 to 8. Each through-opening of each cooling rib has a diameter, particularly an inner diameter, of, for example, at least 5 mm and at most 15 mm. The electrode spacing between the electrodes of the ignition device 60 is at least 0.7 mm and at most 10 mm. The electrodes are apparent from FIG. 2, where they are designated by the reference numerals 136 and 138, by means of, and particularly between, the electrodes 136 and 138 an ignition spark is generated in the combustion chamber 58 for igniting the mixture.

[0087] To support the creation or generation of vortex-like flows of the air portions in the swirl chambers 62 and 76, the air is preferably not introduced into the respective swirl chambers 62 to 76 strictly radially, i.e., in the radial direction of the respective swirl chambers 62 to 76, but tangentially or obliquely to the respective axial direction of the respective swirl chambers 62 to 76, as shown in Figure 2. In other words, the air or the respective air portions preferably enter the respective swirl chambers 62 to 76 tangentially. This allows the impingement of the incoming air to be induced already in the vortex direction, which leads to a particularly high efficiency of vortex generation.

[0088] A fuel pump is used to supply fuel to the burner 42, in particular a power fuel pump for delivering power fuel from the tank 18. Thus, the fuel pump can be, for example, the low-pressure pump 20. The burner 42 is preferably operated with lambda control, so that the mixture has, for example, a combustion air ratio (γ) of at least substantially 1.0. In other words, the burner is preferably operated stoichiometrically, i.e., the mixture is a stoichiometric air-fuel mixture. In other words, the first proportion of air in the mixture and the second proportion of fuel in the mixture are preferably adjusted or controlled as precisely as possible. Therefore, the first amount of air in the mixture, also referred to as combustion air, and the second amount of fuel in the mixture are preferably adjusted and / or calculated at least substantially accurately and introduced into the corresponding swirl chambers 62-76. Therefore, a frequency-controlled piston pump is preferably used as the fuel pump for delivering fuel to or into the burner 42. Such piston pumps may be provided with a spring biased valve, such as a ball valve, at the discharge, particularly to prevent backflow of power fuel or exhaust gases into the fuel pump.

[0089] Such a fuel pump is shown in a schematic longitudinal section in Fig. 17 and is designated by the reference numeral 137. Here, the fuel pump 137 is configured as a piston pump, and the piston for delivering fuel is designated by the reference numeral 138. The spring-loaded valve, which in the embodiment shown in Fig. 17 is configured as a spring-loaded ball valve, is designated by the reference numeral 140 in Fig. 17 and includes, among other things, a mechanical spring unit 142 and a ball 144. In particular, the spring-loaded valve 140 is configured as or functions as a check valve, so that fuel can be delivered by the fuel pump 137 to the burner 42, so that the valve 140 opens in the direction of the burner, but is closed in the opposite direction, so that exhaust gases and air cannot flow back from the burner 42 to the fuel pump 137.

[0090] 13 shows a sixth embodiment of the burner 42 in a schematic longitudinal section, which in particular, like in FIGS. 6 and 12, reveals the outlet openings 64 and 80 and thus the element 82 and the component 74. The injection element 66 is also visible in FIG. 13, although in the example shown in FIG. 13 it is configured as a lance, as in FIGS. 2 and 7. Instead of the outlet openings being arranged or configured on an axial end face 146 of the injection element 66 facing in the axial direction of the swirl chambers 62 to 76, the outlet openings 70 face radially of the swirl chambers 62 to 76 and are thereby formed on an outer circumferential jacket surface 148 of the injection element 66, which extends around a circumference centered on the axial direction of the respective swirl chamber 62 to 76. In other words, rather than each fuel jet 72 exiting the injection member 66 at the end face 146 in the direction of or parallel to the axis of its respective swirl chamber 62-76, the fuel jets 72 exit the injection member 66 perpendicular, or in this example obliquely, to the axial direction of its respective swirl chamber 62-76, as shown by dashed lines 150 in FIG. 13.

[0091] The inner circumferential jacket surface 86 of the component 74 is also called the membrane wall, because the fuel ejected from the injection element 66 through the outlet openings 70 and transferred or injected onto the membrane wall forms the aforementioned membrane or fuel film on the membrane wall (inner circumferential jacket surface 86). To particularly favorably transfer or direct the fuel onto the membrane wall, for example, a simple lance can be used instead of an atomizing nozzle, such as the injection element 66 shown in FIG. 13. The lance includes a small tube 152, at the end of which at least two outlet openings 70, for example configured as cross holes, are attached. Here, the fuel does not exit the lance or small tube 152 in the axial direction of the respective swirl chamber 62-76, but rather in the radial direction of the respective swirl chamber 62-76 or obliquely to the radial direction. Preferably, the fuel leaving the outlet opening 70 is atomized in order to be able to transfer or direct it particularly efficiently to the membrane attachment and, in this case, in particular to the membrane wall. For this purpose, it is provided that a venturi nozzle 154 is arranged on or above the surface of the membrane wall, also called the membrane attachment wall, in particular in the axial direction of the respective swirl chambers 62 to 76, whose axial direction coincides with the axial and longitudinal extension direction of the injection element 66, in particular of the small tube 152, at the level of the outlet openings 70, which are preferably arranged at the same axial level in each case. In other words, the venturi nozzle 154 is preferably provided in the swirl chamber 62 in which the outlet opening 70 is also arranged, and the narrowest flow cross-section of the venturi nozzle through which the first portion of air can pass is preferably arranged in the axial direction of the respective swirl chamber 62 to 76 and thus of the injection element 66 so that the narrowest, smallest or smallest flow cross-section of the venturi nozzle 154 and the respective outlet opening 70 are arranged at the same height in the axial direction of the respective swirl chamber 62 to 76 and thus of the injection element 66. This allows for particularly favorable atomization of the fuel flowing through the outlet opening 70. In particular, the venturi nozzle 154 and the injection element 66 function in the manner of a jet pump.The first portion of the air flows through the venturi nozzle 154, i.e., through its narrowest flow cross section. Since the outlet openings 70 are each at least partially arranged in the narrowest flow cross section of the venturi nozzle 154, i.e., the narrowest flow cross section of the venturi nozzle 154 and the outlet openings 70 are arranged at the same height in the axial direction of the injection element 66 and thus in the flow direction of the first portion of the air flowing through the venturi nozzle 154, the first portion of the air acts or functions as a driving medium, which, as it were, sucks the fuel as a suction medium, in particular through the outlet openings 70, so that the driving medium sucks the suction medium (fuel) through the outlet openings 70. This results in a particularly favorable atomization of the fuel in the swirl chamber 62.

[0092] FIG. 14 partially shows a seventh embodiment of the burner in a schematic longitudinal section. In this seventh embodiment, the injection element 66 is configured as a lance, for example. It can be seen that each fuel jet 72, in particular its longitudinal axis, forms an angle β, also called the jet angle, with an imaginary plane EB extending perpendicular to the axial direction of the respective swirl chamber 62-76 and thus perpendicular to the respective flow direction of the respective air portion flowing through the respective swirl chamber 62-76. The axial direction of each swirl chamber 62-76 coincides with the longitudinal extension or longitudinal extension of the injection element 66 and thus with its axial direction. The outlet openings 70 are spaced apart, particularly evenly distributed, in a circumferential direction extending around the axial direction of the injection element 66. In order to generate as thin and uniform a fuel film as possible on the film attachment portion, i.e., on the inner circumferential outer surface 86, the number of outlet openings 70 is preferably at least 2 and at most 10. In other words, for example, the number of outlet openings 70 is intended to be in the range of 2 to 10. For example, the angle β is preferably intended to be in the range of 10° to 60° in order to already guide the impact of the fuel in the flow direction. Furthermore, each outlet opening 70, which is preferably circular and configured, for example, as a bore, is intended to have a diameter, in particular an inner diameter, in the range of 3 mm to 50 mm.

[0093] FIG. 15 shows another possible embodiment of an injection element 66 in a partially cutaway schematic side view. In the embodiment shown in FIG. 15, the injection element 66 is configured as an injection nozzle, such as those used in oil heating burners. In the embodiment shown in FIG. 15, the injection element 66 has a head 155, a swirl slot 156, a volute 158, a secondary filter 160, and a primary filter 162. The injection element 66 of FIG. 15 has at least one, or exactly one, outlet opening 70, which is arranged or configured on its axial end face 146, also referred to as the axial end face. This means that a fuel jet 72 flowing through the outlet opening 70 exits the injection element 66, and thus the respective swirl chamber 62-76, in the axial direction from the outlet opening 70 and thus from the injection element 66. In other words, in FIG. 15, the fuel jets 72 or their major or central longitudinal axes extend at least substantially axially, i.e., parallel to the axial direction of the respective swirl chambers 62-76.

[0094] FIG. 16 shows a block diagram illustrating the operation, particularly the control, of the burner 42. The temperature of the exhaust gas at the inlet point E2 or downstream of the inlet point E2, particularly upstream of the component 36b, is designated T5. For example, the temperature T5 is measured, particularly by a temperature sensor, thereby determining a value, also referred to as the T5 value, that characterizes the temperature T5. The T5 value is represented in FIG. 16 by block 164. The T5 value is transmitted, particularly as an input variable, to block 166. Block 166 illustrates an initial state in which, for example, the air supply to the burner 42 is closed, the fuel pump is deactivated, thereby deactivating the fuel supply to the burner 42, and the ignition device 60 is deactivated. Arrow 168 indicates the so-called burner release. As a result of the burner release, the ignition device 60 is switched on, i.e., activated, in block 170. In block 172, a combustion air ratio of, for example, 0.9 is set in the mixture, thus starting the burner 42. Furthermore, for example, in block 172, the air pump is activated and the fuel pump is activated. Subsequently, for example, in block 174, the combustion air ratio of the mixture is adjusted to 1.03, and the fuel pump operates at a low frequency. In block 176, for example, the ignition device 60 is deactivated. Block 178 illustrates the operating state of the burner 42. In this operating state, the air supply to or into the burner 42 is opened, the fuel pump is switched on, and the ignition device 60 is deactivated, so that the burner 42 receives a supply of air and fuel. Arrow 180 indicates that the burner release is revoked, particularly if the temperature T5 exceeds a limit value, for example, 400°C.

[0095] In block 182, a comparison is made in which the actual value of the temperature T5 is compared with a target value for the temperature T5. The actual value of the temperature T5 is, for example, the T5 value mentioned above and / or is, for example, measured by a temperature sensor mentioned above, in particular at the inlet point E2 or downstream of the inlet point E2, in particular at a point in the exhaust pipe 26 arranged upstream of the component 36b. If, for example, the comparison shows that the actual value is lower than or equal to the target value, then, in particular in block 174, the operation of the fuel pump and the air pump remains regulated, with the fuel pump being represented in FIG. 16 by block 184 and the air pump by block 186. For example, if the actual value is higher than the setpoint value, then in block 188, the fuel pump is controlled, in particular by an electronic computing device, also referred to as a control device, and / or in block 190, the air pump is controlled, in particular by a control device, and in particular the fuel pump or the air pump is changed in terms of their respective operation, in particular the actual value is reduced, for example, until the actual value corresponds to or is lower than the setpoint value.

[0096] In block 192, the amount of air in the mixture is determined, in particular by measuring the air flow. Arrow 194 further indicates that the amount of fuel is determined, in particular measured. In block 196, the combustion air ratio (γ) is determined, in particular calculated, depending on the determined, in particular measured, amount of air and the determined, in particular measured, or calculated amount of fuel. In particular, in block 196, the actual combustion air ratio of the mixture is determined, in particular calculated. In block 198, the actual combustion air ratio is compared with a second set value of the combustion air ratio, which is, for example, 1.03. If the actual combustion air ratio corresponds to the set value of the combustion air ratio, or if the actual combustion air ratio differs only slightly from the set value of the combustion air ratio and the difference between the actual combustion air ratio and the set value of the combustion air ratio is, in particular, numerically greater than or equal to a limit value, the current operation of burner 42, in particular the fuel pump and the air pump, is maintained. However, if the actual combustion air ratio differs too much from the desired combustion air ratio, then, as indicated by arrow 200, the air pump and / or fuel pump, for example, are modified in their respective operation, particularly by controlling the fuel pump or air pump, so as to at least reduce or eliminate the difference between the actual combustion air ratio and the desired combustion air ratio. Finally, block 202 shows that the desired value for temperature T5 is set from or by the control device, particularly in block 182. Alternatively or additionally, the control device can set or output the desired combustion air ratio, particularly in block 198.

[0097] Figure 18 shows the swirl-generating device 107 of the burner 42 in a schematic, partially cross-sectional perspective view. The air passages LK1 and LK2 are particularly clearly visible in Figure 18. The outer air passage LK2 is defined radially outward of the respective swirl chamber 62 to 76 by a first wall 109 of the swirl-generating device 107, which is particularly solid and which surrounds, for example, the respective swirl chamber 62 to 76 completely in the circumferential direction and thus the air passage LK2 completely. The outer air passage LK2 is defined radially inward of the respective swirl chamber 62 to 76 by a second wall 111 of the swirl-generating device 107, which is particularly solid and which preferably surrounds, for example, the respective swirl chamber 62 to 76 completely in the circumferential direction and thus completely surrounds the air passage LK1. It is particularly clear that each air passage LK1-LK2 is configured at least substantially annularly, i.e., configured as an annular passage. Radially inwardly of the respective swirl chamber 62-76, the air passage LK1 is bounded by a body 113 of the swirl-generating device 107, which is configured in particular as a solid body, and which, as will be explained in more detail below, is an air guide. For example, it is conceivable that the swirl-generating device 107 is configured in one piece, whereby the walls 109 and 111 are configured in one piece with each other and / or the walls 109 and / or 111 are configured in one piece with the body 113.

[0098] 18, the vortex generating device 107 comprises an inner first vortex generator 115, which comprises a first inner vortex generator 94. In the embodiment shown in Fig. 18, the vortex generator 94 is also configured, in particular, as an at least partially curved or arched guide vane, so that the air flowing through the air passage LK1, i.e. the first portion of the air, is guided and redirected by the vortex generator 94, so that a vortex-like first flow of the first portion of the air can be or is generated by the vortex generator 94, i.e. the vortex generator 115. In particular, it is conceivable for each vortex generator 94 to be configured integrally with the wall 109 and / or 111 and / or integrally with the main body 113. It is clear that the vortex generators 94 are arranged in the air passage LK1, and the vortex generators 94 are arranged consecutively and in particular spaced apart from one another in the circumferential direction of the respective vortex chambers 62 to 76 and thus in the circumferential direction of the vortex generating device 107.

[0099] The vortex generating device 107 comprises a vortex generating arrangement 115 arranged in the air passage LK1 and having a vortex generator 94, and a second outer vortex generating arrangement 117 arranged in the air passage LK2 and having a second outer vortex generator 96. The vortex generators 96 are thus arranged in the air passage LK2, and are arranged consecutively and in particular spaced apart from one another in the circumferential direction of the respective vortex chambers 62 to 76 and thus in the circumferential direction of the vortex generating device 107. By means of the vortex generators 96, i.e. by means of the vortex generating arrangement 117, a portion of the air flowing through the air passage LK2 is redirected, deflected or otherwise guided in such a way that a second vortex-shaped flow of the second portion of air is generated. Each vortex generator 96 is preferably configured integrally with the walls 109 and / or 111, and / or with the body 113, and / or with the respective vortex generator 94, so that the vortex generating device 107 is preferably configured as a whole integral unit. In the embodiment shown in Figure 18, each vortex generator 96 is also configured as an at least partially curved or arched guide vane or air guide vane, i.e., having an arched transition. The number of first, inner vortex generators 94 is preferably, for example, in the range of 6 to 11. The number of second, outer vortex generators 96 is preferably in the range of 8 to 14.

[0100] Each air passage LK1-LK2 has an area, also referred to as a cross-section, upstream of the respective vortex generator 115-117 and / or downstream of the respective vortex generator 115-117. In this example, each air passage LK1-LK2 is annular, so the respective areas are the areas of the annular surfaces. Preferably, each vortex generator 94-96 covers or shields at least 20 percent and at most 60% of the area of ​​the respective air passage LK1-LK2 located upstream and / or downstream of the respective vortex generator 115-117, thereby achieving particularly favorable vortex generation. The central body 113 is closed and therefore not traversable by air. Furthermore, the main bodies 113 themselves are configured rotationally symmetrical with respect to their longitudinal or longitudinal central axes, which coincide with the axial direction of the respective vortex chambers 62 to 76 and thus with the axial direction of the vortex generating device 107. In particular, in the present example, all the main bodies 113 are configured as particularly central and / or closed sections.

[0101] Each vortex generator 94-96 forms with the above-mentioned imaginary plane EB an angle β that is preferably in the range of 10 to 45 degrees, for example. Furthermore, each vortex generator 94-96 is preferably intended to cause a deflection of a portion of the air flowing through the respective air passage LK1-LK2 by a deflection angle that is preferably in the range of 70 to 90 degrees.

[0102] In order to achieve a particularly favorable mixture formation, it is preferable that the swirl generator 115, in particular the swirl generator 94, extends or is manufactured in the opposite direction to the swirl generator 117, in particular to the swirl generator 96, so that the first vortex-shaped flow of the first portion of air has a first direction of rotation, in particular about the axial direction of each of the swirl chambers 62 to 76, and the second vortex-shaped flow of the second portion of air preferably has a second direction of rotation, in particular about the axial direction of each of the swirl chambers 62 to 76, the first direction of rotation being opposite or opposite to the second direction of rotation.

[0103] The vortex generating device 107 is applied in particular in the embodiment of the burner 42 shown in Fig. 19, which differs from the above-described embodiments in particular in that the burner 42 has a pre-chamber, generally designated 204, which forms a first, inner air supply chamber 206 and a second, outer air supply chamber 208. To this end, the burner 42 of Fig. 19 has a separating wall 210 which is constructed in particular as a solid body, preferably having an inherent rigidity. The separating wall 210 has at least one length LW which is arranged or extends upstream of the vortex generating devices 115 and 117 of the vortex generating device 107 in the flow direction of the air portions flowing through the vortex chambers 62 and 76. The direction of flow of the air through each swirl chamber 62 and 76 coincides with the axial direction of the respective swirl chamber 62-76, or the respective flow directions of the respective portions of air extend parallel to the axial direction of the respective swirl chamber 62-76, which axially coincides with the axial directions of the vortex generating device 107, the pre-chamber 204, the air supply chamber 206, and the air supply chamber 208. The radial direction of each air supply chamber 206-208 extends perpendicular to the axial direction of the respective air supply chamber 206-208. As can be seen from FIG. 19, the separation wall 210 allows a first portion of air to be supplied to the inner vortex chamber 62 and thus to the vortex generator 115. The inner first air supply chamber 206, which is associated with the inner vortex chamber 62 and is arranged upstream of the first vortex generator 115, is configured as a through-opening in the radial direction of the air supply chambers 206 and 208 and thus to the vortex chambers 62 and 76, and is formed in the length region LW of the separation wall 210, except for in this example just one overflow opening 212, which is connected to the outer vortex chamber 76 and thus to the vortex generator. 117, an air supply chamber 206 extending about the axial direction of the air supply chambers 206 and 208, which is fluidly connected with the inner air supply chamber 206 via an overflow opening 212, and an outer air supply chamber 208 which surrounds the inner air supply chamber 206 in particular so as to completely circumferentially surround the vortex chambers 62 and 76, and which is separated from the outer air supply chamber 208 via which a second portion of air can be supplied to the outer vortex chamber 76 and thus to the outer second vortex generator 117.The length region LW extends from the respective vortex generating device 115-117 parallel to the axial direction of the respective vortex chamber 62-76, facing the injection element 66 (injection element), opposite the respective flow direction of the respective air portion, in the direction indicated by arrow 214 in FIG. 19 , continuously, i.e., without interruption, except for the overflow openings 212, to a wall 216 of the burner 42, which is particularly solid and has through-openings 218 arranged in the wall 216, through which the injection element 66 can inject liquid fuel into the inner vortex chamber 62. This means that the through-openings 218 can be passed through by the fuel flowing through the injection element 66. Furthermore, the length region LW extends completely around the circumference of the respective air supply chamber 206-208, except for the overflow openings 212.

[0104] Furthermore, the burner 42 of FIG. 19 has a supply channel 218 through which air can flow, which is in direct communication with the outer air supply chamber 208, in particular via its channel opening 220. The supply channel 218 is, for example, a structural component of the air supply path 54. The air flowing through the supply channel 218, which forms the first and second sections, flows through the supply channel 218 and in particular through the channel opening 220 along a flow direction also referred to as the intake direction. In other words, the air flows through the channel opening 220 along the aforementioned intake direction and thus leaves the supply channel 218 and enters the outer air supply chamber 208. As already explained above, it is intended that the intake direction does not, for example, extend strictly in the radial direction of the respective swirl chambers 62 to 76, i.e., not strictly perpendicular to the axial direction of the respective swirl chambers 62 to 76, but, as is the case in FIG. 19, preferably extends obliquely to the respective axial direction of the respective swirl chambers 62 to 76. Air can thus be introduced via the supply channel 218, and in particular via its channel opening 220, into the outer air supply chamber 208, from where a second portion of the air can be transferred via the overflow opening 212 to the inner air supply chamber 206. As a result, the air introduced via the supply channel 218, and in particular via the channel opening 220, into the outer air supply chamber 208 is divided into portions: a first portion which enters the air supply chamber 206 and ultimately flows through the air channel LK1 and the inner swirl chamber 62, and a second portion which remains in the air supply chamber 208 and ultimately flows through the air channel LK2 and the swirl chamber 76. This allows particularly favorable mixture pretreatment to be carried out.

[0105] In the embodiment of FIG. 19 , the injection element (injection element 66), which is particularly configured as an injection element, has just one outlet opening 70 through which the injection element can provide, and in particular eject, liquid fuel flowing through the injection element. Thus, fuel can be discharged from the injection element via the outlet opening 70, which is pierceable by the liquid fuel flowing through the injection element, and the injection element communicates directly with the first inner air supply chamber 206 via the outlet opening 70. In other words, the passage 68 pierceable by the liquid fuel has the outlet opening 70, which communicates directly with the air supply chamber 206 via the outlet opening 70, and thus does not communicate with the swirl chamber 62 or the swirl chamber 76, so that the outlet opening 70 is located upstream of the swirl chamber 62 in the flow direction of the respective air portions and, therefore, outside the swirl chamber 62. Thus, for example, the injection element (injection element 66) injects fuel directly into the air supply chamber 206 via the outlet opening 70. In this case, the outlet opening 70 is formed in the axial end face 146 of the injection element, which axial end face 146 faces towards the air supply chamber 206 or towards the main body 113 in the axial direction of the vortex chambers 62 to 76 and thus in the axial direction of the air supply chambers 206 and 208, which in turn coincide with the axial direction of the injection element and its longitudinal extension.

[0106] 19 further shows that the body 113, in particular at least the subregions TBK of the body 113, is arranged in the inner air supply chamber 206 and faces the injection element, in particular the end face 146 and thus the outlet opening 70, in the direction indicated by the arrow 214. Here, the body 113 is convexly curved, in at least its subregions TBK, toward the injection element, in particular the end face 146, and is particularly spherical or truncated. This allows the air or a first portion of the air flowing toward the swirl chamber 62 to impinge on the subregions TBK and to be guided by the subregions TBK to the swirl generators 115 in a particularly flow-friendly manner. Here, the body 113, in particular the subregions TBK, are arranged between the swirl generators 115 in the radial direction of the respective swirl chambers 62 to 76 and thus in the radial direction of the swirl-generating device 107. This is understood in particular to mean that the vortex generators 94 are arranged in a continuous manner around the circumference of each vortex chamber 62 to 76 and thus around the body 113, in particular evenly distributed.

[0107] It is particularly clear that the separation wall 210 is or is formed by an air separation tube, by means of which the air supply chambers 206 and 208 are radially separated from one another. An overflow opening 212, here configured as an example bore, is provided, through which a first portion of air can flow from the outer air supply chamber 208 to the inner air supply chamber 206.

[0108] 19 additionally has a cooling jacket 222 configured as a water-cooling jacket or mantle, which in this example surrounds the length LBE of the injection element in the circumferential direction of the respective swirl chamber 62 to 76 and thus in the circumferential direction of the injection element, in particular completely, around the circumference of the injection element. The cooling jacket 222 can be passed through by a cooling fluid, preferably configured as a liquid, at least partially, in particular at least substantially or completely made of water, by which the injection element can be particularly preferably cooled.

[0109] Fig. 20 shows in a schematic side view a possible embodiment of an ignition device 60, configured as a spark plug by way of example. As can be seen from Fig. 20, the ignition device 60 has a plurality of cooling ribs 230 extending radially outward from a body 224 of the ignition device 60 in the radial direction of the ignition device 60, which extends perpendicularly to the longitudinal extension of the ignition device 60 and is indicated by a double arrow 226 in Fig. 20, and spaced apart in the longitudinal extension of the body 224, which generally coincides with the longitudinal extension of the ignition device 60 and is indicated by a double arrow 228 in Fig. 20, and which can be used to particularly favorably cool the ignition device 60.

[0110] As is apparent from Figure 21, at least one of the ribs 230, and preferably each cooling rib 230, has a through opening 232, which may be configured as a bore and / or may be circular, for example. The cooling ribs, and in particular their spacing from one another, become particularly clear from Figure 22.

[0111] Finally, Fig. 23 partially shows in a schematic cross-sectional view another embodiment of the burner 42. Here, the burner 42 has a closure member 132 that is movable relative to the outlet openings 64 and 80, and thereby relative to the component 74 and relative to the component 82, between an open position shown in Fig. 12 and a closed position shown in Fig. 23. In the closed position, the outlet opening 80 is closed, i.e., fluidly sealed, by the closure member 132, and in the closed position the closure member 132 is at least partially located within the outlet opening 80. In the embodiment shown in Fig. 23, the closure member 132 passes through the outlet opening 80 and projects into the outlet opening 64. Since the outlet opening 80 is closed by the closure member 132 in the closed position, and since the outlet opening 80 is arranged downstream of the outlet opening 64 as seen in the direction of air flow, i.e. as seen in the direction of flow of the respective air portion, when the closure member 132 is in its closed position, particles and gases from the combustion chamber 58 cannot flow through the outlet opening 80, and therefore particles and gases of the combustion chamber 58 cannot flow through the outlet opening 64 either. This makes it possible to protect both the air supply path 54 and the power fuel supply path 46 from contamination by gases and / or particles from the combustion chamber 58.

[0112] In Fig. 12, the closure element 132 is exemplarily movable along an element direction between a closed position and an open position, which extends parallel to or coincides with the axial direction of the respective swirl chambers 62 to 76. In Fig. 23, the closure element 132 is pivotable about a pivot axis SA extending through the center of rotation between the closed and open positions relative to the outlet openings 64 and 80, and thus relative to the component 74 and relative to the component 82. The closure element 132 is associated with an actuator 234, which can be actuated, for example electrically and / or pneumatically and / or hydraulically, by means of which the closure element 132 can be moved, in particular pivoted, between the closed and open positions. To this end, the actuator 234 is connected to the closure element 132, in particular in a link-like manner, via a lever mechanism 236. For example, the actuator 234 may move, i.e., slide, the lever members 238 and 240 of the lever mechanism 236 at least translationally, and the lever members 238 and 240 may be linked at least indirectly or directly to the closure member 132 so that, for example, translational movement of the lever members 238 and 240 is converted into pivotal movement of the closure member 132, thereby enabling the closure member 132 to pivot between a closed position and an open position. [Explanation of symbols]

[0113] 10 Drive unit 12 Internal combustion engine 14 Engine block 16 cylinders 18. Tank 20 Low-pressure pump 22 High-pressure pump 24 Intake pipe 26 Exhaust pipe 28 Exhaust gas turbocharger 30 Compressor 32 Turbine 34 Shaft 36a-d Components 38 Metering device 40 Mixing chamber 42 Burner 44 Flame 46 Power fuel supply route 48 Power fuel piping 50 Valve member 52 Electronic computing equipment 54 Air supply path 55 Valve member 56 Pump 58 Combustion chamber 60 Ignition system 62 Inner vortex chamber 64 First Outlet Opening 66 Injection member Aisle 68 70 Outlet opening 72 Fuel Jet 74 components 76 Outer vortex chamber 78 Separation wall 80 Second Outlet Opening 82 Components 84 atomizing lip 86 Inner circumference outer surface 88 Recirculation prevention plate 90 Through-flow opening 92 Supply room 94 Vortex generator 96 Vortex generator 98 Through-flow opening 100 Hole Plate 102 Discharge opening 104 Arrow 106 vortex flow 107 Vortex generating device 108 Through opening 109 Wall section 110 Closing device 111 Wall 112 Closure member 113 Body 114 Opening cross section 115 Vortex generator 116 Chamber component 117 Eddy current generator 118 Inner circumferential outer surface 120 Chamber part 122 Chamber part 124 Intermediate Room 126 dashed line 128 Discharge taper 130 double arrow 132 Closure member 134 threads 136 Electrode 137 Fuel Pump 138 Piston 140 valves 142 Spring 144 balls 146 End face 148 Mantle side 150 dashed line 152 Canaliculus 154 Venturi nozzle 155 Head 156 Vortex Slit 158 spiral bodies 160 Secondary Filter 162 Primary Filter 164 blocks 166 blocks 168 Arrow 170 blocks 172 blocks 174 blocks 176 blocks 178 blocks 180 Arrow 182 blocks 184 blocks 186 blocks 188 blocks 190 blocks 192 blocks 194 Arrow 196 blocks 198 blocks 200 arrows Block 202 204 Pre-chamber 206 Inner air supply chamber 208 Outer air supply chamber 210 Separation wall 212 Overflow opening 214 Arrow 216 Wall 218 Supply passage 220 Passage opening 222 Cooling cloak 224 Main Unit 226 double arrow 228 double arrow 230 Cooling Rib 232 Through opening 234 Actuator 236 Lever mechanism 238 Lever member 240 Lever member E1 introduction location E2 introduction location V1 connection point V2 connection point T1 part T2 part T part K End Edge LK1 air passage LK2 air passage K1 Torus K2 Torus TB part Di outer diameter Da outer diameter W wall area R radius α angle l1 length d1 Inner diameter d2 inner diameter L1 length domain β angle EB plane LW Length domain TBK partial area LBE Length Domain

Claims

1. A burner (42) for an exhaust pipe (26) through which exhaust gases of an internal combustion engine (12) of a motor vehicle can flow, a combustion chamber (58) in which a mixture containing air and liquid fuel is ignited and burned; an inner swirl chamber (62) through which a first portion of air can pass, the inner swirl chamber (62) having a first vortex generating device (115) capable of inducing a vortex flow of the first portion of air, and a first outlet opening (64) through which the first portion of air passing through the inner swirl chamber (62) can pass, and through which the first portion of air can be discharged from the inner swirl chamber (62); an injection member (66) pierceable by a liquid fuel, by which fuel can be injected into the inner swirl chamber (62), the first outlet opening (64) of which can also be pierced by fuel expelled from the injection member (66); an outer swirl chamber (76) circumferentially surrounding at least one length region of the inner swirl chamber (62) and traversable by a second portion of air, the outer swirl chamber having a second vortex generating device (117) capable of inducing a vortex flow of the second portion of air; and a second outlet opening (80) traversable by the second portion of air flowing through the outer swirl chamber (76), by fuel flowing through the first outlet opening (64), and by the first portion of air flowing through the inner swirl chamber (62) and the first outlet opening (64), through which the respective portions of air and fuel can be introduced into the combustion chamber (58); a separation wall (210) separating the inner air supply chamber (206) from the outer air supply chamber (208) so as to be able to supply a first portion of the air to the inner swirl chamber (62) and to be able to supply a second portion of the air to the outer swirl chamber (76) via the outer air supply chamber (208) surrounding the inner swirl chamber (62) and the outer swirl chamber (76) in the circumferential direction of the inner air supply chamber (206) and the outer swirl chamber (76); at least one or exactly one overflow opening (212) formed in the length region (LW) of the separation wall, located upstream of the first vortex generating device (115) and the second vortex generating device (117) as seen in the flow direction of the air portion flowing through the inner vortex chamber (62) and the outer vortex chamber (76), the overflow opening (212) being capable of fluidly connecting or connecting the inner air supply chamber (206) and the outer air supply chamber (208); a supply passage (218) through which air can flow and which communicates with the outer air supply chamber (208), through which air can be introduced into the outer air supply chamber (208) and from which a first portion of the air can be transferred through the overflow opening (212) to the inner air supply chamber (206), thereby dividing the air introduced into the outer air supply chamber (208) into portions; A burner (42) comprising:

2. 2. The burner (42) according to claim 1, characterized in that the injection element (66) has at least one outlet opening (70) through which fuel can flow, and through which fuel can be discharged from the injection element (66), and the injection element (66) communicates directly with the inner air supply chamber (206).

3. 3. The burner (42) according to claim 2, characterized in that the guide bodies (113) arranged in the inner air supply chamber (206) and facing the injection elements (66) and arranged between the first vortex generating devices (115) in the radial direction of the inner vortex chamber (62) are curved convexly towards the injection elements (66) and are arranged at least partially upstream of the first vortex generating devices (115).

4. 4. The burner (42) according to claim 1, wherein the first outlet opening (64) terminates in an end edge (K) in the flow direction of the first portion of the air flowing through the first outlet opening (64), the end edge being worked in such a way that it is formed by an atomizing lip (84) that tapers towards the end edge (K) in the flow direction of the first portion of the air flowing through the first outlet opening (64) and terminates at the end edge (K).

5. Burner (42) according to claim 4, characterized in that said end edge (K) is machined.

6. The burner (42) according to any one of claims 1 to 5, characterized in that a cooling mantle (222) surrounding at least one length region (LBE) of the injection element (66) in the circumferential direction of the injection element (66) can be passed through by a cooling fluid for cooling the injection element (66).

7. 7. A burner (42) according to claim 6, characterized in that the cooling fluid is a cooling liquid.

8. The burner (42) according to any one of claims 1 to 7, characterized in that the burner (42) has an ignition device (60) by means of which the mixture in the combustion chamber (58) can be ignited, and the ignition device (60) has at least one or more cooling ribs (230) for cooling the ignition device (60), the ribs standing outward from a body (224) of the ignition device in a radial direction of the ignition device (60) and spaced apart from one another in a longitudinal extension direction (228) of the body (224).

9. The burner (42) of claim 8, wherein each cooling rib (230) has a plurality of through openings (232).

10. 10. The burner (42) according to any one of claims 1 to 9, characterized in that at least one closure member (132) is movable relative to the first outlet opening (64) and the second outlet opening (80) between at least one closed position in which at least one of the first outlet opening (64) and the second outlet opening (80) is fluidly blocked and at least one open position in which at least one of the first outlet opening (64) and the second outlet opening (80) is unblocked.

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