Patent ID: 12221914

DETAILED DESCRIPTION OF THE DRAWINGS

Identical or functionally identical elements are provided with the same reference numerals in the figures.

FIG.1shows, in a schematic depiction, a drive device10of a motor vehicle preferably designed as a motor car, in particular as a passenger car. This means that the motor vehicle designed as a land vehicle has the drive device10in its fully produced state and can be driven by means of the drive device10. The drive device10has an internal combustion engine12also described as an internal combustion motor, which has an engine block14also described as an engine housing. The internal combustion engine12additionally has cylinders16, which are formed or delimited, in particular directly, by the engine block14. During a fired operation of the internal combustion engine12, respective combustion processes are running in the cylinders16, from which an exhaust gas of the internal combustion engine12results. For this purpose, an in particular liquid fuel is introduced, in particular directly injected, into the respective cylinder16within a respective work cycle of the internal combustion engine12. The internal combustion engine12can be designed as a diesel engine, such that the fuel is preferably a diesel fuel. A tank18, also described as a fuel tank, is provided in which the fuel is or can be received. A respective injector is for example assigned to the respective cylinder16, by means of which the fuel can be introduced, in particular directly injected, into the respective cylinder16. By means of a low-pressure pump20, the fuel is fed from the tank18to a high-pressure pump22, by means of which the fuel is fed to the injectors or to a fuel distribution element shared by the injectors and also described as a rail or a common rail. The injectors can be provided with the fuel from the fuel distribution element shared by the injectors by means of the fuel distribution element, and can introduce, in particular directly inject, the fuel from the fuel distribution element into the respective cylinder16.

The drive device10comprises an intake tract24that can be flowed through by fresh air, by means of which the fresh air flowing through the intake tract24is guided to and into the cylinder16. The fresh air forms a mixture of fuel and air with the fuel, which mixture comprises the fresh air and the fuel, and is ignited and thus combusted in the respective cylinder16within the respective work cycle. The mixture of fuel and air is in particular ignited via self-ignition. Exhaust gas of the internal combustion engine12, of which the exhaust gas is also described as engine exhaust gas, results from the ignition and combustion of the mixture of fuel and air.

The drive device10has an exhaust gas tract26that can be flowed through by the exhaust gas from the cylinders16. The drive device10additionally comprises an exhaust gas turbocharger28that has a compressor30arranged in the intake tract24and a turbine32arranged in the exhaust gas tract26. The exhaust gas can flow out of the cylinders16, flow into the exhaust gas tract26and then flow through the exhaust gas tract26. The turbine32can be driven by the exhaust gas flowing through the exhaust gas tract26. The compressor30can be driven by the turbine32, in particular via a shaft34of the exhaust gas turbocharger28. By driving the compressor30, the fresh air flowing through the intake tract24is compressed by means of the compressor30. Several components36a-dare arranged in the exhaust gas tract26, the components being designed as respective exhaust gas aftertreatment devices, i.e., exhaust gas aftertreatment components for aftertreating the exhaust gas. The components36a-dare arranged following one after the other in the flow direction of the exhaust gas of the internal combustion engine12flowing through the exhaust gas tract26, and are thus connected to one another in series or serially. For example, the component36ais an oxidation catalyst, in particular a diesel oxidation catalyst (DOC). Furthermore, the component36can be a nitrogen oxide storage catalyst (NSK). The component36bcan be an SCR catalyst, which is also simply described as an SCR. The component36ccan be a particle filter, in particular a diesel particle filter (DPF). The component36dcan for example have a second SCR catalyst and/or an ammonia slip catalyst (ASC).

The motor vehicle has a structure for example designed as a self-supporting body that forms or delimits an interior of the motor vehicle also described as a passenger cell or safety cell. During a respective journey of the motor vehicle, people can be located in the interior. For example, the structure forms or delimits an engine compartment in which the internal combustion engine12is arranged. The exhaust gas turbocharger28is for example arranged in the engine compartment. The structure additionally has a base, also described as a main base, via which the interior is at least partially, in particular at least substantially or completely delimited downwards in the vertical direction of the vehicle. For example, the components36a, b, care arranged in the engine compartment, such that for example the components36a, bandcform a so-called hot end or are components of a so-called hot end. The hot end can in particular be directly flange-mounted on the turbine32. The component36dis for example arranged outside of the engine compartment and underneath the base in the vertical direction of the vehicle, such that for example the component36dforms a so-called cold end or is a component of the so-called cold end.

The drive device10comprises a dosing device38, by means of which an in particular liquid reducing agent can be introduced into the exhaust gas tract26at an introduction point E1and can for example be introduced into the exhaust gas flowing through the exhaust gas tract26. The reducing agent is preferably an aqueous urea solution that can provide ammonia, which can react with nitrogen oxides potentially contained in the exhaust gas to form water and nitrogen in a selective catalytic reduction. The selective catalytic reduction can be catalytically caused and/or supported by the SCR catalyst. It can be seen fromFIG.1that the introduction point E1is arranged upstream of the component36band downstream of the component36ain the flow direction of the exhaust gas flowing through the exhaust gas tract26. The exhaust gas tract26preferably has a mixing chamber40in which the reducing agent introduced into the exhaust gas at the introduction point E1can be advantageously mixed with the exhaust gas.

The drive device10and thus the motor vehicle additionally comprise a burner42by means of which—as is explained in more detail in the following—at least one of the components36b, c, darranged downstream of the burner42in the flow direction of the exhaust gas flowing through the exhaust gas tract26can be quickly and efficiently heated and/or kept warm. The burner42can combust a mixture, in particular while forming a flame44, and in particular while providing a burner exhaust gas, wherein the burner exhaust gas or the flame44is or can be introduced into the exhaust gas tract26at an introduction point E2. This means that the burner42is arranged so to speak on the introduction point E2. In the exemplary embodiment described inFIG.1, the introduction point E2is arranged upstream of the components36b, canddand downstream of the component36a. In other words, in the exemplary embodiment shown inFIG.1, the burner42is arranged upstream of the components36b, c, dand downstream of the component36a. As an alternative, it is conceivable that the burner42or the introduction point E2is arranged upstream of the component36aand in particular downstream of the turbine32. The previously specified mixture to be combusted in the burner42or by means of the burner42comprises air and a liquid fuel. In the exemplary embodiment shown inFIG.1, the propellant used as the combustible fuel and/or at least a partial quantity of the air which is added to the burner42and is used to form the mixture, can for example originate from the intake tract24. For this purpose, a fuel supply path46is provided, which is or can be fluidically connected to the burner42on the one hand and on the other hand to a fuel conduit48. The fuel conduit48can be flowed through by the fuel flowing from the tank18to the injectors or to the fuel distribution element. The fuel supply path46is fluidically connected to the fuel conduit48at a first connection point V1, wherein the connection point V1is arranged downstream of the low-pressure pump20and upstream of the high-pressure pump22in the flow direction of the fuel flowing from the tank18to the fuel distribution element or to the respective injector. At least a part of the liquid fuel flowing through the fuel conduit48can be removed from the fuel conduit48at the connection point V1and introduced into the fuel supply path46. The fuel introduced into the fuel supply path46can flow through the fuel supply path46and is guided to and in particular into the burner42as the fuel by means of the fuel supply path46. A first valve element50is arranged in the fuel supply path46, by means of which a quantity of the fuel flowing through the fuel supply path46and thus to be added to the burner42can be adjusted. An electronic computer52also described as a control device is provided, by means of which the valve element50can be controlled, such that the quantity of the fuel flowing through the fuel supply path46and to be added to the burner42can be adjusted, in particular is to be regulated, by means of the control device via the valve element50.

An air supply path54is further provided, via which or by means of which the burner can be or is provided with the air to form the mixture. This means that the air supply path54can be flowed through by the air from which the mixture is formed. A pump56also described as an air pump is arranged in the air supply path54, by means of which pump the air can be fed through the air supply path54and can thus be fed to the burner42. For example, the low-pressure pump20also described as a low-pressure fuel pump is described as a fuel pump, by means of which the fuel is fed through the fuel supply path46and thus to the burner42.

It can be recognized that the air supply path54is fluidically connected to the intake tract24at a second connection point V2. Thus, for example, at least a part of the fresh air flowing through the intake tract24can be removed from the intake tract24at the connection point V2and introduced into the air supply path54. The fresh air introduced into the air supply path54can flow through the air supply path54as the air, and is guided to and in particular into the burner42by means of the air supply path54. A second valve element55is arranged in the air supply path54, by means of which second valve element the quantity of the air that is used to form the mixture and flows through the supply path54and thus flows through the burner42can be adjusted. For example, the control device is designed to control the valve element55, such that for example the quantity of the air that is used to form the mixture and flows through the air supply path54and thus to be added to the burner42can be adjusted, in particular is to be controlled, by means of the control device via the valve element55.

FIG.2shows a first embodiment of the burner42in a schematic sectional view. The burner42has a combustion chamber58in which the air added to the burner42and the mixture added to the burner42and comprising liquid fuel is to be ignited and thus combusted, i.e., it to be ignited and thus combusted during an operation of the burner42. For this purpose, an ignition device60designed for example as a spark plug or glow plug or glow element is provided, by means of which ignition device at least one ignition spark can be generated in the combustion chamber58, in particular using electrical energy or electrical current. By means of the ignition spark, the mixture in the combustion chamber58is ignited and combusted, in particular while providing the burner exhaust gas and/or while providing the flame44. By means of the burner exhaust gas or by means of the flame44, the exhaust gas flowing through the exhaust gas tract26can for example be quickly and efficiently heated and/or kept warm, such that, for example, at least the component36bcan be quickly and efficiently heated and/or kept warm by means of the exhaust gas that has been heated and/or kept warm and that flows through the components36b, candd.

The burner42has an inner swirl chamber62that can be flowed through by a first part of the air that is added to the burner42, and causes a turbulent first flow of the first part of the air. This should in particular be understood to mean that the first part of the air flows turbulently through at least one first partial region of the swirl chamber62and/or flows turbulently out of the swirl chamber62and/or flows turbulently into the combustion chamber58. The inner swirl chamber62has in particular exactly one first outflow opening64that can be flowed through by the first part of the air along a first through direction of the outflow opening64and thus along a first flow direction coinciding with the first through direction. The first part of the air can be removed from the inner swirl chamber62via the first outflow opening64. This means that the first part of the air can flow out of the inner swirl chamber62via the first outflow opening64. The burner42further comprises an introduction element in the form of an injection element66, which has a conduit68that can be flowed through by the liquid fuel that is added to the burner42.

In the first embodiment, the injection element66is designed as a lance that is also described as a fuel lance. The conduit68, and thus the injection element66, has at least one exit opening70that can be flowed through by the liquid fuel flowing through the conduit68. It can be seen fromFIG.2that in the first embodiment, the conduit68, and thus the injection element66has at least or exactly two exit openings70, for example designed as holes. The exit opening70can be flowed through by the fuel along a respective second through direction, such that the fuel flowing through the injection element66can be injected out of or can exit from the injection element66via the respective exit opening70and can be injected, and thus introduced, into the inner swirl chamber62, in particular directly. In other words, the injection element66or the conduit68leads into the inner swirl chamber62via the respective exit opening70, such that the liquid fuel can be injected into the inner swirl chamber62, in particular directly, via the respective exit opening70by means of the injection element66. The respective second through direction of the respective exit opening70coincides with a respective second flow direction along which the fuel can flow through the respective exit opening70. It can be recognized that the fuel can be injected out of the injection element66via the respective exit opening70while forming a respective fuel jet72, and can thus be injected, in particular directly, into the inner swirl chamber62. For example, the respective fuel jet72, of which the longitudinal central axis coincides for example with the respective second through direction or with the respective second flow direction, is designed at least substantially conically. In addition, for example, the injection element66, and thus presently the conduit68, has a longitudinal direction or longitudinal extension or longitudinal extension direction that runs in parallel with the first through direction, and thus in parallel with the first flow direction, in particular with the first through direction, and thus coincides with the first flow direction. It can further be seen fromFIG.2that the first through direction, and thus the first flow direction coincide with the axial direction of the outflow opening64and with the axial direction of the inner swirl chamber62. The respective second through direction or the respective second flow direction runs perpendicularly or presently obliquely to the first through direction, and thus to the first flow direction and to the axial direction of the swirl chamber62and the outflow opening64.

The swirl chamber62is at least partially, in particular at least substantially and thus more than half or even completely formed or delimited by a preferably single-part component74preferably of the burner42, such that the component74also forms or delimits the outflow opening64.

The burner42further has an outer swirl chamber76that surrounds at least one longitudinal region and presently also the first outflow opening64in the peripheral direction of the swirl chamber62, in particular completely continuously running around the axial direction of the swirl chamber62. The component74has a dividing wall78that is arranged between the swirl chambers62and76in the radial direction of the swirl chamber62and the radial direction of which runs perpendicular to the axial direction of the swirl chamber62. The swirl chambers62and76are thus separated from each other in the radial direction of the swirl chamber65by the dividing wall78. The axial direction of the swirl chamber62coincides with the axial direction of the swirl chamber76, such that the radial direction of the swirl chamber62coincides with the radial direction of the swirl chamber76. The outer swirl chamber76can be flowed through by a second part of the air, which is added to the burner42, and is designed to cause a turbulent second flow of the second part of the air. This means that the second part of the air flows turbulently through the swirl chamber76and/or flows turbulently out of the swirl chamber76and/or flows turbulently into the combustion chamber58. In particular, it is preferably provided that the parts of the air have their turbulent flows in the combustion chamber58, and thus run turbulently in the combustion chamber58. The outer swirl chamber76has, in particular exactly, one second outflow opening80that can be flowed through, in particular along a third flow direction, by the second part of the air flowing through the outer swirl chamber76, the third through direction of which second outflow opening, along which the outflow opening80can be flowed through by the second part of the air flowing through the swirl chamber76, presently coincides with the axial direction of the swirl chamber76, and thus with the axial direction of the swirl chamber62. The third through direction coincides with a third flow direction, along which the second part of the air flowing through the outer swirl chamber76flows through or can flow through the outflow opening80. This means in particular that the first through direction coincides with the third through direction and the first through direction coincides with the third flow direction, such that the first flow direction, the third flow direction, the first through direction and the third through direction presently coincide with the axial direction of the swirl chamber62and with the axial direction of the swirl chamber76. The second outflow opening80is arranged downstream of the outflow opening64in the flow direction of the parts of the air, and in particular in series or serially with the outflow opening64, such that the outflow opening80can be flowed through by the second part of the air, by the first part of the air and by the fuel. In particular, the first part of the air is in particular mixed with the fuel due to the turbulent first flow already in the swirl chamber62, in particular while forming a partial mixture. The partial mixture can flow through the outflow opening64and thus flow out of the swirl chamber62, and then flow through the outflow opening80, and is mixed with the second part of the air, in particular due to the advantageous turbulent second flow, whereby the mixture is particularly advantageously prepared, and thus the partial mixture is particularly advantageously mixed with the second part.

It can be seen that the swirl chamber76is at least partially, in particular at least substantially and thus at least more than half or even completely, delimited inwardly in the radial direction of the respective swirl chamber62or76by the component74, in particular by the dividing wall78. The swirl chamber76is at least partially, in particular at least substantially or completely, delimited by a component element82, which is presently designed separately from the component74, outwards in the radial direction of the respective swirl chamber62or76. The component74is at least partially, in particular at least substantially, arranged in the component element82. The outflow opening80is for example partially delimited or formed by the component element82and partially by the component74, in particular with regard to the lowest or smallest flow cross-section of the outflow opening80that can be flowed through by the second part.

In order for at least the component36bto be able to be heated and/or kept warm particularly efficiently, it is provided that—as can be seen particularly clearly fromFIG.3—the first outflow opening64ends in the flow direction of the first part of the air flowing through the first outflow opening64and thus in the flow direction of the fuel flowing through the first outflow opening64on an end edge K that has been machined in a targeted, in particular mechanical, manner and is thus knife-sharp, the edge for example running completely around the outflow opening64in the peripheral direction of the outflow opening64running around the axial direction of the outflow opening64, the axial direction of which coincides with the respective swirl chamber62or76. The knife-sharp end edge K is formed by an atomizing lip84, which is presently formed by the component74. The atomizing lip84tapers in the flow direction of the first part of the air flowing through the first outflow opening64, and thus in the flow direction of the fuel flowing through the first outflow opening64, towards the end edge K, and ends on the end edge K. For example, the end edge K is sanded and/or lathed, and thus mechanically machined in a targeted manner. For example, the fuel is sprayed against the component74in particular while forming the fuel jets72, in particular against a lateral surface86of the component74on the internal periphery, in particular such that a fuel film also simply described as a film is formed from the fuel on the component74, in particular on the lateral surface86on the internal periphery. It can in particular be seen that the inner swirl chamber62is formed, in particular directly, by the lateral surface86on the internal periphery outwards in the radial direction of the inner swirl chamber62. The fuel film is transported by the first turbulent flow, in particular by centrifugal forces resulting from the first turbulent flow, along the lateral surface86on the internal periphery to the end edge K, at which the fuel breaks away from the end edge K, whereby particularly tiny droplets of the fuel result from the fuel or from the fuel film. The component74is thus a so-called prefilmer or functions as a film layer between the turbulent flows. The droplets in combination form a particularly large surface area of the fuel, such that a particularly efficient operation of the burner can be obtained even at low outputs of the burner, whereby no high-cost pumps or no high-cost high-pressure generation are required to generate the small and thus fine droplets of the fuel. The smallest flow cross-section of the second outflow opening80that can be flowed through by the second partial fan is completely delimited or formed inwards by the end edge K in the radial direction of the respective outflow opening64or80.

The burner42further has an anti-recirculation plate88, which, in the first embodiment, is arranged downstream of the outflow opening80and downstream of the component element82in the flow direction of the parts flowing through the outflow opening80and of the fuel flowing through the outflow opening80. The anti-recirculation plate88has a through opening90, which is correspondingly arranged downstream of the outflow opening80and thus can be flowed through by the parts of the air and by the fuel from the swirl chambers62and76. Starting from the through opening90, and in particular starting from the outflow opening80and starting from the component element82, in particular starting from its end, the anti-recirculation plate88extends outwards in the axial direction of the respective swirl chamber62or76, whereby the anti-recirculation plate88protrudes outwards beyond at least a partial region T of the component element82in the radial direction of the respective swirl chamber62or76. Thus, for example, a first part T1of the combustion chamber58is at least partially separated from the second part T2of the combustion chamber58by means of the anti-recirculation plate88. By means of the anti-recirculation plate88, an excessive flow of the mixture flowing through the through opening90and into the combustion chamber58, in particular into the part T2back in the direction of the component element82or back into the part T1can be avoided, such that an advantageous mixture preparation can be achieved.

It can further be seen fromFIG.2that for example the swirl chambers62and76are supplied with the air or the parts of the air via a supply chamber92shared by the swirl chambers62and76. The supply chamber92is arranged upstream of the swirl chambers62and76in the flow direction of the parts flowing through the swirl chambers62and76. This means that the air is first introduced into the supply chamber92via the air supply path54. The air that has been introduced into the supply chamber92can flow through the supply chamber92on its way to and into the swirl chambers62and76and is divided into the first part and the second part, in particular by means of the component74. The air flowing through the air supply path54can for example flow out of the air supply path54along a supply direction and flow into the supply chamber92, wherein the supply direction for example runs obliquely and/or tangentially to the axial direction of the respective swirl chamber62and76, and thus to their respective longitudinal axis.

FIG.4shows the component74also described as a prefilmer in a schematic longitudinal sectional view. It can be seen that at least a part TB of the outer swirl chamber76is formed by the component74. The component74has first swirl generators94of the inner swirl chamber62and second swirl generators96of the outer swirl chamber76. By means of the swirl generators94, the first turbulent flow of the first part of the air is generated, and by means of the swirl generators96, the second turbulent flow of the second part of the air is generated. An inner annular surface, in particular the inner swirl chamber62, is labelled K1inFIG.4, and an outer annular surface, in particular the outer swirl chamber76, is labelled K2inFIG.4. The swirl generators94are arranged in an air conduit LK1of the swirl chamber62, of which the air conduit LK1is delimited, in particular completely, by the component74. The air conduit LK1is in particular delimited outwards and inwards in the radial direction of the respective swirl chamber62or76by the component74. The swirl generators96are arranged in a second air conduit LK2of the swirl chamber76, of which the air conduit LK2is delimited completely and in particular outwards and inwards in the axial direction of the respective swirl chamber62or76by the component74. For example, the swirl generators94and96are also formed by the component74. The air conduit LK1can be flowed through by the first part of the air and the air conduit LK2can be flowed through by the second part of the air, such that the swirl generators94generate or cause the first turbulent flow and the swirl generators96generate or cause the second turbulent flow. An outer diameter of the air conduit LK1also described as an air guide is labelled with Di, and an outer diameter of the air conduit LK2also described as an air guide is labelled with Da inFIG.4.

As can be seen fromFIGS.2to4, the outflow openings64and80also described as nozzles are both aligned in the axial direction. This means that the partial mixture flows at least substantially in the axial direction out of the inner swirl chamber62into the combustion chamber58. Furthermore, the second part of the air also flows at least substantially in the axial direction out of the outer swirl chamber76into the combustion chamber58and on the end edge K, in particular on its break-away point, entrains the finely distributed fuel from the prefilmer in small droplets into the combustion chamber58. The smallest or narrowest flow cross-section of the outer nozzle, and thus of the outflow opening80, is on the break-away point of the inner nozzle, and thus the outflow opening64, i.e., the end edge K.

It is preferably provided that the nozzles, and thus the outflow openings64and80, have the following sizes or surface ratios: The outflow opening64(inner nozzle) preferably has a diameter, in particular an inner diameter, which has 10 percent to 20 percent of Di. It is also preferably provided that the outer nozzle, and thus the outflow opening80, has a diameter, in particular an inner diameter that is for example 10 percent to 35 percent of Da. An annular surface area should be coextensive from the inside to the outside, and thus both the inside and the outside should be 50 percent of the entire annular surface area. In other words, it is preferably provided that the air conduit LK1has a first annular surface area and the air conduit LK2has a second annular surface area, wherein the annular surface areas are preferably the same size.

FIG.5shows a second embodiment of the burner42in a schematic sectional view. In the first embodiment, it is provided for example that the component element82and the anti-recirculation plate88are designed as components that are designed separately from one another and are at least indirectly, in particular directly, connected to each other. In the second embodiment, it is provided that the anti-recirculation plate88is designed as one part with the component element82. In the second embodiment too, it can advantageously be avoided by means of the anti-recirculation plate88that the mixture cannot flow backwards back to the component element82after exiting from the outer nozzle, and thus from the outflow opening80and into the combustion chamber58and form a vortex. The anti-recirculation plate88also simply described as a plate preferably has a diameter, in particular an outer diameter, that is preferably at least as large as Di.

FIG.6shows a section of a third embodiment of the burner42in a perspective view. In the third embodiment, the combustion chamber58has several through openings98that are spaced apart from one another and are separated from one another by respective wall regions W in particular designed as solid bodies, in particular in the radial direction of the respective swirl chamber62or76. Via the through openings98, the burner exhaust gas or the flame44can be removed from the combustion chamber58and introduced into the exhaust gas tract26. The wall regions W are presently designed as one part with one another and formed for example by a perforated disc100formed as one part that is designed as a solid body. Precisely eight through openings98are preferably provided. As can be seen fromFIG.2, it is conceivable in principle that the combustion chamber58has exactly one large and non-subdivided removal opening102, via which the burner exhaust gas or the flame44can be removed from the combustion chamber58and introduced into the exhaust gas tract26. Contrastingly, in the third embodiment, the several through openings98are spaced apart from one another and separated from one another, such that the removal opening102is effectively subdivided or divided into the several through openings98by the wall regions W. It can be seen that the through openings98are equally distributed in the peripheral direction running around the axial direction of the respective swirl chamber62or76and are in particular arranged along a circle, of which the mid-point is arranged in the respective axial direction of the respective swirl chamber62or76. Thus, in the third embodiment, instead of a large exit opening in the form of the large removal opening102, several exit openings in the form of the through openings98are provided, in particular at a respective particular point, to enable an advantageous recirculation in the combustion chamber58. Instead of a smaller exit opening, it is advantageous to use a perforated plate, e.g., the perforated disc100having several smaller openings in the form of the through opening98. The number of through openings98is in a range of three to nine inclusive. The through openings98have a similar or at least substantially identical flow surface or exit surface that can be flowed through by the burner exhaust gas or by the flame44. In total, the through surfaces of the or of all of the through openings98results in a total through surface that is described as a total exit surface, and for example, is 0.8 to 1.8 times as large as a single, centrally arranged opening, e.g., the removal opening102. For example, instead of a central exit opening having a diameter of 25 millimetres, and thus having a surface area of 491 square millimetres, it can be advantageous, depending on flow conditions in the exhaust gas tract26, to implement six smaller openings having a respective diameter of 10.5 millimetres, such that an entire exit surface of 520 square millimetres is represented.

FIG.7shows the third exemplary embodiment of the burner42in a schematic longitudinal sectional view, wherein the perforated disc100also described as a perforated plate is provided. The previously specified advantageous recirculation in the combustion chamber58is depicted by an arrow104inFIG.7. In addition, a turbulent flow of the mixture is depicted inFIG.7and is labelled with106, wherein the turbulent flow106of the mixture in the combustion chamber58results from the respective turbulent flows of the parts of the air. The turbulent flows of the parts of the air, and thus the turbulent flow106of the mixture is in particular implemented via the swirl generators94and96and by the tangential air feed, in particular via the air supply path54. The respective swirl generator94or96is preferably designed as an air guide vane, and not as a quarter-spherical sheet-metal construction, such that the respective turbulent flow can be particularly advantageously generated or caused. The turbulent flows of the parts of the air and, resulting from the latter, the turbulent flow106of the mixture in the combustion chamber58prevents the flame44from being blown out in the combustion chamber58, optimizes a mixing of the air with the fuel in the combustion chamber58, and generates vortex bursting for stabilising the flame44. The recirculation in the combustion chamber58depicted by the arrows104can in particular be implemented by using the perforated plate and, resulting from the latter, a reduction in an exit cross-section, via which the flame44or the burner exhaust gas can be removed from the combustion chamber58and can be introduced into the exhaust gas tract26. Reducing the exit cross-section should be understood to mean that, for example, the entire exit surface of the individual through openings98is smaller than a surface area of the large continuous removal openings102. An improved mixing of the air and the fuel in the combustion chamber58and a longer dwell time of the burning mixture in the combustion chamber58results from the advantageous recirculation in the combustion chamber58depicted by the arrows104, such that when the flame44or burner exhaust gas exits from the combustion chamber58, an excessive emission of non-combusted hydrocarbons (HC) can be avoided in the exhaust gas tract26, and a particularly high temperature of the flame44or of the burner exhaust gas can be implemented on its exit. The recirculation leads in particular to recirculation areas and vortex bursting, whereby a particularly long dwell time of the flame44can be implemented in the combustion chamber58.

FIG.8shows a swirl generation apparatus107in a schematic and partially sectional perspective view, which can for example be a component part of the component74or be formed by the component74. The swirl generation apparatus107comprises the swirl generators94of the inner swirl chamber62and the swirl generators96of the outer swirl chamber76. It can be particularly clearly seen fromFIG.8that the swirl generators96and preferably also the swirl generators94are designed as air guide vanes, which can be designed, in particular formed, in a manner favourable to flow. An excessive loss of pressure can thus be avoided, in particular in comparison with spherical swirl generators. The number of swirl generators94is for example in a range of six to eleven inclusive. As an alternative or in addition, the number of outer swirl generators96is for example in a range of eight to 14 inclusive. The respective air conduit LK1or LK2, in which the swirl generators94or96are arranged, has a respective surface area per se, for example, which is covered for example from at least 20 percent to at most 70 percent by the respective swirl generator arranged in the air conduit LK1or LK2. A particularly advantageous axial obstruction of at least 20 percent and at most 70 percent of the respective surface area is thus provided. A respective radius of the respective air guide vane can extend from at least 40 percent of Di up to an unlimited extent, such that the respective air guide vane can be straight in shape. It is in particular conceivable that the respective air guide vane makes a respective angle α with the respective radial direction of the respective swirl chamber62and76, the angle for example lying in a range of 10 degrees to 45 degrees inclusive. The previously specified radius of the respective air guide vane, also simply described as a vane, is labelled with R inFIG.8. The swirl generators94or96are preferably designed to divert the part of the air flowing through the respective air conduit LK1or LK2, and thus the air flowing through the respective air conduit LK1or LK2and forming the respective part, by 70 degrees to 90 degrees, in particular in relation to the strictly or purely axial direction of the respective swirl chamber62or76. To implement a particularly advantageous mixture preparation, the air guide vanes of the inner and outer swirl chambers62and76can be designed contrary to one another. In other words, it is conceivable that the outer swirl generator96of the outer swirl chamber76and the inner swirl generator94of the inner swirl chamber62are designed to form or to cause the turbulent flows of the parts of the air as contrary or opposite turbulent flows, such that, for example, the first flow is counter-clockwise and the second flow is clockwise or vice versa.

The swirl generation apparatus107has an in particular central through opening108, which is passed through by the injection element66. In other words, the injection element66protrudes through the through opening108into the inner swirl chamber62.

FIG.10shows a closing device110in a schematic front view that is presently designed as an iris diaphragm or in the manner of an iris diaphragm. If the burner42is not operated, it can be advantageous to block an air conduit and a fuel conduit, i.e., for example the air supply path54and/or the fuel supply path46and/or the swirl chambers62and76, and for example the outflow opening64and/or the outflow opening80to avoid exhaust gas of the internal combustion engine12entering the air supply path54, the fuel supply path46, the supply chamber92, the swirl chamber62and/or the swirl chamber76. It is further conceivable to block the combustion chamber58or at least one longitudinal region of the combustion chamber58to avoid exhaust gas of the internal combustion engine12entering the combustion chamber58or its partial region or longitudinal region from the exhaust gas tract26. For this purpose, the closing device110can be used, the closing device for example being able to be arranged in the combustion chamber58or downstream of the combustion chamber58. Closing elements112of the closing device110, the closing elements being able to be moved in the manner of an iris diaphragm, can vary, i.e., variably adjust an opening cross-section114that can be flowed through by the flame44or by the burner exhaust gas and is delimited, in particular directly, by the closing elements112, whereby for example the opening cross-section114can be adjusted, in particular controlled or regulated depending on load. It is thus conceivable to close at least a partial region of the combustion chamber58by means of the closing device110. As an alternative or in addition, the outflow opening80can for example be closed by means of a first closing device110. As an alternative or in addition, the outflow opening80can for example be closed by means of a second closing device110. This in particular has the advantage that an air and fuel supply can be simultaneously blocked by means of a small stopper. No air valve downstream of the pump56is needed either, as it prevents an entry of exhaust gas into the pump56. A much larger exhaust gas flap that is exposed to hot exhaust gas after the combustion chamber58or after its exit is also not required.

It is in particular conceivable that the opening cross-section114is an opening cross-section or exit cross-section, in particular of the combustion chamber58, wherein the flame44or the burner exhaust gas can be removed from the combustion chamber58and introduced into the exhaust gas tract26via the exit cross-section. A tapering of the opening cross-section that is necessary, required or carried out to increase a flow velocity of the flame44or of the burner exhaust gas from the combustion chamber58, in particular by corresponding movement of the closing elements112being implemented in the manner of an iris diaphragm should be represented in a manner favourable to flow. Thus, a conical outlet having an angle of 30 degrees to 70 degrees to the horizontal could be implemented instead of a hole in a flat closing plate, as is implemented, for example, by segments and/or by a cone in an aircraft engine. This can be implemented by a fixed geometry or variably, as in an aircraft engine having individual segments, the segments being foldable, for example in a thrust nozzle, or having a shiftably arranged exit cone that can for example be shifted in the axial direction of the respective swirl chamber62or76.

FIG.11shows a section of the burner42according to a fourth embodiment in a schematic sectional view. It can be seen particularly clearly fromFIG.11, but also fromFIGS.2and7, that the combustion chamber58is formed or delimited by a chamber element116in particular designed as a solid body. In particular, the combustion chamber58, of which the axial direction coincides with the axial direction of the respective swirl chamber62or76, is delimited, in particular directly, along its radial direction running in parallel with the respective radial direction of the respective swirl chamber62or76by a lateral surface118of the chamber element116on the internal periphery. The chamber element116can be designed as one-part. In the fourth embodiment, the chamber element116is designed such that it has two chamber parts120and122that are for example designed as one part with one another, or the chamber parts120and122are component parts that are designed separately from one another and connected to one another. The lateral surface118on the internal periphery is formed by the chamber part122. The chamber parts120and122are arranged within one another, such that at least one longitudinal region of the chamber part120surrounds at least one longitudinal region of the chamber part122in the peripheral direction of the combustion chamber58running around the axial direction of the combustion chamber58, in particular completely continuously, wherein at least the longitudinal region of the chamber part120is spaced apart from the longitudinal region of the chamber part122outwards in the radial direction of the combustion chamber58, in particular while forming a clearance124. The clearance124is arranged in the radial direction of the combustion chamber58between the chamber parts120and122, and is for example designed as an air gap, in particular between the chamber parts120and122. It can further be seen that the removal opening102that is continuous per se or uninterrupted, is formed or delimited by the chamber part122in particular completely continuously in the peripheral direction of the combustion chamber58. In the first embodiment shown inFIG.2, the removal opening102is not subdivided, i.e., is free of a component subdividing the removal opening102into several through openings separated from one another and spaced apart from one another. In the third embodiment shown inFIG.7, however, the perforated disc100, also described as a perforated plate, is arranged in the removal opening102, by means of which disc the removal opening102that is uninterrupted per se, i.e., continuous, is subdivided or divided into the several through openings98spaced apart from one another and separated from one another that are formed in the perforated disc100. The flame44or the burner exhaust gas can flow out of the combustion chamber58along a fourth flow direction running in the axial direction of the combustion chamber58, i.e., running in parallel with the axial direction of the combustion chamber58or coinciding with the axial direction of the combustion chamber58, and can flow through the removal opening102or through the respective through opening98, wherein the fourth flow direction coincides with the first, second and third flow direction. It can be seen that the removal opening102tapers in the flow direction of the burner exhaust gas flowing through the removal opening102, i.e., along the fourth flow direction. For this purpose, the chamber element116, in particular the chamber part120, has a longitudinal region L1tapering in the flow direction of the burner exhaust gas flowing through the removal opening102, the longitudinal region delimiting the removal opening102in the peripheral direction of the combustion chamber58, in particular completely continuously. In other words, the longitudinal region L1, and thus the removal opening102, are conical, i.e., cone-shaped or truncated cone-shaped in the flow direction of the burner exhaust gas flowing through the removal opening102. As the burner exhaust gas or the flame44flows out of the combustion chamber58via the removal opening102, the removal opening102is formed on an exit of the combustion chamber58or forms an exit of the combustion chamber58, wherein in the fourth embodiment, the combustion chamber58is conical in shape at its exit, and thus has a cone formed by the longitudinal region L1. The removal opening102preferably has an internal diameter of 34 mm. In other words, it is preferably provided that the smallest or narrowest internal diameter of the removal opening102that can be flowed through by the burner exhaust gas is 43 mm.

As at least the longitudinal regions of the chamber parts120and122are arranged within one another, and are spaced apart from one another in the radial direction of the combustion chamber58while forming the clearance124, wherein the clearance124is for example filled with air and thus designed as an air gap, a double wall of the combustion chamber58or of the chamber element116is created, whereby the combustion chamber58is insulated by the clearance124, i.e., by the air gap. The combustion chamber58is thus insulated by air gap. In the following, reference is made in particular to the outer diameter Da shown inFIG.4of the prefilmer, in particular of the outer air conduit LK2of the outer swirl chamber76, wherein the air conduit LK2in which the outer swirl generators96are arranged, and thus the outer diameter Da, are formed, in particular completely, by the prefilmer, i.e., by the component74. With reference toFIG.11and the outer diameter Da, the combustion chamber58preferably has an inner diameter d1that is preferably 1.0 times to 3.0 times Da, in particular upstream of the cone or upstream of the longitudinal region L1. It is further preferably provided that the smallest inner diameter d2of the removal opening102, wherein the smallest inner diameter d2of the removal opening102is also described as an exit diameter, is 0.7 times to 2.3 times Da. A smaller exit diameter of the removal opening102maintains the exit velocity of the burner exhaust gas and reduces the influence of the flame44, also described as a burner flame, by the exhaust gas, also described as engine exhaust gas, of the internal combustion engine12. A length11of the combustion chamber58running in the axial direction of the combustion chamber58is preferably 1.5 to 4.0 times Da, in particular without secondary air injection. It is preferably provided with secondary air injection that the length11of the combustion chamber is 2.0 to 5.5 times Da.

Instead of the continuous removal opening102, it is conceivable to use the several through openings98separated from one another and spaced apart from one another. In other words, it is conceivable that the removal opening102that is continuous per se and thus uninterrupted is divided into the several through openings98that are spaced apart from one another and separated from one another, the number of the through openings preferably lying in a range of 3 to 9 inclusive. The respective through opening98has a surface area, also described as an exit surface or through surface, wherein the sum of the surface areas of all of the through openings98is preferably the same as the exit surface of the continuous removal openings102, i.e., the same as the surface area of the removal opening102. The sum of the surface areas of the through openings98is also described as a total exit surface. The through openings98are for example designed as holes. It is conceivable that the sum of the surface areas of all of the through openings98, i.e., the total exit surface, is 0.8 times to 1.8 times the surface area of the or of an uninterrupted, continuous removal opening of the removal opening102of the combustion chamber58. It is in particular conceivable that the perforated disc100is arranged in the removal opening102or in the longitudinal region L1. With regard to the exhaust gas also described as engine exhaust gas, it can be advantageous for the internal combustion engine12to use a deflection element, in particular a deflection element and/or a perforated element, in particular a perforated sheet, wherein the perforated element can in particular be understood to mean an element formed as a solid body that has several holes spaced apart from one another and in particular separated from one another via respective walls, the holes being able to be flowed through by a gas, e.g., the burner exhaust gas or the engine exhaust gas. So that the engine exhaust gas does not excessively negatively influence and destabilize the flame44in the combustion chamber58, for example, it is advantageous to provide a deflection element, e.g., a deflection sheet, in front of the combustion chamber58, i.e., upstream of the combustion chamber58, so that the engine exhaust gas cannot or can only slightly enter the combustion chamber58, in particular against the flow direction, along which the flame44or the burner exhaust gas flows out of the combustion chamber58into the exhaust gas tract26. It is thus preferably provided that the deflection element is arranged upstream of the combustion chamber58, i.e., upstream of the introduction point E2, in the exhaust gas tract26in the flow direction of the engine exhaust gas. A geometry of the deflection element can depend on how the combustion chamber58is arranged in relation to the exhaust gas tract26, i.e., in relation to an exhaust gas conduit of the exhaust gas tract26. The exhaust gas conduit should be understood to mean that the burner exhaust gas or the flame44flows out of the combustion chamber58, in particular along the fourth flow direction, into the exhaust gas conduit, in particular at the introduction point E2. An individual adjustment of the geometry of the deflection element is advantageous.

It is further advantageous, as previously described, that the closing device110or another closing device is arranged on the exit of the combustion chamber58. This should in particular be understood to mean the following: The closing device110can for example be arranged in the longitudinal region L1or in the removal opening102, such that a flow cross-section, which can be flowed through by the burner exhaust gas or by the flame44and via which the burner exhaust gas or the flame44can be removed from the combustion chamber58, in particular at the introduction point E2, and can be introduced into the exhaust gas tract26, in particular into the exhaust gas conduit, is delimited by the closing device110, in particular by the closing elements112, and can consequently be varied, i.e., can be adjusted, by means of the closing device110. The adjustable flow cross-section is in particular the opening cross-section114.

The closing device110can be arranged in the chamber part122and in the removal opening102, or the closing device110or another closing device is arranged downstream of the combustion chamber58, i.e., downstream of the chamber part122and directly connected to the combustion chamber58or to the chamber part122, and is thus arranged downstream of the removal opening102per se. A tapering of the removal opening102, as is implemented in the fourth embodiment by the longitudinal region L1, i.e., by the cone described, leads to an increase of the flow velocity of the burner exhaust gas, wherein the tapering of the exit of the combustion chamber58should be depicted in a manner favourable to flow. The cone presently formed by the longitudinal region L1preferably has an angle, also described as a cone angle, in particular to the axial direction of the combustion chamber58, in particular depicted inFIG.11by a dashed line126, of 30° to 70°. In the fourth embodiment, the cone is formed as a fixed geometry, such that the cone, i.e., the cone angle is fixed, i.e., is not variable. It is conceivable, however, to form the cone variably, e.g., as in an aircraft engine, in particular with regard to its cone angle, in particular via individual segments, which can for example be folded, i.e., can in particular be pivoted relative to the chamber part122as in a thrust nozzle in an aircraft engine, whereby the cone or the cone angle can be adjusted, i.e., can be varied. As an alternative or in addition, it can be provided that the cone or its cone angle can be varied by a shiftably arranged exit cone and/or that an exit cone is provided of which the longitudinal central axis coincides for example with the axial direction of the combustion chamber58and/or can be shifted in the axial direction of the combustion chamber58, in particular relative to the chamber element116, wherein the exit cone, which is preferably arranged coaxially with the combustion chamber58, tapers in the flow direction of the burner exhaust gas flowing through the removal opening102. The feature that the exit cone is arranged coaxially with the combustion chamber58should in particular be understood to mean that the axial direction of the exit cone, and thus of its longitudinal central axis, coincides with the axial direction of the combustion chamber58. By shifting the exit cone in the axial direction of the combustion chamber58relative to the chamber element116, the flow cross-section that can be flowed through by the burner exhaust gas and via which the burner exhaust gas can be removed from the combustion chamber58and can be introduced into the exhaust gas conduit can for example be varied. The exit cone is shown particularly schematically and is labelled with128inFIG.11. A movement direction running in parallel with the axial direction of the combustion chamber58or coinciding with the axial direction of the combustion chamber58and along which the exit cone128can be moved, in particular shifted, translationally relative to the chamber element116is depicted inFIG.11by a double arrow130. It can be recognized that in the radial direction of the combustion chamber58, the flow cross-section that can be flowed through by the burner exhaust gas is delimited outwards by the chamber element116and is delimited inwards by the exit cone128, in particular respectively directly, with the flow cross-section being annular or annular-surface shaped. As the exit cone128tapers in the flow direction of the burner exhaust gas flowing through the removal opening102or the flow cross-section, the flow cross-section is varied by shifting the exit cone128implemented along the movement direction and relative to the chamber element116.

FIG.12shows a section of a fifth embodiment of the burner42in a schematic sectional view. The component74and the component element82can in particular be partially seen inFIG.12, in particular as inFIG.3. If the burner42is not operated, it is advantageous to close an air and fuel conduit, i.e., preferably the outflow openings64and68, to prevent the engine exhaust gas from penetrating the swirl chambers62and76. For this purpose it is conceivable that for example a closing device110is respectively arranged in the outflow opening64and/or in the outflow opening80, or the closing device110is arranged downstream of the outflow opening80and directly connected to the outflow opening80, such that for example a first flow cross-section that can be flowed through by the first part of the air and the fuel, in particular of the outflow opening64, and/or a second flow cross-section that can be flowed through by the parts of the air and by the fuel, in particular of the outflow opening80, or a third flow cross-section that can be flowed through by the parts of the air and by the fuel and is arranged downstream of the outflow opening80and immediately or directly connected to the outflow opening80is variable or can be adjusted by means of the closing device110. The first, second or third flow cross-section is for example the opening cross-section114, i.e., in particular the opening cross-section114of an opening having the opening cross-section114, of which the flow cross-section (opening cross-section114) and thus the surface area can in particular be adjusted in the manner of an iris diaphragm by means of the closing elements112. The respective first, second or third flow cross-section can be adjusted, in particular controlled or regulated, in particular depending on load. For example, it is conceivable to only close the two outflow openings64and80, also described as exit nozzles, by means of the closing device110or by means of another, further closing device, and thus to reduce the first, second or third flow cross-section to zero.

The further closing device can for example be a closing element depicted particularly schematically inFIG.12and labelled with132, which is also described as a closing stopper. The closing element132can for example be moved, in particular in the axial direction of the respective swirl chamber62or76, relative to the component element82and relative to the component74, in particular translationally, in particular between at least one closed position and at least one open position shown inFIG.12. In the closed position, the outflow openings64and80are closed by the closing element132and thus fluidically blocked, in particular while the burner42is deactivated. No engine exhaust gas can thus flow through the outflow openings64and80out of the exhaust gas tract26. In the open position, the closing element132releases the outflow openings64and80, in particular while the burner42is operated. It can be seen that the outflow openings64and80can be or are simultaneously closed by means of the closing element132for example designed as a small stopper, in particular in the closed position of the closing element132. No air valve, such as the valve element55, is required downstream of the pump56, as it can be avoided by means of the closing element132that engine exhaust gas flows out of the exhaust gas tract26through the air supply path54. In other words, it can be avoided by means of the closing element132or by means of the closing device110that engine exhaust gas from the exhaust gas tract26penetrates the pump56. A much larger exhaust gas flap to which hot exhaust gas is applied is also not required downstream of the combustion chamber58, i.e., after its exit.

In the following, the previously specified air gap insulation of the combustion chamber58is explained in more detail: As the combustion chamber58becomes very hot on its outer wall and optionally glows, especially in its full power operation, the air gap insulation can guarantee a particularly safe operation. Heat loss can additionally be kept particularly low by the air gap insulation. It is preferably provided that an in particular thermal insulation surrounds the combustion chamber58in the peripheral direction running around the axial direction of the combustion chamber58, in particular completely continuously. The air gap insulation, and thus the air gap, is provided as this insulation in the present case. The clearance124presently designed as an air gap preferably has a width, in particular a gap width, running in the radial direction of the combustion chamber58, wherein the width, in particular the gap width, is preferably 6% to 25% of Da. It is in particular conceivable that the width lies in a range of 1.5 mm to 6 mm inclusive. It can in particular be seen that the chamber element116is a double-walled and thus air gap-insulated pipe. In other words, the chamber parts120and122form a double-walled and thus air gap-insulated pipe. It is preferably provided that an insulating element formed separately from the chamber element116(air gap-insulated pipe) surrounds the air gap-insulated pipe (chamber element116), i.e., at least one longitudinal region of the chamber element116running in the axial direction of the combustion chamber58, in the peripheral direction of the combustion chamber58, in particular completely continuously. The insulation element is preferably an insulation mat. The insulation element is preferably formed at least from mineral wool and/or sheet metal, whereby the combustion chamber58can be particularly advantageously insulated.

In the following, a possible installation position of the combustion chamber58or of the burner42is described. As has previously been described, the mixture in the combustion chamber58is too thin to combust while releasing heat or heat energy. By means of the heat energy, at least the component36bcan for example be effectively and efficiently heated and/or kept warm. As an alternative or in addition, the component36cfor example designed as a particle filter can be heated. By heating the particle filter, a regeneration of the particle filter can for example be caused or carried out. So that the heat energy of the burner42can now be advantageously used, the latter or the introduction point E2should be arranged as close as possible to the component to be heated or kept warm, such as for example the component36band/or36c. Heat losses can thus also be kept low. To guarantee an advantageous mixing of the engine exhaust gas with the burner exhaust gas, however, a minimum distance to the mixing of the burner exhaust gas with the engine exhaust gas should be provided, wherein this minimum distance extends in particular in the flow direction of the engine exhaust gas flowing through the exhaust gas tract26from the burner42or from the introduction point E2, in particular continuously, to the component to be heated or to be kept warm, e.g., the component36b, in particular to its entrance. In particular, the minimum distance is a minimum distance of the mixing chamber40. The introduction point E2thus cannot advance directly to the entrance of the component36b. It has proved particularly advantageous if a spacing running in particular in the flow direction of the exhaust gas flowing through the exhaust gas tract26between the introduction point E2and the component36bimmediately following the introduction point E2in the flow direction of the exhaust gas tract26is at least 5 to 8 times Da and at most 30 times Da. The feature that the component36bis immediately or directly connected to the introduction point E2in the flow direction of the exhaust gas (engine exhaust gas) flowing through the exhaust gas tract26should be understood to mean that no other, further exhaust gas aftertreatment component is arranged in the flow direction of the exhaust gas flowing through the exhaust gas tract26between the introduction point E2and the component36b. As an alternative or in addition, a diameter, in particular an inner diameter, of the exhaust gas conduit in which the introduction point E2is arranged should broaden conically to at least 6 times Da, in particular after it exits the combustion chamber58, in particular before the exhaust gas enters the component36b. In particular if the component36bis a catalyst, in particular the previously specified SCR catalyst, the component36bhas a substrate. It is thus preferably provided that the previously specified spacing is a spacing running in particular in the flow direction of the exhaust gas flowing through the exhaust gas tract26between the introduction point E2and the substrate of the catalyst. It is thus advantageous if the inner diameter of the exhaust gas conduit broadens to at least 6 times Da after exiting the combustion chamber58, i.e., for example starting from the introduction point E2, before the exhaust gas (engine exhaust gas or burner exhaust gas) is applied to the substrate.

It can be seen fromFIG.2that the ignition device60for example designed as a spark plug, glow plug or glow element has a thread134in particular designed as an outer thread, by means of which the ignition device60is at least in directly screwed to the chamber element116and is thus held on the chamber element116. To obtain a sufficient cooling of the ignition device60, i.e., an advantageous heat removal from the ignition device60, it is advantageous if cooling ribs are applied on the thread134of the ignition device60also described as a spark plug thread. The number of cooling ribs preferably lies in a range of 1 to 7 inclusive. For example, the cooling ribs have a thickness that lies in a range of 2 to 4 mm inclusive. It is further conceivable that the respective cooling rib has a diameter, in particular an outer diameter, of 20 to 80 mm. It is additionally advantageous if the individual cooling ribs have openings, in particular through openings, designed in particular as holes to achieve advantageous heat removal in an environment of the ignition device60, i.e., ambient air, the number of which openings lies in a range of 3 to 8 inclusive. The respective through opening of the respective cooling rib for example has a diameter, in particular an inner diameter, that is at least 5 mm and at most 15 mm. An electrode spacing between electrodes of the ignition device60is at least 0.7 mm and at most 10 mm. The electrodes can be seen fromFIG.2and are labelled136and138, wherein the ignition spark for igniting the mixture in the combustion chamber58is generated by means of the electrodes136and138, in particular between the electrodes136and138.

To support the causation or generation of the turbulent flows of the parts of the air in the swirl chambers62and76, the air should not be introduced strictly radially, i.e., in the radial direction of the respective swirl chambers62or76into the respective swirl chamber62or76, but tangentially or obliquely to the respective axial direction of the respective swirl chamber62or76, as is depicted inFIG.2. In other words, it is advantageous if the air or the respective part of the air flows into the respective swirl chamber62or76tangentially. A surge of the entering air can thus additionally be directed in the swirl direction, which results in the swirl generation being particularly highly effective.

To provide the burner42with the fuel, a fuel pump, e.g., a propellant pump, is used to feed the fuel from the tank18. The fuel pump can thus for example be the low-pressure pump20. It is advantageous to operate the burner42in a lambda-controlled manner, such that for example the mixture has a fuel-air ratio (y) of substantially at least 1.0. In other words, it is preferably provided that the burner is operated stoichiometrically, and the mixture is thus a stoichiometric mixture. In other words again, it is advantageously provided if a first portion of the air in the mixture and a second portion of the fuel in the mixture can be adjusted or regulated particularly precisely. It is advantageous if the first quantity of the air, also described as combustion air, of the mixture and a second quantity of the fuel of the mixture are at least substantially precisely adjusted and/or calculated and are introduced into the respective, corresponding swirl chamber62or76. It is thus advantageous to use a frequency-controlled piston pump as the fuel pump for feeding the fuel to or into the burner42. The frequency-controlled piston pump should be provided with a spring-loaded valve, e.g., a ball valve, on its exit, to prevent fuel or exhaust gas from flowing back, in particular into the fuel pump.

Such a fuel pump is shown inFIG.17in a schematic longitudinal sectional view and is labelled137. The fuel pump137is designed as a piston pump, of which the piston for feeding the fuel is labelled138. The spring-loaded valve, which is designed as a spring-loaded ball valve in the exemplary embodiment shown inFIG.17, is labelled140inFIG.17and comprises an in particular mechanical spring unit142and a ball144. The spring-loaded valve140is in particular designed as a return valve or functions as a return valve, such that the fuel can be fed to the burner42by means of the fuel pump137, such that the valve140opens in the direction of the burner, but blocks it in the opposite direction, such that no exhaust gas and no air can flow out of the burner42back into the fuel pump137.

FIG.13shows a section of a schematic longitudinal sectional view of a sixth embodiment of the burner42, wherein the outflow openings64and80and thus the component element82and the component74can in particular be seen inFIG.6and inFIG.12. The injection element66can also be seen fromFIG.13, the injection element being designed however according toFIGS.2and7as a lance in the exemplary embodiment shown inFIG.13. The exit openings are not arranged or formed on an axial end face146of the injection element66aligned in the axial direction of the swirl chambers62or76, but the exit openings70are aligned in the radial direction of the swirl chambers62or76and formed in a lateral surface148of the injection element66on the outer periphery, the lateral surface148on the outer periphery of the injection element extending around the axial direction of the peripheral direction running around the axial direction of the respective swirl chamber62or76. In other words, the respective fuel jet72does not exit the injection element66at the end face146and not in the axial direction or not in parallel with the axial direction of the respective swirl chamber62or76, and instead the fuel jet72exits the injection element66perpendicular or presently obliquely to the axial direction of the respective swirl chamber62or76depicted by a dashed line150inFIG.13.

The lateral surface86on the internal periphery of the component74is also described as a film wall, as the fuel that is injected out of the injection element66via the exit openings70and is applied or injected against the film wall forms the previously specified film or fuel film on the film wall (lateral surface86on the internal periphery). To apply the fuel particularly advantageously on or against the film wall, a simple lance, e.g., the injection element66shown inFIG.13, can for example be used instead of an atomizing nozzle. The lance comprises a tube152, in the end region of which the at least two exit openings70, for example designed as transverse holes, are applied. The fuel does not exit the lance or the tube152in the axial direction of the respective swirl chamber62or76, and instead exits in the radial direction or obliquely to the radial direction of the respective swirl chamber62or76. So that the fuel exiting the exit openings70can be particularly effectively applied on the prefilmer and in particular on or against the film wall, it is advantageous if the fuel is atomized. For this purpose, it is preferably provided that if a venturi nozzle154is arranged on or at the film wall also described as a prefilmer wall, the venturi nozzle is in particular arranged at the height of the exit openings70in the axial direction of the respective swirl chamber62or76of which the respective axial direction coincides with the axial direction and with the longitudinal extension direction of the injection element66, in particular of the tube152, the exit openings preferably being arranged at the same height in the axial direction. In other words, the venturi nozzle154is preferably provided in the swirl chamber62in which the exit openings70are also arranged, the narrowest flow cross-section of which venturi nozzle that can be flowed through by the first part of the air preferably being arranged in the axial direction of the respective swirl chamber62or76, and thus of the injection element66such that the narrowest or smallest or lowest flow cross-section of the venturi nozzle154and the respective exit opening70are arranged at the same height in the axial direction of the respective swirl chamber62or76and thus in the axial direction of the injection element66. A particularly advantageous atomization of the fuel flowing through the exit openings70can thus be obtained. The venturi nozzle154and the injection element66can in particular function as a kind of jet pump. The first part of the air flows through the venturi nozzle154, i.e., through its narrowest flow cross-section. As the exit openings70are respectively at least partially arranged in the narrowest flow cross-section of the venturi nozzle154, i.e., as the narrowest flow cross-section of the venturi nozzle154and the exit openings70are arranged at the same height in the axial direction of the injection element66and thus the flow direction of the first part of the air flowing through the venturi nozzle154, the first part of the air acts or functions as a propellant that suctions the fuel as a suction medium, so to say, in particular via the exit openings70, such that the propellant suctions the suction medium (fuel) through the exit openings70, so to say. The fuel is thus particularly advantageously atomized in the swirl chamber62.

FIG.14shows a section of a seventh embodiment of the burner in a schematic longitudinal sectional view. In the seventh embodiment, the injection element66is for example designed as a lance. It can be seen that the respective fuel jet72, in particular its longitudinal axis or longitudinal central axis, forms an angle β, also described as a jet angle, with an imaginary plane EB running perpendicular to the axial direction of the respective swirl chamber62or76, and thus perpendicular to the respective flow direction of the respective part of the air flowing through the respective swirl chamber62or76. The axial direction of the respective swirl chamber62or76coincides with the longitudinal extension direction or longitudinal extension of the injection element66, and thus with its axial direction. The exit openings70are arranged distributed and spaced apart from one another in the peripheral direction running around the axial direction of the injection element66, in particular equally. To generate as thin and as even a fuel film as possible on the prefilmer, i.e., on the lateral surface86on the internal periphery, the number of exit openings70is preferably at least 2 and at most 10. In other words, it is for example provided that the number of exit openings70lies in a range of 2 to 10 inclusive. For example, it is preferably provided that the angle β lies in a range of 10° to 60° inclusive, in particular to direct a surge of the fuel as early as in the flow direction. In addition, it is provided that the respective, preferably circular exit opening70that is for example designed as a hole has a diameter, in particular an inner diameter, that lies in a range of 50 mm to 3 mm inclusive.

FIG.15shows a possible further embodiment of the injection element66in a schematic and partially sectional side view. In the exemplary embodiment shown inFIG.15, the injection element66is designed as an injection nozzle, as is used in fuel oil burners. In the exemplary embodiment shown inFIG.15, the injection element66has a head155, a swirl slit156, a vortex body158, a secondary filter160and a primary filter162. The injection element66according toFIG.15has at least or exactly one exit opening70, wherein the exit opening70of the injection element66is designed or formed on its axial end face146, which is also described as an axial end surface. This means that the fuel jet72flowing through the exit opening70in the axial direction of the injection element66, and thus of the respective swirl chamber62or76, exits the exit opening70, and thus the injection element66. In other words, according toFIG.15, the fuel jet72or its longitudinal axis or longitudinal central axis runs at least substantially in the axial direction, i.e., in parallel with the axial direction of the respective swirl chamber62or76.

FIG.16shows a block diagram for depicting an operation, in particular a regulation of the burner42. A temperature of the exhaust gas at the introduction point E2or downstream of the introduction point E2and in particular upstream of the component36bis labelled T5. For example, the temperature T5is measured, in particular by means of a temperature sensor, such that for example a value, also described as a T5value, that characterizes the temperature T5is measured. The T5value is depicted by a block164inFIG.16. The T5values is transferred to a block166, in particular as an input parameter. The block166depicts an initial state in which, for example, an air feed into the burner42is closed, the fuel pump is deactivated, such that a fuel feed into the burner42is also deactivated and the ignition device60is deactivated. An arrow168depicts a so-called burner release, i.e., a release of the burner. As a consequence of the burner release, the ignition device60is switched on, i.e., activated, in a block170. In a block172, a fuel-air ratio of the mixture of 0.9 is for example set to thus obtain a starting operation of the burner42. In addition, in the block172, the air pump is for example activated and the fuel pump is activated. The fuel-air ratio of the mixture is then adjusted to 1.03 in a block174, for example, wherein the fuel pump is operated at a low frequency. In a block176, the ignition device60is for example deactivated. A block178depicts an operating state of the burner42. In the operating state, an air feed to or into the burner42is opened, and the fuel pump is switched on and the ignition device60is deactivated such that the burner42is supplied with the air and the fuel. An arrow180indicates that the burner release is withdrawn, in particular if the temperature T5is greater than a limit value that is 400° ° C., for example.

In a block182, a comparison in which an actual value of the temperature T5is compared with a target value of the temperature T5is implemented. The actual value of the temperature T5is for example the previously specified T5value, and/or for example the actual value of the temperature T5is measured, in particular by means of the previously specified temperature sensor, in particular at the introduction point E2or at a point in the exhaust gas tract26arranged downstream of the introduction point E2, and in particular upstream of the component36b. If, for example, the comparison yields that the actual value is less than or equal to the target value, then a state adjusted in particular in the block174is maintained, in particular with regard to the operation of the fuel pump and the air pump, wherein the fuel pump is depicted inFIG.16by a block184and the air pump by a block186. If, for example, the actual value is greater than the target value, then in the block188, a control of the fuel pump is implemented, in particular by means of an electronic computer also described as a control device, and/or a control of the air pump is implemented in a block190, in particular via the control device, in particular continuously, such that the fuel pump or the air pump is changed with regard to its respective operation, in particular such that the actual value is reduced, until for example the actual value corresponds to the target value or is smaller than the target value.

In a block192, the quantity of the air of the mixture is determined, in particular measured, in particular via an air flow measurement. It is additionally depicted via an arrow194that the quantity of the fuel is determined, in particular measured. In a block196, the fuel-air ratio (y) is determined, in particular calculated, depending on the determined, in particular measured quantity of the air and depending on the determined, in particular measured or calculated quantity of the fuel. In particular, in the block196, an actual value of the fuel-air ratio of the mixture is determined, in particular calculated. In a block198, the actual value of the fuel-air ratio is compared with a second target value of the fuel-air ratio, wherein the second target value is for example 1.03. If the actual value of the fuel-air ratio corresponds to the target value of the fuel-air ratio, or if the actual value of the fuel-air ratio deviates from the target value of the fuel-air ratio only such that a difference between the actual value of the fuel-air ratio and the target value of the fuel-air ratio is in particular larger in magnitude or equal to a limit, then a current operation of the burner42, in particular of the fuel pump and of the air pump is maintained. If, however, the actual value of the fuel-air ratio deviates excessively from the target value of the fuel-air ratio, then, as depicted in particular by an arrow200, the air pump and/or the fuel pump is changed with regard to its respective operation, in particular by controlling the fuel pump or the air pump, in particular such that the difference between the actual value of the fuel-air ratio and the target value of the fuel-air ratio is at least reduced or even eliminated.

Finally, a block202depicts that the target value of the temperature T5is predetermined by or from the control device, in particular in the block182. As an alternative or in addition, the control device can predetermine or emit the target value of the fuel-air ratio, in particular in the block198.

FIG.18shows the swirl generation apparatus107of the burner42in a schematic and partially sectional perspectival view. The air conduits LK1and LK2can be seen particularly clearly fromFIG.18. The outer air conduit LK2is delimited outwards in the radial direction of the respective swirl chamber62or76by a first wall109, designed in particular as a solid body, of the swirl generation apparatus107, of which the wall109for example runs around completely in the peripheral direction of the respective swirl chamber62or76, and thus completely continuously surrounds the air conduit LK2. The outer air conduit LK2is delimited inwards in the radial direction of the respective swirl chamber62or76by a second wall111, in particular designed as a solid body, of the swirl generation apparatus107, of which the wall111preferably runs around completely in the peripheral direction of the respective swirl chamber62or76, and thus completely continuously surrounds the air conduit LK1. It can in particular be seen that the respective air conduit LK1or LK2per se is at least substantially annular in shape, and is thus formed as a ring conduit. The air conduit LK1is delimited inwards by a body113, designed in particular as a solid body, of the swirl generation apparatus107in the radial direction of the respective swirl chamber62or76, wherein—as is explained in more detail in the following—the body113is an air guidance body. For example, the swirl generation apparatus107is formed as one part, such that it is conceivable that the walls109and111are formed as one part with one another and/or the wall109and/or111is formed as one part with the body113.

The swirl generation apparatus107comprises an inner first swirl generation device115that comprises the first inner swirl generation elements94. In the exemplary embodiment shown inFIG.18, too, the swirl generation elements94are formed as guide vanes running in particular at least partially in a bend or in a bend shape, wherein the air flowing through the air conduit LK1, i.e., the first part of the air, is guided, diverted or deflected by means of the swirl generation elements94such that the turbulent first flow of the first part of the air can be or is caused by means of the swirl generation elements94, and thus by means of the swirl generation device115. It is in particular conceivable that the respective swirl generation element94is formed as one part with the wall109and/or111and/or as one part with the body113. It can be seen that the swirl generation elements94are arranged in the air conduit LK1, wherein the swirl generation elements94are arranged one after the other, and in particular spaced apart from one another in the peripheral direction of the respective swirl chamber62or76, and thus in the peripheral direction of the swirl generation apparatus107.

The swirl generation apparatus107comprises the swirl generation device115that has the swirl generation elements94and is arranged in the air conduit LK1and an outer, second swirl generation device117that has the second, outer swirl generation elements96and is arranged in the air conduit LK2. The swirl generation elements96are thus arranged in the air conduit LK2, wherein the swirl generation elements96are arranged one after the other, and in particular spaced apart from one another in the peripheral direction of the respective swirl chamber62or76, and thus in the peripheral direction of the swirl generation apparatus107. By means of the swirl generation elements96, i.e., by means of the swirl generation device117, the part of the air flowing through the air conduit LK2is diverted, deflected or guided such that the second turbulent flow of the second part of the air is caused. The respective swirl generation element96is preferably formed as one part with the wall109and/or111and/or as one part with the body113and/or as one part with the respective swirl generation element94, such that the swirl generation apparatus107is preferably formed as one part in total. In the exemplary embodiment shown inFIG.18, the respective swirl generation element96is also designed as a guide vane or air guide vane that is at least partially formed in a bend or in a bend shape, and thus has a bend-shaped course. The number of first, inner swirl generation elements94preferably lies in a range of six to eleven inclusive. The number of second, outer swirl generation elements96preferably lies in a range of eight to 14 inclusive.

The respective air conduit LK1or LK2per se, i.e., when considering the respective air conduit LK1or LK2without the swirl generation elements94or96, has a surface area also described as a passage cross-section, in particular upstream of the respective swirl generation device115or117and/or downstream of the respective swirl generation device115or117. As the respective air conduit LK1or LK2per se is presently annular in shape, the respective surface area is a respective surface area of a ring surface. It is preferably provided that the respective swirl generation elements94or96cover or block at least 20 percent and at most 60 percent of the surface area of the respective air conduit LK1or LK2per se arranged upstream and/or downstream of the respective swirl generation device115or117, whereby a particularly advantageous swirl generation can be obtained. The body113, which is a central body, is closed, and thus cannot be flowed through by air. The body113per se is additionally formed rotationally symmetrically with regard to its longitudinal axis or longitudinal central axis, which coincides with the axial direction of the respective swirl chamber62or76, and thus with the axial direction of the swirl generation apparatus107. In particular, the body113is presently designed as an in particular central and/or closed profile.

The respective swirl generation element94or96forms for example the angle β with the previously specified imaginary plane EB, the angle preferably lying in a range of 10 degrees to 45 degrees inclusive. It is further preferably provided that the respective swirl generation element94or96causes a deflection of the respective part of the air flowing through the respective air conduit LK1or LK2by a deflection angle that preferably lies in the range of 70 degrees to 90 degrees inclusive.

To obtain a particularly advantageous mixture formation, it is preferably provided that the swirl generation device115, in particular the swirl generation elements94, runs or is designed contrary to the swirl generation device117, in particular the swirl generation elements96, such that the first turbulent flow of the first part of the air has a first direction of rotation, in particular around the respective axial direction of the respective swirl chamber62or76, wherein the second turbulent flow of the second part of the air preferably has a second direction of rotation, in particular around the axial direction of the respective swirl chamber62or76, and wherein the first direction of rotation is contrary to the second direction of rotation or vice versa.

FIG.19shows a possible embodiment of the ignition device60for example designed as a spark plug in a schematic side view. It can be seen fromFIG.19that the ignition device60has several cooling ribs230protruding outwards in the radial direction of the ignition device60from a base body224of the ignition device60, of which the radial direction is depicted inFIG.19by a double arrow226and runs in parallel with the longitudinal extension direction of the ignition device60, and spaced apart from one another in the longitudinal extension direction of the base body224, of which the longitudinal extension direction is depicted inFIG.19by a double arrow228and coincides with the longitudinal extension direction of the ignition device60as a whole, by means of which cooling ribs the ignition device60can be cooled particularly advantageously.

It can be seen fromFIG.20that at least one of the cooling ribs230, preferably the respective cooling rib230, has through openings232that are preferably designed as holes and/or can be circular. The cooling ribs and in particular their spacing can be seen particularly clearly fromFIG.21.

FIG.23shows a section of a further embodiment of the burner42in a schematic sectional view. The burner42has the closing element132that can be moved relative to the outflow openings64and80and relative to the component74and relative to the component element82between the open position shown inFIG.12and the closed position shown inFIG.23. In the closed position, the outflow opening80is closed, i.e., fluidically blocked, by means of the closing element132, wherein the closing element132is at least partially arranged in the outflow opening80in the closed position. In the exemplary embodiment shown inFIG.23, the closing element132penetrates the outflow opening80and protrudes into the outflow opening64. As the outflow opening80is closed by means of the closing element132in the closed position and as the outflow opening80is arranged downstream of the outflow opening64in the flow direction of the air, i.e., the flow direction of the respective part of the air, no particles and no gases from the combustion chamber58can flow through the outflow opening80if the closing element132is in its closed position, such that, furthermore, no particles and no gases from the combustion chamber58can flow through the outflow opening64. Both the air supply path54and the fuel supply path46can thus be protected from contamination by gases and/or particles from the combustion chamber58.

According toFIG.12, the closing element132can, for example, be moved between the closed position and the open position along an element direction running in parallel with the axial direction of the respective swirl chamber62or76or coinciding with the respective axial direction of the respective swirl chamber62or76. According toFIG.22, the closing element132can be pivoted around a pivot axis SA running through a point of rotation between the closed position and the open position relative to the outflow openings64and80, and thus relative to the component74and relative to the component element82. An actuator234that can, for example, be electrically and/or pneumatically and/or hydraulically operated is assigned to the closing element132, the closing element232being able to be moved, in particular pivoted, between the closed position and the open position by means of the actuator. For this purpose, the actuator234is coupled in particular in a hinged manner with the closing element132via a lever arrangement236. For example, the actuator234can move, and thus shift, lever elements238and240of the lever arrangement236at least translationally, wherein the lever elements238and240can be at least indirectly or directly coupled with the closing element132in a hinged manner. Thus, for example, translational movements of the lever elements238and240are transformed into a pivot movement of the closing element132, whereby the closing element132can be pivoted between the closed position and the open position.

It can in particular be seen that the air chamber92is a supply chamber shared by the two swirl chambers62and76and also described as an air supply chamber, which is explained in more detail in the following.

It can be seen fromFIG.7that the burner42has a feeding conduit241that can be flowed through by the air and thus by the parts, the feeding conduit being around the components of the air supply path54. The air conduit241can be flowed through by the air along a flow direction depicted by a double arrow242inFIG.7and leads, in particular directly, into the air chamber92along the flow direction. For this purpose, the feeding conduit241has an exit opening244that can be flowed through by the air and thus by the two parts along the flow direction depicted by the double arrow242. The air flowing through the feeding conduit241along the flow direction can flow through the outflow opening244along the flow direction, and thus via the outflow opening244along the chamber flow direction—depicted by the double arrow242and also simply described as a flow direction—into the air chamber92, such that the feeding conduit241leads directly into the air chamber92along the chamber flow direction via the exit opening244. The air introduced into the air chamber92via the feeding conduit241can flow through the air chamber92along the respective axial direction of the respective swirl chamber62or76, and thus flow out of the air chamber92along the respective axial direction of the respective swirl chamber62or76in order to flow into the respective swirl chamber62or76. The air chamber92is thus an air supply chamber shared by the swirl chambers62and76, the swirl chambers62and76being able to be supplied with the parts of the air via the air chamber. This means that the first part of the air can flow out of the air chamber92, flow into the inner swirl chamber62and then flow through the swirl chamber62, and the second part of the air can flow out of the air chamber92, flow into the outer swirl chamber76and then flow through the outer swirl chamber76. The respective part of the air flows in the previously specified flow direction through the respective swirl chamber62or76, this respective flow direction being depicted by an arrow246inFIG.7. The respective flow direction depicted by the arrow246, in which the respective part of the air flows through the respective swirl chamber62or76, runs in parallel with the respective axial direction of the respective swirl chamber62or76or coincides with the respective axial direction of the respective swirl chamber62or76.

A first direction contrary to the flow direction depicted by the arrow246and running in parallel with the respective axial direction of the respective swirl chamber62or76or coinciding with the respective axial direction of the respective swirl chamber62or76is depicted inFIG.7by an arrow248. The two swirl chambers62and76are respectively at least partially, in particular at least substantially, at least more than half or presently completely overlapped by the air chamber92shared by the swirl chambers62and76in the first direction depicted by the arrow248. The air chamber92extends without interruption, i.e., uninterrupted, both along a second direction depicted by an arrow250inFIG.7and running in parallel with the respective flow direction depicted by the arrow246, and along a third direction depicted by a double arrow252inFIG.7and running perpendicular to the respective flow direction depicted by the arrow246and thus running perpendicular to the second direction. The burner42is thus a burner without a prechamber, free of a central prechamber, whereby a particularly advantageous preparation of the mixture in an installation space-, weight and cost-efficient manner can be represented in its particularly advantageous mixture preparation.

Finally,FIG.23exceptionally shows a further embodiment of the burner42in a schematic sectional view. In the further embodiment according toFIG.23, the injection element66has in particular exactly one exit opening70, which is formed or arranged on the axial end face146of the injection element66. The injection element66has an introduction element housing254designed in particular as a solid body and by which the exit opening70or completely forms or delimits. In other words, the exit opening70is for example formed in the introduction element housing254. The introduction element housing254can be flowed through by the fuel which can be provided by the injection element66via the exit opening70, in particular injected out of the injection element66.

In the embodiment inFIG.23, the injection element66has a valve element256presently designed as an umbrella valve, which can be moved, in particular along a movement direction depicted by a double arrow258inFIG.23, relative to the introduction element housing254, in particular translationally, between at least one introduction position and at least one blocked position. In the blocked position shown inFIG.23, the exit opening70is completely blocked, i.e., locked, by means of the valve element256, such that the injection element66does not provide fuel or the exit opening70cannot be flowed through by the fuel. In the introduction position, however, the valve element256releases the exit opening70, whereby the exit opening70can be flowed through by the fuel, and the injection element66provides the fuel, in particular injects the fuel out of the exit opening70.

In the exemplary embodiment shown inFIG.23, the introduction element housing254has two housing parts260and266, which are preferably designed as components formed separately from one another and connected to one another. The exit opening70is presently formed or delimited, in particular completely, by the housing part266, in particular designed in the housing part266. A support element268which can be moved with the valve element256relative to the introduction housing254is provided on the valve element256. For example, the valve element256and the closing element268are designed as components designed separately from one another and connected to one another. The injection element66additionally has a spring element270presently designed as a mechanical spring, in particular as a pressure spring. The spring element270is or can be supported along the movement direction depicted by the double arrow258, on the introduction element housing254on the one hand, in particular on the housing part266, and on the support element268on the other hand, in particular in each case directly. By moving the valve element256from the blocked position into the introduction position, the spring element270is tensioned, in particular compressed, whereby the spring element270provides a spring force at least in the introduction position. By means of the spring force, the valve element256can be moved from the introduction position into the blocked position, and in particular held in the blocked position. A particularly advantageous dosing of the fuel, also described as fuel dosing, can thus be obtained by means of the valve element256presently designed as an umbrella valve. As the spring force that can be or is provided by the spring element270acts at least indirectly, in particular directly, on the valve element56, which can be moved from the introduction position into the blocked position by means of the spring force, the valve element256is a spring-loaded valve element, which is presently designed as a spring-loaded umbrella valve.

The injection element66has a valve seat272that is presently, in particular directly, formed by the introduction element housing254, in particular by the housing part266. The valve element256has a seat surface274corresponding to the valve seat272, the seat surface also being described as a sealing surface and presently being formed, in particular directly, by the valve256. In the blocked position, the valve element256sits via its seat surface274, in particular directly, on the corresponding valve seat272, such that the seat surface274touches the corresponding valve seat272, in particular directly. In the exemplary embodiment shown inFIG.23, the valve seat272or the sealing surface274is designed in the shape of a cone or truncated cone, and thus has the shape of a cone, of which the longitudinal central axis runs in parallel with the movement direction depicted by the double arrow258, or coincides with the movement direction depicted by the double arrow258.

When viewed for example in combination withFIG.14, it can be seen that the exit opening70is arranged downstream of the swirl generation elements96, such that the fuel can in particular be dosed, in particular dosed in, as required by means of the valve element256downstream of the swirl generation device115and117.

If the burner42is inactive and the internal combustion engine12is running, the valve element56is in the blocked position, such that no gas, e.g., motor exhaust gas or burner exhaust gas, in particular from the combustion chamber58, and dirt particles contained therein can penetrate the exit opening60and thus reach the fuel supply path46, which could lead to deposits there, and consequently to throttle losses in the fuel dosing, such that a particularly advantageous mixture preparation can be guaranteed even over a particularly long lifespan of the burner42.

LIST OF REFERENCE CHARACTERS

10drive device12internal combustion engine14engine block16Cylinder18Tank20low-pressure pump22high-pressure pump24suction tract26exhaust gas tract28exhaust gas turbocharger30compressor32Turbine34Shaft36a-dComponent38dosing device40mixing chamber42Burner44Flame46fuel supply path48fuel conduit50valve element52electronic computer54air supply path55valve element56Pump58combustion chamber60ignition device62inner swirl chamber64first outflow opening66injection element68Conduit70exit opening72fuel jet74component76outer swirl chamber78dividing wall80second outflow opening82component element84atomizing lip86lateral surface on the internal periphery88anti-recirculation plate90through opening92supply chamber94swirl generator96swirl generator98through opening100perforated disc102removal opening104arrow106turbulent flow107swirl generation apparatus108through opening109wall110closing device111wall112closing element113body114opening cross-section115swirl generation device116chamber element117swirl generation device118lateral surface on the internal periphery120chamber part122chamber part124clearance126dashed line128exit cone130double arrow132closing element134thread136electrode137fuel pump138piston140valve142spring144ball146end face148lateral surface150dashed line152tube154venturi nozzle155head156swirl slit158vortex body160secondary filter162primary filter164block166block168arrow170block172block174block176block178block180arrow182block184block186block188block190block192block194arrow196block198block200arrow202block224base body226double arrow228double arrow230cooling rib232through opening234actuator236lever arrangement238lever element240lever element241feeding conduit242double arrow244exit opening246arrow248arrow250double arrow252double arrow254introduction element housing256valve element258double arrow260housing part266housing part268portion element270spring element272valve seat274sealing surfaceE1introduction pointE2introduction pointV1connection pointV2connection pointT1partT2partT partK end edgeLK1air conduitLK2air conduitK1annular surfaceK2annular surfaceTB partDi outer diameterDa outer diameterW wall regionR radiusα angle11lengthd1inner diameterd2inner diameterL1longitudinal regionβ angleEB planeLW longitudinal regionTBK partial regionLBE longitudinal region