Jet burner apparatus

Abstract

The present invention relates to a jet burner apparatus (100) for combusting at least one fuel with at least one oxidising agent, wherein the jet burner apparatus (100) comprises a central longitudinal axis (102) and a main flow direction (104) which is at least approximately parallel to the central longitudinal axis (102), and wherein the jet burner apparatus (100) comprises the following: a flame tube (106) and a guide tube (122) which is arranged inside the flame tube (106); at least one flow duct (124), through which the at least one fuel and the at least one oxidising agent can flow and which is arranged radially outside the guide tube (122) with respect to the central longitudinal axis (102); at least one injection apparatus (130, 162) having a plurality of injection openings for supplying the at least one fuel into the at least one flow duct (124); and at least one swirl apparatus (126, 136) for swirling fuel and / or oxidising agent by means of a plurality of swirl bodies (128, 146); wherein the at least one injection apparatus (130, 162) is arranged in the at least one flow duct (124) such that the oxidising agent flows around the at least one injection apparatus (130, 162) at least approximately on all sides; and wherein the at least one swirl apparatus (126, 136) is arranged upstream or downstream of the at least one injection apparatus (130, 162), with respect to the main flow direction (104).

Description

[0001] Jet burner device

[0002] The present invention relates to a jet burner device for combustion of at least one fuel with at least one oxidizer. Furthermore, the present invention relates to a combustion chamber device with a jet burner device, as well as to a thermal exhaust gas purification system and a gas turbine with a jet burner device.

[0003] Increasingly strict legal requirements, for example in thermal exhaust air purification systems, require a trend towards ever lower NO x -values, which are hardly achievable with the existing burner devices or burners, since currently very high combustion chamber temperatures prevail at low mass flow. In addition, with classic low-NO xIn jet burners, the combustion jet penetrates deep into the flow area behind the burner head, creating larger recirculation areas to the sides of this jet. Consequently, attempts are made to achieve rapid homogenization of fuel and oxidizer through complex injection geometry, but this quickly leads to high investment costs for larger burners. After all, current burners are not designed for the use of hydrogen.

[0004] The present invention is based on the object of creating a jet burner device of the type mentioned above, which is simple and inexpensive to manufacture, achieves a uniform and rapid mixing of fuel and oxidizer, lower NO x emissions and / or is at least prepared for the use of hydrogen / methane mixtures.

[0005] This object is achieved according to the invention in that a jet burner device for the combustion of at least one fuel with at least one oxidizer is provided, wherein the jet burner device has a central longitudinal axis and a main flow direction at least approximately parallel to the central longitudinal axis, and wherein the jet burner device comprises the following: a flame tube and a guide tube arranged within the flame tube, at least one flow channel through which the at least one fuel and the at least one oxidizer can flow and which, with respect to the central longitudinal axis, is arranged radially outside the guide tube, at least one injection device with a plurality of injection openings for supplying the at least one fuel into the at least one flow channel, and at least one swirl device for swirling the fuel and / or oxidizer with a plurality of swirl bodies,wherein the at least one injection device is arranged in the at least one flow channel such that the oxidizer flows around the at least one injection device, and wherein the at least one swirl device is arranged upstream or downstream of the at least one injection device with respect to the main flow direction.

[0006] The advantage of the jet burner device according to the invention is that, compared to conventional jet burner devices, significantly lower NO x -values ​​can be achieved with more uniform combustion. The twisting increases the local velocity and thus the shear layer and turbulence. This increases the mixing of fuel and oxidizer, resulting in an increase in the premixing effects during combustion or thermal oxidation, which leads to a reduction in NO xemissions while simultaneously increasing burnout. The rotation also increases recirculation in the combustion chamber, causing flue gas with reduced oxygen content to flow back into the combustion zone, which also leads to a reduction in NO x emissions. This allows the overall combustion chamber temperature to be reduced while simultaneously reducing NO x emissions can be achieved.

[0007] The rotation of the oxidizer and fuel creates a recirculation area inside the jet burner device, which forces the jet flow outwards. If installed in a combustion chamber with a larger diameter or greater width, the rotation also creates recirculation radially to the side of the jet burner device. This widens the flow downstream of the jet burner device, which results in better mixing, including with secondary air, and a more homogeneous temperature profile, etc., and in the reduction of cold flows, among other things, along the combustion chamber wall. The inventive design of the jet burner device and its operation thus makes it possible to achieve an increased temperature for the entire fluid, i.e. the mixture of oxidizer and fuel, essentially directly downstream of the jet burner device.

[0008] In applications involving thermal exhaust air purification, i.e., the oxidation of any reactive substances dissolved in the oxidizer, an increase in the overall fluid flow downstream of the jet burner device can be achieved, and the entire system can be operated at a low reactor temperature, since any cold air paths with reduced exhaust air purification reactions are greatly reduced. As a result, the dissolved substances can be cleaned at a reduced reactor temperature, resulting in fuel savings and simultaneously reduced NO. x -emissions.

[0009] Jet burners are essentially high-velocity, high-turbulence burners or burner stages. These can be operated with premixed, unpremixed, or postmixed fuel and oxidizer. Different types and effects for flame stabilization and emission reduction are known.

[0010] The low emission values ​​result from jet burner devices with fuel injection into the so-called jet, ie the flow in at least one flow channel, due to the higher flow velocity, which at the same time increases the corresponding turbulence and thus causes better mixing of fuel and oxidizer.

[0011] The velocity distribution in the jet stream in the at least one flow channel is ideally such that the oxidation is stabilized by the turbulent flame velocity being greater than or equal to the flow velocity and thereby providing the mixture of fuel and oxidizer with sufficient energy for oxidation.

[0012] Typically, jet burner devices with direct injection of the fuel into the jet stream in at least one flow channel have a central flame which in particular has velocity components in the direction of the central longitudinal axis. Although such jet burner devices have very low emission values ​​at the correct load point, i.e. at the optimally controlled load point, they also tend to be unstable. Stabilization is therefore preferably achieved via recirculation regions, usually around the flame. It should also be understood that the central longitudinal axis is preferably an axis of symmetry along the jet burner device and that the main flow direction, which is in particular parallel thereto, is an axial direction, i.e. with regard to the main flow direction, any compression is disregarded unless explicitly stated otherwise.

[0013] The at least one flow channel, which preferably runs parallel to the main flow direction, is preferably delimited radially outwardly by the flame tube with respect to the central longitudinal axis. Radially inwardly, the at least one flow channel is preferably delimited by a guide tube, which together form a circular ring-shaped cross-section. However, it is also conceivable for the flow channel not to completely enclose the flame tube, whereby, for example, a substantially C-shape is formed in cross-section, or for the flow channel to be formed in cross-section from a plurality of circular ring sectors, which can be regarded as subunits of the flow channel. The wall thickness of the flame tube and the guide tube can be the same or different.

[0014] Preferably, the flame tube and the guide tube, which is arranged within the flame tube, are aligned parallel to each other. However, it is also conceivable for both tubes to be designed such that they converge toward each other downstream relative to the main flow direction, i.e., either both tubes form an angle greater than zero with the central longitudinal axis, or only one of them forms an angle greater than zero. This reduces the cross-section of the flow channel downstream. Such a taper can also affect only a section of the flow channel.

[0015] It is advantageous if the flame tube is formed with at least one diffuser at its downstream end with respect to the main flow direction, wherein the diffuser can comprise several segments. The widening of the diffuser slows the flow and builds up static pressure. As a result, the diffuser promotes the recirculation of the internal flow. In addition, the geometry of the flame tube is stabilized due to the diffuser; for example, the corresponding end of the flame tube has increased rigidity compared to a cylindrical design. The diffuser preferably causes a portion of the oxidizer that flows along the outside of the flame tube to open up. Opening up or expanding this portion of the oxidizer can be particularly important for rapid mixing of fuel and oxidizer, which preferably leads to better exhaust air purification.

[0016] In one embodiment of the invention, it is provided that the at least one flow channel is annular. It should be understood in this regard that, as previously described, the annular shape of the flow channel can also be formed by a plurality of annular sectors or segments, i.e., the channel can also be interrupted in at least one section with respect to its cross-section.

[0017] In one embodiment of the invention, it is provided that a flow-through cross-sectional area of ​​the at least one flow channel is constant or decreases along the main flow direction.

[0018] In one embodiment of the invention, the flow-through cross-sectional area of ​​the at least one flow channel, relative to the main flow direction, is constant upstream of the at least one injection device and reduced downstream of the at least one injection device. However, it is also possible for the flow-through cross-sectional area to be expanded upstream of the at least one injection device in order to improve the flow into the flow channel.

[0019] This has the advantage of accelerating the fluid flow, thereby stabilizing the flow, resulting in improved mixing through a reduction in separation zones, higher velocities, and higher turbulence. As a result, combustion with higher burnout and lower emissions is achieved.

[0020] The acceleration of the flow at the level of the injection device can also serve as a dynamic flame arrester.

[0021] It is advantageous if the flow-through cross-sectional area of ​​the at least one flow channel, relative to the main flow direction, is reduced several times, preferably in two stages, upstream of the at least one injection device, has a constant flow-through cross-sectional area in the region of the at least one injection device, and is reduced again at least once downstream of the at least one injection device. It is preferred if the ratio of the length of the flow channel upstream of the at least one injection device to the width of the flow-through cross-sectional area is at least 0.5.

[0022] In one embodiment of the invention, it is provided that the at least one injection device is designed in the shape of a ring tube.

[0023] Preferably, the injection device has a round or square cross-section, wherein round or roundish cross-sections should include circular, oval and elliptical cross-sections.

[0024] In one embodiment of the invention, it is provided that the swirl device is fastened to the at least one injection device or is spaced apart from the at least one injection device.

[0025] It is advantageous if the swirl bodies of the swirl device are in the form of straight or curved plates; however, wing profiles or the like are also conceivable.

[0026] In one embodiment of the invention, it is provided that the at least one injection device has first injection openings whose central axes point at least approximately in the main flow direction.

[0027] As a result, the fuel and / or oxidizer is injected into the burner chamber at least approximately parallel to the main flow direction, with the central axis of an injection opening being understood to be its main outflow direction.

[0028] However, it is also conceivable that the center axes of the injection openings and the main flow direction enclose an angle greater than zero, since it may be advantageous not to align the injection openings in the direction of the main flow direction, but rather to specify an angle relative to the main flow direction depending on other adjustable elements of the burner device, for example, to optimize the mixing of injected fuel and flowing oxidizer. In one embodiment of the invention, at least one of the first injection openings has an injection lance projecting in the main flow direction.

[0029] It is advantageous that injection nozzles at the injection openings can increase the exit velocity of the fuel from the injection opening depending on their profile or geometry along the central axis.

[0030] In one embodiment of the invention, it is provided that the at least one injection device has second injection openings, the central axes of which each enclose an angle between 0 degrees and 90 degrees with the main flow direction.

[0031] In particular, it may be advantageous if the second injection openings enclose an angle other than zero with the first injection openings.

[0032] Additional injection openings, which are not aligned in the main flow direction, preferably enable local premixed combustion to occur or at least increase the local mixing of fuel and oxidizer, thereby accelerating the homogenization of the mixture overall in addition to increasing the available fuel volume.

[0033] In a further possible embodiment of the invention, it can be provided that the first and second injection openings can be controlled independently of one another, i.e., either the first, the second, or the first and second injection openings can be activated or deactivated, thereby allowing the fuel flow rate to be adjusted. Furthermore, it is possible for different fuels to be injected via the first and second injection openings. The first and second injection openings of the at least one injection device can be arranged alternately or in groups.

[0034] In one embodiment of the invention, a first and a second injection device are arranged in the at least one flow channel, wherein the first and second injection devices are arranged at the same height or offset from one another with respect to the main flow direction. This makes it possible to mix either a larger amount of fuel or different fuels with the flowing oxidizer within a flow channel.

[0035] In one embodiment of the invention, it is provided that the jet burner device has a first and a second flow channel, wherein the first flow channel is arranged radially inward of the second flow channel with respect to the longitudinal axis, and wherein the second flow channel is delimited radially outward by the flame tube with respect to the central longitudinal axis.

[0036] Thus, on the one hand, the first flow channel is bounded radially inward by a guide tube, and on the other hand, the two flow channels are separated from each other by another guide tube. Preferably, the flame tube and the two guide tubes are aligned parallel to each other.

[0037] In one embodiment of the invention, it is provided that a first injection device is arranged in the first flow channel and a second injection device is arranged in the second flow channel.

[0038] This allows either more fuel to be injected into the total of the flow channels or different fuels to be injected into each injection device.

[0039] In one embodiment of the invention, it is provided that a swirl device is arranged in the first and / or second flow channel, which, with respect to the main flow direction, is arranged upstream of the first and / or second injection device.

[0040] The advantage of this is that by condensing the respective flowing oxidizer portion by means of the swirl device, the mixing of fuel and oxidizer can be accelerated and improved.

[0041] In one embodiment of the invention, it is provided that the jet burner device comprises a plurality of injection lances for injecting at least one fuel, that an injection device and a swirl device are arranged in the first flow channel, and that the injection lances are arranged in the second flow channel, wherein the swirl device is arranged upstream of the injection device with respect to the main flow direction.

[0042] The same fuel or different fuels can be fed into the second flow channel via the injection lances.

[0043] In one embodiment of the invention, it is provided that the jet burner device comprises a plurality of injection lances for injecting at least one fuel, which are arranged at least partially radially within the guide tube.

[0044] Fuel or a mixture of fuel and oxidizer can preferably be injected via the injection lances. The oxidizer flows around or surrounds the outer surface of the injection lances.

[0045] In one embodiment of the invention, it is provided that the jet burner device comprises a central burner stage, wherein the central burner stage is arranged within the guide tube, wherein the central burner stage comprises the following: a flow channel, and a swirl device arranged in the flow channel.

[0046] A beneficial feature of a central burner stage is that an additional axially swirled oxidizer component is supplied to the combustion chamber.

[0047] In one embodiment of the invention, it is provided that the central burner stage further comprises at least one injection device, wherein the at least one injection device is arranged at least partially downstream of the swirl device with respect to the main flow direction, and wherein the injection device of the burner stage comprises a plurality of differently designed injection openings.

[0048] This allows either the same fuel or a different fuel to be injected, which is quickly and efficiently mixed with a wired oxidizer component by a swirl device positioned upstream with respect to the main flow direction.

[0049] In one embodiment of the invention, it is provided that the central burner stage further comprises an orifice plate with a plurality of orifice openings for fuel and / or oxidizer, wherein the orifice plate is arranged downstream of the injection device with respect to the main flow direction, and wherein the orifice plate comprises a plurality of differently designed orifices.

[0050] The advantage of such a central burner stage is that significantly lower NOx levels can be achieved with more uniform combustion compared to conventional pilot stages. More uniform and faster mixing of fuel and oxidizer accelerates the corresponding thermal reactions, thereby lowering the combustion chamber temperature.

[0051] In particular, the use of the orifice plate preferably promotes recirculation, accelerates the injected fuel, and / or enables improved mixing of fuel and oxidizer. As a result, as already mentioned, combustion can preferably take place at lower temperatures, which in particular reduces NOx emissions.

[0052] It is particularly advantageous if two adjacent apertures of the aperture plate and / or two adjacent injection openings of the injection device are designed and / or arranged differently in shape, dimensioning and / or their orientation relative to one another and / or relative to the main flow direction or central longitudinal axis.

[0053] Furthermore, it is advantageous if the orifice plate is arranged on the injection device, ie in the immediate spatial proximity with respect to the main flow direction, but without preventing the flow of the oxidizer around the injection device through the orifice opening of the orifice plate.

[0054] In one embodiment of the invention, it is provided that the flame tube is arranged in a jacket tube in such a way that a bypass flow channel is formed between the flame tube and the jacket tube, through which part of the oxidizer can flow.

[0055] Diverting a portion of the oxidizer flow into the bypass flow channel preferably accelerates the rapid mixing of the fuel and the oxidizer. In one embodiment of the invention, at least one bypass injection device for injecting fuel is arranged in the bypass flow channel between the flame tube and the jacket tube.

[0056] The bypass injection device mixes fuel with a portion of the oxidizer in the bypass flow channel. Thus, the bypass injection enhances combustion. The fuel injected via the bypass injection device can be the same fuel as the fuel injected via the other injection devices, or it can be a different fuel.

[0057] In one embodiment of the invention, it is provided that at least one bypass swirl device for condensing the oxidizer portion is arranged in the bypass flow channel between the flame tube and the jacket tube, wherein the bypass injection device is arranged downstream of the at least one bypass swirl device with respect to the main flow direction.

[0058] This promotes the mixing of the fuel injected through the bypass injection device and the oxidizer portion flowing through the bypass flow channel. Furthermore, the fuel from the bypass injection device is injected into the wired oxidizer portion, resulting in improved mixing.

[0059] In one embodiment of the invention, it is provided that, with respect to the main flow direction, a constriction element is arranged at the upstream end of the jacket tube for adjusting the oxidizer portion flowing through the bypass flow channel.

[0060] The constriction element can be used to adjust the amount of oxidizer flowing through the bypass flow channel. The constriction element is preferably designed as a tubular ring with a rectangular cross-section. For improved distribution of the oxidizer, the upstream surface of the constriction element can also be profiled. It is also conceivable that additional fuel could be injected into the bypass flow channel via the constriction element.

[0061] In one embodiment of the invention, it is provided that the oxidizer enters the jet burner device at a speed of 50 m / s to 70 m / s, in particular 60 m / s.

[0062] The object is further achieved according to the invention by the use of a jet burner device as described above. The jet burner device is used for the combustion of at least one fuel with at least one oxidizer, in particular for the purification of a contaminated gas stream, preferably a gas stream contaminated with organic substances. Such a jet burner device is thus used in particular for exhaust gas purification and / or exhaust air purification.

[0063] The object can further be achieved according to the invention by a combustion chamber system having at least one combustion chamber and at least one jet burner device as described above, wherein the jet burner device is connected at its outer circumference to a bottom of the combustion chamber.

[0064] In one embodiment of the invention, it is provided that the jet burner device is inserted into the combustion chamber device and is fastened outside the combustion chamber device, wherein an annular gap is formed between the outer circumference of the jet burner device and the combustion chamber device, through which a part of the oxidizer can flow.

[0065] As a result, particularly in a burner device with a jacket tube, a portion of the oxidizer flows through the flow channel between the flame tube and the jacket tube, and through the annular gap between the jacket tube and the corresponding insertion area of ​​the combustion chamber device. This annular gap may be asymmetrical due to manufacturing tolerances or thermal deformation. The provision of a jacket tube nevertheless ensures a symmetrical flow from the flame tube to the opening of the combustion chamber device.

[0066] According to the invention, the object can also be further achieved by a thermal exhaust gas purification system with a jet burner device as described above. According to the invention, the object can also be further achieved by a gas turbine device with a jet burner device as described above.

[0067] The object can further be achieved according to the invention by a method for operating a jet burner device according to the invention, which comprises the following steps:

[0068] Supplying oxidizer to a burner head to form at least one oxidizer stream;

[0069] Supplying fuel to an injection device of the burner head; and injecting the fuel by means of the injection device of the burner head into the at least one oxidizer stream

[0070] Further advantages and features of the jet burner device according to the invention are the subject of the following description and the drawings of exemplary embodiments.

[0071] The figures show:

[0072] Fig. 1 is a schematic perspective view of a first embodiment of a jet burner device according to the invention;

[0073] Fig. 2 is a first schematic perspective longitudinal sectional view of the first embodiment of Fig. 1;

[0074] Fig. 3 is a schematic longitudinal sectional view of the first embodiment of Fig. 1;

[0075] Fig. 4 is a schematic perspective longitudinal sectional view of a second embodiment of a jet burner device according to the invention;

[0076] Fig. 5 is a schematic perspective view of a first embodiment of a burner stage;

[0077] Fig. 6 is a schematic perspective sectional view of the first embodiment of Fig. 5; Fig. 7 is a schematic plan view of the first embodiment of Fig. 5;

[0078] Fig. 8 is a schematic perspective view of a third embodiment of a jet burner device according to the invention;

[0079] Fig. 9 is a schematic perspective longitudinal sectional view of the third embodiment of Fig. 8;

[0080] Fig. 10 is a schematic longitudinal sectional view of part of a combustion chamber device according to the invention with an inserted jet burner device;

[0081] Fig. 11 is a schematic perspective view of a second embodiment of a burner stage;

[0082] Fig. 12 is a schematic side view of the second embodiment of a burner stage from Fig. 11;

[0083] Fig. 13 is a schematic perspective view of a third embodiment of a burner stage;

[0084] Fig. 14 is a schematic perspective view of a fourth embodiment of a burner stage;

[0085] Fig. 15 is a schematic perspective view of a fifth embodiment of a burner stage;

[0086] Fig. 16 is a schematic plan view of the fifth embodiment of a burner stage from Fig. 15;

[0087] Fig. 17 is a schematic perspective partial view of a sixth embodiment of a burner stage; and Fig. 18 is a schematic perspective partial view of a seventh embodiment of a burner stage;

[0088] Identical or functionally equivalent elements are provided with the same reference numerals in all figures.

[0089] Fig. 1 shows a schematic perspective view of a first embodiment of a jet burner device 100 according to the invention, which serves to burn at least one fuel with at least one oxidizer.

[0090] The jet burner device 100 is designed to be substantially rotationally symmetrical about a central longitudinal axis 102, with a main flow direction 104 running at least approximately parallel to the central longitudinal axis 102.

[0091] The jet burner device 100 comprises, as components visible in Fig. 1, a flame tube 106, at the downstream end of which a diffuser 108 is formed, wherein it can also be seen in Fig. 1 that the cross section of the flame tube 106 tapers in a section 110, whereby the flow is accelerated.

[0092] The flame tube 106 is surrounded by a jacket tube 112, whereby an annular bypass flow channel 114 is formed between the flame tube 106 and the jacket tube 112, in which a bypass swirl device 116 with a plurality of swirl plates 118 for swirling the oxidizer portion flowing through the bypass flow channel.

[0093] At the upstream end of the jacket tube 112, a constriction element 120 is arranged, with which the proportion of the oxidizer that is to flow through the bypass flow channel 114 can be adjusted.

[0094] Fig. 2 shows a first schematic perspective longitudinal sectional view of the first embodiment from Fig. 1, whereas Fig. 3 shows a purely schematic longitudinal sectional view. In Figs. 2 and 3, it can be seen that a guide tube 122 is arranged within the flame tube 106, whereby a flow channel 124 is formed between the flame tube 106 and the guide tube 122, through which a portion of the oxidizer can flow.

[0095] Within the flow channel 124, a swirl device 126 with a plurality of swirl plates 128 and an annular tube-shaped injection device 130 are arranged, wherein the annular tube-shaped injection device 130 is arranged downstream of the swirl device 126.

[0096] As a result, the flowing portion of the oxidizer is diverted only once for condensation, allowing the flow velocity to be used almost unchanged for mixing with the fuel. This design optimizes fuel injection, ideally resulting in lower pressure losses and / or lower emissions.

[0097] Furthermore, a central burner stage 132 is arranged within the guide tube 122, which comprises an injection device 134 and a swirl device 136. The injection device 134 with injection openings 138 is tubular and aligned parallel to the guide tube 122, so that an annular, central flow channel 140 is formed between the guide tube 122 and the injection device 134.

[0098] The cross-section of the guide tube 122 increases once in the area of ​​the swirl device 126 and once again after the injection device 130. Correspondingly, in section 110 of the flame tube 106, its inner radius is reduced at the level of the swirl device 126 and once again after the injection device 130. Overall, the flow within the flow channel 124 is thereby accelerated in two stages.

[0099] However, it is also conceivable that the cross-sectional area of ​​the flow channel 124 through which the fluid can flow is reduced several times, preferably in two stages, upstream of the injection device 130.

[0100] Fig. 4 shows a schematic perspective longitudinal sectional view of a second embodiment of a jet burner device 100 according to the invention. In contrast to the first embodiment of Figs. 1 and 2, the guide tube 122 has a constant cross-section along the main flow direction 104.

[0101] In addition, the central burner stage 132 within this guide tube 122 comprises, in addition to the injection device 134 and the swirl device 136, a further, annular tube-shaped injection device 142, which is arranged downstream of the swirl device 136, and an orifice plate 144, which is arranged downstream of the annular tube-shaped injection device 142.

[0102] The interaction of the swirl device 136, the injection device 142 and the orifice plate is explained in more detail below in connection with Figs. 5 to 8.

[0103] Figures 5 to 7 show a first embodiment of a central burner stage 132 in a schematic perspective view and sectional view, as well as in a schematic plan view.

[0104] In Figs. 5 to 7, the central burner stage 132 is shown within the swirl device 126 and the injection device 130 of the flow channel 124, without being separated from the guide tube 122.

[0105] It can be seen that both the swirl plates 128 of the swirl device 126 and the swirl plates 146 of the swirl device 136 receive the injection device 130 and the injection device 142, respectively, at least partially at their respective downstream edges.

[0106] The swirl plates 128 and the swirl plates 146 may differ in size and also have a different angle of inclination relative to the main flow direction 104, whereby the respective oxidizer portion flowing through is wired to a different extent.

[0107] The orifice plate 144 is connected to the injection device 134 via webs 148 and is thus fixed in its position.

[0108] The aperture plate 144 has circular apertures 150 and slotted apertures 152, which are arranged alternately in the circumferential direction. The different geometries of the apertures 150, 152 create different zones on the aperture plate 144, which preferably stabilize each other.

[0109] Fuel is injected through the elongated hole-shaped apertures 152 from two injection openings 154 of the injection device 142, whereas fuel is injected through the circular apertures 150 from only one injection opening each.

[0110] Due to the different opening shapes of the orifice plates 150, 152 within an orifice plate 144, different combustion types can occur alongside each other. While the circular orifice plates 150 with an associated injection orifice 154 result in richer combustion, the elongated orifice plates 152 optimally produce leaner combustion, which in turn is stabilized by the richer combustion.

[0111] The two injection openings 154, which supply fuel into the combustion chamber through a slot-shaped aperture 152, are preferably offset radially relative to a longitudinal center axis of the slot-shaped aperture 152, relative to the central longitudinal axis 102.

[0112] This can have the advantage that the burner flame or combustion is stabilized in the radially outer region of the orifice plate 144. This can also be due to the fact that the radially offset arrangement of the slotted orifice 152 and the two injection openings 154 on the radially inner long side of the slotted orifice results in a larger flow of the oxidizer, i.e., hotter flow paths are created at the slotted orifice 152 on the radially outer long sides, while the cooler flow paths are preferentially formed radially inward.

[0113] In other words, it is particularly advantageous if the center point of the corresponding apertures 150, 152 or their center axis, relative to the circumferential direction of the aperture plate 144, is arranged radially further inward than the center point of the associated injection opening or openings 154, because this results in a stable flame at the outer edge of the aperture plate 144.

[0114] The same or different fuel can be injected or supplied via the injection devices 130, 134, 142.

[0115] 8 and 9 show a schematic perspective view and a schematic perspective longitudinal sectional view of a third embodiment of a jet burner device 100 according to the invention.

[0116] Compared to the second embodiment shown in Fig. 4, the jet burner device 100 in Figs. 8 and 9 has an annular tube-shaped bypass injection device 156, which is arranged downstream of the bypass flow channel 114.

[0117] Furthermore, the jacket tube 112 is surrounded by a further jacket tube 158, whereby a further bypass flow channel 160 is formed, through which a part of the oxidizer can flow.

[0118] In addition, a further, annular tube-shaped injection device 162 is arranged within the flow channel 124, which is arranged between the injection device 130 and the guide tube 122.

[0119] In addition, the jet burner device shown in Figs. 8 and 9 comprises a plurality of injection lances 164, via which additional fuel can be supplied to defined locations of the jet burner device in order to influence the combustion.

[0120] Fig. 10 shows a schematic longitudinal sectional view of a part of a combustion chamber device 200 according to the invention with an inserted jet burner device 100.

[0121] The jet burner device 100 is inserted into the combustion chamber device 200 and secured outside the combustion chamber device 200. An annular gap 204, through which a portion of the oxidizer can flow, is formed between the outer circumference of the jet burner device 100 and a combustion chamber section 202 of the combustion chamber device 200. This annular gap 204 can be asymmetrical due to manufacturing tolerances or thermal deformation. By providing a jacket tube 112, a symmetrical flow from the flame tube 106 to the opening of the combustion chamber device 200 nevertheless prevails.

[0122] 11 and 12 show a second embodiment of a burner stage 132, which differs from the first embodiment in that the burner stage has a first orifice plate 166, which is arranged downstream of the inner, annular tubular injection device 142 (hereinafter referred to as first injection device 142), and a second orifice plate 168, which is arranged downstream of the outer annular tubular injection device 130 (hereinafter referred to as second injection device 130).

[0123] In addition, the burner stage 132 in Figs. 11 and 12 does not have a central injection device 134 with injection openings 138. Instead, an inner circular disk 169 is arranged centrally.

[0124] The first aperture plate 166 is divided into four equal segments 170, which are arranged spaced apart from one another with respect to the circumferential direction of the first aperture plate 166.

[0125] The second aperture plate 168 is divided into five equal segments 172, which are arranged spaced apart from one another with respect to the circumferential direction of the second aperture plate 168.

[0126] The segments 170 and 172 are preferably separated from each other in the region of the elongated aperture 152.

[0127] It is also conceivable for the first aperture plate 166 to be divided into more than four segments 170 or fewer than four segments 170, whereby the segments 170 of the first aperture plate 166 may be the same or different from one another. The same applies analogously to the second aperture plate 168, which may also be divided into more or fewer than five segments 172, whereby these segments 172 may also be the same or different. Due to the decoupled arrangement of the segments 170 and 172, less thermal expansion occurs overall. In addition, less waste material is generated during the production of the comparatively smaller segments 170, 172 than during the production of a continuous first or second aperture plate 166, 168.

[0128] In addition, more connections 174 are required to fasten the segments 172, 174, which improves the fixation of the first and second aperture plates 166, 168 and allows a failure of a single connection 174 to be better compensated.

[0129] In Figs. 11 and 12, the particularly preferred embodiment of the connections 174 can also be seen.

[0130] In this particularly preferred embodiment of the connections 174, the connections 174 each comprise a screw 176, a nut 178 and a spacer 180 which is sleeve-shaped.

[0131] Preferably, each segment 170, 172 is attached to the first and second injection devices 142, 130, respectively, by two or more pairs of connections 174, wherein the connections 174 of the individual pairs are arranged on opposite sides of the injection devices 142, 130.

[0132] The nuts 178 are attached, preferably welded, to the sides of the first and second injection devices 142, 130, respectively.

[0133] The spacers 180, which are preferably replaceable, allow the desired distance between the injection device and the orifice plate to be adjusted. This also allows the oxidizer flow around the injection devices 142, 130 and through the orifice plates 166, 168 to be adjusted.

[0134] The spacing of the orifice plates 166, 168 and the lateral fastening of the nuts 178 prevent weld seams or weld spots on the downstream, hot surface of the injection devices 142, 130. The screws 176 are screwed into the corresponding nut 178 to fasten the respective segment 170, 172. The bore provided for the respective connection 174 in the orifice plates 166, 168 can additionally have a thread corresponding to the screw 176.

[0135] Fig. 13 shows a third embodiment of a burner stage 132, which differs from the second embodiment in Figs. 11 and 12 in the manner of fastening the segments 170, 172 to the respective injection device 142, 130.

[0136] In the third embodiment, the connections 174 are also arranged in pairs on opposite sides of the first and second injection devices 142, 130, respectively.

[0137] In the third embodiment, the connections 174 also comprise a screw 176, a nut 178 and a sleeve-shaped spacer 180.

[0138] Each screw 176 of a connecting pair engages through one of the segments 170, 172 into an associated U-shaped bracket 182, which is guided upstream against the first or second injection device 142, 130 and at least partially encompasses them. The two screws 176 are secured to the associated U-shaped bracket 182 by means of the respective nut 178. The two associated spacers 180 of the connecting pair are arranged between the ends of the U-shaped bracket 182 and the corresponding segment, thereby adjusting the distance between this segment and the first or second injection device 142, 130.

[0139] The brackets 182 can be fixed to the respective injection device 142, 130, for example by one or more welding points.

[0140] Alternatively, the brackets 182 are at least partially movable along the circumferential direction of the first and second injection devices 142, 130, respectively, thereby providing a further degree of freedom for reducing thermal stress. The mobility of non-fixed brackets 182 along the circumferential direction can be limited by stops (not shown) attached to the first and second injection devices 142, 130, respectively. The brackets 182 are preferably made of a metal.

[0141] The frictional resistance between the bracket 182 and the first or second injection device 142, 130 can be adjusted via the width of the non-fixed bracket 182. This reduces the risk of the associated, indirectly attached segment 170, 172 tilting about the circumferential axis of the first or second injection device 142, 130.

[0142] The holes for the connections 174 in the first and second aperture plates 166, 168 and also the sleeve-shaped spacers 180 can be provided with an internal thread corresponding to the screws 176.

[0143] Fig. 14 shows a fourth embodiment of a burner stage 132, which differs from the third embodiment in Fig. 13 in that connecting pairs consisting of two screws 176, two nuts 178, and two spacers 180 secure a portion of one of the segments 170, 172 to the first or second injection device 142, 130 not by means of a bracket 182, but by means of a crosspiece 184, which rests on the upstream surface of the injection device opposite the segment. The corresponding segment 170, 172, the two spacers 180 of a connecting pair, and the associated crosspiece 184 thus define a rectangle within the segment.

[0144] It is conceivable that the spacers 180 and / or the transverse webs 184 are attached to the first or second injection device 142, 130.

[0145] Furthermore, the frictional resistance between the crossbar and the first or second injection device 142, 130 can be adjusted via the size of the contact surface of the crossbar.

[0146] Alternatively or additionally, the segments 170, 172 can be secured to the first or second injection device 142, 130 by a plurality of U-shaped metal sheets (not shown). These U-shaped metal sheets, comparable to the brackets 182 in Fig. 13, are guided upstream against the first or second injection device 142, 130 and fastened thereto, for example, by a welded connection. The two legs of the U-shaped metal sheets, which encompass the respective injection device 142, 130 on opposite sides, are divided into a downstream section and an upstream section. The respective downstream section of a leg is rotated about the leg axis, for example by 90 degrees, in order to adjust the distance of the respective segment 170, 172 to the first or second injection device 142, 130.The twisted downstream portions of the legs are passed through corresponding openings in the respective segment 170, 172 and are bent on the downstream side of the segment 170, 172 to secure the set distance.

[0147] Figures 15 and 16 show a fifth embodiment of a burner stage 132 which has noise reduction measures.

[0148] First, the slot-shaped apertures 152 of the segments 170, 172 of the first and second aperture plates 166, 168 are attached on both sides, i.e., to an inner slot web 185 and to the outer slot web 186, by one or two pairs of connections 174 to the first and second injection devices 142, 130, respectively, whereby the inner slot webs 185 and outer slot webs 186 are prevented from flow-induced oscillation or such oscillation is at least reduced.

[0149] Secondly, the slot-shaped apertures 152 of the first and second aperture plates 166, 168 have one or more tapers.

[0150] The tapers are created by bulges 187 of the respective aperture plate 166, 168, which are arranged opposite one another in pairs and which can be continuous or discontinuous with respect to the outer or inner contour, such as jagged or the like, wherein the number of tapers and thus also the number of bulges 187 of adjacent elongated hole-shaped apertures 152 preferably differs along the circumferential direction of the first and second aperture plate 166, 168.

[0151] The term "bulge" in this description and the appended claims refers to a region of the respective orifice plate, disc, or the like that protrudes or protrudes. Such a protruding or protruding region narrows the affected orifice opening in sections or reduces the distance between opposing elements of the burner device in sections. Accordingly, in Figs. 15 and 16, the slot-shaped orifice openings 152, which are formed by two adjacent segments 170, 172, have two pairs of bulges 187, whereas the remaining slot-shaped orifice openings 152 each have only one pair of bulges 187.

[0152] The bulges 187 can be directly opposite each other or can be offset from each other.

[0153] Furthermore, further bulge elements (not shown) can also protrude into the annular gap 188 between the first and second diaphragm plates 166, 168.

[0154] Thirdly, the inner circular disc 169 is preferably also provided with bulges 187 along its outer circumference, so that tapered sections are formed in the annular gap 190 between the inner circular disc 169 and the first diaphragm plate 166.

[0155] Further noise reduction measures are conceivable, which cause symmetrical and / or asymmetrical tapers to be formed in the area of ​​the annular gaps 188, 190 and along the slot-shaped apertures 152.

[0156] Fig. 17 shows a sixth embodiment of a burner stage 132 with a measure for reducing vibration-induced noise at the gaps between two adjacent segments 170 of the first orifice plate 166 or two adjacent segments 172 of the second orifice plate 168.

[0157] In a slot-shaped aperture 152 formed by two adjacent segments 170 or two adjacent segments 172, the slot inner web 185 and the slot outer web 186 are each separated by a gap. The resulting free ends or sections of the webs 185, 186 vibrate due to the oxidizer flow and thereby generate noise.

[0158] To reduce this noise, an upstream-curved extension 192 is provided on one section 194 of the slot outer web 186, which at least partially overlaps or projects beyond the other section 196 of the slot outer web 186. The extension 192 is preferably a portion of the section 194. Alternatively, Fig. 18 shows—in a seventh embodiment of a burner stage 132—a plate-shaped element 198, which is fastened to the upstream surface of the two sections 194, 196 of the split slot outer web 186. Preferably, the plate-shaped element 198 is welded to both sections 194, 196. Such a closure of the gap also prevents vibration of the two sections 194, 196 and, consequently, the local generation of noise.

[0159] Additionally or alternatively, it is conceivable that the gaps between the sections of the elongated hole inner web 185 and the elongated hole outer web 186 of a slot-shaped aperture 152 are covered on the downstream surface by a common, plate-shaped transverse element (not shown). The plate-shaped transverse element is thus oriented at least approximately perpendicular to the circumferential direction of the respective aperture plate 166, 168.

[0160] REFERENCE SYMBOL

[0161] Jet burner device central longitudinal axis main flow direction flame tube

[0162] diffuser

[0163] Flame tube section, 158 Casing tube, 160 Bypass flow channel Bypass swirl device, 128, 146 Swirl plates

[0164] Constriction element guide tube

[0165] Flow channel, 136 Swirl device, 134, 142, 162 Injection device central burner stage, 154 Injection openings central flow channel Orifice plate Webs circular orifice openings slotted orifice openings bypass injection device injection lances first orifice plate second orifice plate segment segment connection

[0166] screw

[0167] Mother

[0168] spacer bracket crossbar

[0169] bulge

[0170] gap

[0171] gap

[0172] extension

[0173] Section of the slot outer web

[0174] Section of the slot outer web Plate-shaped element Combustion chamber device Combustion chamber section

[0175] Annular gap

Claims

Claims: Jet burner device (100) for the combustion of at least one fuel with at least one oxidizer, wherein the jet burner device (100) has a central longitudinal axis (102) and a main flow direction (104) at least approximately parallel to the central longitudinal axis (102), and wherein the jet burner device (100) comprises: a flame tube (106) and a guide tube (122) arranged inside the flame tube (106), at least one flow channel (124) through which the at least one fuel and the at least one oxidizer can flow and which, with respect to the central longitudinal axis (102), is arranged radially outside the guide tube (122), at least one injection device (130, 162) with several injection openings for supplying the at least one fuel into the at least one flow channel (124), and at least one swirl device (126,136) for swirling fuel and / or oxidizer with a plurality of swirl bodies (128, 146), wherein the at least one injection device (130, 162) is arranged in the at least one flow channel (124) such that the oxidizer flows around the at least one injection device (130, 162), and wherein the at least one swirl device (126, 136) is arranged upstream or downstream of the at least one injection device (130, 162) with respect to the main flow direction (104). Jet burner device (100) according to claim 1, characterized in that the at least one injection device (130, 162) has first injection openings whose central axes point at least approximately in the main flow direction (104). Jet burner device (100) according to claim 2, characterized in that at least one of the first injection openings has an injection lance projecting in the main flow direction (104). A jet burner device (100) according to claim 2 or 3, characterized in that the at least one injection device has second injection openings, the central axes of which each form an angle between 0 degrees and 90 degrees with the main flow direction (104). A jet burner device (100) according to claim 4, characterized in that the first injection openings and the second injection openings can be controlled independently of one another. A jet burner device (100) according to any one of claims 1 to 5, characterized in that the at least one flow channel (124) is annular and that a flowable cross-sectional area of ​​the at least one flow channel (124) is constant or decreases along the main flow direction.A jet burner device (100) according to claim 6, characterized in that the cross-sectional area through which the flow can pass through the at least one flow channel (124) is reduced in a constant or multi-stage manner upstream of the at least one injection device (130, 162), with respect to the main flow direction, and that the cross-sectional area through which the flow can pass through the at least one flow channel (124) is reduced or increased downstream of the at least one injection device (130, 162), with respect to the main flow direction. A jet burner device (100) according to any one of claims 1 to 7, characterized in that the at least one injection device (130, 162) is designed in an annular tube shape. Jet burner device (100) according to one of claims 1 to 8, characterized in that the swirl device (126) is attached to the at least one injection device or is spaced away from the at least one injection device.Jet burner device (100) according to one of claims 1 to 9, characterized in that the jet burner device (100) has a first and a second flow channel (124), wherein the first flow channel, with respect to the. The second flow channel (124) is arranged radially inside the longitudinal axis, and the second flow channel (124) is bounded radially outside by the flame tube (106) with respect to the central longitudinal axis (102). A jet burner device (100) according to claim 10, characterized in that a first injection device (130) is arranged in the first flow channel and a second injection device (130) is arranged in the second flow channel (124). A jet burner device (100) according to claims 10 and 11, characterized in that a swirl device (126) is arranged in the first and / or second flow channel (124), which is arranged upstream of the first and / or second injection device (130) with respect to the main flow direction (104).A jet burner device (100) according to claim 10, characterized in that the jet burner device (100) comprises several injection lances (164) for injecting at least one fuel, that an injection device and a swirl device are arranged in the first flow channel, and that the injection lances are arranged in the second flow channel (124), wherein the swirl device is arranged upstream of the injection device with respect to the main flow direction (104). A jet burner device (100) according to any one of claims 1 to 12, characterized in that the jet burner device (100) comprises several injection lances (164) for injecting at least one fuel, which are arranged at least partially radially within the guide tube (122).Jet burner device (100) according to one of claims 1 to 13, characterized in that the jet burner device (100) comprises a central burner stage (132), wherein the central burner stage (132) is arranged within the guide tube (122), wherein the central burner stage (132) comprises: a central flow channel (140), and a swirl device (136) arranged in the central flow channel. Jet burner device (100) according to claim 15, characterized in that the central burner stage (132) further comprises at least one injection device (134, 142), wherein the at least one injection device (134, 142) is arranged at least partially downstream of the swirl device (16) with respect to the main flow direction, and wherein the injection device (134, 142) of the central burner stage (132) comprises several differently shaped injection openings (154). Jet burner device (100) according to claim 16, characterized in that the central burner stage (132) further comprises an orifice plate (144) with a plurality of orifice openings (150, 152) for fuel and / or oxidizer, wherein the orifice plate (144) is arranged downstream of the injection device (142) with respect to the main flow direction (104), and wherein the orifice plate (144) comprises several differently shaped orifice openings (150, 152).A jet burner device (100) according to any one of claims 1 to 17, characterized in that the flame tube (106) is arranged in a jacket tube (112) such that a bypass flow channel (114) is formed between the flame tube (106) and the jacket tube (112), through which a portion of the oxidizer can flow. A jet burner device (100) according to claim 18, characterized in that at least one bypass injection device (156) for injecting fuel is arranged in the bypass flow channel (114) between the flame tube (106) and the jacket tube (112).Jet burner device (100) according to claim 18 or 19, characterized in that at least one bypass swirl device (116) for swirling the oxidizer portion is arranged in the bypass flow channel (114) between the flame tube (106) and the jacket tube (112), wherein the bypass injection device (156) is arranged downstream of the at least one bypass swirl device (116) with respect to the main flow direction (104). Jet burner device (100) according to any one of claims 18 to 20, characterized in that, with respect to the main flow direction (104), at the. A constriction element (120) for adjusting the proportion of oxidizer flowing through the bypass flow channel (114) is arranged at the upstream end of the casing tube (112). A jet burner device (100) according to any one of claims 1 to 21 is used for the combustion of at least one fuel with at least one oxidizer, in particular for the purification of a contaminated gas stream, preferably a gas stream contaminated with organic substances. A combustion chamber system comprising at least one combustion chamber and at least one jet burner device (100) according to any one of claims 1 to 21, wherein the jet burner device (100) is connected to the bottom of the combustion chamber at its outer circumference.Combustion chamber device (200) with a jet burner device (100) according to any one of claims 1 to 21, wherein the jet burner device (100) is inserted into and attached to the combustion chamber device (200), wherein an annular gap (204) is formed between the outer circumference of the jet burner device (100) and the combustion chamber device (200), through which a portion of the oxidizer can flow. Thermal exhaust gas purification system with a jet burner device (100) according to any one of claims 1 to 21. Gas turbine device with a jet burner device (100) according to any one of claims 1 to 21. Method for operating a jet burner device (100) according to any one of claims 1 to 21, comprising the following steps: Supply of oxidizer to a burner head to form at least one oxidizer stream; Supplying fuel to an injection device (130, 134, 142, 162) of the burner head; and Injection of the fuel by means of the injection device (130, 134, 142, 162) of the burner head into the at least one oxidizer stream.

Images