Micro-mixing combustion assembly and micro-mixing combustion chamber

Abstract

The application belongs to the technical field of hydrogen fuel combustion chambers, and provides a micro-mixed combustion assembly and a micro-mixed combustion chamber, which comprise a mixing part, the mixing part comprises a first micro-mixed unit, a second micro-mixed unit and a plurality of spiral swirler, the first micro-mixed unit comprises a plurality of first fuel injection ports, the second micro-mixed unit comprises a plurality of second fuel injection ports, each first fuel injection port and each second fuel injection port are provided with a spiral swirler correspondingly, the spiral swirler extends spirally along the axial direction of the corresponding first fuel injection port and the corresponding second fuel injection port, the plurality of second fuel injection ports are arranged annularly, and the plurality of first fuel injection ports are arranged in the annulus formed by the plurality of second fuel injection ports. Micro-diffusion of fuel can be realized, micro-flame is generated, and backfire or spontaneous combustion is avoided. The spiral swirler guides the gas in the first fuel injection port and the second fuel injection port to form a rotational flow, strengthens the mixing of fuel and air, reduces the high-temperature aggregation of flame, and thus effectively reduces the emission of NOx.

Description

Technical Field

[0001] This application belongs to the field of hydrogen fuel combustion chamber technology, specifically relating to a micro-hybrid combustion component and a micro-hybrid combustion chamber. Background Technology

[0003] Hydrogen, as a highly efficient and clean energy source, has received widespread attention and research due to its advantages such as wide availability, high calorific value, and zero carbon emissions. Furthermore, compared to natural gas, hydrogen has characteristics such as lower density, a wider combustible range, and lower ignition energy.

[0004] However, due to the unique combustion characteristics of hydrogen, the combustion chamber of traditional gas turbines faces many challenges when burning hydrogen: not only is backfire very likely, but there are also defects such as excessive nitrogen oxide (NOx) emissions and a large high-temperature zone inside the combustion chamber, which pose significant safety hazards. Summary of the Invention

[0005] Therefore, the technical problem to be solved by this application is to provide a micro-mixing combustion component and a micro-mixing combustion chamber, which can reduce backfire or spontaneous combustion and reduce safety hazards.

[0006] To address the aforementioned problems, a first aspect of this application provides a micro-hybrid combustion assembly, comprising a mixing section. The mixing section includes a first micro-hybrid unit, a second micro-hybrid unit, and a plurality of spiral swirlers. The first micro-hybrid unit includes a plurality of first fuel nozzles, each of which is correspondingly provided with a spiral swirler, the spiral swirler extending spirally along the axial direction of the corresponding first fuel nozzle. The second micro-hybrid unit includes a plurality of second fuel nozzles, each of which is correspondingly provided with a spiral swirler, the spiral swirler extending spirally along the axial direction of the corresponding second fuel nozzle. The plurality of second fuel nozzles are arranged in a ring, and the plurality of first fuel nozzles are disposed within the ring formed by the plurality of second fuel nozzles.

[0007] Optionally, a plurality of first fuel nozzles are arranged in a circular ring, a plurality of second fuel nozzles are arranged in a circular ring, and the circular ring containing the plurality of first fuel nozzles and the circular ring containing the plurality of second fuel nozzles are concentrically arranged.

[0008] Optionally, the first micro-hybrid unit includes a plurality of first fluid channels, one end of which extends to a first outer wall of the mixing section to form a plurality of first fuel nozzles on the first outer wall, and the other end of which extends to a second outer wall of the mixing section to form a plurality of first air inlets on the second outer wall. The second micro-mixing unit includes a plurality of second fluid channels, one end of which extends to the first outer wall of the mixing section to form a plurality of second fuel nozzles on the first outer wall, and the other end of which extends to the second outer wall of the mixing section to form a plurality of second air inlets on the second outer wall. The spiral vortex is disposed within the first fluid channel and the second fluid channel.

[0009] Optionally, the flow area of ​​the first air inlet decreases along the flow direction, and the flow area of ​​the second air inlet decreases along the flow direction.

[0010] Optionally, the mixing section is provided with a first fuel distribution chamber and a second fuel distribution chamber. The first fuel distribution chamber is isolated from the second fuel distribution chamber. The first fuel distribution chamber is connected to the fuel gas source and the first fluid channel, respectively. The second fuel distribution chamber is connected to the fuel gas source and the second fluid channel, respectively. The micro-hybrid combustion assembly includes a gas supply section, which includes a first fuel supply pipe and a second fuel supply pipe. The first fuel supply pipe and the second fuel supply pipe are disposed on the second outer wall. The first fuel supply pipe is connected to the first fuel distribution cavity to supply fuel into the first fuel distribution cavity, and the second fuel supply pipe is connected to the second fuel distribution cavity to supply fuel into the second fuel distribution cavity.

[0011] Optionally, the first fuel distribution cavity includes a first branch and a second branch, the first branch and the second branch being connected to the first fuel supply pipe respectively; the first branch extends in an arc and is located on the side of the first micro-mixing unit away from the second micro-mixing unit, the second branch extends in an arc and is located on the side of the first micro-mixing unit close to the second micro-mixing unit, and both the first branch and the second branch are connected to each of the first fluid channels. The second fuel distribution cavity includes a third branch and a fourth branch, which are respectively connected to the second fuel supply pipe; the third branch extends in an arc shape and is located on the side of the second micro-mixing unit closer to the first micro-mixing unit, and the fourth branch extends in an arc shape and is located on the side of the second micro-mixing unit away from the first micro-mixing unit; both the third branch and the fourth branch are connected to each of the second fluid channels.

[0012] Optionally, the spiral cyclone includes a first spiral blade and a second spiral blade, the first spiral blade and the second spiral blade extend spirally, the first spiral blade and the second spiral blade are centrally symmetrically arranged, and an axial jet channel is formed at the axis of symmetry.

[0013] Optionally, the blade width of the first helical blade and the blade width of the second helical blade are 1.5 mm to 3 mm, and the helix angle of the first helical blade and the helix angle of the second helical blade are 180°. The circumferential relative position angle between the spiral vortex and the corresponding first fuel nozzle is 75° to 90°, and the circumferential relative position angle between the spiral vortex and the corresponding second fuel nozzle is 75° to 90°. Both the first fuel nozzle and the second fuel nozzle are hydrogen nozzles, and the diameters of the first fuel nozzle and the second fuel nozzle are 0.4 mm to 1 mm.

[0014] Optionally, the mixing section includes a first support mounting ring and a second support mounting ring, wherein the first support mounting ring is coaxially disposed on the inner side of the annulus where the plurality of first fuel nozzles are located, and the second support mounting ring is coaxially disposed on the outer side of the annulus where the plurality of second fuel nozzles are located.

[0015] A second aspect of this application provides a micro-hybrid combustion chamber, including the micro-hybrid combustion assembly as described above.

[0016] The embodiments of this application provide a micro-mixing combustion assembly and a micro-mixing combustion chamber. The micro-mixing combustion assembly, by setting a first micro-mixing unit and a second micro-mixing unit, and arranging multiple second fuel nozzles of the second micro-mixing unit in a ring, and placing multiple first fuel nozzles within the ring formed by the multiple second fuel nozzles, can achieve micro-diffusion of fuel, thereby generating a large number of tiny flames, effectively avoiding backfire, and effectively reducing the high-temperature zone, resulting in a more uniform temperature distribution and reduced NOx emissions. By correspondingly setting a spiral swirler at each first fuel nozzle and each second fuel nozzle, and extending the spiral swirlers spirally, the gas within the first and second fuel nozzles can be guided to form a swirling flow, thereby enhancing fuel-air mixing. After fuel injection, it quickly and uniformly mixes with air, reducing the sustained high-temperature accumulation of the flame, effectively avoiding backfire, and effectively reducing the high-temperature zone, resulting in a more uniform temperature distribution, reduced NOx emissions, and improved fuel combustion safety. Attached Figure Description

[0017] Figure 1 This is a first-view perspective three-dimensional structural diagram of the micro-hybrid combustion component according to an embodiment of this application. Figure 2 for Figure 1 Enlarged structural diagram at point A; Figure 3 This is a three-dimensional structural diagram of the micro-hybrid combustion assembly from a side view according to an embodiment of this application; Figure 4 for Figure 3 Schematic diagram of the cross-sectional structure at point BB; Figure 5 This is a two-dimensional structural diagram of the micro-hybrid combustion component according to an embodiment of this application; Figure 6 This is a side view of the cross-sectional structure of the micro-hybrid combustion assembly according to an embodiment of this application. Figure 7 This is a three-dimensional structural diagram of the spiral cyclone separator according to an embodiment of this application.

[0018] The reference numerals in the attached figures are as follows: 1. First micro-mixing unit; 2. First fuel nozzle; 3. Spiral vortex generator; 31. First spiral blade; 32. Second spiral blade; 4. First support mounting ring; 5. First fuel supply pipe; 6. Second micro-mixing unit; 7. Second fuel nozzle; 8. Second fuel supply pipe; 9. Second support mounting ring; 10. Fuel gas distribution chamber; 11. First fuel distribution channel; 111. First branch; 112. Second branch; 12. Second fuel distribution channel; 121. Third branch; 122. Fourth branch; 13. First air inlet; 14. Second air inlet; 15. First outer wall; 16. Second outer wall; 17. Connecting hole. Detailed Implementation

[0019] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0020] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0021] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection between two components. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0022] The embodiments of this application are described below with reference to the accompanying drawings. It should be understood that the embodiments described herein are for illustration and explanation only and are not intended to limit this application.

[0023] See also Figures 1 to 7 As shown, according to a first aspect of the embodiments of this application, a micro-hybrid combustion assembly is provided, including a mixing section. The mixing section includes a first micro-hybrid unit 1, a second micro-hybrid unit 6, and a plurality of spiral swirlers 3. The first micro-hybrid unit 1 includes a plurality of first fuel nozzles 2, each of which is correspondingly provided with a spiral swirler 3, which extends spirally along the axial direction of the corresponding first fuel nozzle 2. The second micro-hybrid unit 6 includes a plurality of second fuel nozzles 7, each of which is correspondingly provided with a spiral swirler 3, which extends spirally along the axial direction of the corresponding second fuel nozzle 7. The plurality of second fuel nozzles 7 are arranged in a ring, and the plurality of first fuel nozzles 2 are disposed within the ring formed by the plurality of second fuel nozzles 7.

[0024] By setting up a first micro-mixing unit 1 and a second micro-mixing unit 6, and arranging multiple second fuel nozzles 7 of the second micro-mixing unit 6 in a ring, and placing multiple first fuel nozzles 2 within the ring formed by the multiple second fuel nozzles 7, micro-diffusion of fuel can be achieved, thereby generating a large number of tiny flames and effectively preventing backfire or spontaneous combustion. By providing a spiral vortex 3 for each first fuel nozzle 2 and a corresponding spiral vortex 3 for each second fuel nozzle 7, and extending the spiral vortex 3 spirally, the gas in the first fuel nozzle 2 and the second fuel nozzle 7 can be guided to form a vortex, thereby enhancing the mixing of fuel and air. After fuel injection, it quickly and evenly mixes with air, reducing the sustained high temperature accumulation of the flame, effectively suppressing backfire, and effectively reducing the high temperature zone, resulting in a more uniform temperature distribution, reducing NOx emissions, and improving fuel combustion safety.

[0025] In one embodiment, the micro-mixing combustion assembly is used for micro-diffusion combustion of fuel, that is, fuel and air are mixed in the first micro-mixing unit 1 and the second micro-mixing unit 6 under the action of the spiral vortex 3 and sprayed out by a plurality of first fuel nozzles 2 and a plurality of second fuel nozzles 7.

[0026] The first fuel nozzle 2 and the second fuel nozzle 7 are disposed on the wall surface on the same side of the mixing section.

[0027] Among them, the spiral swirler 3 is long and narrow, and the length direction of the spiral swirler 3 is the axial direction of the corresponding first fuel nozzle 2 and second fuel nozzle 7. The spiral swirler 3 extends in its own length direction while twisting in its own circumferential direction, thus forming a spiral shape.

[0028] Multiple first fuel nozzles 2 are arranged in a circular ring, and multiple second fuel nozzles 7 are arranged in a circular ring. The circular ring containing the multiple first fuel nozzles 2 and the circular ring containing the multiple second fuel nozzles 7 are concentrically arranged.

[0029] By arranging the annulus containing multiple first fuel nozzles 2 and the annulus containing multiple second fuel nozzles 7 concentrically, the mixing of fuel and air becomes more uniform, thereby improving combustion efficiency and enabling the combustion of a large number of small flame clusters of fuel, effectively reducing the risk of combustion thermoacoustic oscillations.

[0030] Among them, multiple first fuel nozzles 2 are evenly arranged along a circular trajectory to form an inner ring structure, and multiple second fuel nozzles 7 are evenly arranged along a circular trajectory to form an outer ring structure. The inner ring structure and the outer ring structure are set with the same central axis.

[0031] Specifically, the mixing section is roughly disc-shaped, with the first fuel nozzle 2 and the second fuel nozzle 7 disposed on one axial end face of the mixing section. The central axes of the annulus containing the first fuel nozzle 2 and the annulus containing the second fuel nozzle 7 are collinear with the central axis of the mixing section. That is, the mixing section, the annulus containing the first fuel nozzle 2, and the annulus containing the second fuel nozzle 7 are coaxially arranged.

[0032] In one embodiment, there are 12 first fuel nozzles 2, which are evenly arranged in a circular pattern. There are 18 second fuel nozzles 7, which are evenly arranged in a circular pattern.

[0033] The first micro-hybrid unit 1 includes a plurality of first fluid channels, one end of which extends to the first outer wall 15 of the mixing section to form a plurality of first fuel nozzles 2 on the first outer wall 15, and the other end of which extends to the second outer wall 16 of the mixing section to form a plurality of first air inlets 13 on the second outer wall 16.

[0034] The second micro-mixing unit 6 includes a plurality of second fluid channels, one end of which extends to the first outer wall 15 of the mixing section to form a plurality of second fuel nozzles 7 on the first outer wall 15, and the other end of which extends to the second outer wall 16 of the mixing section to form a plurality of second air inlets 14 on the second outer wall 16.

[0035] The spiral vortex 3 is disposed within the first fluid channel and the second fluid channel.

[0036] By setting up a first fluid channel and a first air inlet 13, as well as a second fluid channel and a second air inlet 14, a stable flow path for air is provided. By setting up a spiral vortex generator 3 in the first and second fluid channels, a mounting position for the spiral vortex generator 3 is provided, while ensuring that fuel and air are fully mixed in the first and second fluid channels.

[0037] In this configuration, one end of each first fluid channel extends in a straight line to the first outer wall 15 of the mixing section to form a first fuel nozzle 2, and the other end extends to the second outer wall 16 of the mixing section to form a first air inlet 13. That is, one end of each first fluid channel corresponds to a first fuel nozzle 2, and the other end corresponds to a first air inlet 13. Each first fluid channel has a corresponding first fuel nozzle 2 and a first air inlet 13.

[0038] In this configuration, one end of each second fluid channel extends in a straight line to the first outer wall 15 of the mixing section to form a second fuel nozzle 7, and the other end extends to the second outer wall 16 of the mixing section to form a second air inlet 14. That is, one end of a single second fluid channel corresponds to a second fuel nozzle 7, and the other end corresponds to a second air inlet 14.

[0039] Each first fluid channel is equipped with a corresponding spiral vortex 3, and each second fluid channel is equipped with a corresponding spiral vortex 3.

[0040] In one embodiment, the number of first fluid channels, first fuel nozzles 2, and first air inlets 13 are all 12. The number of second fluid channels, second fuel nozzles 7, and second air inlets 14 are all 18.

[0041] The flow area of ​​the first air inlet 13 decreases along the flow direction, and the flow area of ​​the second air inlet 14 decreases along the flow direction.

[0042] By reducing the flow area of ​​the first air inlet 13 along the flow direction and reducing the flow area of ​​the second air inlet 14 along the flow direction, the initial flow velocity of the air injection can be increased, allowing the high-speed air and hydrogen fuel to mix more thoroughly, further optimizing the mixing uniformity, and continuously shortening the time for the mixed gas to flow through the high-temperature region, thus continuously reducing nitrogen oxide emissions.

[0043] The first air inlet 13 has a decreasing flow area along the flow direction, meaning that the cross-sectional size of the first air inlet 13 that allows air to circulate gradually narrows and decreases along the direction of airflow. Similarly, the second air inlet 14 has a decreasing flow area along the flow direction, meaning that the cross-sectional size of the second air inlet 14 that allows air to circulate gradually narrows and decreases along the direction of airflow.

[0044] The mixing section is provided with a first fuel distribution chamber 11 and a second fuel distribution chamber 12. The first fuel distribution chamber 11 is isolated from the second fuel distribution chamber 12. The first fuel distribution chamber 11 is connected to the fuel gas source and the first fluid channel, respectively. The second fuel distribution chamber 12 is connected to the fuel gas source and the second fluid channel, respectively.

[0045] By setting up a first fuel distribution chamber 11 and a second fuel distribution chamber 12 that are isolated from each other, the operator can adjust the hydrogen fuel supply flow rate of the first fuel distribution chamber 11 and the second fuel distribution chamber 12 respectively according to the working conditions, so as to achieve independent graded control to adapt to the combustion load requirements under different working conditions.

[0046] The first fuel distribution chamber 11 and the second fuel distribution chamber 12 are independent of each other, and the hydrogen fuel in the first fuel distribution chamber 11 will not be interconnected with the hydrogen fuel in the second fuel distribution chamber 12.

[0047] In one embodiment, the mixing section is finely machined to form a first fuel distribution cavity 11 and a second fuel distribution cavity 12 that are independent and annular. Specifically, the interior space of the mixing section is divided into two non-communicating sealed areas by an integrally formed solid partition wall. One sealed area forms the first fuel distribution cavity 11, and the other sealed area forms the second fuel distribution cavity 12. The solid partition wall completely blocks the gas flow channel between the two cavities, thereby completing the isolation between the two.

[0048] The micro-hybrid combustion assembly includes a gas supply section, which includes a first fuel supply pipe 5 and a second fuel supply pipe 8. The first fuel supply pipe 5 and the second fuel supply pipe 8 are disposed on the second outer wall 16. The first fuel supply pipe 5 is connected to the first fuel distribution cavity 11 to supply fuel into the first fuel distribution cavity 11, and the second fuel supply pipe 8 is connected to the second fuel distribution cavity 12 to supply fuel into the second fuel distribution cavity 12.

[0049] By arranging the first fuel supply pipe 5 and the second fuel supply pipe 8 on the second outer wall 16 of the mixing section, it is convenient to centrally connect and install external pipelines. By connecting the first fuel supply pipe 5 to the first fuel distribution chamber 11 and the second fuel supply pipe 8 to the second fuel distribution chamber 12, the hydrogen fuel supplied to the first fuel distribution chamber 11 and the second fuel distribution chamber 12 can be independently controlled. The supply amount to the first fuel distribution chamber 11 and the second fuel distribution chamber 12 can be adjusted according to the combustion load, thereby widening the power adjustment range for stable operation of the device.

[0050] In one embodiment, flow control valves are respectively installed on the pipe sections of the first fuel supply pipe 5 and the second fuel supply pipe 8. The operator can adjust the opening of the flow control valve on the corresponding pipe according to different operating load conditions of the unit, thereby changing the flow rate of hydrogen fuel entering the first fuel distribution chamber 11 and the flow rate of hydrogen fuel entering the second fuel distribution chamber 12, matching the fuel supply required by the first micro-hybrid unit 1 and the second micro-hybrid unit 6, and further improving the flexibility of combustion condition adjustment and the controllability of equipment operation.

[0051] The first fuel distribution cavity 11 includes a first branch 111 and a second branch 112, which are respectively connected to the first fuel supply pipe 5. The first branch 111 extends in an arc shape and is located on the side of the first micro-mixing unit 1 away from the second micro-mixing unit 6, and the second branch 112 extends in an arc shape and is located on the side of the first micro-mixing unit 1 closer to the second micro-mixing unit 6. Both the first branch 111 and the second branch 112 are connected to each of the first fluid channels.

[0052] By setting up the first branch 111 and the second branch 112, hydrogen fuel can be simultaneously delivered to the first fluid channel from the inner and outer sides of the first micro-mixing unit 1, respectively, improving the uniformity of hydrogen fuel supply to the first micro-mixing unit 1 and thus enhancing the overall combustion uniformity. Simultaneously, by setting both the first branch 111 and the second branch 112 to an arc shape, the flow resistance during hydrogen fuel delivery is reduced, gas supply pressure loss is minimized, and a continuous and stable supply is ensured.

[0053] In this configuration, both the first branch 111 and the second branch 112 extend in an arc shape. The first branch 111 is located on the side of the first micro-hybrid unit 1 away from the second micro-hybrid unit 6, and the second branch 112 is located on the side of the first micro-hybrid unit 1 closer to the second micro-hybrid unit 6. That is, the first micro-hybrid unit 1 is located between the first branch 111 and the second branch 112. The first branch 111 and the second branch 112 are symmetrically distributed around the inner and outer sides of the first micro-hybrid unit 1. Both the first branch 111 and the second branch 112 are connected to all the first micro-hybrid units 1 through a connecting hole 17. One end of the connecting hole 17 is opened to the inner wall of the first branch 111 or the second branch 112, and the other end is opened to the inner wall of the first fluid channel, so that the hydrogen fuel in the first branch 111 and the second branch 112 can enter the first fluid channel through the connecting hole 17.

[0054] The second fuel distribution cavity 12 includes a third branch 121 and a fourth branch 122, which are respectively connected to the second fuel supply pipe 8. The third branch 121 extends in an arc shape and is located on the side of the second micro-mixing unit 6 closer to the first micro-mixing unit 1, while the fourth branch 122 extends in an arc shape and is located on the side of the second micro-mixing unit 6 away from the first micro-mixing unit 1. Both the third branch 121 and the fourth branch 122 are connected to each of the second fluid channels.

[0055] By setting up the third branch 121 and the fourth branch 122, hydrogen fuel can be simultaneously supplied to the second fluid channel from the inner and outer sides of the second micro-mixing unit 6, respectively, improving the uniformity of hydrogen fuel supply to the second micro-mixing unit 6 and thus enhancing the overall combustion uniformity. Simultaneously, by setting both the third branch 121 and the fourth branch 122 to an arc shape, the flow resistance during hydrogen fuel transportation is reduced, gas supply pressure loss is minimized, and a continuous and stable supply is ensured.

[0056] The third branch 121 and the fourth branch 122 both extend in an arc shape. The third branch 121 is located on the side of the second micro-hybrid unit 6 closest to the first micro-hybrid unit 1, and the fourth branch 122 is located on the side of the second micro-hybrid unit 6 furthest from the first micro-hybrid unit 1. That is, the second micro-hybrid unit 6 is located between the third branch 121 and the fourth branch 122. The third branch 121 and the fourth branch 122 are symmetrically distributed around the inner and outer sides of the second micro-hybrid unit 6. Both the third branch 121 and the fourth branch 122 are connected to all the second micro-hybrid units 6 through the connecting hole 17. One end of the connecting hole 17 is opened to the inner wall of the third branch 121 or the fourth branch 122, and the other end is opened to the inner wall of the second fluid channel, so that the hydrogen fuel in the third branch 121 and the fourth branch 122 can enter the second fluid channel through the connecting hole 17.

[0057] The spiral cyclone 3 includes a first spiral blade 31 and a second spiral blade 32. The first spiral blade 31 and the second spiral blade 32 extend spirally. The first spiral blade 31 and the second spiral blade 32 are centrally symmetrically arranged and form an axial jet channel at the axis of symmetry.

[0058] By setting up a first helical blade 31 and a second helical blade 32, and arranging them symmetrically at the center, preheated air is guided by the first and second helical blades 31 and 32 to form a high-shear vortex flow field. This rapidly tears and entrains the laterally injected hydrogen fuel, achieving highly uniform mixing within a very short space. An axial jet channel is formed at the axis of symmetry between the first and second helical blades 31 and 32, creating a cold, high-speed axial jet that directly penetrates and sweeps through the downstream high-temperature core region. The central jet overcomes the drawback of reduced axial velocity caused by strong vortices, effectively reducing the peak flow field temperature and significantly shortening the residence time of the fluid in the high-temperature reaction zone. This effectively hinders the synthesis pathway of thermal NOx, ultimately achieving safe, stable, and clean combustion of hydrogen fuel. The coupling of the first and second helical blades 31 and 32 with the central jet achieves a synergistic effect of highly efficient mixing and extremely low emissions.

[0059] The first helical blade 31 and the second helical blade 32 are fixedly connected. The symmetrical center positions of the first helical blade 31 and the second helical blade 32 form a complete and continuous axial jet channel. When the air flows through the helical vortex 3, part of it is twisted by the first helical blade 31 and the second helical blade 32 to form a rotating mixed airflow, and the other part directly passes through the central axial jet channel to form a cold axial high-speed jet.

[0060] The first helical blade 31 and the second helical blade 32 are centrally symmetrical and twisted in an alternating manner, forming a hollow axial jet channel between the first helical blade 31 and the second helical blade 32.

[0061] The study found that moderate swirling intensity can greatly promote the mixing of hydrogen fuel and air. However, excessive swirling intensity will significantly reduce the axial velocity of the flow field, which not only easily leads to the upward movement of the flame surface and the generation of a larger flame surface, but also greatly increases the residence time of reactants in the high-temperature combustion zone, resulting in extremely high NOx emissions. In order to balance the contradiction between high mixing rate and low NOx emissions, the swirler in this embodiment is precisely defined. The blade width of the first helical blade 31 and the blade width of the second helical blade 32 are 1.5 mm to 3 mm, and the helix angle of the first helical blade 31 and the helix angle of the second helical blade 32 are 180°. The circumferential relative position angle between the swirler 3 and the corresponding first fuel nozzle 2 is 75° to 90°, and the circumferential relative position angle between the swirler 3 and the corresponding second fuel nozzle 7 is 75° to 90°. By using a specific combination of blade width, lift angle, and relative position angle, the passing air can generate a moderate swirling flow that is neither too strong nor too weak. This ensures rapid and slight mixing of the fuel while maintaining sufficient axial purging speed, effectively suppressing the formation of thermal NOx.

[0062] In one embodiment, both the first fuel nozzle 2 and the second fuel nozzle 7 are hydrogen nozzles, and the diameter of the first fuel nozzle 2 and the diameter of the second fuel nozzle 7 are 0.4 mm to 1 mm.

[0063] By strictly controlling the diameters of the first fuel nozzle 2 and the second fuel nozzle 7 within the range of 0.4 mm to 1 mm, effective micro-diffusion of hydrogen fuel can be achieved. The tiny nozzle size allows the hydrogen fuel to form a fine jet when it is ejected, which can be rapidly and uniformly sheared and mixed by the swirling air.

[0064] The mixing section includes a first support mounting ring 4 and a second support mounting ring 9. The first support mounting ring 4 is coaxially disposed on the inner side of the annulus where the plurality of first fuel nozzles 2 are located, and the second support mounting ring 9 is coaxially disposed on the outer side of the annulus where the plurality of second fuel nozzles 7 are located.

[0065] By setting a first support mounting ring 4 and a second support mounting ring 9, and coaxially positioning the first support mounting ring 4 on the inner side of the annulus where multiple first fuel nozzles 2 are located, and coaxially positioning the second support mounting ring 9 on the outer side of the annulus where multiple second fuel nozzles 7 are located, the overall structural rigidity and installation stability of the micro-hybrid combustion assembly are improved, and the service life of the micro-hybrid combustion assembly is extended.

[0066] The first support mounting ring 4 and the second support mounting ring 9 are both complete annular rings, coaxially arranged, and also coaxial with the disc-shaped mixing section. The first support mounting ring 4 is approximately located at the center of the mixing section, and the second support mounting ring 9 is located along the outer periphery of the mixing section. Both the first support mounting ring 4 and the second support mounting ring 9 are located on the first outer wall 15 and protrude from the first outer wall 15 in a direction away from the second outer wall 16.

[0067] According to a second aspect of the embodiments of this application, a micro-hybrid combustion chamber is provided, including the micro-hybrid combustion assembly as described above.

[0068] The micro-hybrid combustion chamber provided in this application embodiment includes a micro-hybrid combustion component as described in any of the above technical solutions, and therefore possesses all the beneficial effects of the micro-hybrid combustion component of the above technical solutions.

[0069] It will be readily understood by those skilled in the art that the aforementioned advantageous methods can be freely combined and superimposed without conflict.

[0070] The above are merely preferred embodiments of this application and are not intended to limit this application. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this application should be included within the protection scope of this application. The above are merely implementation methods of this application. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of this application, and these improvements and modifications should also be considered within the protection scope of this application.

Claims

1. A micro-hybrid combustion assembly, characterized in that, The system includes a mixing section, which comprises a first micro-mixing unit (1), a second micro-mixing unit (6), and a plurality of spiral vortex generators (3). The first micro-mixing unit (1) includes a plurality of first fuel nozzles (2), each of which is correspondingly provided with a spiral vortex generator (3), which extends spirally along the axial direction of the corresponding first fuel nozzle (2). The second micro-mixing unit (6) includes a plurality of second fuel nozzles (7), each of which is correspondingly provided with a spiral vortex generator (3), which extends spirally along the axial direction of the corresponding second fuel nozzle (7). The plurality of second fuel nozzles (7) are arranged in a ring, and the plurality of first fuel nozzles (2) are disposed within the ring formed by the plurality of second fuel nozzles (7).

2. The micro-hybrid combustion assembly according to claim 1, characterized in that, Multiple first fuel nozzles (2) are arranged in a circular ring, and multiple second fuel nozzles (7) are arranged in a circular ring. The circular ring containing the multiple first fuel nozzles (2) and the circular ring containing the multiple second fuel nozzles (7) are concentrically arranged.

3. The micro-hybrid combustion assembly according to claim 1, characterized in that, The first micro-mixing unit (1) includes a plurality of first fluid channels, one end of which extends to the first outer wall (15) of the mixing section to form a plurality of first fuel nozzles (2) on the first outer wall (15), and the other end of which extends to the second outer wall (16) of the mixing section to form a plurality of first air inlets (13) on the second outer wall (16). The second micro-mixing unit (6) includes a plurality of second fluid channels, one end of which extends to the first outer wall (15) of the mixing section to form a plurality of second fuel nozzles (7) on the first outer wall (15), and the other end of which extends to the second outer wall (16) of the mixing section to form a plurality of second air inlets (14) on the second outer wall (16). The spiral vortex (3) is disposed in the first fluid channel and the second fluid channel.

4. The micro-hybrid combustion assembly according to claim 3, characterized in that, The flow area of ​​the first air inlet (13) decreases along the flow direction, and the flow area of ​​the second air inlet (14) decreases along the flow direction.

5. The micro-hybrid combustion assembly according to claim 3, characterized in that, The mixing section is provided with a fuel gas distribution chamber (10), and the fuel gas distribution chamber (10) is provided with a first fuel distribution channel (11) and a second fuel distribution channel (12). The first fuel distribution channel (11) and the second fuel distribution channel (12) are isolated from each other. The first fuel distribution channel (11) is connected to the fuel gas source and the first fluid channel, respectively. The second fuel distribution channel (12) is connected to the fuel gas source and the second fluid channel, respectively. The micro-hybrid combustion assembly includes a gas supply section, which includes a first fuel supply pipe (5) and a second fuel supply pipe (8). The first fuel supply pipe (5) and the second fuel supply pipe (8) are disposed on the second outer wall (16). The first fuel supply pipe (5) is connected to the first fuel distribution cavity (11) to supply fuel into the first fuel distribution cavity (11). The second fuel supply pipe (8) is connected to the second fuel distribution cavity (12) to supply fuel into the second fuel distribution cavity (12).

6. The micro-hybrid combustion assembly according to claim 5, characterized in that, The first fuel distribution cavity (11) includes a first branch (111) and a second branch (112), the first branch (111) and the second branch (112) are respectively connected to the first fuel supply pipe (5); the first branch (111) extends in an arc and is located on the side of the first micro-mixing unit (1) away from the second micro-mixing unit (6), the second branch (112) extends in an arc and is located on the side of the first micro-mixing unit (1) close to the second micro-mixing unit (6), and the first branch (111) and the second branch (112) are both connected to each of the first fluid channels; The second fuel distribution cavity (12) includes a third branch (121) and a fourth branch (122), which are respectively connected to the second fuel supply pipe (8); the third branch (121) extends in an arc and is located on the side of the second micro-mixing unit (6) close to the first micro-mixing unit (1), and the fourth branch (122) extends in an arc and is located on the side of the second micro-mixing unit (6) away from the first micro-mixing unit (1). The third branch (121) and the fourth branch (122) are both connected to each of the second fluid channels.

7. The micro-hybrid combustion assembly according to claim 1, characterized in that, The spiral vortex (3) includes a first spiral blade (31) and a second spiral blade (32). The first spiral blade (31) and the second spiral blade (32) extend spirally. The first spiral blade (31) and the second spiral blade (32) are centrally symmetrically arranged and form an axial jet channel at the axis of symmetry.

8. The micro-hybrid combustion assembly according to claim 7, characterized in that, The blade width of the first helical blade (31) and the blade width of the second helical blade (32) are 1.5 mm to 3 mm, and the helix angle of the first helical blade (31) and the helix angle of the second helical blade (32) are 180°. The circumferential relative position angle between the spiral vortex (3) and the corresponding first fuel nozzle (2) is 75° to 90°, and the circumferential relative position angle between the spiral vortex (3) and the corresponding second fuel nozzle (7) is 75° to 90°. Both the first fuel nozzle (2) and the second fuel nozzle (7) are hydrogen nozzles, and the diameters of the first fuel nozzle (2) and the second fuel nozzle (7) are 0.4 mm to 1 mm.

9. The micro-hybrid combustion assembly according to claim 2, characterized in that, The mixing section includes a first support mounting ring (4) and a second support mounting ring (9). The first support mounting ring (4) is coaxially disposed on the inner side of the annulus where the plurality of first fuel nozzles (2) are located, and the second support mounting ring (9) is coaxially disposed on the outer side of the annulus where the plurality of second fuel nozzles (7) are located.

10. A micro-mixing combustion chamber, characterized in that, Includes the micro-hybrid combustion assembly as described in any one of claims 1 to 9.

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