Micro-mixing cluster nozzle structure and method for aero-kerosene micro-hydrogen micro-turbojet combustion chamber with variable flow channel

Abstract

The present application relates to the field of aviation power technology, in particular to the micro mixing cluster nozzle structure and method of the aviation kerosene hydrogenation micro turbojet combustion chamber with variable flow channel; the nozzle structure comprises: a plurality of micro mixing units, an air outer guide ring and an air shunt cover; the micro mixing unit comprises a hydrogen supply channel, a hydrogen distribution pipe network, a hydrogen gas collection cavity, an air micro mixing unit channel, a hydrogen-air premixing section and a premixed gas outlet; the hydrogen supply channel is used for supplying sufficient hydrogen to the micro mixing unit; the inlet of the hydrogen gas collection cavity is communicated with the outlet of the hydrogen supply channel; the inlet of the hydrogen distribution pipe network is communicated with the outlet of the hydrogen gas collection cavity; the hydrogen distribution pipe network has a plurality of inlet channels and an opposite outlet channel with a number of two times of the number of inlet channels. The nozzle structure can effectively improve the adaptability of the micro turbojet engine to the change of fuel from aviation kerosene to hydrogen, inhibit backfire and reduce engine carbon emission.

Description

Technical Field

[0001] This invention relates to the field of aviation power technology, specifically to the structure and method of a micro-mixing nozzle for a micro-turbojet combustor that converts kerosene to hydrogen using a variable flow path. Background Technology

[0002] As compact, high thrust-to-weight ratio, and rapid-response small power plants, micro turbojet engines are widely used in unmanned aerial vehicles (UAVs), target drones, cruise missiles, and distributed energy systems. Traditional micro turbojet engines mainly use aviation kerosene, but its fossil fuel properties bring carbon emission pressures, making it difficult to meet the needs of sustainable development.

[0003] Hydrogen energy has become an important technological path due to its clean and zero-carbon nature. However, hydrogen differs significantly from aviation kerosene in terms of physical properties: hydrogen has a low density and weak jet penetration, easily causing uneven mixing and localized rich combustion, leading to increased NOx emissions; at the same time, hydrogen flame propagation speed is extremely high, easily causing backfire, spontaneous combustion, and thermoacoustic instability, threatening combustion chamber safety. Micro-mixing combustion technology, by premixing hydrogen and air through microchannels, can significantly reduce NOx emissions, but existing solutions still have shortcomings in suppressing backfire and controlling thermoacoustic oscillations. For micro turbojet engines, with their small combustion chamber characteristic size and high heat load, these problems are particularly prominent.

[0004] Meanwhile, for micro turbojet engines with evaporator tubes, air typically enters the combustion chamber from the tail of the flame tube through the channel between the outer shell of the flame tube and the casing, where fuel and air mix within the evaporator tube. Figure 6 As shown, the flow channel is U-shaped and not suitable for hydrogen fuel micro-hybrid structures. Summary of the Invention

[0005] Therefore, the technical problem to be solved by the present invention is to overcome the problems of backfire, spontaneous combustion and thermoacoustic instability in the existing micro turbojet combustor, thereby providing a micro-mixing cluster nozzle structure and method for a variable flow channel aviation kerosene to hydrogen micro turbojet combustor.

[0006] To address the aforementioned technical problems, this invention provides a micro-mixing cluster nozzle structure for a variable-flow-channel aviation kerosene-to-hydrogen micro-turbojet combustor, comprising: multiple micro-mixing units, an outer air guide ring, and an air distribution shroud. Each micro-mixing unit includes a hydrogen supply channel, a hydrogen distribution network, a hydrogen collection cavity, an air micro-mixing unit channel, a hydrogen-air premixing section, and a premixed gas outlet. The hydrogen supply channel supplies sufficient hydrogen to the micro-mixing units. The inlet of the hydrogen collection cavity is connected to the outlet of the hydrogen supply channel, and the inlet of the hydrogen distribution network is connected to the outlet of the hydrogen collection cavity. The hydrogen distribution network has multiple inlet channels and a number of inlet channels. The air micro-mixing unit channel has a double-sided counter-outlet channel; the inlet of the air micro-mixing unit channel is connected to the counter-outlet channel of the hydrogen distribution network, and the hydrogen from the counter-outlet channel is vertically injected into the hydrogen-air premixing section; the inlet of the air micro-mixing unit channel receives air from the outer air guide ring and the air splitter hood; the hydrogen-air premixing section connects the outlet of the hydrogen distribution network and the outlet of the air micro-mixing unit channel; the hydrogen from the hydrogen distribution network and the air from the air micro-mixing unit channel are premixed in the hydrogen-air premixing section; and the premixed gas is ejected from the outlet of the hydrogen-air premixing section.

[0007] Furthermore, the outer air guide ring and the air splitter are distributed in a ring shape on the inner and outer sides of the nozzle to guide the main airflow, so that the main airflow is concentrated and enters the central micro-mixing unit.

[0008] Furthermore, the hydrogen distribution network is arranged near the inlet of the air micro-mixing unit channel.

[0009] Furthermore, the hydrogen distribution network has a hexagonal cross-section, with six inlet channels and twelve opposing outlet channels.

[0010] Furthermore, the hydrogen in the hydrogen supply channel is divided into six radial paths through the inlet channel of the hydrogen distribution network, and then distributed to the six air micro-mixing unit channels distributed in a ring array via twelve opposing outlet channels.

[0011] Furthermore, the hydrogen supply channel is arranged at the center of the air micro-mixing unit channels distributed in a ring array.

[0012] Furthermore, the hydrogen gas from the outlet of the hydrogen distribution network is injected vertically into the hydrogen-air premixing section, where it mixes with the air drawn in from the inlet of the air micro-mixing unit before the premixed gas outlet.

[0013] Furthermore, the multiple micro-mixing units are arranged in a ring array, and the hydrogen supply channel and the air micro-mixing unit channel are relatively evenly distributed.

[0014] Furthermore, the micro-hybrid unit has twelve units.

[0015] This invention also provides a method for operating the micro-mixing nozzle structure of the micro-turbojet combustor for converting aviation kerosene to hydrogen using a variable flow path, including: Hydrogen gas is regulated by an external hydrogen source and flows into the hydrogen collection chamber through the hydrogen supply channel. After pressure equalization and pulsation attenuation are completed in the hydrogen collection chamber, it enters the hydrogen distribution network evenly. The hydrogen gas flows along multiple inlet channels of the hydrogen distribution network to the end of each network and is ejected at high speed from the opposite outlet channel in the form of subsonic or sonic jets, vertically entering the inlet area of ​​the corresponding hydrogen-air premixing section. At the same time, the high-pressure air mainstream delivered from the external compressor undergoes radial and circumferential redistribution under the guidance of the air outer guide ring and air splitter, with most of the air being guided and concentrated into the air micro-mixing unit channel located in the central region. The air is gradually accelerated in the air micro-mixing unit channel and meets the opposite hydrogen jet near the channel outlet. The two begin to mix violently at the inlet of the hydrogen-air premixing section. Finally, the fully mixed hydrogen-air premixed gas is accelerated and ejected through the premixed gas outlet, entering the downstream engine combustion chamber, where it achieves low-emission, high-efficiency premixed combustion under the action of the ignition source.

[0016] The technical solution of this invention has the following advantages: (1) The mixing of hydrogen and air adopts a micro-mixing structure, which can effectively improve the adaptability of the micro turbojet engine to the fuel change from aviation kerosene to hydrogen through the nozzle structure, suppress backfire, and reduce engine carbon emissions. This structure can make the fuel and air mix before entering the combustion chamber, eliminate local high temperature areas, and thus reduce nitrogen oxide emissions. At the same time, if the flow channel form of the existing aviation kerosene evaporator is directly applied, backfire is likely to occur due to the large diameter of the evaporator. The air micro-mixing unit channel diameter of the micro-mixing nozzle structure created in this invention is small enough to make the jet velocity exceed the flame propagation speed of hydrogen, thereby effectively mitigating the risk of hydrogen combustion backfire.

[0017] (2) The micro premixed nozzle not only optimizes the intake channel structure, but also adapts to the conversion of aviation kerosene to hydrogen fuel. This avoids the problem that the original flow channel structure of the rear-intake aviation kerosene micro turbojet engine with evaporator pipe will cause the mainstream compressed air to flow directly axially, and the mainstream cannot enter the central micro-mixing channel after the conversion to hydrogen fuel. At the same time, the fuel is changed from aviation kerosene to hydrogen, which is cleaner than carbon fuel, has extremely high fuel mass energy density, good combustion characteristics, and lower ignition energy.

[0018] (3) The core of this invention lies in upgrading the original fuel nozzles of the aviation kerosene micro turbojet engine to hydrogen fuel micro premixed nozzle assemblies by replacing a small number of parts. This solution does not require redesigning or modifying the main structure of the engine casing, compressor, turbine, and flame tube; fuel switching can be achieved simply by removing and replacing the corresponding parts through specific interfaces. This not only significantly reduces the amount of engineering work and the cycle of design and modification, but also facilitates the rapid batch upgrade of existing aircraft models. Furthermore, combined with metal 3D printing technology, the complex sub-millimeter-level micro-pore array and fuel gas path structure inside the micro premixed nozzle can be further optimized and quickly integrated, significantly compressing the entire process cycle from parametric design iteration to finished product manufacturing.

[0019] The summary section is provided to present the chosen concepts in a simplified form, which will be further described in the detailed description below. The summary section is not intended to identify essential or necessary features of this disclosure, nor is it intended to limit the scope of this disclosure. Attached Figure Description

[0020] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0021] Figure 1 A schematic diagram of the micro-mixing nozzle structure of the aviation kerosene-to-hydrogen micro turbojet combustion chamber with variable flow channel provided by the present invention. Figure 2 A perspective view of the micro-mixing nozzle structure of the micro-turbojet combustion chamber for converting aviation kerosene to hydrogen, provided by the present invention. Figure 3 A cross-sectional view of the hydrogen distribution network of the micro-mixing nozzle structure of the micro-turbojet combustion chamber for converting aviation kerosene to hydrogen provided by the present invention. Figure 4 A side cross-sectional view of the micro-mixing nozzle structure of the aviation kerosene-to-hydrogen micro turbojet combustion chamber with variable flow channel provided by the present invention. Figure 5 A cross-sectional view of the micro-mixing nozzle structure of the micro-turbojet combustion chamber for converting aviation kerosene to hydrogen, provided by the present invention. Figure 6 A schematic diagram of the combustion chamber structure of a primitive model of an aviation kerosene engine; Figure 7 This is a schematic diagram of the nozzle assembly in the combustion chamber provided by the present invention.

[0022] Explanation of reference numerals in the attached figures: 1. Micro-mixing unit; 2. Air outer guide ring; 3. Air splitter hood; 4. Hydrogen supply channel; 5. Hydrogen distribution network; 51. Inlet channel; 52. Opposite outlet channel; 6. Hydrogen collection cavity; 7. Air micro-mixing unit channel; 8. Hydrogen-air premixing section; 9. Premixed gas outlet. Detailed Implementation

[0023] In the following description, only certain exemplary embodiments are briefly described. As those skilled in the art will recognize, the described embodiments can be modified in various ways without departing from the spirit or scope of this disclosure. Therefore, the drawings and description are to be considered exemplary in nature and not restrictive.

[0024] The preferred embodiments of this disclosure are described below with reference to the accompanying drawings. It should be understood that the preferred embodiments described herein are for illustration and explanation only and are not intended to limit this disclosure.

[0025] Please see Figures 1 to 7 As shown, this invention provides multiple micro-mixing units 1, an air outer guide ring 2, and an air splitter hood 3. Each micro-mixing unit includes a hydrogen supply channel 4, a hydrogen distribution network 5, a hydrogen collection chamber 6, an air micro-mixing unit channel 7, a hydrogen-air premixing section 8, and a premixed gas outlet 9. The hydrogen supply channel 4 supplies sufficient hydrogen to the micro-mixing unit 1. The inlet of the hydrogen collection chamber 6 is connected to the outlet of the hydrogen supply channel 4, and the inlet of the hydrogen distribution network 5 is connected to the outlet of the hydrogen collection chamber 6. The hydrogen distribution network 5 has multiple inlet channels 51 and twice the number of opposing outlet channels 52. The air micro-mixing unit... The inlet of unit channel 7 is connected to the opposite outlet channel 52 of the hydrogen distribution network 5. The hydrogen from the opposite outlet channel 52 is vertically injected into the hydrogen-air premixing section 8. The inlet of the air micro-mixing unit channel 7 receives air after being guided by the outer air guide ring 2 and the air splitter hood 3. The hydrogen-air premixing section 8 is connected to the outlet of the hydrogen distribution network 5 and the outlet of the air micro-mixing unit channel 7. The hydrogen from the hydrogen distribution network 5 and the air from the air micro-mixing unit channel 7 are premixed in the hydrogen-air premixing section 8. The premixed gas is ejected from the hydrogen-air premixing section 8 through the premixed gas outlet 9.

[0026] The specific source of hydrogen is not limited. For example, any existing feasible hydrogen production method can be used, such as water electrolysis, natural gas reforming, or industrial by-product hydrogen, as long as it can continuously supply hydrogen to the hydrogen supply channel 4 to meet the pressure and flow requirements. The hydrogen supply channel 4 can be connected to an external hydrogen source pipeline.

[0027] The hydrogen collection chamber 6 is a pressure-stabilizing chamber with a certain volume. It can be designed as an annular chamber or a combination of independent chambers surrounding each micro-mixing unit. Its function is to stabilize and equalize the incoming hydrogen, reduce pressure pulsations that may be caused by the hydrogen supply pipeline, and ensure that the inlet pressure of the downstream hydrogen distribution network 5 is uniform and stable.

[0028] The inlet of the hydrogen distribution pipeline 5 is connected to the outlet of the hydrogen collection cavity 6, which is used to further finely distribute the hydrogen in the collection cavity to the corresponding injection positions of each micro-mixing unit.

[0029] In this embodiment, the hydrogen distribution network 5 is hexagonal in shape and has six inlet channels 51 and twelve opposing outlet channels 52.

[0030] The air micro-mixing unit channels 7, which correspond to the six arrays, are structurally integrally formed to form a reliable sealed connection.

[0031] The hydrogen in the hydrogen supply channel 4 is divided into six radial paths through the inlet channel 51 of the hydrogen distribution network 5, and then distributed to the six air micro-mixing unit channels 7 arranged in a ring array via twelve opposing outlet channels 52.

[0032] The hydrogen supply channel 4 is located at the center of the six air micro-mixing unit channels 7 arranged in a ring array.

[0033] The hexagonal star-shaped pipe network is divided into six inlet channels 51 and correspondingly equipped with 12 opposing outlet channels 52. Specifically, each hexagonal star has two opposing outlets at its star-point ends, namely opposing outlet channels 52, so that the hydrogen injection direction is symmetrically arranged on both sides of the air flow channel, thereby injecting hydrogen into the air flow in the form of opposing jets, which enhances the momentum exchange and mixing uniformity between hydrogen and air.

[0034] Multiple micro-mixing units 1 are arranged in a ring array, and the hydrogen supply channel 4 and the air micro-mixing unit channel 7 are relatively evenly distributed.

[0035] The air micro-mixing unit channel 7 is used to guide and accelerate the compressed air entering the micro-mixing unit. The inlet of the hydrogen-air premixing section 8 is connected to the outlet of the hydrogen distribution network 5, that is, the internal flow channel of the air micro-mixing unit channel 7 intersects with the outlet of the hydrogen distribution network 5 upstream of the premixing section, so that the air and hydrogen establish a defined flow coupling relationship before entering the premixing section.

[0036] The hydrogen distribution network 5 is arranged near the inlet of the air micro-mixing unit channel 7. Each opposing outlet channel 52 faces the direction of air flow, so that hydrogen is injected into the downstream hydrogen-air premixing section 8 at high speed in a vertical or near-vertical direction.

[0037] It should be noted that the inlet of the air micro-mixing unit channel 7 also receives air from the air outer guide ring 2 and the air splitter shroud 3 after it has been diverted and reorganized.

[0038] The air guide ring 2 and the air splitter shroud 3 are distributed in a ring on the inner and outer sides of the nozzle to guide the main airflow, so that the main airflow is concentrated and enters the central micro-mixing unit 1.

[0039] The outer air guide ring 2 is coaxially mounted around the periphery of multiple micro-mixing units 1 and fixed to the nozzle housing; the air splitter shroud 3 is installed on the intake side of the micro-mixing unit 1 and can be in the form of a conical shroud or an arc-shaped guide plate. When the engine is running, the main stream of compressed air from the compressor outlet reaches the nozzle tip, and through the combined guidance and deflection of the outer air guide ring 2 and the air splitter shroud 3, most of the air is forced to change its flow direction and concentrate into the air micro-mixing unit channel 7 of each micro-mixing unit 1.

[0040] This structural design effectively overcomes the defects caused by the flow channel structure of the original rear-intake micro turbojet engine with evaporator pipe, where the mainstream compressed air flows directly axially. When the fuel is changed from aviation kerosene to hydrogen and the evaporator pipe is removed, it is difficult to form an effective air intake in the central area, resulting in insufficient air supply to the micro-mixing channel. This invention, through the reasonable matching of the outer air guide ring 2 and the air splitter shroud 3, ensures that air can flow into the central micro-mixing unit channel as needed, guaranteeing the stable organization and mixing of hydrogen and air at the designed equivalence ratio.

[0041] Hydrogen gas from the outlet of the hydrogen distribution network 5 is injected vertically into the hydrogen-air premixing section 8, where it mixes with the air drawn in at the inlet of the air micro-mixing unit channel 7 before the premixed gas outlet 9.

[0042] The hydrogen-air premixing section 8 is a mixing channel of a specific length, which is connected after the outlet of the hydrogen distribution network 5 and the outlet of the air micro-mixing unit channel 7.

[0043] In the hydrogen-air premixing section 8, the hydrogen jet from the hydrogen distribution network 5 undergoes vigorous gas premixing with the accelerated airflow from the air micro-mixing unit channel 7. Because the hydrogen is injected vertically into the mainstream airflow in a counter-current jet manner, strong shear and vortices are formed at the inlet of the premixing section, enabling the two gases to achieve uniform mixing within a short distance. Furthermore, under design conditions, the velocity of the mixed gas jet is significantly higher than the flame propagation velocity of hydrogen, thus mechanistically preventing hydrogen combustion backfire.

[0044] The premixed gas outlet 9 is connected to the end of the hydrogen-air premixing section 8, and the premixed gas outlet 9 can be designed as a tapered nozzle to further accelerate the fully mixed hydrogen-air premixed gas and inject it into the head of the engine combustion chamber, where it is then ignited by the ignition device for stable and clean combustion. The working method of the micro-mixing nozzle structure of the micro-turbojet combustor for converting aviation kerosene to hydrogen using a variable flow channel includes: Hydrogen gas is regulated by an external hydrogen source and flows into the hydrogen collection chamber 6 through the hydrogen supply channel 4. After pressure equalization and pulsation attenuation are completed in the hydrogen collection chamber 6, it enters the hydrogen distribution network 5 evenly. The hydrogen gas flows along the multiple inlet channels 51 of the hydrogen distribution network 5 to the end of each network and is ejected at high speed from the opposite outlet channel 52 in the form of subsonic or sonic jets, and is vertically injected into the inlet area of ​​the corresponding hydrogen-air premixing section 8. At the same time, the high-pressure air mainstream delivered from the external compressor undergoes radial and circumferential redistribution under the guidance of the air outer guide ring 2 and the air splitter shroud 3, with most of the air being guided and concentrated into the air micro-mixing unit channel 7 located in the central region. This flow path design completely avoids the problem of insufficient air entering the central micro-mixing channel caused by the direct axial flow of the mainstream in the original rear-intake aviation kerosene micro turbojet engine with evaporator, thus enabling hydrogen fuel to obtain a sufficient supply of oxidizer.

[0045] The air is gradually accelerated in the air micro-mixing unit channel 7 and meets the opposite hydrogen jet near the channel outlet. The two begin to mix violently at the inlet of the hydrogen-air premixing section 8. The structure and length of the hydrogen-air premixing section 8 are designed to ensure that hydrogen and air are fully and uniformly mixed under high-speed flow conditions. At the same time, it ensures that the overall velocity of the mixed jet is much greater than the flame propagation velocity of hydrogen under this condition, which fundamentally suppresses the tendency of backfire and improves the flame safety performance of the nozzle.

[0046] Finally, the fully mixed hydrogen-air premixed gas is accelerated and ejected through the premixed gas outlet 9 and enters the downstream engine combustion chamber, where it achieves low-emission and high-efficiency premixed combustion under the action of the ignition source.

[0047] Based on the above embodiments, several modifications and improvements can be made.

[0048] For example, the number of micro-hybrid units 1 is not limited to six, and can be appropriately set to four, eight, twelve or other numbers according to the size of the combustion chamber head and power requirements; The shape of the hydrogen distribution network 5 is not limited to a hexagonal star shape. Other polygonal star shapes or ring pipes with distribution pipes can also be used, as long as the hydrogen can be evenly distributed to each micro-mixing unit and form opposing or tangential jets in the air flow channel. The specific shapes of the air splitter shroud 3 and the outer air guide ring 2 can be optimized according to aerodynamic design requirements; the materials of each component can be selected from high-temperature resistant stainless steel, nickel-based alloys such as Inconel 718, and other materials adapted to the hydrogen environment and combustion chamber thermal environment. These improvements and refinements should also be considered within the scope of protection of this invention.

[0049] Obviously, the above embodiments are merely illustrative examples for clear explanation and are not intended to limit the implementation. Those skilled in the art will recognize that other variations or modifications can be made based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. However, obvious variations or modifications derived therefrom are still within the scope of protection of this invention.

Claims

1. A micro-mixing nozzle structure for a variable-flow-channel aviation kerosene-to-hydrogen micro-turbojet combustion chamber, characterized in that, include: Multiple micro-mixing units (1), an external air guide ring (2), and an air distribution hood (3). The micro-mixing unit (1) includes a hydrogen supply channel (4), a hydrogen distribution network (5), a hydrogen collection chamber (6), an air micro-mixing unit channel (7), a hydrogen-air premixing section (8), and a premixed gas outlet (9). The hydrogen supply channel (4) is used to supply sufficient hydrogen to the micro-mixing unit (1). The inlet of the hydrogen collection cavity (6) is connected to the outlet of the hydrogen supply channel (4). The inlet of the hydrogen distribution network (5) is connected to the outlet of the hydrogen collection cavity (6). The hydrogen distribution network (5) has multiple inlet channels (51) and twice the number of opposing outlet channels (52). The inlet of the air micro-mixing unit channel (7) is connected to the opposite outlet channel (52) of the hydrogen distribution network (5), and the hydrogen in the opposite outlet channel (52) is vertically injected into the hydrogen-air premixing section (8). The inlet of the air micro-mixing unit channel (7) receives air from the air outer guide ring (2) and the air splitter (3). The hydrogen-air premixing section (8) is connected to the outlet of the hydrogen distribution network (5) and the outlet of the air micro-mixing unit channel (7). The hydrogen from the hydrogen distribution network (5) and the air from the air micro-mixing unit channel (7) are premixed in the hydrogen-air premixing section (8). The premixed gas outlet (9) sprays out the premixed gas mixed in the hydrogen-air premixing section (8).

2. The micro-mixing nozzle structure of the aviation kerosene-to-hydrogen micro-turbojet combustion chamber with variable flow channel as described in claim 1, characterized in that: The air guide ring (2) and the air splitter (3) are distributed in a ring on the inside and outside of the nozzle to guide the main airflow, so that the main airflow is concentrated and enters the central micro-mixing unit (1).

3. The micro-mixing nozzle structure of the aviation kerosene-to-hydrogen micro-turbojet combustion chamber with variable flow channel as described in claim 2, characterized in that: The hydrogen distribution network (5) is located near the inlet of the air micro-mixing unit channel (7).

4. The micro-mixing nozzle structure of the aviation kerosene-to-hydrogen micro-turbojet combustion chamber with variable flow channel according to any one of claims 1-3, characterized in that: The hydrogen distribution network (5) has a hexagonal cross-section and six inlet channels (51) and twelve opposing outlet channels (52).

5. The micro-mixing nozzle structure of the aviation kerosene-to-hydrogen micro-turbojet combustion chamber with variable flow channel as described in claim 4, characterized in that: The hydrogen in the hydrogen supply channel (4) is divided into six radial paths through the inlet channel (51) of the hydrogen distribution network (5), and then distributed to the six air micro-mixing unit channels (7) distributed in a ring array via twelve opposing outlet channels (52).

6. The micro-mixing nozzle structure of the aviation kerosene-to-hydrogen micro-turbojet combustion chamber with variable flow channel as described in claim 5, characterized in that: The hydrogen supply channel (4) is arranged at the center of the air micro-mixing unit channels (7) distributed in a ring array.

7. The micro-mixing nozzle structure of the aviation kerosene-to-hydrogen micro-turbojet combustion chamber with variable flow channel as described in claim 6, characterized in that: Hydrogen gas from the outlet of the hydrogen distribution network (5) is injected vertically into the hydrogen-air premixing section (8) and mixed with the air drawn in at the inlet of the air micro-mixing unit channel (7) before the premixed gas outlet (9).

8. The micro-mixing nozzle structure of the aviation kerosene-to-hydrogen micro-turbojet combustion chamber with variable flow channel as described in claim 7, characterized in that: Multiple micro-mixing units (1) are arranged in a ring array, and the hydrogen supply channel (4) and the air micro-mixing unit channel (7) are relatively evenly distributed.

9. The micro-mixing nozzle structure of the aviation kerosene-to-hydrogen micro-turbojet combustion chamber with variable flow channel as described in claim 8, characterized in that: The micro-mixing unit (1) has twelve units.

10. The operating method of the micro-mixing nozzle structure of the aviation kerosene-to-hydrogen micro-turbojet combustion chamber with variable flow channel according to any one of claims 1-9, characterized in that, include: Hydrogen gas is regulated by an external hydrogen source and flows into the hydrogen collection chamber (6) through the hydrogen supply channel (4). After pressure equalization and pulsation attenuation are completed in the hydrogen collection chamber (6), it enters the hydrogen distribution network (5) evenly. The hydrogen gas flows along the multiple inlet channels (51) of the hydrogen distribution network (5) to the end of each network and is ejected at high speed from the opposite outlet channel (52) in the form of subsonic or sonic jets, and is vertically injected into the inlet area of ​​the corresponding hydrogen-air premixing section (8). At the same time, the high-pressure air stream from the external compressor undergoes radial and circumferential redistribution under the guidance of the air outer guide ring (2) and the air splitter (3), and most of the air is guided and concentrated into the air micro-mixing unit channel (7) located in the central region. The air is gradually accelerated in the air micro-mixing unit channel (7) and meets the opposite hydrogen jet near the channel outlet. The two begin to mix violently at the inlet of the hydrogen-air premixing section (8). Finally, the fully mixed hydrogen-air premixed gas is accelerated and ejected through the premixed gas outlet (9) and enters the downstream engine combustion chamber, where it achieves low-emission and high-efficiency premixed combustion under the action of the ignition source.

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