Aviation igniter based on hydrogen catalytic combustion

Abstract

The invention provides an aviation igniter based on hydrogen catalytic combustion, and belongs to the technical field of aviation power. The problem that a hydrogen ignition nozzle is difficult to mix is solved. Comprising a hydrogen flow divider, main combustion hydrogen pipes, an igniter head shell, a positioning end plate and an igniter tail shell, the head end of the hydrogen flow divider is provided with a hydrogen supply channel, the tail end of the hydrogen flow divider is provided with a hydrogen catalytic combustion channel, the middle section of the hydrogen flow divider is provided with a plurality of hydrogen radial outlets, and each hydrogen radial outlet is connected with one main combustion hydrogen pipe; the main combustion hydrogen pipe axially extends into the igniter tail shell; an air catalytic combustion channel and a catalytic combustion gas mixing section are sequentially arranged in the igniter head shell in the gas circulation direction. The igniter head shell is connected with the igniter tail shell through a positioning end plate, a catalytic combustion gas reaction section is arranged in the igniter tail shell, and a plurality of air main combustion channels are evenly distributed in the circumferential direction of the igniter tail shell. And the main combustion hydrogen pipe is communicated with the air main combustion channel.

Description

Technical Field

[0001] The invention belongs to the technical field of aviation power, and in particular relates to an aviation igniter based on hydrogen catalytic combustion. Background Art

[0002] In the field of aircraft engine ignition, hydrogen is considered an ideal green fuel because it produces only water upon combustion and has a high calorific value per unit mass. However, hydrogen's unique physical properties pose challenges for practical application: Due to its small molecular size, hydrogen diffuses rapidly, making it prone to uneven mixing with air. Furthermore, hydrogen combustion occurs over a wide concentration range, making flame stabilization control difficult. Currently, common ignition systems utilize mechanical mixing structures or premixed combustion. However, hydrogen is less dense than air, and in the high-velocity airflow environment of an engine, hydrogen and air are prone to stratification, with some areas being too rich in hydrogen and others too thin. This uneven mixing directly leads to flame instability and, in extreme cases, even flashback or flameout. Under the volatile engine operating conditions during flight, existing nozzles often cannot ensure rapid and uniform hydrogen diffusion, posing reliability and safety risks to the ignition process. While recently developed catalytic combustion technology can reduce the complexity of the reaction, it places extremely high demands on the uniform mixing of the fuel and air. However, the currently designed catalytic ignition device has not been fully optimized in terms of the coordination between the hydrogen transmission and distribution path and the catalytic area, which has restricted the catalytic effect and makes it difficult to meet the urgent demand for stable ignition under the harsh high-temperature and high-pressure operating conditions of aircraft engines. Summary of the Invention

[0003] In view of this, the present invention aims to propose an aviation igniter based on hydrogen catalytic combustion to solve the problem of difficult gas mixing in the hydrogen ignition nozzle.

[0004] To achieve the above-mentioned objectives, the present invention adopts the following technical solutions: an aviation igniter based on hydrogen catalytic combustion, comprising a hydrogen diverter, a main combustion hydrogen pipe, an igniter head shell, a positioning end plate and an igniter tail shell, wherein the hydrogen diverter, the main combustion hydrogen pipe, the igniter head shell, the positioning end plate and the igniter tail shell are integrally formed; the interior of the hydrogen diverter is hollow, the head end of the hydrogen diverter is provided with a hydrogen supply channel, and the tail end is provided with a hydrogen catalytic combustion channel, the middle section of the hydrogen diverter is provided with a plurality of hydrogen radial outlets along the circumferential direction, each of the hydrogen radial outlets is connected to the inlet end of a main combustion hydrogen pipe, and the tail end side wall of the hydrogen catalytic combustion channel is provided with a hydrogen catalytic combustion channel outlet; the main combustion hydrogen pipe is provided with a hydrogen main combustion channel, and the outlet end of the main combustion hydrogen pipe extends axially to the interior of the igniter tail shell; the ignition The head shell of the igniter is a hollow cylinder, and an air catalytic combustion channel and a catalytic combustion gas mixing section are sequentially arranged in the hollow area of ​​the igniter head shell along the gas flow direction, and the outlet of the hydrogen catalytic combustion channel is located inside the catalytic combustion gas mixing section; the igniter head shell is connected to the igniter tail shell through a positioning end plate, and a plurality of air main combustion channel inlets are evenly distributed in the circumferential direction on the positioning end plate; a catalytic combustion gas reaction section is axially provided through the central axis of the igniter tail shell, and a plurality of air main combustion channels are evenly distributed in the circumferential direction of the central axis; the inlets of the plurality of air main combustion channels are respectively connected to the plurality of air main combustion channel inlets in a one-to-one correspondence; the inlet of the catalytic combustion gas reaction section is connected to the catalytic combustion gas mixing section, the inner surface of the catalytic combustion gas reaction section is coated with a catalyst, and the outlet of the main combustion hydrogen pipe is connected to the air main combustion channel.

[0005] Furthermore, the outer wall profile of the hydrogen splitter is a continuous smooth curved surface.

[0006] Furthermore, the diameter of the hydrogen supply channel is larger than the diameter of the hydrogen radial outlet, and the diameter of the hydrogen radial outlet is larger than the diameter of the hydrogen catalytic combustion channel.

[0007] Furthermore, the end of the hydrogen catalytic combustion channel is closed, and the plurality of hydrogen catalytic combustion channel outlets are evenly distributed along the circumferential direction.

[0008] Furthermore, the inlet of the air catalytic combustion channel is a tapered inlet.

[0009] Furthermore, the main air combustion channels are distributed outside the catalytic combustion gas reaction section.

[0010] Furthermore, the outlet of the main air combustion channel is a gradually expanding outlet.

[0011] Furthermore, the outlet of the catalytic combustion gas reaction section is a gradually expanding outlet.

[0012] Furthermore, the outlet end of the hydrogen main combustion channel is perpendicular to the axis of the air main combustion channel.

[0013] Furthermore, the catalyst is a platinum catalyst.

[0014] Compared with the prior art, the present invention has the following beneficial effects: 1. The hydrogen manifold, main combustion hydrogen pipe, head housing, positioning end plate, and tail housing in the aviation igniter of the present invention are integrally formed and coaxially arranged, eliminating local turbulence or pressure loss caused by assembly gaps and ensuring that hydrogen and air flow in the same direction within each channel, thereby avoiding uneven mixing caused by sudden changes in the flow path. 2. The hydrogen manifold of the present invention has multiple radial hydrogen outlets evenly distributed around the circumference, which are connected to the corresponding main combustion hydrogen pipes, allowing hydrogen to diffuse from the center to the surrounding multi-channels. Combined with the structure in which the diameter of the hydrogen supply channel is larger than the radial outlet, a graded pressure reduction and diversion is formed, which significantly improves the uniformity of hydrogen distribution in the main combustion area and effectively solves the mixing difficulties caused by localized accumulation of large-flow hydrogen. 3. The outlet of the hydrogen catalytic combustion channel of the present invention extends directly into the interior of the catalytic combustion gas mixing section, so that the pre-catalyzed high-temperature hydrogen flow and air are forcibly mixed in a confined space. Combined with the acceleration effect of the tapered inlet of the air catalytic combustion channel, micro-mixing of hydrogen and air is achieved before entering the reaction section. 4. The main air combustion channel of the present invention is evenly distributed around the catalytic combustion gas reaction section and is arranged perpendicular to the outlet of the main hydrogen combustion channel. This creates a swirl when the air flows through the annular channel, generating strong shear turbulence with the radially injected hydrogen in the outlet area, thus solving the problem of the rapid diffusion rate of hydrogen molecules affecting the mixing effect. 5. The gradually expanding outlet of the main combustion air channel of the present invention matches the gradually expanding outlet of the catalytic combustion gas counter-section, thereby ensuring that the gas ejected from the catalytic combustion channel can ignite the slightly mixed gas ejected from the main combustion air channel, while solving the risks of backfire and blowout. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The accompanying drawings, which constitute part of the present invention, are provided to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are provided to explain the present invention and do not constitute an undue limitation of the present invention. In the accompanying drawings: Figure 1 This is a schematic diagram of the axial structure of an aviation igniter based on hydrogen catalytic combustion according to the present invention; Figure 2 This is a schematic cross-sectional view of an aviation igniter based on hydrogen catalytic combustion according to the present invention; Figure 3This is a side structural diagram of an aviation igniter based on hydrogen catalytic combustion according to the present invention. Figure 4 This is a schematic diagram of the axial structure of a hydrogen manifold of an aviation igniter based on hydrogen catalytic combustion according to the present invention; Figure 5 The figure is a schematic cross-sectional structural diagram of a hydrogen manifold of an aviation igniter based on hydrogen catalytic combustion according to the present invention.

[0016] In the picture: 1. Hydrogen diverter; 1-1. Hydrogen supply channel; 1-2. Hydrogen axial outlet; 1-3. Hydrogen radial outlet; 1-4. Hydrogen catalytic combustion channel; 2. Main combustion hydrogen pipe; 2-1. Hydrogen main combustion channel; 3. Ignitor head shell; 3-1. Air catalytic combustion channel; 4. Positioning end face; 4-1. Air main combustion channel inlet; 5. Ignitor tail shell; 5-1. Air main combustion channel; 5-2. Catalytic combustion gas mixing section; 5-3. Catalytic combustion gas reaction section. DETAILED DESCRIPTION

[0017] The following will be combined with the accompanying drawings in the embodiments of the present invention to clearly and completely explain the technical solutions in the embodiments of the present invention. It should be noted that the embodiments of the present invention and the features therein can be combined with each other without conflict, and the embodiments described are only part of the embodiments of the present invention, not all of the embodiments.

[0018] Specific implementation method: see Figure 1-5Describe this embodiment, an aviation igniter based on hydrogen catalytic combustion, including a hydrogen diverter 1, a main combustion hydrogen pipe 2, an igniter head shell 3, a positioning end plate 4 and an igniter tail shell 5, the hydrogen diverter 1, the main combustion hydrogen pipe 2, the igniter head shell 3, the positioning end plate 4 and the igniter tail shell 5 are integrally formed, the hydrogen diverter 1, the igniter head shell 3, the positioning end plate 4 and the igniter tail shell 5 adopt an integrated coaxial design to ensure that the hydrogen flow path is efficient and has good sealing. The integral molding of the hydrogen diverter 1, the main combustion hydrogen pipe 2, the igniter head shell 3, the positioning end plate 4 and the igniter tail shell 5 is achieved through additive manufacturing technology, specifically 3D printing Process, in the molding process, firstly, the overall digital model of the igniter is generated based on computer-aided design modeling, and then 3D printing equipment is used to perform layer-by-layer stacking manufacturing, and the printing material is selected, and the powder or wire is melted by a high-energy heat source, and all the components are directly integrally molded within one printing cycle, thereby obtaining an igniter structure with a seamless structure and no welding or bolt connection points, avoiding the leakage risk in traditional split manufacturing and significantly improving the durability and reliability in high temperature environments. After printing is completed, surface finishing and dimensional refinement are performed; the hydrogen diverter 1 is hollow inside, and the head end of the hydrogen diverter 1 is provided with a hydrogen supply channel 1-1, and the tail end is provided with a hydrogen catalytic combustion channel 1-4, and the hydrogen diverter The middle section of the device 1 is evenly distributed with multiple hydrogen radial outlets 1-2 along the circumferential direction, each of the hydrogen radial outlets 1-2 is connected to the inlet end of a main combustion hydrogen pipe 2, and the tail end side wall of the hydrogen catalytic combustion channel 1-4 is provided with a hydrogen catalytic combustion channel outlet 1-3. The hydrogen diverter 1 is mainly responsible for the primary distribution and diversion of hydrogen. After the hydrogen enters the hydrogen supply channel 1-1, part of the hydrogen flows into the main combustion hydrogen pipe 2 from the hydrogen radial outlet 1-2, and the other part flows into the hydrogen catalytic combustion channel 1-4, and then is discharged to the next channel through the hydrogen catalytic combustion channel outlet 1-3. The hydrogen flowing into the hydrogen catalytic combustion channel 1-4 is used for catalytic ignition and flows into the main combustion hydrogen pipe 2. The hydrogen inside is used to provide a stable main fuel source; the main combustion hydrogen pipe 2 is provided with a hydrogen main combustion channel 2-1, and the outlet end of the main combustion hydrogen pipe 2 extends axially to the inside of the igniter tail shell 5. The main combustion hydrogen pipe 2 is used to transport the hydrogen required for the main combustion, and the middle section of the multiple hydrogen manifolds 1 is uniformly provided with multiple hydrogen radial outlets 1-2 along the circumferential direction, which correspond one-to-one to the inlets of the multiple hydrogen main combustion channels 2-1, thereby ensuring that the hydrogen entering from the hydrogen manifold 1 can be evenly distributed to the main combustion hydrogen pipe 2, thereby improving the uniformity of combustion. The multiple main combustion hydrogen pipes 2 can ensure that the hydrogen is evenly transported to the inside of the igniter tail shell 5, thereby providing a stable main fuel source;The igniter head shell 3 is a hollow cylinder, and an air catalytic combustion channel 3-1 and a catalytic combustion gas mixing section 3-2 are sequentially arranged in the hollow area of ​​the igniter head shell 3 along the gas flow direction. The hydrogen catalytic combustion channel outlet 1-3 is located inside the catalytic combustion gas mixing section 3-2. The igniter head shell 3 is mainly used to construct an initial environment for catalytic ignition. The air catalytic combustion channel 3-1 is used to introduce external air into the catalytic combustion gas mixing section 3-2, and the hydrogen catalytic combustion channel outlet 1-3 is used to transport the diverted hydrogen to the catalytic combustion gas mixing section 3-2. The catalytic combustion gas mixing section 3-2 is a place where hydrogen and air are pre-mixed. The hydrogen in the hydrogen catalytic combustion channel 1-4 and the air introduced into the air catalytic combustion channel 3-1 are evenly mixed in the catalytic combustion gas mixing section 3-2 to provide an ideal reaction gas for catalytic combustion. The catalytic combustion preparation of the ignition source is realized through the igniter head shell 3 to ensure that the mixed gas can be reliably ignited even at low pressure; the igniter head shell 3 is connected to the igniter tail shell 5 through the positioning end plate 4, and a plurality of air main gas cylinders are evenly distributed along the circumferential direction on the positioning end plate 4. The combustion channel inlet 4-1, the positioning end plate 4 serves as an interface for structural support and airflow guidance, and multiple air main combustion channel inlets 4-1 are used to guide air into the interior of the igniter tail shell 5; the catalytic combustion gas reaction section 5-2 is axially penetrated at the center axis of the igniter tail shell 5, and multiple air main combustion channels 5-1 are evenly distributed along the circumferential direction of the center axis, and the inlets of the multiple air main combustion channels 5-1 are respectively connected to the multiple air main combustion channel inlets 4-1 in a one-to-one correspondence; the inlet of the catalytic combustion gas reaction section 5-2 is connected to the catalytic combustion gas mixing section 3-2 The inner surface of the catalytic combustion gas reaction section 5-2 is coated with a catalyst. The outlet of the main combustion hydrogen pipe 2 is connected to the main air combustion channel 5-1. The catalytic combustion gas reaction section 5-2 is where the catalytic combustion reaction occurs. The catalyst on the inner surface of the catalytic combustion gas reaction section 5-2 generates a high-temperature fire source. External air enters the main air combustion channel 5-1 through the main air combustion channel inlet 4-1. The hydrogen output from the outlet of the main combustion hydrogen pipe 2 mixes with the air in the main air combustion channel 5-1 to achieve the purpose of slight mixing, ensuring combustion in the main combustion chamber.

[0019] The working principle of the present invention is as follows: Hydrogen enters from the external system through the hydrogen supply channel 1-1 of the hydrogen diverter 1, and part of the hydrogen flows through the hydrogen catalytic combustion channel 1-4 to the catalytic combustion gas mixing section 3-2 for catalytic ignition; the other part flows into the main combustion hydrogen pipe 2 through multiple hydrogen radial outlets 1-2 and is stored as the main fuel; the hydrogen from the hydrogen catalytic combustion channel 1-4 is mixed with the air introduced from the air catalytic combustion channel 3-1 to ensure that the hydrogen and air are fully mixed, thereby forming a mixed gas in which the hydrogen and air are evenly mixed, and then the mixed gas flows into the catalytic combustion gas reaction section 5-2, and the mixed gas undergoes a catalytic combustion reaction under the action of the catalytic combustion gas catalyst, thereby generating a high-temperature stable fire source, which serves as the initial ignition source; at the same time, the hydrogen main combustion channel 2-1 of the main combustion hydrogen pipe 2 enters the air main combustion channel 5-1, and the air introduced into the air main combustion channel 5-1 by the multiple air main combustion channel inlets 4-1 of the positioning end plate enters The mixture is mixed to form a combustible gas mixture, which is discharged from the outlet of the main air combustion channel 5-1. The initial ignition source is discharged from the outlet of the catalytic combustion gas reaction section 5-2 to ignite the combustible gas mixture discharged from the main air combustion channel 5-1. The main combustion process spreads rapidly at high temperature to produce a large flame, providing the required initial heat source or continuous combustion support for the aircraft engine. The present invention ensures the reliability of the hydrogen flow path through an integrated coaxial design, and diverts the hydrogen through the hydrogen diverter 1, so that a part of the diverted hydrogen enters the air catalytic combustion channel 3-1 and is premixed with the air in the main air combustion channel 5-1. In the catalytic combustion gas reaction section 5-2, the catalyst triggers low-temperature combustion to produce a reliable ignition source, and the other part of the hydrogen flows into the main air combustion channel 5-1 through the main combustion hydrogen pipe 2 and is micro-mixed with the air in the main air combustion channel 5-1 to form a combustible gas mixture, thereby achieving the characteristics of low emissions from premixed combustion and no backfire from diffusion combustion.

[0020] The outer wall profile of the hydrogen splitter 1 is a continuous smooth curved surface. The smooth curved surface can reduce the flow resistance of hydrogen and avoid flow separation caused by sudden changes in the structure, thereby affecting the mixing effect of hydrogen and air.

[0021] The diameter of the hydrogen supply channel 1-1 is larger than the diameter of the hydrogen radial outlet 1-2, thereby ensuring that the hydrogen supply channel 1-1 can provide sufficient hydrogen for combustion. The reduction of the hydrogen radial outlet 1-2 can enhance the penetration of the hydrogen jet, so that the hydrogen ejected from the hydrogen radial outlet 1-2 enters the air main combustion channel 5-1 through the hydrogen main combustion channel 2-1 and is fully mixed within a short distance. The diameter of the hydrogen radial outlet 1-2 is larger than the diameter of the hydrogen catalytic combustion channel 1-4, which can accelerate the hydrogen jet and improve the mixing efficiency of hydrogen with air when it enters the air catalytic combustion channel 3-1 through the hydrogen catalytic combustion channel 1-4.

[0022] The ends of the hydrogen catalytic combustion channels 1-4 are closed, and the multiple hydrogen catalytic combustion channel outlets 1-3 are evenly distributed along the circumferential direction. The ends of the hydrogen catalytic combustion channels 1-4 are closed so that hydrogen can only flow out radially through the side wall 1-3 outlet, avoiding axial direct flow and causing insufficient mixing. The circumferentially evenly distributed outlets form an annular injection array, and the lateral injection of hydrogen enhances the shear force of the gas, thereby accelerating the mixing of hydrogen and air and improving the diffusion coverage of hydrogen in the catalytic combustion gas mixing section 3-2.

[0023] The inlet of the air catalytic combustion channel 3 - 1 is a tapered inlet, and the cross-sectional area of ​​the tapered inlet gradually shrinks to form a Venturi effect, thereby accelerating the flow of external air into the air catalytic combustion channel 3 - 1 .

[0024] The main air combustion channels 5-1 are evenly distributed on the outside of the catalytic combustion gas reaction section 5-2, and directly absorb the heat released by the outer wall of the catalytic combustion through heat conduction, thereby preheating the hydrogen in the main hydrogen combustion channel 2-1. The preheated hydrogen can be more easily mixed with air in the area of ​​the main air combustion channel 5-1, thereby reducing the ignition temperature threshold and improving combustion efficiency.

[0025] The outlet of the main air combustion channel 5-1 is a gradually expanding outlet, and the cross-sectional area of ​​the gradually expanding outlet gradually increases, thereby expanding the contact area between the combustible mixture and the catalytic ignition fire source, so that the initial fire source can quickly ignite the mixture.

[0026] The outlet of the catalytic combustion gas reaction section 5-2 is a gradually expanding outlet, which allows the initial fire source to diffuse radially toward the outer periphery, thereby expanding the contact area with the mixed gas from the outlet of the main combustion channel 5-1.

[0027] The outlet end of the hydrogen main combustion channel 2-1 is perpendicular to the axis of the air main combustion channel 5-1, and hydrogen is vertically inhaled into the air main combustion channel 5-1, thereby enhancing the radial penetration ability of hydrogen in the air flow, thereby expanding the contact area between hydrogen and air to achieve a micro-mixing effect, and at the same time avoiding backfire ignition of the main combustion hydrogen pipe 2-1.

[0028] The catalyst is a platinum catalyst, which has excellent low-temperature catalytic activity and can trigger the reaction of hydrogen and oxygen at a relatively low temperature. The low ignition temperature meets the rapid start-up requirements of aviation igniters and reduces preheating energy consumption.

[0029] The specific embodiments of the present invention disclosed above are intended only to help illustrate the present invention. The specific embodiments do not describe all details in detail, nor do they limit the invention to the specific embodiments described. Numerous modifications and variations are possible based on the contents of this specification. These embodiments are selected and described in detail in this specification to better explain the principles and practical applications of the present invention, thereby enabling those skilled in the art to better understand and utilize the present invention.

Claims

1. An aviation igniter based on hydrogen catalytic combustion, characterized by: The invention comprises a hydrogen diverter (1), a main combustion hydrogen pipe (2), an igniter head shell (3), a positioning end plate (4) and an igniter tail shell (5), wherein the hydrogen diverter (1), the main combustion hydrogen pipe (2), the igniter head shell (3), the positioning end plate (4) and the igniter tail shell (5) are integrally formed; the hydrogen diverter (1) is hollow inside, the head end of the hydrogen diverter (1) is provided with a hydrogen supply channel (1-1), the tail end is provided with a hydrogen catalytic combustion channel (1-4), and the middle section of the hydrogen diverter (1) is provided with a hydrogen supply channel (1-1). A plurality of hydrogen radial outlets (1-2) are uniformly distributed along the circumferential direction, each of the hydrogen radial outlets (1-2) is connected to the inlet end of a main combustion hydrogen pipe (2), and a hydrogen catalytic combustion channel outlet (1-3) is provided on the tail end side wall of the hydrogen catalytic combustion channel (1-4); a hydrogen main combustion channel (2-1) is provided through the main combustion hydrogen pipe (2), and the outlet end of the main combustion hydrogen pipe (2) extends axially to the interior of the igniter tail shell (5); the igniter head shell (3) is a hollow cylinder, and the igniter An air catalytic combustion channel (3-1) and a catalytic combustion gas mixing section (3-2) are sequentially arranged in the hollow area of ​​the head shell (3) along the gas flow direction, and the hydrogen catalytic combustion channel outlet (1-3) is located inside the catalytic combustion gas mixing section (3-2); the igniter head shell (3) is connected to the igniter tail shell (5) through a positioning end plate (4), and a plurality of air main combustion channel inlets (4-1) are uniformly distributed on the positioning end plate (4) along the circumferential direction; the igniter tail shell (5) is axially penetrated by a central axis. A catalytic combustion gas reaction section (5-2) is provided, and a plurality of air main combustion channels (5-1) are uniformly distributed along the circumferential direction of the central axis, the inlets of the plurality of air main combustion channels (5-1) are respectively connected to the plurality of air main combustion channel inlets (4-1) in a one-to-one correspondence; the inlet of the catalytic combustion gas reaction section (5-2) is connected to the catalytic combustion gas mixing section (3-2), the inner surface of the catalytic combustion gas reaction section (5-2) is coated with a catalyst, and the outlet of the main combustion hydrogen pipe (2) is connected to the air main combustion channel (5-1).

2. The aviation igniter based on hydrogen catalytic combustion according to claim 1, characterized in that: The outer wall profile of the hydrogen splitter (1) is a continuous smooth curved surface.

3. The aviation igniter based on hydrogen catalytic combustion according to claim 1, characterized in that: The diameter of the hydrogen supply channel (1-1) is larger than the diameter of the hydrogen radial outlet (1-2), and the diameter of the hydrogen radial outlet (1-2) is larger than the diameter of the hydrogen catalytic combustion channel (1-4).

4. The aviation igniter based on hydrogen catalytic combustion according to claim 1, characterized in that: The ends of the hydrogen catalytic combustion channels (1-4) are closed, and the plurality of hydrogen catalytic combustion channel outlets (1-3) are evenly distributed along the circumferential direction.

5. The aviation igniter based on hydrogen catalytic combustion according to claim 1, characterized in that: The inlet of the air catalytic combustion channel (3-1) is a tapered inlet.

6. The aviation igniter based on hydrogen catalytic combustion according to claim 1, characterized in that: The main air combustion channels (5-1) are evenly distributed outside the catalytic combustion gas reaction section (5-2).

7. The aviation igniter based on hydrogen catalytic combustion according to claim 1, characterized in that: The outlet of the main air combustion channel (5-1) is a gradually expanding outlet.

8. The aviation igniter based on hydrogen catalytic combustion according to claim 1, characterized in that: The outlet of the catalytic combustion gas reaction section (5-2) is a gradually expanding outlet.

9. The aviation igniter based on hydrogen catalytic combustion according to claim 1, characterized in that: The outlet end of the hydrogen main combustion channel (2-1) is perpendicular to the axis of the air main combustion channel (5-1).

10. The aviation igniter based on hydrogen catalytic combustion according to claim 1, characterized in that: The catalyst is a platinum catalyst.

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