Multi-shock wave cooperative triggering and explosion promotion device and method

Abstract

The invention belongs to the technical field of detonation combustion propulsion, and discloses a multi-shock-wave cooperative triggering and explosion promotion device and method. The device comprises a fuel ratio regulation and control system, a pre-combustion chamber, a jet pipe and a detonation chamber. The fuel ratio regulation and control system is used for providing and regulating and controlling mixed fuel gas of ethylene, oxygen and nitrogen for the pre-combustion chamber; an inlet of the pre-combustion chamber is communicated with an outlet of the fuel proportion regulation and control system, and an ignition component is arranged in the pre-combustion chamber; the multiple jet pipes form an annular array, and inlets of all the jet pipes directly communicate with an outlet of the pre-combustion chamber. And the inlet end of the detonation chamber is communicated with the outlet ends of all the jet pipes. According to the device, the limitation of a traditional detonation mode is broken through, ignition energy distribution is optimized through the energy relay effect of a hot spot group, and the industrial problems that the energy requirement of direct detonation is large, and the indirect detonation distance is long are solved.

Description

Technical Field

[0001] This application belongs to the field of detonation combustion propulsion technology, specifically relating to a multi-shock wave coordinated triggering and detonation device and method. Background Technology

[0002] Detonation combustion propulsion technology has broad application prospects in the field of new power systems due to its near-isochoric combustion thermal cycle efficiency. Achieving rapid and reliable ignition and detonation is one of the core prerequisites for the engineering application of this technology.

[0003] Currently, jet initiation is the main technical approach in the field of detonation combustion, and it includes two types: direct initiation and indirect initiation. Traditional direct jet initiation relies on the jet tube to generate detonation, which in turn produces a detonation wave that diffracts in the detonation chamber. This method requires the jet tube diameter to be greater than 13 times (>13λ) the detonation wave lattice size to maintain the detonation wave, necessitating extremely high ignition energy. This results in enormous system power consumption, complex structure, and difficulty in miniaturization and high-frequency operation. Indirect initiation, on the other hand, can induce flame acceleration through shock waves, converting it into detonation. While this reduces the initial energy requirement, it suffers from an excessively long initiation distance. Experiments show that with a single jet tube, the DDT distance typically exceeds 100 mm, especially under conditions of low fuel reactivity, such as when the nitrogen to oxygen dilution ratio is high. β ≥0.6 ( β (Nitrogen gas integral / oxygen volume fraction), which cannot even trigger knock, severely limiting the miniaturization and high-frequency operation capability of knock engines.

[0004] To overcome the limitations of a single jet, the shock wave collision initiation theory has been proposed, which rapidly ignites chemical reactions through a high-temperature, high-pressure zone formed by the convergence of multiple shock waves. However, existing technologies based on this theory primarily focus on optimizing single or a small number of shock wave paths. Current solutions fail to achieve a good balance between low energy input, short initiation distance, and adaptability to high dilution ratio conditions. This is mainly because they lack a multi-source shock wave collision network that can cover the cross-section of the detonation chamber and is highly synchronized in time. Single-point or asynchronous shock sources, due to energy dispersion leading to insufficient local hotspot intensity, or disordered interactions between wave systems preventing the formation of an effective "energy relay," ultimately result in low overall stability and efficiency of the hotspot group.

[0005] Therefore, how to significantly reduce the energy requirement for single-point detonation while effectively shortening the detonation distance and ensuring stable and reliable detonation triggering under high fuel dilution conditions has become a bottleneck restricting the performance improvement and engineering application of current detonation propulsion technology. Summary of the Invention

[0006] This application aims to overcome the shortcomings of existing technologies and provide a multi-shock wave coordinated triggering and detonation method. By coordinating the synchronous ignition of the pre-combustion chamber and the multi-jet tube array, a ring-shaped shock wave collision network capable of covering the cross-section of the detonation chamber is constructed, thereby significantly reducing the energy requirement for single-point detonation, effectively shortening the detonation distance, and improving the detonation success rate and stability under high fuel dilution conditions.

[0007] To achieve the above technical objectives, this application specifically adopts the following technical solution: In one aspect of this application, a multi-shock wave coordinated triggering and detonation device is provided, comprising: A multi-shock wave coordinated triggering and detonation device includes: a fuel ratio control system, a pre-combustion chamber, a jet tube, and a detonation chamber; The fuel ratio control system is used to provide and control the mixed fuel gas of ethylene, oxygen and nitrogen to the pre-combustion chamber; the inlet of the pre-combustion chamber is connected to the outlet of the fuel ratio control system, and an ignition component is provided inside the pre-combustion chamber; there are multiple jet pipes forming a ring array, and the inlet of all jet pipes is directly connected to the outlet of the pre-combustion chamber, and the circumferential diameter of the ring array is 6mm; the inlet end of the detonation chamber is connected to the outlet end of all jet pipes, and the detonation chamber has a square cross-section structure with internal dimensions of 30mm wide × 30mm deep × 200mm long.

[0008] In one embodiment, the number of jet tubes is 6, arranged in a symmetrical ring; the center of the ring array coincides with the center of the inlet section of the detonation chamber.

[0009] In one embodiment, the inner diameter of the jet tube is 2.45 mm.

[0010] In one embodiment, the length of the jet tube L p It is 100-200mm in diameter, and its axis is perpendicular to the inlet plane of the detonation chamber.

[0011] In one embodiment, at least one transparent observation window is provided on the wall of the detonation chamber.

[0012] In one embodiment, the fuel ratio control system includes independent ethylene, oxygen, and nitrogen pipelines, which converge before a mixing chamber; the nitrogen and oxygen pipelines are equipped with features for adjusting the nitrogen-to-oxygen dilution ratio. β The flow meter, among which β The adjustment range is 0≤ β ≤1.

[0013] In another aspect of this application, a method for multi-shock wave coordinated triggering and detonation using the above-described device is provided, comprising the following steps: S1: A mixture of ethylene, oxygen, and nitrogen is introduced into the device to fill the pre-combustion chamber, jet pipe, and detonation chamber; S2: The mixed gas in the pre-combustion chamber is ignited by the ignition component in the pre-combustion chamber, and the flame synchronously enters each jet tube arranged in a ring array; S3: After the flame develops inside the jet tube, it is ejected from the jet tube outlet, forming multiple leading shock waves that enter the detonation chamber. S4: The leading shock wave propagates in the detonation chamber and is reflected by the wall to form a reflected shock wave; S5: The leading shock wave and the reflected shock wave converge in the detonation chamber, forming a high-temperature and high-pressure zone and inducing the generation of local hot spots, which in turn couple with the flame to accelerate the chemical reaction, thereby triggering the detonation.

[0014] In one embodiment, the detonation chamber is 30mm wide × 30mm deep × 200mm long, and the circumferential diameter of the annular array is 6mm.

[0015] In one embodiment, the leading shock wave enters the detonation chamber at a speed of 1931.6 m / s and, after being reflected by the wall, forms a collision angle of 30°-60° with the flame front.

[0016] In one embodiment, the jet forms a ring-shaped shock wave network through the jet tubes arranged in a ring array. When the ring-shaped shock wave network collides in the detonation chamber, the local pressure rises sharply to 2.1 MPa, and a hot spot cluster is generated through shock wave interference. The hot spot cluster occurs in an area 80-120 mm away from the entrance of the detonation chamber. The hot spot diameter of the hot spot cluster is 5-8 mm and the temperature is ≥3000 K.

[0017] The beneficial effects of this application are as follows: 1) A shock wave collision network constructed through a six-tube ring array forms a dense cluster of hot spots in the center of detonation chamber 3, reducing the detonation distance from over 100 mm for traditional single-tube jets to between 43 mm and 60 mm. This is particularly beneficial in terms of dilution ratio. β Under the harsh operating condition of 0.8, the detonation success rate has been steadily increased from 65% for single-tube structures to over 85%.

[0018] 2) The enhancement effect generated by multiple shock wave collisions reduces the occurrence of hot spot extinction problems under high dilution ratio conditions, and lowers the nitrogen dilution ratio limit for stable initiation from... β =0.6 increased to β =0.8 or above.

[0019] 3) The ring array disperses the concentrated energy into multiple synchronous shock wave sources, and achieves efficient energy convergence through the orderly collision of multiple shock waves, solving the problem of excessive energy demand for direct detonation at a single point.

[0020] 4) The ring array covers the entire cross section of the detonation chamber 3. By generating multiple synchronous hot spots, the energy blind zone of the single jet is eliminated, realizing a technological leap from "single-point burst" to "network collaboration".

[0021] 5) The integrated design of the six-tube ring array and the square detonation chamber 3 reduces the device volume by 30%. The quartz glass window and high-speed camera system support real-time optical diagnosis of the hotspot evolution process, providing data support for engineering transplantation.

[0022] 6) The gas can be pre-combusted in the pre-combustion chamber 1, which greatly shortens the time difference between the flame entering different jet tubes 2, so that the flame enters the jet tube 2 synchronously, and then the six jets are simultaneously transmitted into the detonation chamber 3, realizing the orderly collision, reflection and coupling of multiple shock waves. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the structure of the multi-shock wave coordinated triggering and detonation device according to an embodiment of this application; Figure 2 This is a schematic diagram of a multi-shock wave detonation embodiment of this application; Figure 3 This is a schematic diagram of the fuel ratio control system according to an embodiment of this application; In the diagram: 1-Pre-combustion chamber, 2-Jet tube, 3-Detonation chamber, 4-Observation window. Detailed Implementation

[0024] The technical solution of this application will be clearly and completely described below with reference to specific embodiments. However, those skilled in the art will understand that the embodiments described below are only some embodiments of this application, not all embodiments, and are only used to illustrate this application, and should not be regarded as limiting the scope of this application. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0025] In one specific implementation, refer to Figures 1-3 As shown, a multi-shock wave coordinated triggering and detonation device is provided, including: a fuel ratio control system, a pre-combustion chamber 1, a jet tube 2, and a detonation chamber 3; The fuel ratio control system is used to provide and control the mixed fuel gas of ethylene, oxygen and nitrogen to the pre-combustion chamber 1; the inlet of the pre-combustion chamber 1 is connected to the outlet of the fuel ratio control system, and the pre-combustion chamber 1 is equipped with an ignition component; the jet pipe 2 is a six-tube annular array, and the inlet of the jet pipe 2 is directly connected to the outlet of the pre-combustion chamber 1; the inlet end of the detonation chamber 3 is connected to the outlet ends of all jet pipes 2, and the detonation chamber 3 has a square cross-section structure.

[0026] The fuel ratio control system introduces and fills the pre-combustion chamber 1, jet pipe 2, and detonation chamber 3 with a proportionally mixed gas mixture. The ignition component in the pre-combustion chamber 1 is ignited (e.g., spark plug discharge), igniting the combustible mixture in the pre-combustion chamber 1. The gas is pre-combusted in the pre-combustion chamber 1, which greatly shortens the time difference between the flames entering different jet pipes 2, allowing the flames to enter the jet pipes 2 synchronously, and then allowing the six jets to enter the detonation chamber 3 synchronously, realizing the orderly collision, reflection, and coupling of multiple shock waves. The flame rapidly develops within the pre-combustion chamber 1. Due to its direct connection between the outlet and the inlet of the jet pipes 2, and the pressure equalization and flow guiding effect of the pre-combustion chamber 1, the flame synchronously enters the six jet pipes 2. After accelerating within the jet pipes 2, the flame generates a leading shock wave. This leading shock wave exits from the nozzle and enters the square detonation chamber 3. The leading shock wave propagates axially along the detonation chamber 3, compressing the unburned gas mixture ahead. It is then reflected by the inner wall of the detonation chamber 3, forming a reflected shock wave. The leading shock wave and the reflected shock wave converge in the center of the detonation chamber 3, forming a ring-shaped shock wave collision network. The mutual interference of the shock waves increases the pressure, creating a high-temperature, high-pressure zone. This couples with the flame, accelerating the chemical reaction. Collisions between adjacent transverse waves induce the generation of local hotspot clusters. During the collision of the ring-shaped shock wave network formed by the multiple jets, hotspots with a diameter of approximately 5 mm are induced in the center of the detonation chamber 3, rapidly generating free radicals such as CH•, OH•, and O•. Ultimately, this achieves the orderly collision, reflection, and coupling of multiple shock waves.

[0027] In some embodiments, the circumferential diameter of the annular array is 6 mm, and the internal dimensions of the detonation chamber 3 are: 30 mm wide × 30 mm deep × 200 mm long. The square cross-section, combined with the wall reflection angle, allows the formation of a regular shock wave system through wall reflection. This system, through repeated collisions with the flame, generates RM instability, accelerating the conversion of turbulent flame into detonation. β When the value is 0.4, the DDT distance can be shortened by 50%.

[0028] Among them, reference Figure 2 As shown, the leading shock wave enters the detonation chamber 3 from the jet tube 2 at a speed of 1931.6 m / s and produces a diffraction effect. After being reflected by the wall of the detonation chamber 3 at 45°±5°, the diffracted wave forms a collision angle of 30°-60° with the flame front. In the region 80-120 mm away from the inlet of the detonation chamber 3, a high temperature and high pressure zone with a diameter of 5-8 mm and a temperature ≥3000 K is induced. The chemical reaction is accelerated by the chain reaction of free radicals such as CH•, OH•, and O•. The free radicals are mixed by the turbulent flow induced by the shock wave, causing the ethylene molecules to decompose into intermediate products such as C2H3• and CH2•.

[0029] The collision mechanism of the annular shock wave network is as follows: the leading shock wave ejected from the jet pipe 2 propagates along the axis of the detonation chamber 3 at a speed of 1931.6 m / s. Adjacent shock waves form an annular collision network with an angle of 30°-60° in a region 80-120 mm away from the inlet of the detonation chamber 3, causing the local pressure to rise sharply to 2.1 MPa. Through shock wave interference, a hot spot group with a diameter of 5-8 mm is generated, realizing the orderly collision and energy relay of multiple shock waves.

[0030] In some embodiments, the number of jet tubes 2 is six, arranged in a symmetrical ring to form a ring array. The circumferential diameter of the ring array is 6 mm. The center of the ring array precisely coincides with the center of the inlet section of the detonation chamber 3, ensuring that the leading shock waves ejected from all jet tubes 2 can enter the detonation chamber 3 synchronously and symmetrically, so as to form a ring shock wave collision network.

[0031] Each of the jet tubes 2 has an inner diameter of 2.45 mm and a length of... L p The length is adjustable within a variable range, i.e., 100-200mm. The axis of the jet tube 2 is perpendicular to the inlet plane of the detonation chamber 3. The length of the jet tube 2 is adjustable from 100-200mm, enabling dynamic control of the shock wave intensity. L p When the diameter is 100mm, the exit velocity is 1931.6m / s, directly triggering detonation; when L p When the velocity drops to 1388 m / s at 200 mm, it detonates upon collision with the wall after coupling with the flame, thus solving the problem of poor adaptability to working conditions caused by the fixed length of traditional single jets.

[0032] In some embodiments, reference is made to Figure 3 As shown, the fuel ratio control system includes independent ethylene, oxygen, and nitrogen pipelines, which converge before the mixing chamber. The volumetric flow rate ratio of nitrogen to oxygen is specified. β Adjust by flow meter β The adjustment range is 0≤ β ≤1.

[0033] β =0-1 wide range adjustment allows for precise control of fuel activity, when β When the shock wave intensity is ≤0.2, multiple shock wave collisions form local high-temperature and high-pressure regions, inducing rapid chemical reactions, and the intensity of multiple jets is increased by 17.8% compared to a single jet; when β When the value is ≥0.6, the shock wave attenuation is reduced by the arrangement of the annular jet, and the hot spot intensity can still be maintained under a high dilution ratio, breaking through the explosive limit of traditional technology.

[0034] In some embodiments, for ease of observation, a transparent quartz glass observation window 4 is provided on the side wall of the detonation chamber 3, enabling real-time optical diagnosis of the detonation process via a high-speed camera. The camera is an i-SPEED 713, equipped with a 400-700nm bandpass filter, and the spark plug and high-speed camera are synchronously triggered via a BNC line.

[0035] In another specific embodiment, refer to Figures 1-3 As shown, a shock wave-coordinated triggering and detonation method is provided, including the following steps: S1: A mixed combustion gas of ethylene, oxygen and nitrogen is introduced into the device to fill the pre-combustion chamber 1, the jet pipe 2 and the detonation chamber 3.

[0036] The inlet of the pre-combustion chamber 1 is connected to the outlet of the fuel ratio control system, and the pre-combustion chamber 1 is equipped with an ignition component; the jet tube 2 is a six-tube annular array, and the inlet of the jet tube 2 is directly connected to the outlet of the pre-combustion chamber 1; the inlet of the detonation chamber 3 is connected to the outlet of all the jet tubes 2, and the detonation chamber 3 has a square cross-section structure.

[0037] In some embodiments, the annular array has a circumferential diameter of 6 mm, the number of jet tubes 2 is 6, the inner diameter is 2.45 mm, and the length is... L p The diameter of each jet tube 2 is 100-200mm, and the axis of each jet tube 2 is perpendicular to the inlet plane of the detonation chamber 3. The internal dimensions of the detonation chamber 3 are: 30mm wide × 30mm deep × 200mm long.

[0038] S2: The mixed gas in the pre-combustion chamber 1 is ignited by the ignition component in the pre-combustion chamber 1, and the flame enters the jet pipes 2 arranged in the annular array simultaneously.

[0039] The mixture of ethylene, oxygen, and nitrogen gas filling the pre-combustion chamber 1 is ignited by a spark plug installed inside the pre-combustion chamber 1, causing initial combustion within the chamber. Since the outlet of the pre-combustion chamber 1 is directly connected to the inlet of the jet pipe 2, and the chamber's design serves to equalize pressure and synchronize flow, the flames generated by combustion can synchronously enter the inlets of each jet pipe 2 arranged in a ring array.

[0040] S3: After the flame develops inside the jet tube 2, it is ejected from the outlet of the jet tube 2, forming multiple leading shock waves that enter the detonation chamber 3.

[0041] After the flame enters each jet tube 2, it continues to accelerate and develop within the tube. During this process, accompanied by intense combustion and compression effects, a strong pressure wave is generated and rapidly intensifies into a leading shock wave. The flame and the leading shock wave propagate forward together within the jet tube 2. When it reaches the outlet of the jet tube 2, the leading shock wave is ejected from the outlet at high speed first, and multiple leading shock waves from multiple jet tubes 2 are simultaneously introduced into the inlet of the detonation chamber 3.

[0042] S4: The leading shock wave propagates within the detonation chamber 3 and is reflected by the wall to form a reflected shock wave.

[0043] After the multiple leading shock waves enter the detonation chamber 3, they propagate forward along the axial direction of the chamber, pre-compressing the unburned gas mixture in front of them. When the leading shock waves reach the wall of the detonation chamber 3, due to the diffraction effect generated by the leading shock waves entering the chamber 3 from behind the jet pipe 2, the leading shock waves are reflected by the wall of the detonation chamber 3 at an angle of 45°±5° to form reflected waves. The propagation direction of the reflected waves intersects with the propagation path of the original leading shock waves.

[0044] S5: The leading shock wave and the reflected shock wave converge in the detonation chamber 3, forming a high-temperature and high-pressure zone and inducing the generation of local hot spots, which couple with the flame to accelerate the chemical reaction, thereby triggering the detonation.

[0045] In some embodiments, the propagation speed of the leading shock wave entering the detonation chamber 3 is 1931.6 m / s. After being reflected by the wall of the detonation chamber 3, the propagation path of the leading shock wave forms a collision angle of 30°-60° with the subsequently arriving flame front. This collision occurs in an axial region 80-120 mm from the inlet end face of the detonation chamber 3.

[0046] Multiple shock waves, synchronously injected by multi-jet tubes 2 arranged in a ring array, form a regular ring-shaped shock wave network within the detonation chamber 3. When the shock wave fronts within this ring-shaped shock wave network collide with each other in the central region of the detonation chamber 3, a strong shock wave interference effect is generated. This interference effect causes a sharp increase in local gas pressure in the collision region, reaching a maximum of approximately 2.1 MPa. Under high temperature and pressure, the mutual interference between the shock waves induces the formation of a hotspot cluster. In a preferred embodiment, the hotspot cluster occurs within a region 80-120 mm from the inlet of the detonation chamber 3, and the hotspots in the cluster have a diameter of 5-8 mm and a temperature ≥3000 K.

[0047] Example 1 Reference Figures 1-3 As shown, this embodiment provides a multi-shock wave coordinated triggering and detonation device, including a fuel ratio control system, a pre-combustion chamber 1, a jet pipe 2, and a detonation chamber 3.

[0048] The jet tubes 2 consist of six tubes, each with an inner diameter of 2.45 mm and a length of 150 mm. These tubes are symmetrically arranged in a ring array on a 6 mm diameter circle, forming a six-tube ring array. The length of each jet tube 2 is... L p The jet tube 2 is 100-200mm long. One end of the jet tube 2 is connected to the output end of the pre-combustion chamber 1, and the other end is connected to the input end of the detonation chamber 3. The jet tube 2 extends along the axial direction of the detonation chamber 3, and the axis is perpendicular to the inlet plane of the detonation chamber 3. At the same time, the center of the six-tube annular array coincides with the inlet center of the detonation chamber 3.

[0049] The uniform distribution of the 6-tube ring array can generate 6 symmetrical shock waves, forming a regular shock wave collision zone at the 3 inlet of the detonation chamber. Compared with the single shock wave of the traditional single jet, the detonation distance can be shortened from more than 100mm to 43-60mm.

[0050] The pre-combustion chamber 1 has a volume of approximately 100 cubic centimeters. The gas is pre-combusted in the pre-combustion chamber 1, which significantly shortens the time difference between the flames entering different jet tubes 2, allowing the flames to enter the jet tubes 2 synchronously. This, in turn, allows the six jets to enter the detonation chamber 3 synchronously, achieving orderly collision, reflection, and coupling of multiple shock waves.

[0051] The detonation chamber 3 has a square cross-section structure with internal dimensions of 30mm wide × 30mm deep × 200mm long.

[0052] The fuel ratio control system includes independent ethylene, oxygen, and nitrogen pipelines. Flow meters are installed in the oxygen and nitrogen pipelines to adjust the volumetric flow rate ratio of nitrogen to oxygen. β Specifically, ethylene and oxygen are combined in a 1:3 volume ratio (appropriate chemical ratio), and then premixed with nitrogen in the mixing chamber before detonation chamber 3. β =0.8), which is transported to the pre-combustion chamber 1 through a transition pipe with an inner diameter of 6mm.

[0053] When the shock wave propagates to the middle of detonation chamber 3 (80 mm from the entrance), it couples with the flame front, inducing local energy accumulation at the crescent-shaped flame front (symmetrically positioned 10 mm from the upper and lower walls). Schlieren image sequences show that the brightness of this area increases sharply at 7.847 ms, forming an explosion hotspot with a diameter of about 5 mm, triggering the detonation wave.

[0054] In this embodiment, after the mixed gas with an initial pressure of 1 atm and a temperature of 293 K is ignited, the leader shock wave enters the detonation chamber 3 at an ultrasonic speed of 1931.6 m / s first, and forms a symmetrical shock wave system after being reflected by the upper and lower walls, while the jet flame enters about 3 μs later due to the reduced fuel activity.

[0055] When the shock wave propagates to the middle of detonation chamber 3 (80 mm from the entrance), it couples with the flame front, inducing local energy accumulation at the crescent-shaped flame front (symmetrically positioned 10 mm from the upper and lower walls). Schlieren image sequences show that the brightness of this area increases sharply at 7.847 ms, forming an explosion hotspot with a diameter of about 5 mm, triggering the detonation wave.

[0056] Comparative Example Similar to Example 1, except that the multi-jet tube was removed and replaced with a single-jet tube with an inner diameter of 6mm to ensure that the detonation energy remained unchanged, and the experiment was repeated.

[0057] Compared with single-jet initiation (initiation distance of 85mm under the same conditions), this application reduces the initiation distance to 70mm (reduction of about 18%) through the wall reflection synergy of the annular jet, while increasing the initiation success rate from 65% for single jet to 85% for multi-jet, verifying the effectiveness of shock wave-flame composite drive under high dilution ratio.

[0058] Although the embodiments of this application have been described above in conjunction with the accompanying drawings, this application is not limited to the specific embodiments and application fields described above. The specific embodiments described above are merely illustrative and instructive, not restrictive. Those skilled in the art can make many other forms based on the guidance of this specification and without departing from the scope of protection of the claims of this application, and these are all within the scope of protection of this application.

Claims

1. A multi-shock wave coordinated triggering and detonation device, characterized in that, This includes a fuel ratio control system, a pre-combustion chamber, a jet tube, and a detonation chamber; The fuel ratio control system is used to provide and control the mixed fuel gas of ethylene, oxygen and nitrogen to the pre-combustion chamber; the inlet of the pre-combustion chamber is connected to the outlet of the fuel ratio control system, and an ignition component is provided inside the pre-combustion chamber; there are multiple jet pipes forming a ring array, and the inlet of all jet pipes is directly connected to the outlet of the pre-combustion chamber, and the circumferential diameter of the ring array is 6mm; the inlet end of the detonation chamber is connected to the outlet end of all jet pipes, and the detonation chamber has a square cross-section structure with internal dimensions of 30mm wide × 30mm deep × 200mm long.

2. The multi-shock wave coordinated triggering and detonation device according to claim 1, characterized in that, The number of jet tubes is 6, arranged in a symmetrical ring; the center of the ring array coincides with the center of the inlet section of the detonation chamber.

3. The multi-shock wave coordinated triggering and detonation device according to claim 1, characterized in that, The inner diameter of the jet tube is 2.45 mm.

4. The multi-shock wave coordinated triggering and detonation device according to claim 1, characterized in that, The length of the jet tube L p It is 100-200mm in diameter, and its axis is perpendicular to the inlet plane of the detonation chamber.

5. The multi-shock wave coordinated triggering and detonation device according to claim 1, characterized in that, At least one transparent observation window is provided on the wall of the detonation chamber.

6. A method for multi-shock wave coordinated triggering and detonation using the device described in any one of claims 1 to 5, characterized in that, Includes the following steps: S1: A mixture of ethylene, oxygen, and nitrogen is introduced into the device to fill the pre-combustion chamber, jet pipe, and detonation chamber; S2: The mixed gas in the pre-combustion chamber is ignited by the ignition component in the pre-combustion chamber, and the flame synchronously enters each jet tube arranged in a ring array; S3: After the flame develops inside the jet tube, it is ejected from the jet tube outlet, forming multiple leading shock waves that enter the detonation chamber. S4: The leading shock wave propagates in the detonation chamber and is reflected by the wall to form a reflected shock wave; S5: The leading shock wave and the reflected shock wave converge in the detonation chamber, forming a high-temperature and high-pressure zone and inducing the generation of local hot spots, which in turn couple with the flame to accelerate the chemical reaction, thereby triggering the detonation.

7. The multi-shock wave coordinated triggering and detonation method according to claim 6, characterized in that, The leading shock wave enters the detonation chamber at a speed of 1931.6 m / s and, after being reflected by the wall, forms a collision angle of 30°-60° with the flame front.

8. The multi-shock wave coordinated triggering and detonation method according to claim 6, characterized in that, The jets form a ring-shaped shock wave network through the jet tubes arranged in a ring array. When the ring-shaped shock wave network collides in the detonation chamber, the local pressure rises sharply to 2.1 MPa, and a hot spot cluster is generated through shock wave interference. The hot spot cluster occurs in the area 80-120 mm away from the entrance of the detonation chamber. The hot spot diameter of the hot spot cluster is 5-8 mm and the temperature is ≥3000 K.

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