Detonation mechanism and detonation engine

Abstract

This application discloses a detonation mechanism and a detonation engine. The detonation mechanism includes a detonation chamber, which comprises: a detonation cavity having a first outlet; an inlet on the cavity wall for combustible gas to enter; and an exhaust chamber communicating with the detonation cavity, having a second outlet, through which the gas produced by detonation within the detonation cavity is discharged. In this embodiment, when a vacuum low pressure is generated within the detonation cavity at the moment of detonation, if some of the discharged exhaust gas is drawn back into the detonation cavity, this portion of exhaust gas can enter the exhaust chamber and then be discharged through the second exhaust port. This avoids the residual large amount of detonation-suppressing gas within the detonation cavity, which could affect the stability of continuous detonation.

Description

Technical Field

[0001] This disclosure relates to new energy industry technologies, specifically to a detonation mechanism and a detonation engine. Background Technology

[0002] In detonation engines of related technologies, the detonation chamber of the detonation mechanism that causes detonation usually has a detonation cavity. Most of the high-temperature and high-pressure exhaust gas generated by detonation is discharged through the outlet of the detonation cavity. However, at the moment of detonation, a vacuum and low pressure are generated in the detonation cavity, which causes some of the exhaust gas that has been discharged to be drawn back into the detonation cavity and cannot be discharged. Since the back-drawn exhaust gas contains a large amount of nitrogen, carbon dioxide and water vapor, which are detonation suppressing gases that inhibit the detonation reaction, especially when the detonation frequency is high, a large amount of detonation suppressing gases will affect the stability of continuous detonation, and thus affect the stable output of the detonation engine. Utility Model Content

[0003] The purpose of this disclosure is to provide a detonation mechanism and a detonation engine to overcome the problem of insufficient detonation stability in existing detonation mechanisms.

[0004] According to a first aspect of the present disclosure, a detonation mechanism is provided, the detonation mechanism including a detonation chamber, the detonation chamber including: a detonation cavity having a first outlet; an inlet for entering combustible gas is provided on the cavity wall of the detonation cavity; and an exhaust cavity communicating with the detonation cavity having a second outlet, the gas after detonation in the detonation cavity being discharged through the first outlet and the second outlet.

[0005] The detonation mechanism provided in this embodiment has a detonation chamber and an exhaust chamber that are interconnected. Most of the exhaust gas generated after detonation in the detonation chamber is discharged through the first exhaust port, while a portion enters the exhaust chamber and is discharged through the second exhaust port, facilitating exhaust. Moreover, since detonation is not required in the exhaust chamber, the temperature inside the exhaust chamber is lower than that inside the detonation chamber. When a vacuum low pressure is generated in the detonation chamber at the moment of detonation, if some of the discharged exhaust gas is drawn back into the detonation chamber, due to the influence of temperature and pressure differences, this portion of exhaust gas can enter the exhaust chamber and then be discharged through the second exhaust port. This avoids the residual large amount of detonation suppressant gas in the detonation chamber, which could affect the stability of continuous detonation.

[0006] Furthermore, in some embodiments, the first and second exhaust ports are located at the same end of the detonation chamber. This design facilitates the concentrated exhaust of combustible gases in the detonation chamber in the same direction after detonation, thereby enabling the detonation chamber to directly or indirectly transmit a larger thrust to the rotating mechanism of the detonation engine, driving the rotating shaft of the rotating mechanism to rotate rapidly.

[0007] Furthermore, in some embodiments, the air inlet is located on the cavity wall of the detonation chamber at the end away from the first air outlet. This allows the shock wave generated after the combustible gas detonation to propagate in large quantities towards the direction of the first air outlet, rather than impacting the cavity wall in the reverse direction and wasting work, thus improving transmission efficiency.

[0008] Furthermore, in some embodiments, the exhaust chamber is located outside the detonation chamber, and the sidewall of the exhaust chamber facing the detonation chamber is shared with the sidewall of the detonation chamber facing the exhaust chamber.

[0009] In these embodiments, at least a portion of the wall of the detonation chamber is shared with a portion of the wall of the exhaust chamber, resulting in a simple detonation chamber structure and small footprint. Furthermore, the adjacent design of the detonation chamber and exhaust chamber facilitates the rapid entry of exhaust gas generated after the detonation of combustible gas in the detonation chamber into the exhaust chamber. Moreover, by placing the exhaust chamber outside the detonation chamber, its wall has more contact with the outside environment, resulting in a lower temperature in the exhaust chamber compared to the detonation chamber. During the detonation, when some of the already discharged exhaust gas is drawn back into the detonation chamber, the temperature and pressure differences further facilitate the rapid entry of this back-drawn exhaust gas into the exhaust chamber. This portion of exhaust gas can form a vortex with the back-drawn exhaust gas in the exhaust chamber and be discharged through the second outlet, preventing the presence of excessive residual detonation-suppressing gas in the detonation chamber, which could affect the stability of continuous detonation.

[0010] Furthermore, in some embodiments, the exhaust chamber is located on one side of the detonation chamber and is distributed side by side with the detonation chamber at intervals.

[0011] In these embodiments, the exhaust chamber and detonation chamber are spaced apart and do not share a common wall. This results in a lower temperature inside the exhaust chamber, especially when the chamber wall is in direct contact with the outside environment. The temperature inside the exhaust chamber is significantly lower than that in the detonation chamber. Therefore, during detonation, the temperature and pressure differences facilitate the rapid entry of exhaust gas back into the detonation chamber, preventing the presence of excessive residual detonation-suppressing gas in the detonation chamber and thus maintaining the stability of continuous detonation. Furthermore, this arrangement allows for separate forming of the exhaust chamber and detonation chamber, simplifying manufacturing.

[0012] Furthermore, in some embodiments, the detonation chamber includes: an inner liner, the inner cavity of which forms the detonation chamber, and one end of the inner liner having a first vent; and an outer liner disposed on the outer periphery of the inner liner, the space between the outer liner and the inner liner forming an exhaust chamber, one end of which has a second vent. The second vent and the first vent are located at the same end of the detonation chamber, the second vent being located on the outer periphery of the first vent, and the inner liner wall having a connecting hole communicating with the detonation chamber and the exhaust chamber. Here, the inner liner and the outer liner respectively form the detonation chamber and the exhaust chamber, resulting in a simple structure and ease of manufacturing.

[0013] Furthermore, in some embodiments, the outer liner partially surrounds the inner liner in the height direction, so that the end of the inner liner away from the first air outlet is exposed, and the end of the outer liner away from the first air outlet is circumferentially sealed to the outer peripheral wall of the inner liner; or the outer liner surrounds the outer peripheral wall of the inner liner and the bottom wall away from the first air outlet; or the outer liner partially surrounds the inner liner in the circumferential direction and shares a portion of the outer peripheral wall of the inner liner.

[0014] In these embodiments, the outer liner can partially surround the inner liner, with one end of the inner liner exposed in the height direction, or a portion of the inner liner exposed in the circumferential direction. This reduces the material used in the outer liner, lowering costs and minimizing its space occupation. Furthermore, it facilitates the placement of an air inlet on the exposed portion of the inner liner, eliminating the need for the air inlet to penetrate the outer liner and directly connect to the detonation chamber, simplifying manufacturing. Alternatively, the outer liner can completely surround the inner liner, including its outer peripheral wall and the bottom wall away from the first air outlet. This provides ample space in the exhaust chamber, facilitating the entry of exhaust gas and its discharge through the second air outlet. Moreover, it eliminates the need to consider the sealing between the outer and inner liners, simplifying outer liner manufacturing.

[0015] Furthermore, in some embodiments, there are multiple connecting holes, which are circumferentially spaced on the outer peripheral wall of the inner liner. This facilitates the entry of exhaust gas generated after detonation into the exhaust chamber.

[0016] Furthermore, in some embodiments, the connecting hole is connected to the end of the exhaust chamber furthest from the second outlet. This helps ensure that sufficient gas is discharged through the first outlet to perform work after detonation. Moreover, it facilitates the entry of waste gas that is instantly drawn back into the detonation chamber into the exhaust chamber through the connecting hole, forming a vortex with the waste gas drawn back into the exhaust chamber, and then being discharged through the second outlet.

[0017] Furthermore, in some embodiments, the detonation chamber includes: a first chamber, the inner cavity of which forms a detonation chamber, and one end of the first chamber having a first vent; and a second chamber, arranged side-by-side on one side of the first chamber and spaced apart from it, the inner cavity of the second chamber forming an exhaust chamber, and one end of the second chamber having a second vent. The first and second chambers are connected by a connecting portion. Here, the first and second chambers are used to form the detonation chamber and the exhaust chamber respectively, resulting in a simple structure and ease of manufacturing.

[0018] Furthermore, in some embodiments, the detonation mechanism further includes an igniter disposed on the wall of the detonation chamber, the igniter being used to ignite the combustible gas within the detonation chamber. This facilitates the direct ignition of the combustible gas using the igniter, causing detonation.

[0019] Furthermore, in some embodiments, the igniter is positioned near the air inlet on the wall of the detonation chamber, or the igniter extends into the detonation chamber through the air inlet. The abundance of combustible gas near the igniter ensures that detonation occurs after ignition.

[0020] Furthermore, in some embodiments, the detonation chamber wall has a mounting port, and a mounting bracket is provided at the mounting port, with the air inlet and igniter both integrated on the mounting bracket. Installation is convenient.

[0021] A detonation engine is provided according to a second aspect of the present disclosure, including the detonation mechanism as provided in the first aspect of the present disclosure.

[0022] The detonation engine disclosed herein has the detonation mechanism of any of the above embodiments, and thus has the beneficial effects of any of the above embodiments, which will not be described in detail here. Attached Figure Description

[0023] Other features, objects, and advantages of this application will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0024] Figure 1 This is a schematic diagram of the structure of a detonation engine according to one embodiment;

[0025] Figure 2 This is a three-dimensional structural schematic diagram of a detonation engine according to one embodiment;

[0026] Figure 3 for Figure 2 A three-dimensional structural diagram of a detonation engine with the end caps of the fixed structure removed;

[0027] Figure 4 An exploded view of the detonation mechanism of a detonation engine according to one embodiment;

[0028] Figure 5 A cross-sectional view of the detonation mechanism of a detonation engine according to one embodiment;

[0029] Figure 6 This is a schematic diagram of the detonation mechanism of a detonation engine according to one embodiment;

[0030] Figure 7 A schematic diagram of the detonation chamber exhaust principle of a detonation engine according to one embodiment. Figure 1 ;

[0031] Figure 8 A schematic diagram of the detonation chamber exhaust principle of a detonation engine according to one embodiment. Figure 2 ;

[0032] Figure 9 A cross-sectional view of a double-layered detonation chamber of a detonation engine according to one embodiment;

[0033] Figure 10 A cross-sectional view of a dual-chamber detonation chamber of a detonation engine according to one embodiment;

[0034] Figure 11 A cross-sectional view of the dual-chamber detonation chamber of a detonation engine according to another embodiment;

[0035] Figure 12 An exploded view of the fixing mechanism of a detonation engine according to one embodiment;

[0036] Figure 13 for Figure 12 A three-dimensional structural diagram of the shell from another angle;

[0037] Figure 14 This is a schematic diagram of the pressurization mechanism of a detonation engine according to one embodiment;

[0038] Figure 15 An exploded view of the rotating mechanism of a detonation engine according to one embodiment (rotating shaft not shown);

[0039] Figure 16 for Figure 15 A three-dimensional structural diagram of the middle cover from another angle;

[0040] Figure 17 for Figure 15 A three-dimensional structural diagram of the inner shell from another angle;

[0041] Figure 18 for Figure 15 A three-dimensional structural diagram of the flywheel;

[0042] Figure 19 for Figure 15 A three-dimensional structural diagram of the flywheel housed within the outer casing;

[0043] Figure 20 for Figure 19 A magnified view of a portion of region III;

[0044] Figure 21 A cross-sectional view of the rotating mechanism of a detonation engine according to one embodiment;

[0045] Figure 22 for Figure 21 A magnified view of a portion of region II;

[0046] Figure 23 An exploded view of the separation mechanism of a detonation engine according to one embodiment;

[0047] Figure 24 This is a schematic diagram of the main body of the separation mechanism of a detonation engine according to one embodiment;

[0048] Figure 25 This is a schematic diagram of the water circulation logic of a detonation engine according to one embodiment.

[0049] Explanation of reference numerals in the attached figures:

[0050] 1. Pressurization mechanism; 10. Pressurization pipe; 11. Connecting plate; 12. Working fluid inlet;

[0051] 2. Detonation mechanism; 21. Detonation chamber; 211. Inner liner; 2111. Detonation cavity; 2112. First outlet; 2113. Connecting hole; 2114. Flange; 212. Outer liner; 2121. Limiting groove; 213. Exhaust cavity; 2131. Second outlet; 214. First liner; 215. Second liner; 216. Connecting part; 22. Air inlet; 23. Hydrogen inlet; 24. Ignition device; 25. Mounting bracket;

[0052] 3 Rotating mechanism; 31 Cover; 311 Recessed receiving part; 312 First annular protrusion; 32 Outer shell; 321 Outer shell inlet; 322 Outlet; 323 Second annular protrusion; 324 Connecting wall; 325 Protrusion; 326 Sleeve; 33 Rotating disk; 331 First cover plate; 332 Second cover plate; 333 Flywheel; 3331 Wing; 3332 Second groove; 3333 One-way flow channel; 3334 Connecting groove; 3335 Stop part; 334 Annular groove; 335 First groove; 34 Rotating shaft; 35 First bearing; 36 Second bearing;

[0053] 4 Separation mechanism; 40 Inner wall; 41 Separation body; 410 Baffle; 411 Sealing ring; 412 First sealing partition; 4121 Free end; 413 Second sealing partition; 4131 Free end; 414 Air guide channel; 4141 Closed end; 4142 Open end; 415 Separation chamber inlet; 416 Separation chamber outlet; 417 Liquid port; 418 Exhaust pipe; 419 Anti-backflow plate; 42 Sealing cover; 421 Heat sink;

[0054] 5. Fixing mechanism; 51. Fixing cover; 511. Through hole; 52. Fixing shell; 521. Fixing shell bottom wall; 5211. Cooling medium inlet; 5212. Cooling medium outlet; 5213. Mounting groove; 5214. Limiting rib; 5221. Fixing wall; 523. First connection port; 53. Boss;

[0055] 6. Circulating pump; 7. Solenoid valve; 9. Cooling medium. Detailed Implementation

[0056] The present application will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the relevant application and not intended to limit the application. For ease of description, only the parts relevant to this application are shown in the accompanying drawings. It should be noted that, unless otherwise specified, the embodiments and features described in these embodiments can be combined with each other.

[0057] This application provides a detonation engine for generating kinetic energy by detonating a combustible gas of low purity. Furthermore, the generated kinetic energy can also be used to generate electricity. The combustible gas includes, but is not limited to, hydrogen, and can also be other clean energy sources. For ease of description, the following example uses a mixture of hydrogen and an oxidizing gas.

[0058] In one embodiment, such as Figure 1 As shown, the detonation engine of this embodiment includes: a detonation mechanism 2, a pressurization mechanism 1 connected to the detonation mechanism 2, and a rotation mechanism 3 connected to the pressurization mechanism 1. The combustible gas entering the detonation mechanism 2 can be ignited and detonated to generate a shock wave. The working fluid in the pressurization mechanism 1 can receive and transmit the pressure generated by the shock wave, and enter the rotation mechanism 3 to drive the rotation shaft 34 of the rotation mechanism 3 to rotate.

[0059] The detonation mechanism 2 is a chamber structure and is the part that generates pressure. It is filled with a mixture of hydrogen and an oxidizing gas. This mixture refers to a gas mixture that will undergo a detonation reaction upon ignition. For example, it could be a mixture of hydrogen and oxygen, or a mixture of hydrogen and air; hereinafter referred to as the hydrogen mixture. Ignition of the detonation mechanism 2, which is filled with the hydrogen mixture, causes a detonation within its chamber, generating a detonation shock wave and thus pressure.

[0060] The pressurizing mechanism 1 is also a chamber structure, responsible for transmitting pressure. A working medium (the medium that performs the work) is injected into the pressurizing mechanism 1, and this working medium withstands the pressure generated by the detonation shock wave produced by the detonation mechanism 2. The substances that can be used as working media can be broadly divided into two types: one is a substance that is insoluble in water and does not react with water, and is liquid at room temperature and relatively high temperatures, such as mercury, gasoline, diesel, and kerosene. This type of working medium, filling the pressurizing mechanism 1, can withstand and transmit the pressure of the detonation shock wave generated by the detonation mechanism 2, effectively improving pressure transmission efficiency. The other type of working medium is a substance that is liquid at room temperature and gaseous at high temperatures; specifically, it is a working medium that can change from liquid to gaseous under the action of the detonation shock wave, such as water or organic liquids. Because the hydrogen mixture and gas detonation generate a large amount of heat, the working fluid in the pressurizing mechanism 1 is heated into a gaseous state. The gaseous working fluid, after being heated, has excellent expansion properties and a large work capacity. The gaseous working fluid fills the entire pressurizing mechanism 1, bearing the pressure of the detonation shock wave generated by the detonation mechanism 2 while simultaneously expanding and doing work. In this embodiment, water is used as an example. Water is sprayed into the pressurizing mechanism 1 through the working fluid inlet 12. The heat generated by the detonation of the hydrogen mixture instantly heats this water into water vapor. The water vapor fills the entire pressurizing mechanism 1, bearing the pressure of the shock wave generated by the detonation mechanism 2 while simultaneously expanding and doing work.

[0061] The rotating mechanism 3 is the part that receives pressure. Inside the rotating mechanism 3 is a rotor structure that can maintain pressure and do work. The expansion of water vapor drives the rotor to rotate, thereby further outputting kinetic energy.

[0062] The detonation mechanism 2, pressurization mechanism 1, and rotation mechanism 3 are all sealed together, meaning that the parts that generate, transmit, and receive pressure are all sealed and pressure-maintaining. Because the pressure transmission efficiency generated by the detonation of the hydrogen mixture within the detonation mechanism 2 is too low, utilizing a liquid working fluid or the expansion of a gaseous working fluid to transmit pressure significantly improves energy conversion efficiency and reduces dependence on high-purity hydrogen compared to the absence of a pressurization mechanism 1. This lowers costs and provides strong support for the economic viability and sustainable development of the hydrogen energy industry.

[0063] Taking water as the working medium as an example, the pressure generated by the detonation of the hydrogen mixture is transferred through the expansion of water vapor. The water vapor continuously expands under high heat, and as it expands and propels itself, it transfers the pressure generated by the hydrogen mixture detonation to the rotating mechanism 3 to perform work. Furthermore, the detonation mechanism 2 generates a detonation shock wave through high-frequency ignition, while the pressurizing mechanism 1 continuously adds water and is continuously heated by the heat generated by the detonation, causing the water vapor to expand repeatedly. It can be understood that both the pressure-generating and pressure-receiving parts are compressed at both ends of the pressure-transferring part, thus generating continuous pressure and continuously performing work. According to the engine power requirements, the ideal state is that the pressurization mechanism 1 is always filled with water vapor, that is, the water vapor pushed out and the water vapor injected into the pressurization mechanism 1 are kept in balance. In other words, the detonation mechanism 2 continuously pulses detonate, and the water vapor in the pressurization mechanism 1 is also continuously pulsedly pushed into the rotating mechanism 3 and transmits pressure. Water is also replenished into the pressurization mechanism 1 accordingly, so that the cavity of the pressurization mechanism 1 is always filled with water vapor and is kept in an expanded state due to continuous heat absorption, so as to achieve stable rotation of the rotating shaft 34 of the rotating mechanism 3.

[0064] Figure 1 The shape of the detonation mechanism 2 shown is for illustrative purposes only and can be designed according to actual needs. Furthermore, the entire machine can have multiple detonation mechanisms 2. A mixture of hydrogen and air (or oxygen) in a specific ratio can be introduced into the detonation mechanism 2. This intake method helps to ensure thorough mixing of hydrogen and air (or oxygen) in a constant ratio, guaranteeing the detonation effect after ignition of the detonation mechanism 2. Alternatively, hydrogen and air (or oxygen) can be introduced into the detonation mechanism 2 through two separate channels. This intake method involves the hydrogen and air (or oxygen) mixing and diffusing after entering the detonation mechanism 2. The piping is simple and easy to implement. The ratio of hydrogen and air (or oxygen) within the detonation mechanism 2 can be controlled by separately controlling the intake volume of each type of gas, thereby ensuring the detonation effect.

[0065] Figure 1 The shape of the pressurizing mechanism 1 shown is for illustrative purposes only and can be designed to meet the function of pressure transmission according to actual needs. The number of pressurizing mechanisms 1 included in the whole machine is adapted to the number of detonation mechanisms 2; and the position and number of working fluid inlets 12 are not limited and can be designed according to factors such as the shape of the pressurizing mechanism 1.

[0066] Figure 1 The shape of the rotating mechanism 3 shown is only schematic. In this embodiment, the rotating mechanism 3 preferably has a rotor structure (i.e., the flywheel in the following embodiment) with a passive one-way valve that has a pressure-holding function. Since the flow channel design with the passive one-way valve has a flow-blocking effect, it can achieve a certain degree of pressure holding. This rotor structure can not only effectively receive the pressure transmitted from the pressurizing mechanism 1, but also discharge the exhaust gas (exhaust gas after detonation and water vapor, etc.).

[0067] The embodiments disclosed herein achieve detonation efficiency enhancement by generating pressure through ignition and detonation of the hydrogen-hydrogen mixture in the detonation mechanism, and by utilizing the working fluid in the pressurization mechanism to transmit pressure and enter the rotation mechanism to perform work. This reduces the dependence on high-purity hydrogen, which is beneficial for reducing costs, and significantly improves the hydrogen-to-electricity conversion efficiency, providing strong support for the economic and sustainable development of the hydrogen energy industry.

[0068] In one embodiment, such as Figure 2 As shown, the detonation engine includes: a detonation mechanism 2, a pressurization mechanism 1, a rotation mechanism 3, a fixing mechanism 5, and a separation mechanism 4.

[0069] In one embodiment, such as Figure 2 and Figure 3 As shown, the detonation engine adopts a multi-layered structure arranged in a star shape, meaning that multiple detonation mechanisms 2 are distributed in the same layer around the same center line, roughly arranged in a star shape to form the detonation layers. Correspondingly, the number of pressurizing mechanisms 1 matches the number of detonation mechanisms 2. The first ends of the multiple pressurizing mechanisms 1 are connected to the multiple detonation mechanisms 2 in a one-to-one correspondence, and the second ends of the multiple pressurizing mechanisms 1 are circumferentially connected to the rotating mechanism 3. The rotating mechanism 3 is a rotating layer arranged parallel to the detonation layers of the detonation mechanisms 2, with the detonation layers stacked on top of the rotating layers. The separation mechanism 4 is a separation layer arranged parallel to the rotating layers, with the rotating layers stacked on top of the separation layers. The aforementioned multi-layered detonation engine with a star-shaped arrangement has a compact structure and a more rational layout, and can easily accommodate different power requirements by increasing the diameter of the circumferential layer structures. Moreover, the power of the detonation engine can be expanded by extending it into multiple three-layer structures.

[0070] In one embodiment, such as Figures 3 to 6As shown, the detonation mechanism 2 includes a detonation chamber 21 and an igniter 24. The detonation chamber 21 has a double-layered structure, comprising an inner chamber 211 and an outer chamber 212. The inner chamber 211 has an internal cavity that serves as the detonation chamber 2111, providing space for the detonation of the hydrogen mixture. The space between the outer chamber 212 and the inner chamber 211 is an exhaust chamber 113, serving as a temporary storage space for some of the waste gas generated during the detonation, and allowing for both extraction and exhaust. One end of the inner chamber 211 also has a first exhaust port 2112 communicating with the detonation chamber 2111. The first exhaust port 2112 can be formed by an exhaust pipe, which can be integrally formed with the inner chamber 211. At least one communicating hole 2113 is provided on the cavity wall of the detonation chamber 2111. A radially outwardly extending flange 2114 is formed on the outer peripheral wall of the detonation chamber 2111 near its bottom. The outer liner 212 is fitted over the inner liner 211, and the bottom of the outer liner 212 is circumferentially sealed to the flange 2114. The outer liner 212 partially surrounds the inner liner 211 in the height direction. The outer liner 212 has a second vent 2131 on the side away from the flange 2114. The first vent 2112 and the second vent 2131 are located at the same end of the detonation chamber 21, and the first vent 2112 extends from the second vent 2131 beyond the outer liner 212, so that an exhaust chamber 213 is formed between the outer liner 212 and the inner liner 211. The detonation chamber 2111 inside the inner liner 211 is connected to the exhaust chamber 213 through the connecting hole 2113. Figure 7 The arrows indicate the direction of airflow. When the hydrogen-hydrogen mixture ignites and detonates in the inner liner 211, most of the high-temperature, high-pressure exhaust gas generated by the detonation is directly discharged through the first outlet 2112, while the remaining exhaust gas enters the exhaust chamber 213 through the connecting hole 2113 and is discharged through the second outlet 2131. Because a vacuum low pressure is generated within the inner liner 211 during the detonation, some of the discharged exhaust gas is drawn back into the inner liner 211. Since the drawn-back exhaust gas contains a large amount of nitrogen, carbon dioxide, and water vapor, which suppress the detonation reaction, especially at high detonation frequencies, a large amount of suppressing gas can affect the stability of continuous detonations. It is understandable that... Figure 8As shown, in the double-layered structure of the detonation chamber 21, the outer chamber 212 is in direct contact with the outside atmosphere, while the inner chamber 211 generates a large amount of heat after detonation. This causes the temperature in the exhaust chamber 213 between the outer chamber 212 and the inner chamber 211 to be lower than the temperature in the detonation chamber 2111. Due to the temperature and pressure difference, the exhaust gas drawn back during detonation quickly enters the outer chamber 212 from the inner chamber 211 through the connecting hole 2113, i.e., the exhaust chamber 213. This part of the exhaust gas and the exhaust gas drawn back in the exhaust chamber 213 form a vortex in the exhaust chamber 213 and are discharged from the second outlet 2131. This reduces the amount of exhaust gas drawn back in the inner chamber 211, thereby reducing the total amount of detonation-suppressing gas in the inner chamber 211 that inhibits the detonation reaction. This effectively reduces the impact of the exhaust gas drawn back on the detonation reaction, thereby improving the stability of continuous detonation.

[0071] In one embodiment, the air inlet and igniter 24 of the detonation chamber 21 are disposed on the flange 2114, and the air inlet is connected to the detonation chamber 2111. The igniter 24 extends into the detonation chamber 2111. Air and hydrogen enter the detonation chamber 2111 through the air inlet, and the igniter 24 is controlled to ignite, causing the hydrogen mixture to be ignited and detonation to occur. In this embodiment, an installation port can be provided on the cavity wall of the detonation chamber, and an integrated mounting bracket 25 can be installed at the installation port. The air inlet includes an air inlet 22 and a hydrogen inlet 23. The air inlet 22, the hydrogen inlet 23, and the igniter 24 are all integrated on the mounting bracket 25. The air inlet 22 and the hydrogen inlet 23 are connected to the detonation chamber 2111, and one end of the igniter 24 extends into the detonation chamber 2111 from the bottom of the mounting bracket 25. The centralized arrangement of the igniter 24, air inlet 22, and hydrogen inlet 23 facilitates thorough mixing of air and hydrogen for rapid ignition. Furthermore, this centralized layout saves space and helps improve the power density of the detonation engine.

[0072] In one embodiment, the detonation chamber 21 of the detonation mechanism 2, unlike the embodiments described above, is a structure in which a portion of the inner liner 211 encloses an outer liner 212, such as... Figure 9 As shown, the detonation chamber's dual-chamber structure includes an inner chamber 211 and an outer chamber 212 that completely encloses the inner chamber 211. The outer chamber 212 surrounds the outer peripheral wall of the inner chamber 211 and its bottom wall away from the first outlet 2112. An exhaust chamber 213 is formed between the inner chamber 211 and the outer chamber 212. The detonation chamber 2111 inside the inner chamber 211 communicates with the exhaust chamber 213 through a connecting hole 2113. The exhaust chamber 213 has ample space, facilitating the entry of exhaust gas and its discharge through the second outlet 2131. Furthermore, there is no need to consider the sealing between the outer chamber 212 and the inner chamber 211, making the outer chamber 212 easy to manufacture. To ensure sufficient detonation, the air inlet and igniter 24 of the detonation chamber 21 are positioned at any location on the inner chamber 211 away from the first outlet 2112.

[0073] In one embodiment, the detonation chamber of the detonation mechanism 2, unlike those in the above embodiments, has a double-layered structure, such as... Figure 10 As shown, the detonation chamber 21 has a dual-chamber structure, comprising an inner chamber 211 and an outer chamber 212 sharing one side of its wall with the inner chamber 211. The outer chamber 212 partially surrounds the inner chamber 211 in the circumferential direction and shares a portion of its outer peripheral wall with the inner chamber 211. The detonation cavity 2111 of the inner chamber 211 communicates with the outer chamber 212 through a connecting hole 2113. An exhaust chamber 213 is formed between the shared wall of the outer chamber 212 and the inner chamber 211 and the outer chamber 212. That is, the detonation cavity 2111 inside the inner chamber 211 communicates with the exhaust chamber 213 through the connecting hole 2113. To ensure sufficient detonation, the air inlet and igniter 24 of the detonation chamber 21 are located at any position on the inner chamber 211 away from the first air outlet 2112. Similarly, the outer liner 212, which does not share the same wall as the inner liner 211, is in direct contact with the outside atmosphere. This makes the temperature of the exhaust chamber 213 between the outer liner 212 and the inner liner 211 lower than the temperature inside the inner liner 211. Due to the temperature and pressure difference, the back-absorbed exhaust gas during the detonation will quickly enter the outer liner 212 from the inner liner 211 through the connecting hole 2113, i.e., the exhaust chamber 213. This part of the exhaust gas forms a vortex with the back-absorbed exhaust gas in the exhaust chamber 213 and is discharged from the second exhaust port 2131.

[0074] In one embodiment, there are multiple connecting holes 2113, which are circumferentially spaced on the outer peripheral wall of the inner liner 211. This facilitates the entry of exhaust gas generated after detonation in the detonation chamber 2111 into the exhaust chamber 213. The connecting holes 2113 can be connected to the end of the exhaust chamber 213 furthest from the second outlet 2131. This helps ensure that sufficient gas is discharged through the first outlet 2112 to perform work after detonation. Furthermore, it facilitates the entry of exhaust gas drawn back into the detonation chamber 2111 during the instantaneous detonation into the exhaust chamber 213 through the connecting holes 2113, forming a vortex with the back-drawn exhaust gas in the exhaust chamber 213, and then being discharged through the second outlet 2131.

[0075] In one embodiment, the detonation chamber of the detonation mechanism 2, unlike those in the above embodiments, has a double-layered structure, such as... Figure 11As shown, the dual-chamber structure of the detonation chamber includes: a first chamber 214 and a second chamber 215 arranged side-by-side and spaced apart from the first chamber 214. The detonation chamber 2111 in the first chamber 214 and the exhaust chamber 213 in the second chamber 215 are connected by a connecting part 216. The connecting part 216 can be a connecting pipe, with one end connected to the connecting hole 2113 and the other end connected to the exhaust chamber 213. The connecting part 216 can be integrally formed with at least one of the first chamber 214 and the second chamber 215. To ensure sufficient detonation, the air inlet and igniter 24 of the detonation chamber 21 are located at any position on the first chamber 214 away from the first air outlet 2112. Similarly, the second chamber 215 is in direct contact with the outside atmosphere and does not require detonation, which makes the temperature inside the second chamber 215 lower than the temperature inside the first chamber 214. Due to the temperature difference and pressure difference, the back-absorbed exhaust gas at the moment of detonation will quickly enter the second chamber 215 from the first chamber 214 through the connecting part. This part of the exhaust gas forms a vortex with the back-absorbed exhaust gas inside the second chamber 215 and is discharged from the second outlet 2131 of the second chamber 215.

[0076] This embodiment of the disclosure sets the detonation chamber 21 as a dual-chamber structure. By utilizing the temperature difference between the first chamber 214 and the second chamber 215, the exhaust gas drawn back into the first chamber 214 will be discharged from the second chamber 215, thereby reducing the amount of exhaust gas stored in the first chamber 214. This reduces the total amount of detonation-suppressing gas in the first chamber 214 that inhibits the detonation reaction, effectively reducing the impact of the exhaust gas drawn back on the detonation reaction, and thus improving the stability of continuous detonation.

[0077] In one embodiment, such as Figure 3 As shown, the detonation mechanism 2 is housed in the fixing mechanism 5. When the detonation mechanism 2 detonates, the energy generated by the detonation produces a large amount of heat, causes strong vibrations, and generates huge noise. Therefore, placing the detonation mechanism 2 in the fixing mechanism 5 can fix the detonation mechanism 2, cool it down, and reduce noise.

[0078] In one embodiment, such as Figure 12 and Figure 13 As shown, the fixing mechanism 5 includes a fixing cover 51 and a fixing housing 52. The fixing housing 52 has a detonation mechanism receiving cavity for accommodating and fixing the detonation mechanism 2. The fixing cover 51 covers the fixing housing 52 and further fixes the detonation mechanism 2 in the detonation mechanism receiving cavity.

[0079] In one embodiment, within the enclosed detonation mechanism receiving cavity formed by the fixed housing 52 and the fixed cover 51, a cooling medium 9 can be accommodated in addition to the space excluding the detonation mechanism 2. The cooling medium 9 can be an organic liquid, oil, etc., preferably water. The cooling medium 9 filling the cavity space of the fixed housing 52 excluding the detonation mechanism 2 is equivalent to immersing the detonation mechanism 2 in the cooling medium 9. This allows for heat exchange, cooling the high-temperature detonation mechanism 2 after detonation. Since the cooling medium 9 is not conducive to sound wave conduction, it also reduces the significant noise generated by the detonation. Simultaneously, the cooling medium 9 also absorbs heat and increases in temperature.

[0080] In one embodiment, the fixed housing 52 includes a bottom wall 521 and a side wall connected to the bottom wall 521. A cooling medium inlet 5211 and a cooling medium outlet 5212 are provided on the bottom wall 521 of the fixed housing. After heat exchange with the high-temperature detonation mechanism 2, the temperature of the cooling medium 9 inside the fixed housing 52 rises. When a certain temperature threshold is reached, new cooling medium 9 can be added to the fixed housing 52 through the cooling medium inlet 5211, while the high-temperature cooling medium 9 is discharged from the fixed housing 52 through the cooling medium outlet 5212, thus ensuring that the temperature of the cooling medium 9 meets the cooling requirements and guarantees the cooling effect.

[0081] In one embodiment, the sidewall of the fixed shell includes multiple fixed walls 5221, each fixed wall 5221 having a first connection port 523. The outlet end of the detonation mechanism 2 is connected to the pressurization mechanism 1 via the first connection port 523. The detonation mechanism 2 can be bolted to the fixed wall 5221, for example, to the wall surface on the outer periphery of the first connection port 523, to prevent the detonation mechanism 2 from moving axially. The bottom wall 521 of the fixed shell is also provided with the same number of limiting ribs 5214 as the fixed walls 5221, which can prevent the detonation mechanism 2 from moving radially. Correspondingly, as Figure 6 As shown, the outer shell 212 of the detonation chamber 21 of the detonation mechanism 2 has a recessed limiting groove 2121 on the side near the bottom wall 521 of the fixed shell. The limiting groove 2121 is adapted to the limiting rib 5214 on the bottom wall 521 of the fixed shell of the fixed mechanism 5, thereby preventing the detonation mechanism 2 from moving radially. The limiting rib 5214 extends along the axial direction of the detonation mechanism 2. At this time, the limiting rib 5214 is perpendicular to the wall surface around the first connection port 523. Of course, the limiting rib 5214 can also extend obliquely, both of which can restrict the movement of the detonation mechanism 2 along the plane where the first connection port 523 is located.

[0082] In one embodiment, the fixed cover 51 is circular and has at least one through hole 511. The number of through holes 511 is adapted to the number of detonation mechanisms 2, and the multiple through holes 511 are arranged in a ring around the center of the end cover at the same interval angle on the fixed cover 51. When the fixed cover 51 is installed on the fixed housing 52, the air inlet of the detonation mechanism 2 is connected to the combustible gas source through the through hole 511. For example, the mounting bracket 25, air inlet 22, hydrogen inlet 23, and igniter 24 of the integrated detonation mechanism 2 can extend through the through hole 511. To make the detonation chamber 21 more securely installed on the fixed mechanism 5, the mounting bracket 25 can be connected to the hole wall of the through hole 511 by welding. Of course, the mounting bracket 25 can also be fixed by other methods, not limited to welding.

[0083] In one embodiment, the fixing mechanism 5 further includes a boss 53, which is located at the center of the bottom wall 521 of the fixing shell and protrudes into the detonation mechanism receiving cavity. The boss 53 and the side wall of the fixing shell together form a space for accommodating the detonation mechanism 2 and the cooling medium 9. The detonation mechanism 2 is distributed on the outer periphery of the boss 53. The side of the boss 53 away from the detonation mechanism receiving cavity forms a mounting groove 5213, which is used to connect with the rotating mechanism 3. The mounting groove 5213 can accommodate a part of the rotating mechanism 3, thereby reducing the overall size of the detonation engine and improving the power density of the detonation engine.

[0084] In one embodiment, such as Figure 2 , Figure 3 and Figure 14 As shown, the pressurizing mechanism 1 includes a pressurizing pipe 10, which can receive and transmit the pressure generated by detonation, and is preferably a metal pipe. The first end of the pressurizing pipe 10 is connected to the detonation mechanism 2, and the second end is connected to the rotating mechanism 3. A working fluid inlet 12 is provided on the pressurizing pipe 10, which is positioned as close as possible to the connection with the detonation mechanism 2 to improve the efficiency of pressure transmission by the working fluid within the pressurizing mechanism 1. Taking water as the working fluid, the water injected into the pressurizing mechanism 1 can be directly and quickly heated into water vapor by the heat generated by the detonation of the detonation mechanism 2. The water vapor further expands under high heat and performs work, improving the pressure transmission efficiency. Both ends of the pressurizing pipe 10 are connected to connecting plates 11, which allows for a more secure connection between the pressurizing pipe 10 and the fixed housing 52 and the outer shell 32 of the rotating mechanism 3, preventing pressure leakage. Furthermore, the connecting plates 11 have through holes, with the pipe opening of the pressurizing pipe 10 aligned with the through holes. The connecting plates 11 can be connected to the pressurizing pipe 10 by welding. One end of the pressurizing tube 10 is connected to the fixed wall 5221 of the fixing mechanism 5; the other end of the pressurizing tube 10 is connected to the connecting wall 324 of the rotating mechanism 3 (e.g., Figure 15As shown, the pressurized tube 10 connects the detonation mechanism 2 and the rotating mechanism 3. The pressurized tube 10 is a bent tube structure, such as an arc-shaped tube. After one end is connected to the detonation mechanism 2, the bent tube is located on the outer periphery of the fixed mechanism 1 at a relatively far air inlet from the rotating mechanism 3. For example, the first end and the second end of the pressurized tube 10 are distributed vertically along the axial direction of the rotating mechanism 3 and staggered in the circumferential direction of the rotating mechanism 3. This structure ensures the length of the pressurized tube 10 while making the overall volume smaller and improving the power density of the detonation engine.

[0085] In one embodiment, such as Figures 15 to 22 As shown, the rotating mechanism 3 includes a cover 31, a shell 32, a rotating disk 33 and a rotating shaft 34. The rotating shaft 34 is mounted on the rotating disk 33 and is rotatably mounted together in the rotating disk receiving cavity formed by the cover 31 and the shell 32.

[0086] A protrusion is formed on the outer side of the cover 31, and a recessed receiving portion 311 is formed on the inner side of the cover 31 corresponding to the protrusion. A first bearing 35 is disposed in the recessed receiving portion 311. The outer shell 32 is generally disc-shaped and has a rotating disk receiving cavity for placing the rotating disk 33. An opening is provided on the outer circumference of the outer shell 32. A sleeve 326 protrudes from the side of the center of the outer shell 32 away from the cover 31. The sleeve 326 communicates with the rotating disk receiving cavity of the outer shell 32. A second bearing 36 is disposed in the sleeve 326. A rotating shaft 34 passes through the rotating disk 33 and is connected to the rotating disk 33, so that the rotating shaft 34 and the rotating disk 33 rotate together. Specifically, the rotating shaft 34 and the rotating disk 33 are connected as a whole by means of a flat key, spline, etc. One end of the rotating shaft 34 is received in the recessed receiving portion 311 and passes through the first bearing 35. The other end of the rotating shaft 34 passes through the second bearing 36 and is disposed in the sleeve 326 and extends out of the sleeve 326. The rotating shaft 34 extending beyond the sleeve 326 can be connected to a motor and drive it to rotate to generate electricity, thus the detonation engine and the motor are combined to form a generator.

[0087] The rotating disk receiving cavity formed by the outer shell 32 has multiple outer shell inlets 321 and outlets 322 on its cavity wall. The multiple outer shell inlets 321 and outlets 322 are arranged alternately. In this embodiment, the outer periphery of the cavity wall of the outer shell 32 has a connecting wall 324 and a protrusion 325. The outer shell inlets 321 are formed on the connecting wall 324. The protrusion 325 protrudes from the outer periphery of the cavity wall, and the outlet 322 penetrates the side of the protrusion 325 away from the cover 31. The outer shell inlets 321 are connected to the pressurizing mechanism 1, and the outlets 322 are connected to the separation cavity inlet 415 of the separation mechanism 4.

[0088] The rotating disk 33 includes a first cover plate 331, a second cover plate 332, and a flywheel 333. The first cover plate 331 and the second cover plate 332 have roughly the same structure and are fixed to both sides of the flywheel 333, respectively. A first annular ridge 312 is formed on the inner side of the cover 31 near the outer edge. The first annular ridge 312 may include multiple annular ridges with the same center but different radii. The radius difference between two adjacent annular ridges is approximately equal to the width of the annular ridge. A second annular ridge 323 is formed on the bottom wall of the rotating disk receiving cavity formed by the outer shell 32. The second annular ridge 323 may include multiple annular ridges with the same center but different radii. The radius difference between two adjacent annular ridges is approximately equal to the width of the annular ridge. On the side of the first cover plate 331 and the second cover plate 332 away from the flywheel 333, there is an annular groove 334 that mates with the first annular protrusion 312 and the second annular protrusion 323. There are gaps between the mating surfaces of the first annular protrusion 312 and the annular groove 334, and between the mating surfaces of the second annular protrusion 323 and the annular groove 334, thus forming a non-contact first seal. The axial gap A is between 0.3mm and 0.6mm, preferably 0.5mm; the radial gap R is between 0.1mm and 0.4mm, preferably 0.3mm. It is understood that non-contact seals have advantages such as no lubrication required, low power consumption, long lifespan, and stable operation.

[0089] The outer peripheral walls of the first cover plate 331 and the second cover plate 332 are provided with a plurality of first grooves 335 along the axial direction. The flywheel 333 has a disc-shaped structure, including an upper surface and a lower surface. The edge of the flywheel 333 forms a plurality of serrated wings 3331, and the edge of the wings 3331 is provided with second grooves 3332 along the axial direction. The second grooves 3332 correspond one-to-one with the first grooves 335, that is, the second grooves 3332 and the first grooves 335 are aligned in the axial direction. The diameter of the first cover plate 331 and the second cover plate 332 is equal to the diameter of the flywheel 333 and slightly smaller than the inner wall diameter of the outer shell 32. The rotating disk 33 is rotatably disposed in the receiving cavity of the outer shell 32. There is a gap between the first grooves 335 and the inner wall of the outer shell 32, that is, a non-contact second seal is formed.

[0090] When the rotating disk 33 rotates at high speed in the rotating disk receiving cavity formed by the cover 31 and the outer shell 32, the first seal and the second seal can prevent gas leakage into the rotating disk 33, thereby improving the pressure work efficiency of the rotating disk 33. Moreover, since both the first seal and the second seal are non-contact seals, they have advantages such as no need for lubrication, low power consumption, long service life, and stable operation.

[0091] A gap is formed between the wingtips of every two adjacent winglets 3331, and this gap axially penetrates the upper and lower surfaces of the wingtips of every two adjacent winglets 3331. A unidirectional flow channel 3333 is recessed on the upper and / or lower surfaces of the junction of every two adjacent winglets 3331. The unidirectional flow channels 3333 on the flywheel 333 are arranged in groups, and each passive unidirectional valve group includes multiple unidirectional flow channels 3333. The starting end of each unidirectional flow channel 3333 is located at the junction of two adjacent winglets 3331, and the ending ends of each unidirectional flow channel 3333 in each group are interconnected. The passive unidirectional valve groups on the surface of the flywheel 333 are evenly or symmetrically distributed. In this embodiment, each passive unidirectional valve group includes four unidirectional flow channels 3333, and four groups are arranged on each surface. The ending ends of the four unidirectional flow channels 3333 in each group are connected by a connecting groove 3334. It should be noted that... Figure 18 and Figure 19 The unidirectional flow channel 3333 in the middle has a flow-stopping function from the starting end to the ending end, and a flow-forward function from the ending end to the starting end. The working fluid entering the unidirectional flow channel 3333 in the reverse direction (from the starting end to the ending end) is discharged from other unidirectional flow channels 3333 in the same group in the forward direction (from the ending end to the starting end) through the connecting groove 3334. The working fluid entering the rotating mechanism 3 from the pressurizing mechanism 1 enters from the outer shell inlet 321. The wing 3331 is set as an inclined structure to bear the pressure and do work. The working fluid enters the unidirectional flow channel 3333, which has a flow-stopping function from the starting end to the ending end. This structure can capture torque and also act as a flywheel to provide inertia. In addition, the explosion is a pulse load with a short time. In order to prolong the work time, the channel of the flywheel 333 is narrowed and a unidirectional flow channel 3333 structure is adopted to prolong the explosion work time and improve the energy capture efficiency. This one-way flow-stopping structure does not require an external one-way valve. It is a purely mechanical structure that is easy to implement and has a long service life. Furthermore, by simulating a closed fan blade through the one-way flow channel 3333, the working fluid and exhaust gas after work flow flow through other one-way flow channels 3333 within the group flow from the end end into the connecting groove 3334 and then back to the starting end, and finally are discharged from the rotating mechanism 3. This serves to discharge the working fluid and exhaust gas after work, thereby eliminating the need for an additional exhaust structure and further achieving a compact structure, which is beneficial to improving the power density of the detonation engine.

[0092] For example, the unidirectional flow channel 3333 has a stop 3335 that blocks the flow of the working medium from the starting end to the ending end, and the stop 3335 can guide the working medium to flow in the opposite direction from the ending end of the unidirectional flow channel 3333 to its starting end. Figure 19As shown, in the two sets of protruding serrations facing each other on adjacent winglets 3331, the gaps between one set of serrations and the other set of serrations opposite each other are distributed, and the side of the serrations facing the outer periphery of the flywheel 333 is constructed as a stop portion 3335. Of course, the stop portion 3335 may also include a stop rib protruding towards the cover body 31 in the gap between the serrations of each set of serrations.

[0093] In one embodiment, such as Figure 23 and Figure 24 As shown, the separation mechanism 4 includes a separation body 41 and a sealing cover 42 connected to the separation body 41. To adapt to the shape of the fixing mechanism 5 that houses the detonation mechanism 2 and the shape of the rotating mechanism 3, the separation body 41 and the sealing cover 42 are generally disc-shaped. A separation cavity is recessed on one end face of the separation body 41. The separation cavity has a meandering gas guiding channel 414. The separation cavity inlet 415 is located on the cavity wall and communicates with the first end of the gas guiding channel 414. The separation cavity outlet 416 is located on the cavity wall and communicates with the second end of the gas guiding channel 414. The separation cavity contains a liquid working medium. The cavity wall of the separation cavity is also provided with a liquid port 417 for the liquid working medium to enter and exit. The sealing cover 42 seals the separation cavity.

[0094] For example, the separating body 41 can have a recessed separating cavity on its end face, with a sealing ring 411 protruding near the separating cavity. A first sealing partition 412 and a second sealing partition 413 can protrude from the bottom wall of the separating cavity. The first end of the first sealing partition 412 is connected to the inner wall 40 of the separating cavity and is connected to the sealing ring 411. The second end of the first sealing partition 412 is a free end 4121. The second sealing partition 413 is located on the side of the first sealing partition 412 away from the inner wall 40. The first end of the second sealing partition 413 is connected to the inner wall 40 of the separating cavity and is connected to the sealing ring 411. The first end of the second sealing partition 413 is adjacent to the free end 4121 of the first sealing partition 412, and the second end of the second sealing partition 413 is a free end 4131, adjacent to the first end of the first sealing partition 412. Therefore, the inner wall 40, the first sealing partition 412, and the second sealing partition 413 together form a meandering air guide channel 414. The first end of the gas guiding channel 414 is a closed end 4141 formed by the inner wall 40 of the separation chamber and the first sealing partition 412, and the second end of the gas guiding channel 414 is an open end 4142 formed by the free ends 4131 of the first sealing partition 412 and the second sealing partition 413. A separation chamber inlet 415 is provided on the bottom wall of the separation chamber, located between the inner wall 40 and the first sealing partition 412, near the closed end 4141 of the gas guiding channel 414. A separation chamber outlet 416 is provided on the bottom wall of the separation chamber away from the open end 4142. In this embodiment, the separation body 41 has a symmetrical structure centered on the centerline L, that is, the first sealing partition 412, the second sealing partition 413, and the separation chamber inlet 415 are all symmetrically arranged around the centerline L. The separation chamber inlet 415 corresponds to and is docked with the outlet 322 of the rotating mechanism 3, allowing the exhaust gas, water vapor, and working fluid generated by detonation to enter the separation mechanism 4. A liquid inlet 417 is provided on the inner wall of the separation body 41 away from the outlet 416 of the separation chamber, for injecting liquid working medium into the separation mechanism 4 or discharging liquid working medium from the separation mechanism 4.

[0095] It should be noted that the detonation engine does not operate as... Figure 1 and Figure 21 Instead of being placed vertically (i.e., the rotation axis 34 is in the vertical direction), it is like... Figure 23 and Figure 24(Only the separation body 41 is shown) It is placed horizontally. That is to say, when the detonation engine is in use, the separation chamber outlet 416 is located above and the liquid inlet 417 is located below, and the separation chamber outlet 416 is higher than the free end 4121 of the first sealing partition 412. Liquid working fluid is added to the separation mechanism 4 through the liquid inlet 417. The liquid working fluid must not be higher than the free end 4121 of the first sealing partition 412 to prevent the liquid working fluid from being discharged from the separation chamber inlet 415. The liquid working fluid entering the separation mechanism 4 is confined in the space between the two first sealing partitions 412. The gaseous working fluid and exhaust gas after the detonation work enter the air guide channel 414 through the separation chamber inlet 415. After being filtered and cooled by the liquid working fluid, the liquid working fluid is cooled and remains in the separation mechanism 4, while the exhaust gas is discharged through the separation chamber outlet 416.

[0096] To prevent the liquid working medium in the separation mechanism 4 from overflowing from the separation chamber outlet 416 due to vibration or shaking, a baffle 410 can be provided on the bottom wall of the separation chamber near the separation chamber outlet 416, so that it is located below the separation chamber outlet 416 in use.

[0097] To achieve better exhaust performance, an exhaust pipe 418 is installed at the outlet 416 of the separation chamber.

[0098] To better prevent the liquid working fluid in the separation mechanism 4 from flowing between the first sealing partition 412 and the sealing ring 411 and being discharged from the separation chamber inlet 415 due to vibration or shaking caused by the detonation engine, an anti-backflow plate 419 can also be provided between the first sealing partition 412 and the second sealing partition 413.

[0099] Additionally, multiple heat sinks 421 can be provided on the side of the sealing cover 42 away from the separation body 41 for heat dissipation of the liquid working fluid inside the separation mechanism 4. Figure 24 (Multiple points are used to represent the exhaust gas) to cool it down.

[0100] In summary, taking water as the working fluid as an example, the working principle of this embodiment is explained as follows: Hydrogen gas entering the detonation chamber 21 mixes with air to form a hydrogen-air mixture. Ignition device 24 ignites the hydrogen-air mixture, causing a detonation and generating a shock wave. The shock wave enters the pressurization mechanism 1. Simultaneously, water is sprayed into the pressurization mechanism 1 through the working fluid inlet 12. The heat generated by the detonation instantly heats this water into water vapor. The water vapor fills the entire pressurization mechanism 1, and while bearing the pressure generated by the detonation shock wave from the detonation mechanism 2, the water vapor expands and does work. It enters the rotating disk receiving cavity formed by the cover 31 and the outer shell 32 through the outer shell inlet 321 of the rotating mechanism 3, pushing the rotating disk 33 to rotate. The water vapor and the exhaust gas generated by the detonation are discharged from the outlet 322 and enter the separation mechanism 4 through the separation chamber inlet 415. Then, it enters the water in the separation mechanism 4 through the gas guide channel 414. Water vapor and the exhaust gas generated by detonation are filtered and cooled by water, so that the water vapor is cooled into water and remains in the separation mechanism 4, while the exhaust gas is discharged through the separation chamber outlet 416.

[0101] In one embodiment, based on the aforementioned detonation engine, water is used as the working fluid and also as a cooling medium, providing a water circulation scheme, such as... Figure 25 As shown, the fixed mechanism 5 has a detonation mechanism receiving cavity inside, and the detonation mechanism 2 is installed inside the detonation mechanism receiving cavity. The detonation mechanism 2 inside the detonation mechanism receiving cavity is filled with liquid water. The cavity wall of the detonation mechanism receiving cavity is provided with a first connection port 523 and a second connection port. The first connection port 523 is connected to the working fluid inlet 12 of the pressurizing mechanism 1. The liquid water can be detonated and heated by the detonation mechanism 2 to form high temperature and high pressure water, and enter the pressurizing mechanism 1 through the working fluid inlet 12. The separation mechanism 4 has liquid water inside, which is used to separate the working fluid and discharge the waste gas. The separation cavity inlet 415 of the separation mechanism 4 is connected to the outlet 322 of the rotating mechanism 3. The separation cavity outlet 416 of the separation mechanism 4 is connected to the second connection port through the circulation pump 6.

[0102] Water in separation mechanism 4 (water tank) is pressurized by circulation pump 6, and the high-pressure water enters fixed mechanism 5 (water jacket). The high-temperature detonation chamber 21, located inside the water jacket, heats the water to a high temperature after detonation. The water jacket is a sealed structure, and the water becomes high-temperature, high-pressure water after being heated. Water in the water jacket is discharged under the control of solenoid valve 7 and intermittently injected into pressurization mechanism 1 (acceleration tube) according to the detonation frequency. The water injected into the acceleration tube is heated and vaporized into water vapor by the ultra-high temperature gas ejected from detonation chamber 21. The water vapor, acting as a working fluid, expands upon heating, thus performing work and enhancing the detonation effect. The detonation gas and water vapor enter rotating mechanism 3 (flying disc) together, driving flywheel 333 to perform work. After the work is done, the exhaust gas containing water vapor is discharged, and the water vapor enters the water tank with the exhaust gas, condensing into water and remaining in the tank. The water vapor cools down and circulates, recovering energy and completing the cycle. Other exhaust gases are discharged from the water tank.

[0103] In this embodiment, water is used as both the working fluid for detonation enhancement and the cooling medium for detonation chamber 21. The heat generated by detonation vaporizes the water into water vapor. After the water vapor is further heated and expands to do work, it is cooled back into water by water in the water tank. The water in the water tank is extracted, pressurized, and used to cool the high-temperature detonation chamber 21. Due to heat exchange, pressurized and heated water is obtained. After being filled into the pressurization mechanism 1, the pressurized and heated water is heated back into water vapor by the heat generated after detonation. In this way, water and energy are recycled and reused in the system. Only a small amount of water needs to be added to keep the engine running continuously. Moreover, the overall size of the detonation engine is reduced, which is beneficial to improving the power density of the detonation engine.

[0104] In one embodiment, a detonation generator including the above-described detonation engine is provided.

[0105] The above description is merely a preferred embodiment of this application and an explanation of the technical principles employed. Those skilled in the art should understand that the scope of protection involved in this application is not limited to technical solutions formed by specific combinations of the above-described technical features, but should also cover other technical solutions formed by arbitrary combinations of the above-described technical features or their equivalents without departing from the technical concept. For example, technical solutions formed by substituting the above features with (but not limited to) technical features with similar functions disclosed in this application.

Claims

1. A detonation mechanism, characterized by, The detonation mechanism includes a detonation chamber (21), which comprises: A detonation chamber (2111) has a first outlet (2112); an inlet for entering combustible gas is provided on the chamber wall of the detonation chamber (2111); The exhaust chamber (213) is connected to the detonation chamber (2111). The exhaust chamber (213) has a second outlet (2131). The gas after detonation in the detonation chamber (2111) can be discharged through the first outlet (2112) and the second outlet (2131).

2. The detonation mechanism of claim 1, wherein, The first gas outlet (2112) and the second gas outlet (2131) are located at the same end of the detonation chamber (21); and / or The air inlet is located on the cavity wall of the detonation chamber (2111) at one end away from the first air outlet (2112).

3. The detonation mechanism of claim 1, wherein, The exhaust chamber (213) is located outside the detonation chamber (2111), and the sidewall of the exhaust chamber (213) facing the detonation chamber (2111) is shared with the sidewall of the detonation chamber (2111) facing the exhaust chamber (213); or The exhaust chamber (213) is located on one side of the detonation chamber (2111) and is distributed side by side with the detonation chamber (2111) at intervals.

4. The detonation mechanism according to claim 1, characterized in that, The detonation chamber (21) includes: The inner liner (211) has an inner cavity that forms the detonation chamber (2111), and one end of the inner liner (211) has the first vent (2112). An outer liner (212) is disposed on the outer periphery of the inner liner (211), and the space between the outer liner (212) and the inner liner (211) forms the exhaust chamber (213). One end of the outer liner (212) has a second air outlet (2131). The second air outlet (2131) and the first air outlet (2112) are located at the same end of the detonation chamber. The second air outlet (2131) is located on the outer periphery of the first air outlet (2112), and the inner liner (211) has a connecting hole on its wall that connects the detonation chamber (2111) and the exhaust chamber (213).

5. The detonation mechanism of claim 4, wherein, The outer liner (212) partially surrounds the inner liner (211) in the height direction, such that the end of the inner liner (211) away from the first air outlet (2112) is exposed, and the end of the outer liner (212) away from the first air outlet (2112) is circumferentially sealed to the outer peripheral wall of the inner liner (211); or The outer liner (212) surrounds the outer peripheral wall of the inner liner (211) and the bottom wall away from the first air outlet (2112); or The outer liner (212) partially surrounds the inner liner (211) in the circumferential direction and shares a portion of the outer peripheral wall of the inner liner (211).

6. The detonation mechanism of claim 4, wherein, The number of the connecting holes is multiple, and the multiple connecting holes are circumferentially spaced on the outer peripheral wall of the inner liner (211); and / or The connecting hole is connected to the end of the exhaust chamber (213) away from the second air outlet (2131).

7. The detonation mechanism of claim 1, wherein, The detonation chamber (21) includes: A first chamber (214) has an inner cavity that forms the detonation chamber (2111), and one end of the first chamber (214) has the first air outlet (2112). The second bladder (215) is arranged side by side on one side of the first bladder (214) and spaced apart from the first bladder (214). The inner cavity of the second bladder (215) forms the exhaust cavity (213). One end of the second bladder (215) has the second air outlet (2131). The first bladder (214) and the second bladder (215) are connected by a connecting part (216).

8. The detonation mechanism of claim 1, wherein, The detonation mechanism also includes: An igniter (24) is disposed on the cavity wall of the detonation chamber (2111) and is used to ignite the combustible gas in the detonation chamber (2111).

9. The detonation mechanism of claim 8, wherein, The igniter (24) is disposed on the cavity wall of the detonation chamber (2111) near the air inlet, or the igniter (24) extends into the detonation chamber (2111) through the air inlet; and / or The detonation chamber (2111) has an installation port on its cavity wall, and a mounting bracket (25) is provided at the installation port. The air inlet and the igniter (24) are both integrated on the mounting bracket (25).

10. A detonation engine characterized by, Includes the detonation mechanism as described in any one of claims 1 to 9.

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