A multi-chamber annular array cyclic intermittent self-controlled ordered explosive vibration power device

Abstract

This invention discloses a multi-chamber annular array cyclic intermittent self-controlled ordered detonation power device, belonging to the field of detonation power engines. It includes a detonation combustion chamber ring, front and rear end covers, a central rotating shaft, fuel supply, and an electric flame and electronic control system. Multiple sets of fan-shaped detonation combustion chambers are fixedly arranged in annular array, and can employ single-ring or multi-ring nested structures to expand power. The front and rear end covers rotate synchronously with the rotating shaft, engaging with the chamber rings with low friction. A passive unidirectional pressure-stabilizing and self-controlled flow-guiding structure is formed by a counter-tilted compressor fan and regenerative spiral blades, eliminating the need for mechanical one-way valves. This invention employs contactless electric field coupling initiation, with electrode alignment and closed-loop interlocked power supply to avoid leakage and accidental ignition. Following the "equivalent design, non-equivalent implementation" arrangement rule, the multi-chamber staggered intermittent detonation significantly reduces vibration impact. It features two working sequences: pure fuel detonation and electric flame energy storage composite, adaptable to various working conditions including low altitude, high altitude, vacuum, and confined spaces. It is available in thrust-type and torque-type configurations, outputting axial thrust and rotational torque respectively. The device can be equipped with dual-layer independent hydrogen blending and fuel supply, exhaust gas waste heat hydrogen production, and airborne self-generating modules, making it suitable for aircraft, rockets, ships, heavy-duty equipment, and generator sets. It effectively overcomes the shortcomings of traditional detonation equipment, such as severe vibration, short lifespan, poor controllability, single operating conditions, and insufficient safety. It features a simple structure, stable operation, wide applicability, high energy utilization, and flexible power expansion.

Description

Technical Field

[0001] This invention belongs to the field of detonation power engine technology, specifically relating to a multi-chamber annular array cyclic intermittent self-controlled ordered detonation power device, which can be adapted to two power forms: axial thrust output and rotational torque output. It is widely used in power matching scenarios in many fields such as aerospace vehicles, missiles, rockets, extraterrestrial object exploration equipment, ships, heavy transportation equipment, and stationary power generation equipment. Background Technology

[0002] With its characteristics of fast energy release rate, high energy density and excellent work efficiency, detonation power devices have become the core research and development direction of the new generation of power equipment. Compared with traditional turbojet and piston power devices, they have significant advantages in terms of high thrust density and high structural potential.

[0003] Existing conventional detonation power devices generally suffer from several technical shortcomings: First, the combustion chamber structure is fixed and operates under continuous high-temperature and high-pressure detonation conditions, making it highly dependent on the high-temperature resistance, high-pressure resistance, and impact resistance of the structural materials. This results in large alternating loads, severe vibrations, and short service life, making stable engineering applications difficult. Second, the detonation sequence of multiple combustion chambers is disordered, easily leading to problems such as synchronous detonation, gas backflow, and accidental ignition, resulting in large fluctuations in power output and poor operational stability. Third, traditional devices require additional configurations such as check valves, flow guiding components, and pressurization structures. The auxiliary components result in a complex overall structure, excessive weight, and high processing and maintenance costs. Fourth, the adaptability to different operating conditions is limited, only suitable for conventional atmospheric fuel combustion conditions, and cannot meet the power requirements of extreme conditions such as high-altitude hypoxia, space vacuum, and underwater confinement. Fifth, the electrode conduction mostly adopts a mechanical contact structure, which suffers from severe wear, is prone to electric spark leakage, has insufficient safety redundancy, and lacks a systematic electrical control interlock, voltage stabilization and sealing, and energy recovery structure. Its overall performance is difficult to meet the requirements of high performance, long life, high safety, and multi-condition adaptability of high-end equipment.

[0004] For example, in 2012, the inventors proposed an intermittent spur turbine engine technology (patent application number: 201210115103.3). This technology integrates the pulse detonation vibration working mechanism and adopts an intermittent cyclic combustion mode in the combustion chamber. Compared with traditional detonation engines, it can effectively reduce the average operating temperature of the entire machine and extend the service life of the equipment. However, this technology still has inherent limitations: the combustion chamber is a passive air intake structure, and the fuel enters the combustion chamber directly, resulting in uneven fuel-air mixing; it only has a single function of combustion detonation, which limits its applicable scenarios; and the use of spark plug ignition and simultaneous detonation of multiple combustion chambers can generate instantaneous ultra-large impact loads, which can easily cause damage to structural components.

[0005] In summary, existing detonation vibration devices suffer from core defects such as unreasonable structural design, poor detonation controllability, short lifespan, limited operating conditions, insufficient safety, and low energy utilization. There is an urgent need to develop a multi-chamber ordered detonation vibration device that is structurally simple, has controllable timing, is widely adaptable to operating conditions, is stable and safe in operation, and has both thrust and torque output capabilities. Summary of the Invention

[0006] The purpose of this invention is to overcome the shortcomings of the prior art and provide a multi-chamber annular array cyclic intermittent self-controlled ordered detonation vibration device. This device strictly optimizes the cavity layout, end cap structure, electrical control system, fuel supply and timing control logic to achieve multi-chamber time-sharing ordered intermittent detonation vibration. It does not require additional unidirectional flow guide components and has the advantages of voltage stabilization and backflow prevention, non-contact electrical control detonation, multi-mode working condition adaptation, and efficient energy recovery. It can be compatible with axial thrust and rotational torque output, solving the technical problems of short life, poor stability, single working condition and low safety of the prior art.

[0007] To achieve the above objectives, the present invention provides a technical solution: a multi-chamber annular array cyclic intermittent self-controlled ordered detonation vibration power device, the core structure of which includes a detonation combustion chamber ring, a front end cover, a rear end cover, a central rotating shaft, a fuel supply system, and an electric flame generation control system.

[0008] The detonation combustion chamber ring is a fixed structure, formed by multiple fan-shaped, trapezoidal, or fan-trapezoidal transitional detonation combustion chambers with consistent cross-sections, evenly arranged at equal angles along the circumference.

[0009] The central rotating shaft is rotatably assembled with the inner ring of the detonation combustion chamber ring via bearings; the front end cover and the rear end cover are respectively fitted onto the front and rear end faces of the detonation combustion chamber ring, and the front end cover and the rear end cover are fixedly connected to the central rotating shaft and rotate synchronously with the central rotating shaft; a non-combustible, insulating, high-temperature resistant, lubricating isolation layer is provided between the fitting end faces of the front end cover, the rear end cover and the detonation combustion chamber ring, so that the end cover and the chamber ring form a low-friction relative rotational fit.

[0010] Each of the detonation combustion chambers is equipped with an electric flame electrode assembly arranged longitudinally, with corresponding electric flame conduction negative electrodes provided on the front and rear covers; one of the electric flame conduction negative electrodes is used for electric flame heating, and the other electric flame conduction negative electrode is used for electric flame ignition and detonation; the positive electrode of the electric flame electrode assembly is fixedly connected to the external power supply circuit, and the negative electrode is connected to the external circuit by forming an electric field coupling with the electric flame conduction negative electrode through movable alignment, with no mechanical contact during the entire process.

[0011] The front cover and the rear cover are evenly distributed with closed and open workstations along the circumference; the front cover has a compressor fan blade inclined towards the open workstation at the starting edge of the closed workstation, and the rear cover has a regenerative spiral blade inclined towards the open workstation at the ending edge of the closed workstation; the inner and outer circumferential edges of the compressor fan blade and the regenerative spiral blade are integrally formed with a reinforced cylindrical surface.

[0012] The compressor fan blades and the regenerative spiral blades are arranged at opposite angles, and together they form a unidirectional flow guiding structure that stabilizes pressure and prevents backflow, thereby achieving unidirectional airflow in the chamber and stabilizing pressure to prevent backflow.

[0013] With the front cover open, it completes chamber misalignment ventilation, fresh working fluid inflation and pressurization, and oil mixing; the closed section can be embedded with a special electric flame conduction negative electrode for electric flame heating, which can stably activate the electric flame preheating and energy storage function for non-combustible working fluids under closed conditions, while constraining the high-pressure detonation airflow in the cavity to only release pressure in one direction towards the rear cover, avoiding disorderly leakage of front pressure and ensuring concentrated output of axial thrust.

[0014] When the rear cover is closed, it works with the front cover to complete the chamber sealing and compression, precise fuel injection or electric flame constant temperature heating and energy storage, and reserve pressure potential energy and thermal energy for subsequent instantaneous detonation. The area where the rear cover begins to open is equipped with electric flame conduction negative electrodes for electric flame ignition, and the detonation depressurization and chamber ventilation processes are started in sequence according to the preset time sequence.

[0015] Furthermore, the electric flame electrode group includes at least one positive electric flame generating electrode and at least one interconnected negative electric flame generating electrode; the axial length of the positive electric flame generating electrode is less than that of the negative electric flame generating electrode, and the distance between the positive electric flame generating electrode and the negative electric flame generating electrode on the end cap is greater than the distance between the positive electric flame generating electrode and the negative electric flame generating electrodes in the same group.

[0016] The positive and negative electrodes of the electric flame generator are fixedly installed inside the corresponding detonation combustion chamber by insulating support components. The insulating support components have pre-embedded conductive conductors that extend outward to the outside of the device housing. The positive electrodes of the electric flame generators corresponding to each detonation combustion chamber are first connected in series with the linkage control switch modules, and then connected in parallel to each other before being uniformly connected to the positive electrode of the high-voltage DC power supply.

[0017] The linkage control switch module connected in series with the positive electrode of the electric flame generator in each chamber forms a closed-loop linkage control based on the alignment signal between the negative electrode of the electric flame generator and the negative electrode of the electric flame conduction in that chamber. When the negative electrode of the electric flame generator is not connected to the negative power supply circuit, the linkage control switch module forcibly cuts off the positive power supply circuit. Only when the negative electrode of the electric flame generator and the negative electrode of the electric flame conduction are precisely aligned and coupled to conduct, the positive power supply circuit is momentarily connected.

[0018] The negative electrodes of the electric flame conduction system on the front and rear covers are connected to the negative electrode of the high-voltage DC power supply in sequence via wires, conductive slip rings, and elastic carbon brushes.

[0019] The positive electrode, negative electrode, and negative electrode of the electric flame generator are all made of tungsten-based alloy; the power supply circuits of all electrodes inside the device are equipped with a fully insulated shielding structure.

[0020] The power unit is divided into two structural types: axial thrust type and torque type.

[0021] The axial thrust type power unit is equipped with an axial air intake structure, and its energy recovery spiral blades have a small tilt angle and short axial length, which are used to convert the energy of the detonation airflow into axial linear thrust.

[0022] The torque-type power unit is equipped with a side air intake structure, and the front end of the central rotating shaft extends outward and is fitted with a front cover to form a torque output end; the torque-type regenerative spiral blades have a large inclination angle and a longer axial length, and the rear side of the regenerative spiral blades is equipped with an impeller assembly consisting of multi-stage stationary impellers and moving impellers.

[0023] The stationary impeller is fixedly connected to the outer casing of the device, and the moving impeller is fixedly connected to the tail shroud, the central rotating shaft, the front end cover, and the rear end cover to achieve synchronous rotation; the inner circumferential edge of the stationary impeller is integrally formed into an inner cylindrical surface, and the outer circumferential edge of the moving impeller is integrally formed into an outer cylindrical surface; a thermal expansion gap is reserved between the stationary impeller and the moving impeller to accommodate thermal expansion and contraction; along the airflow direction, the number of blades of each impeller increases progressively, and the air outlet flow cross section expands progressively.

[0024] Furthermore, the fuel supply system adopts the following conveying structure: the front section of the central rotating shaft is set as a hollow shaft tube, or a nested outer tube is used to form a dynamic fuel transmission path by utilizing the gaps between them; the device is also equipped with an external fixed fuel delivery pipeline and a rotating movable oil receiving interface; a fuel atomizing nozzle is set on the inner circumferential cylindrical surface of the front end cover and located upstream of the compressor fan blades.

[0025] The fuel is sequentially transported to the fuel atomizing nozzle via an external fixed fuel delivery pipeline, a rotating movable oil receiving interface, a dynamic fuel transmission passage, and an external dynamic delivery pipeline. The fuel atomizing nozzle is then sprayed radially or obliquely toward the detonation combustion chamber, where it is uniformly mixed with the intake airflow before entering the chamber.

[0026] The fuel is compatible with all free-flowing liquid and gaseous combustibles, such as methanol, kerosene, gasoline, diesel, and liquefied petroleum gas.

[0027] Furthermore, the fuel supply system adopts a dual-layer independent dynamic fuel transmission path structure. One layer of the path transports the main fuel, and the other layer transports hydrogen separately. A hydrogen one-way valve nozzle is installed on the front end cover at the upstream position corresponding to the electric flame ignition station. The main fuel and hydrogen are respectively transported to the fuel atomizing nozzle and the hydrogen one-way valve nozzle through their respective independent external fixed fuel delivery pipelines, rotary movable oil receiving interfaces, dynamic fuel transmission paths, and external dynamic delivery pipelines, so as to realize the main fuel hydrogen-blended combustion detonation or electric flame preheating hydrogen-blended assisted detonation.

[0028] When the device is started for the first time, an external driving force is required to drive the front cover, rear cover and central shaft to rotate in an oriented manner according to the existing technical solutions, so as to complete the alignment of each station and achieve the first detonation; the torque type power unit is adjusted to the no-load operation position before starting; the high-power type can be equipped with a small auxiliary electric drive motor to realize the autonomous start of the whole machine without the need for external drive equipment.

[0029] Furthermore, the device includes two standardized operating timing modes; Operating mode one is the pure fuel knock mode, and the timing allocation of each component is as follows: Front-end cover timing: 1 / 2 closed 1 / 2 open → fully open → fully closed; Backend cover timing: 1 / 2 open 1 / 2 closed → fully closed → fully open; The single-cycle timing function is as follows: staggered air exchange → pressurized fuel injection and air-fuel mixture → electric flame ignition and explosion, instantaneous pressure relief and power generation; The mode is divided into three functional sections, which are adapted to conventional low-altitude atmospheric conditions. During the detonation and depressurization process, the high-pressure gas acts in the opposite direction on the end face of the front cover, forming an axial concentrated thrust to provide flight propulsion power for the whole machine. On the other hand, it impacts the energy recovery spiral blades of the rear cover at high speed, and autonomously drives the front and rear covers to rotate synchronously on the same axis by relying on the airflow impact force. It automatically cycles through the full-time switching of each chamber for air exchange, pressurization, preheating, detonation, and depressurization. At the same time, it can coaxially drive auxiliary components such as the generator rotor to operate, realizing multi-level recovery and utilization of detonation residual pressure energy, reducing the ineffective energy loss of the whole machine, and adapting to the high-efficiency and long-term operation requirements of missiles, rockets, and extraterrestrial exploration equipment.

[0030] Operating mode two is a hybrid mode with electric flame energy storage. The timing allocation of each component is as follows: Front-end cover timing: 1 / 2 closed 1 / 2 open → fully open → fully closed → fully closed; Backend cover timing: 1 / 2 open 1 / 2 closed → full domain closed → full domain closed → full domain open; The single-cycle timing function is as follows: staggered air exchange → pure air filling or pressurized fuel injection mixture → non-combustible working fluid electric flame heating and energy storage → electric flame ignition and explosion, instantaneous pressure relief and work. Mode 2 is divided into 4 functional sections, of which the 3rd functional section is dedicated to the optional electric flame heating expansion detonation module; if only fuel detonation is performed, the 3rd functional section is idle, which is suitable for special and complex working conditions.

[0031] The working section refers to the standard circumferential dimension of the combustion chamber corresponding to the radial cross-section on the front and rear end caps; the functional section is the actual circumferential dimension corresponding to the completion of a single air exchange, pressurization, heating, and detonation process; the circumferential dimension of the functional section is variable and can be greater than, equal to, or less than the standard working section dimension according to the thrust requirement. Key structural parameters such as the circumferential ratio of closed to open end caps, the dimensions of functional sections, and the axial length of the combustion chamber can all be optimized and calibrated through simulation and whole-machine testing in combination with equipment type, fuel type, and airspace conditions to ensure accurate operating sequence, minimal vibration, and optimal power efficiency of the device.

[0032] Furthermore, the number of detonation combustion chambers in a single synchronous detonation operation is M≥2; the device adopts a "symmetrical design, symmetrical implementation" structural layout: during the design phase, the number of working sections of the front and rear covers is equal to the number of preset detonation combustion chambers; during the actual processing and assembly phase, the actual number of chambers in the detonation combustion chamber ring is at least one more than the number of working sections of the end cover.

[0033] Taking M=4 as an example, in working mode one, 4×3=12 standard working sections can be formed by matching and arranging the front and rear end covers. When using an equivalent structural design, the total number of knock chambers in the combustion chamber ring is set to 12; if an asymmetrical structural scheme is used, the total number of chambers must be at least one more than the number of standard working section groups.

[0034] If only one chamber is added, that is, 13 fan-shaped detonation chambers are evenly distributed along the circumference: the four detonation chambers that work synchronously with the whole machine will detonate one by one as the front and rear end covers rotate through one working section, which can completely avoid the strong impact and resonance defects of the whole machine caused by the synchronous detonation of multiple chambers. However, this solution has a drawback: the equipment will produce a wobbling problem similar to that of a single-blade fan during operation.

[0035] The optimization solution is as follows: select a larger M value and group the chambers to achieve sequential detonation of each chamber; when the layout is not equal, the total number of chambers is increased by 2 or 3 compared with the standard number of groups, so as to eliminate the phenomenon of simultaneous detonation of multiple chambers from the root and greatly improve the stability of the whole machine operation.

[0036] Furthermore, a thin layer of non-flammable, high-temperature resistant lubricating grease, such as PFPE perfluoropolyether, is filled between the mating surfaces of the detonation combustion chamber ring and the front and rear end covers. The lubricating grease is added to the central shaft along the outside of the fuel line or through a parallel dedicated oil pipe, and automatically dispersed to the sealing contact surface by the centrifugal force generated by the intake airflow and the rotation of the end cover.

[0037] To prevent high-temperature gas leakage, 1 to 2 radial pressure relief grooves are opened on the end face of the partition between adjacent detonation combustion chambers. If necessary, the end face of the partition is widened and thickened. Pressure relief vents connecting the front and rear ends are opened on the radial outer edge of the partition, and pressure relief vents are opened on the inner ring edge of the detonation combustion chamber.

[0038] Furthermore, the device is equipped with a power generation module, which includes a permanent magnet block and a stator winding. The permanent magnet block is embedded and fixed on the reinforced cylindrical surface of the outer peripheral edge of the front cover compressor fan blade. The stator winding is fixedly assembled inside the device's fixed housing, and the permanent magnet block and the stator winding are arranged radially opposite each other.

[0039] Furthermore, the device is equipped with an on-site hydrogen production system; the on-site hydrogen production system recovers the waste heat from the engine tail and exhaust gas to heat the hydrogen production feedstock, and dynamically adjusts the heat exchange area with electromagnetic heating or a movable heat exchange device to precisely control the medium temperature and realize the recycling of hydrogen production and waste heat.

[0040] Furthermore, the device adopts a multi-ring nested detonation combustion chamber structure to increase the total number of detonation combustion chambers, adapting to the ultra-high power requirements of heavy-duty transport equipment and large ships; each ring chamber is independently equipped with compressor fan blades, energy recovery spiral blades, and independent electrical control circuits, and follows the aforementioned "equivalent design, non-equivalent implementation" layout rule; each chamber partition has radial and circumferential pressure relief grooves, and all grooves are interconnected to prevent high-temperature gas leakage between rings and prevent accidental ignition from causing equipment damage.

[0041] Furthermore, double-layered, triple-layered, and higher-layered nested annular cavities can all be divided into outer and inner annular groups. After grouping, each annular cavity in the outer group adopts a uniform number of detonation combustion chambers, while each annular cavity in the inner group adopts a separate, uniform number of detonation combustion chambers. The number of chambers in the inner and outer groups can be designed differently. Detonation combustion chambers at the same radial position share a common set of electric flame linkage control switch modules. The electric flame linkage control switch modules for the outer group are mounted on the outside of the device housing; the electric flame linkage control switch modules for the inner group are mounted inside the inner annular cavity of the device. By zoning control modules in the inner and outer sections and sharing a single electrical control unit for radially aligned cavities, the number of high-voltage lines is reduced, the overall insulation and shielding structure is simplified, and high-voltage signal crosstalk between multiple cavities is avoided.

[0042] This invention addresses the common industry problem of vibration and noise generated by pulse detonation impact, high-speed airflow disturbance, and alternating loads during the operation of multi-chamber annular array cyclic intermittent detonation vibration power devices. It optimizes the structural design for noise reduction and vibration damping. The device utilizes a multi-chamber annular array layout with layered impedance composite silencing chambers. Each detonation chamber's exhaust end is matched with a microporous perforated sound-absorbing bushing and an expanded buffer noise reduction channel. Relying on the mechanical rotational intermittent detonation characteristics of the annular array chambers, the detonation pulses of each chamber naturally alternate and stagger, avoiding the superposition and amplification of sound waves caused by simultaneous multi-chamber detonation, thus weakening the generation of strong pulse noise at the sound source. Simultaneously, a high-temperature resistant damping sound-absorbing composite layer is installed on the outer wall of the device, which, together with the waste heat recovery channel, forms a smooth airflow buffer noise reduction path, significantly reducing detonation impact noise and airflow howling noise. Meanwhile, vibration-damping and conformal-fitting gaskets, such as Rogers PORON-XRD60 vibration-damping and conformal-fitting gaskets, are installed at the support positions of the central rotating shaft and the inner ring bearing of the detonation combustion chamber, as well as at the axial positioning positions of the central rotating shaft and the front and rear covers. Relying on the high resilience and energy absorption characteristics of the polymer gaskets, the instantaneous axial impact force generated by the sequential detonation of each combustion chamber is gradually weakened, alleviating the structural fatigue and overall vibration loss caused by alternating impact loads. Through the coordinated design of structural noise reduction and vibration damping, the overall operating noise and vibration amplitude are significantly reduced, meeting the low-noise and stable operation requirements of generator sets, low-altitude aircraft, and ship power equipment, and effectively expanding the applicability of the device in various fields such as civil low-altitude transportation and near-shore ship propulsion. Beneficial effects

[0043] Compared with the prior art, the present invention has the following beneficial effects: 1. Multi-chamber ring array orderly detonation, stable operation and long equipment life: This invention adopts a fixed ring array detonation combustion chamber structure, combined with the layout rule of "equivalent design, non-equivalent implementation", to achieve multi-chamber cyclic intermittent time-sharing detonation, abandoning the ultra-large impact load of traditional synchronous detonation, and greatly reducing the vibration of the whole machine and structural fatigue damage; the end cover and the chamber ring adopt a frictionless relative rotational fit, combined with a high-temperature resistant lubricated sealing structure, with no mechanical wear loss. At the same time, the full-area insulation shielding and non-contact electric field coupling electrode design completely solve the industry pain points of high temperature ablation, mechanical wear and short life of traditional detonation devices, and greatly improve the service life and operational stability of the equipment.

[0044] 2. Passive unidirectional pressure stabilization and flow guidance, highly simplified and lightweight structure: The reverse tilting layout of the front cover's air fan blades and the rear cover's energy return spiral blades naturally forms a unidirectional flow guidance and pressure stabilization backflow structure. There is no need to assemble additional mechanical one-way valves, flow guides and other auxiliary components, which greatly simplifies the overall structure, reduces the number of parts, and lowers the equipment's weight and processing and maintenance costs. The blade edges are integrally formed reinforced cylindrical surfaces, which also serve as structural reinforcement, improving the end cover's resistance to knocking and thermal deformation, and significantly improving structural strength and reliability.

[0045] 3. Dual working sequence modes, adaptable to multiple working conditions: This invention is equipped with two standardized timing modes: pure fuel detonation and electric flame energy storage composite detonation. It can adapt to conventional low-altitude atmospheric fuel combustion conditions, as well as special and complex working conditions such as high-altitude oxygen deficiency, space vacuum, and underwater confinement. It can achieve detonation work of combustible working media such as fuel oil and gas, and can also achieve expansion detonation of non-combustible working media through electric flame heating. It has a wide range of working condition adaptability and the equipment is extremely versatile.

[0046] 4. Dual power output forms, adaptable to diverse application scenarios: The device is divided into two types of structures: axial thrust type and torque type. The thrust type structure can output high-intensity axial linear thrust, which is suitable for propulsion scenarios such as aircraft, missiles, rockets, and deep space probes. The torque type structure efficiently converts airflow energy through multi-stage impeller assembly to output stable high torque, which can meet the rotational power requirements of ships, heavy transportation equipment, generator sets, etc. One machine can adapt to the power needs of multiple fields.

[0047] 5. Closed-loop interlocking electrical control system with sufficient safety redundancy and prevention of accidental detonation: The system adopts a differentiated electrode layout and closed-loop linkage control logic. The power supply circuit can only be connected when the chamber electrode and the end cover conductive electrode are precisely aligned and coupled. Combined with the full-area insulation shielding structure, it completely avoids safety hazards such as leakage, inter-cavity sparking, and premature detonation. The tungsten-based alloy non-contact electrodes have no mechanical friction loss, are resistant to high-temperature erosion, and ensure the safe and stable operation of the electrical system.

[0048] 6. Dual-layer independent fuel supply, high combustion efficiency and safety: The dual-layer dynamic transmission path enables independent delivery and precise mixing and combustion of the main fuel and hydrogen, effectively improving fuel combustion efficiency and solving the problems of flameout, carbon buildup and incomplete combustion in traditional power units; the hydrogen nozzle integrates a one-way valve structure to eliminate the risk of backfire from gas flow, making the fuel supply system safe and reliable, while also being compatible with a wide range of liquid and gaseous combustible working fluids.

[0049] 7. Expandable energy self-sufficiency and waste heat recovery functions, with excellent energy efficiency: An optional integrated power generation module can be equipped to generate electricity independently by rotating the end cap to cut magnetic field lines, meeting the power needs of the whole machine's electronic control, ignition, and sensing equipment, and achieving closed-loop self-sufficiency of electricity; It can be equipped with an on-site hydrogen production system to recover waste heat from the equipment for recycling, accurately regulate hydrogen operation, and significantly improve the overall energy utilization rate; The multi-ring nested cavity structure can expand the power level as needed to meet the needs of ultra-high power equipment.

[0050] 8. Perfect sealing and pressure relief structure, low operating loss and high reliability: Through the combination of high-temperature resistant lubricating grease automatic sealing, partition radial pressure relief groove, air guide hole and inner ring pressure relief passage, high pressure gas is effectively guided, gas leakage is blocked, end face gas leakage and fire problems are eliminated, ensuring stable detonation conditions, reducing energy loss and improving the reliability of continuous equipment operation. Attached Figure Description

[0051] Figure 1 This is a schematic diagram of the longitudinal cross-sectional structure of the thrust-type self-generating power generation function of the present invention; Figure 2 This is a schematic diagram of the longitudinal cross-sectional structure of the thrust-type explosion-assisted and self-generating power generation function of the present invention. Figure 3 This is a schematic diagram of the miniaturized ducted fan-type thrust structure of the present invention; Figure 4 This is a schematic diagram of the basic torque-type longitudinal cross-sectional structure of the present invention; Figure 5 This is a schematic diagram of the torque-type structure of the present invention with waste heat hydrogen production and hydrogen doping functions; Figure 6 This is a front view schematic diagram of the dual detonation combustion chamber ring structure of the present invention.

[0052] Explanation of reference numerals in the attached diagram: 1. Fan-shaped detonation combustion chamber; 2. Front end cover; 3. Rear end cover; 4. Central shaft; 5. Bearing; 6. Compressor fan blade; 7. Regenerative spiral blade; 8. Main casing; 9. Front casing; 10. Rear casing; 11. Inlet fairing; 12. Wake fairing; 13. Positioning pin; 14. End cover fastening nut; 15. End cover fastening screw; 16. Fairing support; 17. Fuel delivery pipe; 18. Central shaft tube; 19. Fuel nozzle; 20. Blade edge cylindrical surface; 21. Generator rotor permanent magnet block; 22. Generator stator winding; 23. Positive electrode for chamber electric flame generation; 24. Negative electrode for chamber electric flame generation; 25. Generator module casing; 26. Negative electrode for front end cover electric flame conduction; 27. Negative electrode for rear end cover electric flame conduction; 28. Conductive slip ring; 29. ​​Carbon brush; 30. 31. Power control switch; 32. Chamber electrode support; 33. Outer shell connecting flange; 34. Control switch module; 35. Hydrogen nozzle; 36. Insulation layer; 37. Wire; 38. Cooling airflow channel; 39. Movable sealed oil receiving interface; 40. Front cover; 41. Shaft sleeve outer tube; 42. Outer pipeline; 43. Oil sealing plug; 44. Ducted fan blade; 45. Support component; 46. Ducted fan housing; 47. Hydrogen delivery pipe; 48. Dynamic fuel delivery pipeline; 49. Stationary impeller; 50. Moving impeller; 51. Heat exchange device; 52. Tangential air inlet; 53. Power output end; 54. Hydrogen generator; 55. Hydrogen production feedstock; 56. Pressure relief hole; 57. Pressure relief groove. Detailed Implementation

[0053] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. These embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit the scope of protection of the present invention. Based on the technical concept of the present invention, equivalent substitutions, modifications, and optimizations made by those skilled in the art without creative effort are all within the scope of protection of the present invention.

[0054] Example 1: As Figure 1 As shown, this embodiment is an axial thrust type multi-chamber annular array cyclic intermittent self-controlled ordered detonation power device, which is mainly used for axial propulsion power scenarios of aircraft, missiles, rockets, and deep space probes.

[0055] The detonation combustion chamber ring is a fixed structure, formed by multiple fan-shaped detonation combustion chambers 1 with the same cross-section evenly arranged at equal angles along the circumference; the central rotating shaft 4 is rotatably assembled with the inner ring of the detonation combustion chamber ring through bearings 5; the front end cover 2 and the rear end cover 3 are respectively fitted and assembled on the front and rear end faces of the detonation combustion chamber ring, and the front end cover and the rear end cover are fixedly connected to the central rotating shaft 4 through positioning groove pins 13 and rotate synchronously with the central rotating shaft; the mating end faces of the front end cover, the rear end cover and the detonation combustion chamber ring are filled with a non-combustible insulating high-temperature resistant lubricating grease PFPE perfluoropolyether high-temperature resistant lubricating medium isolation layer, so that the end cover and the chamber ring form a low-friction relative rotational fit.

[0056] Each of the detonation combustion chambers 1 is provided with an electric flame electrode group arranged longitudinally, and electric flame conduction negative electrodes 26 are correspondingly matched on the front end cover and the rear end cover; wherein the outer negative electrode 24 is movably aligned with the electric flame conduction negative electrode of the front end cover and connected to the external circuit for electric flame heating, and the inner negative electrode 24 is movably aligned with the electric flame conduction negative electrode of the rear end cover and connected to the external circuit for electric flame ignition and detonation, and the outer negative electrode and the inner negative electrode are interconnected.

[0057] The front cover and the rear cover are evenly distributed with closed and open workstations along the circumference; the front cover has a compressor fan blade 6 inclined towards the open workstation at the starting edge of the closed workstation, and the rear cover has a regenerative spiral blade 7 inclined towards the open workstation at the ending edge of the closed workstation. In this embodiment, an axial air intake structure is adopted. The regenerative spiral blade has a small inclination angle and a short axial length, so energy is preferentially converted into axial thrust. The inner and outer circumferential edges of the compressor fan blade and the regenerative spiral blade are integrally formed with a reinforced cylindrical surface 20.

[0058] The compressor fan blades and the regenerative spiral blades are arranged at opposite angles. Together, they form a unidirectional flow guiding structure that stabilizes pressure and prevents backflow, thus achieving unidirectional airflow in the chamber and stabilizing pressure to prevent backflow.

[0059] The positive and negative electrodes of the electric flame generator are fixedly installed inside the corresponding detonation combustion chamber by means of insulating support 31. The insulating support has a pre-embedded conductive conductor that extends outward to the outside of the device housing. The insulating support can be made of materials such as zirconium oxide or silicon nitride. The positive electrodes of the electric flame generators corresponding to each detonation combustion chamber are first connected in series with the linkage control switch module 33, and then connected in parallel to each other and connected to the positive electrode of the high voltage DC power supply.

[0060] The linkage control switch module 33 connected in series with the positive electrode of the electric flame generator in each chamber forms a closed-loop linkage control based on the alignment signal between the negative electrode of the electric flame generator and the negative electrode of the electric flame conduction in that chamber. When the negative electrode of the electric flame generator is not connected to the negative power supply circuit, the linkage control switch module forcibly cuts off the positive power supply circuit. Only when the negative electrode of the electric flame generator and the negative electrode of the electric flame conduction are precisely aligned and coupled to conduct, the positive power supply circuit is instantaneously connected.

[0061] The negative electrode 26 for electric flame conduction on the front cover and the rear cover is connected to the negative electrode of the high voltage DC power supply in sequence through a wire, a conductive slip ring 28, an elastic carbon brush 29, and a power control switch 30.

[0062] The positive electrode, negative electrode, and negative electrode of the electric flame generator are all made of tungsten-based alloy; the power supply circuits of all electrodes inside the device are equipped with a fully insulated shielding structure.

[0063] The fuel supply system uses a hollow shaft tube 18 at the front of the central rotating shaft as a dynamic fuel transmission path; the device is also equipped with an external fixed fuel delivery pipeline 17 and a rotating movable sealed oil receiving interface 38; a fuel atomizing nozzle 19 is set on the inner circumferential cylindrical surface of the front cover and located upstream of the compressor fan blades.

[0064] Fuel is introduced through the fuel delivery pipe 17 via the top of the air intake shroud 11, and then through the high-speed rotating adapter movable sealed oil receiving interface 38 to the central shaft pipe 18. It is transported along the hollow shaft pipe to the air intake area of ​​the front cover 2, and then radially injected into the air intake channel in front of the compressor fan blades 6 through the fuel nozzle 19. It is fully and evenly mixed with the high-pressure air intake airflow under the forced airflow of the compressor fan, and then enters the detonation combustion chamber 1 to wait for detonation.

[0065] The fuel is compatible with various easily flowing liquid combustibles such as methanol, kerosene, gasoline, diesel, and liquefied petroleum gas, as well as various gaseous combustibles.

[0066] When the device is started for the first time, an external driving force is required to drive the front cover, rear cover and central shaft to rotate in an oriented manner according to the existing technical solutions, so as to complete the alignment of each station and achieve the first detonation; the torque-type power unit is adjusted to the no-load operation position before starting.

[0067] To prevent high-temperature combustion gas leakage, one or two radial pressure relief grooves 56 are formed on the end face of the radial partition between adjacent detonation combustion chambers. Pressure relief vents 55 connecting the front and rear ends are formed on the radial outer edge of the partition. Pressure relief vents 37 are formed between the inner ring edge of the detonation combustion chamber and the bearing 5. Figure 1 , Figure 6 As shown.

[0068] This embodiment is equipped with a power generation module, which includes a permanent magnet block 21 and a stator winding 22. The permanent magnet block is embedded and fixed on the reinforced cylindrical surface 20 on the outer periphery of the front cover compressor fan blade. The stator winding is fixedly assembled inside the device fixing power generation module housing 25, and the permanent magnet block and the stator winding are arranged radially opposite each other. The power generation module housing 25 is fixedly connected to the front housing 9 and the main housing 8 through flanges 32 at the front and rear, respectively. The main housing 8 is also fixedly connected to the rear housing 10 through flanges.

[0069] Example 2: Figure 2 As shown, this embodiment is a thrust-type multi-chamber annular array cyclic intermittent self-controlled ordered detonation hydrogen-infused axial jet engine of the present invention with hydrogen-assisted detonation function. Based on embodiment 1, the central rotating shaft adopts a hollow shaft tube, and a nested outer tube structure is added to form a double-layer independent dynamic fuel supply system. The outer pipeline transports the main fuel such as kerosene and methanol, while the central pipeline independently transports hydrogen. The two media are completely isolated.

[0070] The main fuel is supplied to the outer pipeline 41 via the fuel delivery pipe 17 through the high-speed rotating adapter movable sealing oil receiving interface 38, and is delivered to the air intake area of ​​the front cover 2. It is then radially sprayed out through the fuel nozzle 19, mixed with the air intake flow, and enters the chamber.

[0071] Hydrogen gas is delivered via an external fixed hydrogen delivery pipeline 46, a rotary movable sealed oil receiving interface 38, a dynamic hollow shaft tube 18, and an external dynamic hydrogen delivery pipeline 47, and is directly injected into the combustion chamber about to experience detonation through a hydrogen one-way valve nozzle 34 located upstream of the ignition position on the front end cover. This achieves hydrogen-assisted combustion and detonation. The hydrogen nozzle has a built-in passive one-way valve structure, preferably a spherical one-way piston type one-way valve, which automatically seals the pipeline during high-pressure backflow due to detonation, completely eliminating the safety hazard of backfire, effectively improving fuel combustion efficiency, and solving the problems of difficult ignition and easy flameout under lean conditions at high altitudes.

[0072] Example 3: As shown in Figure 3, this example is a miniaturized modified ducted fan thrust-type multi-chamber annular array cyclic intermittent self-controlled ordered detonation hydrogen-infused axial jet engine, suitable for power support scenarios of small low-altitude aircraft and vertical take-off and landing aircraft. This example is adapted and optimized based on the core structure of Example 1: the axial length of the central rotating shaft 4 is extended, the tilt angle of the regenerative propeller blades is appropriately increased, the built-in power generation module is eliminated, and the overall structure is simplified and the weight is reduced.

[0073] The central shaft front end 41 directly drives the ducted fan blades 43, eliminating the need for intermediate transmission structures and minimizing power loss. The ducted fan housing and the thrust engine housing are fixedly connected via a support member 44, forming an inner and outer double-ducted airflow channel. The inner duct airflow enters the chamber to participate in detonation work, while the outer duct airflow is used for forced cooling of the entire unit, simultaneously superimposed with aerodynamic thrust, resulting in excellent combined thrust output performance. This embodiment fully inherits the core control functions of the original model, such as timing control, contactless electronic control, unidirectional voltage stabilization, and time-sharing detonation.

[0074] When the front and rear end cover operates at low speeds, the ducted fan assembly can be removed, leaving only the outer bypass structure. The outer bypass relies on high-speed jet ejection to create a low-pressure zone, continuously introducing ambient airflow to amplify thrust, and also continuously cooling the main body of the detonation engine.

[0075] Example 4: Figure 4 As shown, this embodiment is a torque-type multi-chamber annular array cyclic intermittent self-controlled ordered detonation engine, suitable for rotating power output scenarios such as ships, heavy vehicles, and generator sets. The device adopts a side tangential air intake 50, and the front end of the central rotating shaft extends to form a front casing 39 to form a torque output end 51; the regenerative spiral blades have a large inclination angle and a longer axial length, and a multi-stage static and dynamic impeller assembly is assembled on the rear side of the blades.

[0076] The stationary impeller 47 is fixed to the equipment casing 8 to achieve airflow stabilization and rectification. The moving impeller 48 rotates synchronously with the central shaft and the front and rear end covers. Both the moving and stationary impellers have an integrated cylindrical surface on their circumferential edges for reinforcement. A thermal expansion gap is reserved between the stationary and moving impellers to avoid high-temperature friction and wear. The number of impeller blades increases gradually along the airflow direction, and the flow cross section expands gradually, efficiently converting the energy of the detonation airflow into mechanical torque.

[0077] This embodiment retains the core structures such as multi-chamber orderly detonation, closed-loop electronic control interlock, dual-layer fuel supply, dual-time sequence working mode, and sealed pressure relief. Before starting, it needs to be adjusted to the no-load position to reduce the starting driving force requirements, ensuring stable operation and smooth torque output.

[0078] Example 5: Figure 5 As shown, this embodiment is a multi-chamber annular array cyclic intermittent self-controlled ordered detonation torque engine with on-site hydrogen production and hydrogen-assisted detonation functions. Based on the torque-type structure of Embodiment 4, it is equipped with an on-site hydrogen production system and the hydrogen-assisted detonation module described in Embodiment 2. The on-site hydrogen production system includes hydrogen production raw material 53, heat exchange device 49, hydrogen generator 52, etc.; wherein the heat exchange device is placed at the exhaust tail of the torque-type engine to recover the waste heat of the equipment exhaust gas. With the help of the expandable heat exchange device, the heat exchange area is dynamically adjusted to precisely control the temperature of hydrogen production raw materials such as methanol and water, so as to realize the recycling of waste heat and on-site hydrogen production.

[0079] The produced hydrogen is transported to the chamber ignition station through an independent pipeline, and mixed as needed to aid combustion, thereby improving the detonation efficiency and torque output power. At the same time, the one-way valve nozzle eliminates the risk of backfire, taking into account both high energy efficiency and high safety, and can be adapted to complex working conditions such as heavy-load continuous operation and underwater closed power.

[0080] Example 6: As shown in Figure 6, this example adopts a double-ring nested detonation combustion chamber structure. Each ring chamber is independently equipped with a compressor fan blade, a regenerative spiral blade, and a dedicated electrical control circuit. The overall layout follows the principle of "equivalent design, non-equivalent implementation".

[0081] Each inner and outer ring cavity is equipped with 20 sets of combustion chambers. Two sets of combustion chambers at the same radial position share a single electric flame control module, corresponding to the first type of working mode design: a single complete working cycle is divided into 3 functional segments, with each functional segment corresponding to a working segment. Theoretically, the number of synchronous detonation working chambers is M=6, corresponding to 18 working segments and 18 standard chambers per single ring. In this embodiment, the actual configuration of a single ring is 20 chambers, which is 2 sets more than the theoretical value. This indicates that the synchronous working combustion chambers are divided into two sets for staggered detonation. The specific detonation timing logic needs to be further verified and improved through subsequent experiments.

[0082] Each chamber partition has interconnected radial and circumferential pressure relief grooves 56; a pressure relief vent 55 is provided on the outer edge of the radial groove of the outer ring, penetrating the front and rear end faces; a pressure relief vent 37 is reserved between the inner ring cavity sidewall and the central bearing. The above-mentioned pressure relief structure can effectively block the gas flow between the inner and outer rings, avoid accidental ignition of adjacent combustion chambers, and can multiply the total number of detonation combustion chambers of the whole machine, greatly improve the power output, and is suitable for ultra-high power equipment application scenarios such as heavy launch vehicles and large ships.

[0083] Furthermore, double-layered, triple-layered, and higher-layered nested annular cavities can all be divided into outer and inner annular groups. After grouping, each annular cavity in the outer group adopts a uniform number of detonation combustion chambers, while each annular cavity in the inner group adopts a separate, uniform number of detonation combustion chambers. The number of chambers in the inner and outer groups can be designed differently. Detonation combustion chambers at the same radial position share a common set of electric flame linkage control switch modules. The electric flame linkage control switch modules for the outer group are mounted on the outside of the device housing; the electric flame linkage control switch modules for the inner group are mounted inside the inner annular cavity of the device. By zoning control modules in the inner and outer sections and sharing a single electrical control unit for radially aligned cavities, the number of high-voltage lines is reduced, the overall insulation and shielding structure is simplified, and high-voltage signal crosstalk between multiple cavities is avoided.

[0084] The above description is merely a preferred embodiment of the present invention and is not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A multi-chamber annular array cyclic intermittent self-controlled ordered detonation vibration dynamic device, characterized in that, It includes a detonation combustion chamber ring, a front cover, a rear cover, a central rotating shaft, a fuel supply system, and an electric flame generation and control system; The detonation combustion chamber ring is a fixed component, which is formed by multiple detonation combustion chambers with cross-sections of fan-shaped, trapezoidal or fan-shaped trapezoidal transition structure evenly arranged and enclosed along the circumference at equal angles; the partitions of adjacent detonation combustion chambers are provided with connected radial pressure relief grooves, the outer edge of the partitions is provided with pressure relief vents that penetrate the front and rear end faces, and the inner ring of the detonation combustion chamber ring is provided with pressure relief vents. The central rotating shaft is rotatably assembled with the inner ring of the detonation combustion chamber ring via bearings; the front end cover and the rear end cover are respectively fitted onto the front and rear end faces of the detonation combustion chamber ring, and the front end cover and the rear end cover are fixedly connected to the central rotating shaft and rotate synchronously; a high-temperature resistant insulating and lubricating isolation layer is provided between the front end cover, the rear end cover and the fitting end face of the detonation combustion chamber ring, and the two form a low-friction relative rotational fit. Each detonation combustion chamber is longitudinally arranged with an electric flame electrode group. The front and rear covers are equipped with corresponding electric flame conduction negative electrodes. One set of electric flame conduction negative electrodes is used for electric flame heating, and the other set is used for electric flame ignition and detonation. The positive electrode of the electric flame electrode group is connected to an external power supply circuit, and the negative electrode is connected by electric field coupling with the electric flame conduction negative electrode without mechanical contact. The front cover and the rear cover are divided into closed and open workstations along the circumference; the front cover has a compressor fan blade inclined towards the open workstation at the beginning of the closed workstation, and a regenerative spiral blade inclined towards the open workstation at the end of the closed workstation of the rear cover; the compressor fan blade and the regenerative spiral blade are integrally formed reinforced cylindrical surfaces on their inner and outer peripheral edges. The compressor fan blades and the energy recovery spiral blades are arranged at opposite angles to form a unidirectional flow guide, pressure stabilization and backflow prevention structure. The device has M≥2 detonation combustion chambers that perform work synchronously in a single operation. It adopts an equivalent design and asymmetrical implementation layout: the number of end cap working sections in the design stage is consistent with the number of preset chambers, and the actual number of assembled chambers is at least 1 more than the number of end cap working sections. This enables the detonation combustion chambers to perform staggered gas filling, fuel mixing, and preheating standby processes. The device is equipped with two standardized timing operation modes: pure fuel detonation and electric flame energy storage composite.

2. The multi-chamber annular array cyclic intermittent self-controlled ordered detonation vibration dynamic device according to claim 1, characterized in that, The electric flame electrode group includes at least one electric flame generating positive electrode and at least one group of mutually conductive electric flame generating negative electrodes; the axial length of the electric flame generating positive electrode is less than that of the electric flame generating negative electrode, and the distance between the electric flame generating positive electrode and the electric flame conducting negative electrode is greater than the distance between the positive electrode and the negative electrode in the same group. The positive and negative electrodes of the electric flame generator are fixed in the chamber by an insulating support, and the conductor inside the insulating support leads out to the outside of the device housing; the positive electrodes of the electric flame generators in each chamber are connected in series with a linkage control switch module and then connected in parallel to the positive electrode of a high-voltage DC power supply. The linkage control switch module is controlled in a closed loop based on the alignment signal between the negative electrode of the electric flame generator and the negative electrode of the electric flame conduction; the positive power supply circuit is turned on only when the two are precisely aligned and coupled; the negative electrode of the electric flame conduction is connected to the negative electrode of the high voltage DC power supply via a wire, a conductive slip ring, and a flexible carbon brush. The positive electrode, negative electrode, and negative electrode of the electric flame generator are made of tungsten-based alloy, and all electrode power supply circuits are equipped with a fully insulated shielding structure.

3. The multi-chamber annular array cyclic intermittent self-controlled ordered detonation vibration dynamic device according to claim 1, characterized in that, The power unit is divided into two types: axial thrust type and torque type. The axial thrust type adopts an axial air intake structure, with a small tilt angle and short axial length of the energy recovery spiral blades, and the airflow energy is mainly converted into axial thrust. The torque type adopts a side tangential air intake structure, and the front end of the central rotating shaft extends to form a torque output end; the torque type regenerative spiral blade has a large inclination angle and a longer axial length, and a multi-stage impeller assembly is set on its rear side, the impeller assembly including stationary impeller and moving impeller; The stationary impeller is fixed to the outer casing of the device, while the moving impeller is fixedly connected to the tail shroud, central shaft, front end cover, and rear end cover and rotates synchronously. The inner ring of the stationary impeller is integrally formed with an inner cylindrical surface, and the outer ring of the moving impeller is integrally formed with an outer cylindrical surface. A thermal expansion gap is reserved between the stationary impeller and the moving impeller. Along the airflow direction, the number of blades of each impeller increases and the airflow cross section expands step by step.

4. The multi-chamber annular array cyclic intermittent self-controlled ordered detonation vibration dynamic device according to claim 1, characterized in that, The fuel supply system is equipped with a dynamic fuel transmission path, which is formed by a hollow central shaft tube or the gap between the central shaft tube and the nested outer tube; the device is also equipped with an external fixed fuel pipeline and a rotating movable oil receiving interface; a fuel atomizing nozzle is provided upstream of the front end cover air compressor fan blades; Fuel is delivered to the fuel atomizing nozzle via an external fixed fuel pipeline, a rotating movable fuel receiving interface, and a dynamic fuel transmission path, and is injected radially or obliquely into the chamber to mix with the intake air; the fuel includes, but is not limited to, liquid and gaseous combustible media such as methanol, kerosene, gasoline, diesel, and liquefied petroleum gas; The fuel supply system is a dual-layer independent passage structure, with one layer transporting the main fuel and the other layer transporting hydrogen separately; a hydrogen one-way valve nozzle is provided upstream of the ignition station on the front end cover; the main fuel and hydrogen are transported independently in two separate paths to achieve hydrogen-blended detonation or electric flame preheating with hydrogen-blended auxiliary detonation; When the device is started, the external drive mechanism drives the end cover and the central shaft to rotate to complete the initial detonation; the torque type device is adjusted to the no-load position before starting.

5. The multi-chamber annular array cyclic intermittent self-controlled ordered detonation vibration dynamic device according to claim 1, characterized in that, The two standardized working timing modes are as follows: The first working mode is the pure fuel knock mode. A single working cycle is divided into three functional segments, and the timing sequence is as follows: staggered air exchange, pressurized fuel injection and air-fuel mixture, electric flame ignition and depressurization to do work; the timing sequence of the front cover is semi-closed and semi-open, fully open, and fully closed; the timing sequence of the rear cover is semi-open and semi-closed, fully closed, and fully open, which is suitable for conventional low-altitude atmospheric conditions. Working mode two is an electric flame energy storage composite mode. A single working cycle is divided into four functional segments, with the following sequence: staggered air exchange, gas or pressurized fuel injection mixture, electric flame heating and energy storage of non-combustible working fluid, and electric flame ignition and depressurization for work. The front cover sequence is semi-closed and semi-open, fully open, fully closed, and fully closed. The rear cover sequence is semi-open and semi-closed, fully closed, fully closed, and fully open. The third functional segment is an optional heating process, which is idle when performing fuel detonation and is suitable for special working conditions such as high altitude, vacuum, and closed environments. The circumferential ratio of the end cap opening and closing, the circumferential dimensions of the functional sections, and the axial length of the chamber were optimized through simulation and whole-machine testing.

6. The multi-chamber annular array cyclic intermittent self-controlled ordered detonation vibration dynamic device according to claim 1, characterized in that, The lubrication isolation layer uses a perfluoropolyether-based high-temperature resistant lubricating medium; the lubricating medium is injected into the central rotating shaft through a special oil pipe and is evenly distributed on the sealing surface by the intake airflow and the centrifugal force of the end cap rotation.

7. The multi-chamber annular array cyclic intermittent self-controlled ordered detonation vibration dynamic device according to claim 1, characterized in that, It also includes an optional power generation module; the power generation module includes a permanent magnet block and a stator winding; the permanent magnet block is embedded on the outer reinforced cylindrical surface of the front cover blade, the stator winding is fixed to the inner side of the device housing, and the permanent magnet block and the stator winding are arranged radially opposite to each other.

8. The multi-chamber annular array cyclic intermittent self-controlled ordered detonation vibration dynamic device according to claim 1, characterized in that, It also includes an optional on-site hydrogen production system; the on-site hydrogen production system recovers the waste heat of the exhaust gas to heat the hydrogen production raw materials, is equipped with a heat exchange device with adjustable heat exchange area, and is combined with electromagnetic heating for precise temperature control to realize waste heat recycling for hydrogen production.

9. The multi-chamber annular array cyclic intermittent self-controlled ordered detonation vibration dynamic device according to claim 1, characterized in that, The detonation combustion chamber ring is provided with two or more nested annular structures; each layer of the chamber is independently configured with compressor fan blades, energy recovery spiral blades and dedicated electronic control circuits, all following the layout of equal design and non-equal implementation; the partitions of each layer are connected to provide radial and circumferential pressure relief grooves to prevent interlayer gas leakage and avoid cross-ring misignition. The multi-layered nested annular cavity is divided into an outer ring and an inner ring. Each ring in the outer ring adopts the same number of detonation combustion chambers. The detonation combustion chambers at the same radial position share a set of electric flame linkage control switch modules, which are installed on the outside of the device shell. Each ring in the inner ring adopts another set of the same number of detonation combustion chambers. The detonation combustion chambers at the same radial position share a set of electric flame linkage control switch modules, which are installed inside the inner ring cavity of the device.

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