A disc impact rotor engine

Abstract

The application discloses a disc impact rotor engine and relates to the field of rotor power, which comprises a disc impact rotor engine main body, a compressor, an ignition and stable combustion mechanism, an emergency gas afterburning restart mechanism, a power supply control module, a cooling mechanism, a water injection power increasing mechanism and a waste gas heat recovery mechanism; the ignition and stable combustion mechanism is integrated with a plasma flame stable combustion unit and a spark plug ignition unit, can be automatically switched according to aerospace, military high-end scenes and civil general scenes, and is matched with a flame state sensor to realize real-time monitoring of the working condition of a combustion chamber; after flameout, an electric control system automatically triggers the emergency restart; the engine adopts impact combustion, realizes instantaneous fuel injection, instantaneous ignition and instantaneous explosion power, has strong power output, is matched with a double-mode ignition and stable combustion structure to ensure stable and reliable combustion, adopts a small-sized closed direct injection combustion chamber, relies on plasma or a spark plug to stabilize the flame to avoid flameout, and can be directly used as an independent power source to drive various equipment.

Description

Technical Field

[0001] This invention relates to rotor power technology, specifically to a disc-type impact rotor engine. Background Technology

[0002] The disc-type impact rotor engine can be used directly as an independent power source to drive various types of equipment. It is mainly used in multi-rotor and non-multi-rotor manned and cargo drones, military drones, heavy-load drones, aerospace equipment, military tanks, special combat vehicles, ships, engineering machinery, special mobile power supply equipment, aerospace equipment, new energy vehicle power systems, and new energy range-extending power systems, achieving efficient direct drive power output from the rotor engine and lightweight equipment design.

[0003] Existing power units mostly use piston engines, which suffer from technical drawbacks such as severe wear of reciprocating parts, high vibration, short service life, and high maintenance costs. Conventional rotary engines generally use a single, fixed compressor model, which cannot match the operating requirements of different speed conditions. It is difficult to balance high-speed and low-speed conditions, resulting in low overall operating efficiency. Furthermore, the heat from the exhaust gas is directly emitted after power output, and the heat resources cannot be recovered and utilized, leading to insufficient energy utilization. At the same time, traditional rotary engines have poor combustion chamber flame stability, which can easily lead to accidental flameout under varying operating conditions and airflow disturbances. They also lack a reliable emergency restart mechanism, making them unsuitable for direct drive applications across all fields. Moreover, they have a limited range of fuel compatibility and cannot be adapted to various combustible fuels. Currently, small rotary engines generally suffer from industry-wide problems such as low thermal efficiency, short lifespan, unstable operation, and poor overall performance, which have been difficult to overcome for a long time. Summary of the Invention

[0004] The purpose of this invention is to provide a disc-type impact rotor engine to solve the problems of severe wear, high vibration, short service life, and high maintenance cost of reciprocating components in the prior art.

[0005] To achieve the above objectives, the present invention provides the following technical solution: a disc-type impact rotor engine, comprising an engine body, a compressor, an ignition and combustion stabilization mechanism, an emergency gas combustion restart mechanism, a power supply control module, a cooling mechanism, a water spray power enhancement mechanism, and an exhaust heat recovery mechanism, characterized in that: the engine body is provided with mutually isolated and sealed compression chambers and power chambers; the compressor and rotor engine can be assembled in three layouts: coaxial left and right, vertically independent, and front and rear connected in series; the compression side only compresses air, while the power side independently completes the combustion gas impact work; both sides are completely sealed and isolated, with no gas crossflow or pressure interference; the main body has an integrally formed disc-type impact impeller, and the outer edge is provided with an annular impact working surface. The engine features internal heat dissipation vents and relies on the directional high-pressure airflow from one side of the combustion chamber to impact the outer circumference of the impeller for work. The entire unit has no reciprocating moving parts, and the output shaft is rigidly directly connected to the load, eliminating the need for a gearbox. The combustion chamber is a high-temperature resistant, pressure-bearing, sealed cavity, employing a direct injection fuel-air mixture, instantaneous fuel injection, instantaneous ignition, and instantaneous ramming and detonation combustion mode. The engine is equipped with a full-condition adaptive electronic fuel injection system that automatically adjusts the fuel injection quantity according to speed and load. The compressor is integrated into the main body and cannot be externally mounted; it can be any of the following types: rolling piston, rotary vane, or centrifugal. When arranged coaxially on both sides, the compressor and rotor rotate synchronously. When arranged with separate upper and lower chambers or in series front and rear configurations, the compressor uses an independent shaft drive. (Low speed 30...) It is suitable for rolling piston and rotary vane compressors for operating speeds of 00r / min to 12000r / min, and for centrifugal compressors for high-speed operating speeds of 10000r / min to 60000r / min. The ignition and stabilization mechanism integrates a plasma stabilization unit and a spark plug ignition unit, which can work independently or in conjunction, and are automatically switched by the power supply control module according to the operating conditions. The machine body is equipped with a flame sensor to monitor the combustion status. The emergency gas re-ignition mechanism includes a high-pressure gas storage chamber and an electromagnetic injection valve. When the flame is extinguished, the electronic control module controls the injection of combustible gas to reignite it. The cooling mechanism can be either air-cooled or jacketed water-cooled. The water injection power enhancement mechanism injects water into the combustion chamber for vaporization and power enhancement. The exhaust gas heat recovery mechanism has heat exchange pipes built into the shell. It recovers waste heat to preheat the intake air to 300-500℃; the whole machine is lightweight, weighing approximately 40kg for 60kW, 70kg for 100kW, and 110kg for 150kW. For civilian applications, a shock-absorbing and protective structure can be added; all chambers, impellers, pipelines, and combustion chambers are standardized independent components, separated by dedicated seals, making disassembly and maintenance simple; the machine is compatible with gasoline, diesel, kerosene, jet fuel, liquefied petroleum gas, methanol, and ethanol, with operating speeds from 3000r / min to 60000r / min and power from 60kW to 500kW. It features low vibration, long service life, and is suitable for drones, aerospace, military vehicles, ships, construction machinery, new energy vehicles, and mobile power stations.

[0006] Furthermore, the power supply control module is the overall control unit of the machine, which uniformly controls the dual ignition unit, flame sensor, afterburner injection valve, and electronic fuel injection system to achieve intelligent and coordinated regulation of the entire machine under all operating conditions.

[0007] Furthermore, the air compression chamber is only responsible for compressing air, while the power chamber independently completes the work done by the gas impact. The two chambers are completely sealed and isolated, with no pressure interference between them and no internal structural interference.

[0008] Furthermore, the high-pressure gas is concentrated on the annular working area around the impeller, resulting in concentrated and stable power output. At the same time, it simplifies the overall machine processing and assembly structure and reduces production and manufacturing costs.

[0009] Furthermore, the three assembly layouts of the compressor and engine can be freely matched with three types of compressors, and any compressor can be adapted to any of the left-right, up-down, or front-back installation methods.

[0010] Furthermore, the power supply control module is electrically connected to the plasma stabilization unit and the spark plug ignition unit respectively. The power supply control module has a built-in operating condition determination unit and ignition mode switching logic, and collects engine speed, load and intake air temperature operating parameters in real time. When the operating parameters are in the preset high operating condition threshold range, the plasma stabilization unit is activated; when the operating parameters are in the preset normal operating condition threshold range, the spark plug ignition unit is activated.

[0011] Furthermore, the water is injected into the high-temperature combustion chamber via the water injection booster mechanism to rapidly vaporize, thereby improving combustion efficiency and simultaneously increasing engine output power.

[0012] Furthermore, the waste heat from the exhaust gas is recovered through an internal heat exchange pipeline to preheat the compressed air entering the combustion chamber, effectively reducing fuel consumption and improving power output efficiency.

[0013] Furthermore, the machine has no reciprocating transmission structure and no seals that suffer long-term frictional wear, resulting in low operating vibration amplitude and enabling continuous and stable operation for extended periods.

[0014] Furthermore, the modular and standardized component design of the entire machine allows for independent disassembly and replacement of each functional cavity and power component, resulting in lower difficulty and cost of later inspection and maintenance.

[0015] Compared with existing technologies, the present invention provides a disc-type impact rotor engine, which uses a disc-type impact rotor engine as its core power source. The engine adopts impingement combustion to achieve instantaneous fuel injection, instantaneous ignition, and instantaneous deflagration for power output. It is equipped with a plasma flame stabilization unit and a spark plug ignition unit, which can flexibly switch between high-end aerospace and civilian ground conditions. With the help of flame sensors and electronic control systems, it can achieve automatic flameout monitoring and emergency forced restart to ensure stable and reliable combustion. It has no reciprocating moving parts and no vulnerable sealing structure. The engine can operate at speeds ranging from 3000 r / min to 60000 r / min and has a rated power ranging from 30 kW to 500 kW. It can be used directly as an independent power source for direct drive operation of equipment in all fields of aviation, aerospace, military, land and sea. It is stable, efficient and reliable.

[0016] It can use various combustible fuels such as diesel, gasoline, kerosene, aviation kerosene, liquefied gas, methanol, and ethanol without modifying the engine structure, and is suitable for fuel use in all scenarios.

[0017] The engine supports the independent selection and assembly of three types of compressors: rolling piston, rotary vane, and centrifugal. It is suitable for rolling piston and rotary vane compressors for low and medium speed conditions, and centrifugal compressors for high speed conditions. Each engine is equipped with only one type of compressor, perfectly matching the operating conditions across the entire speed range.

[0018] A water-spraying power-enhancing mechanism is added to spray water during the combustion process, which is then vaporized at high temperature to improve combustion efficiency and increase engine output power. A waste heat recovery mechanism is also provided to recover waste heat from the rotary engine exhaust gas, thereby improving the overall energy utilization efficiency.

[0019] The entire unit adopts a lightweight structural design, achieving extreme lightweight in aviation models and retaining significant lightweight advantages even after the addition of protective and shock-absorbing structures for civilian ground models. It requires no additional counterweight and is directly adaptable to the lightweight, compact installation and power usage needs of all scenarios, including non-multi-rotor manned and cargo drones, military drones, heavy-duty drones, aerospace equipment, military tanks, special vehicles, ships, construction machinery, new energy vehicles, and special mobile power supplies. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this invention. For those skilled in the art, other drawings can be obtained based on these drawings.

[0021] Figure 1 A cross-sectional view of a disc-type impact rotor engine provided in an embodiment of the present invention;

[0022] Figure 2 This is a cross-sectional view of a rotary vane compressor provided in an embodiment of the present invention;

[0023] Figure 3 A cross-sectional view of a rolling rotor compressor provided in an embodiment of the present invention;

[0024] Figure 4 This is a cross-sectional view of a centrifugal compressor provided in an embodiment of the present invention;

[0025] Figure 5 A cross-sectional view of a rotary vane type rotor engine provided in an embodiment of the present invention;

[0026] Figure 6 A cross-sectional view of a rolling rotor engine provided in an embodiment of the present invention;

[0027] Figure 7 A cross-sectional view of a centrifugal rotary engine provided in an embodiment of the present invention;

[0028] Figure 8 A cross-sectional view of a coaxial vane rotary engine provided in an embodiment of the present invention;

[0029] Figure 9 A cross-sectional view of a coaxial rolling rotor engine provided in an embodiment of the present invention;

[0030] Figure 10 A cross-sectional view of a coaxial centrifugal rotor engine provided in an embodiment of the present invention.

[0031] Explanation of reference numerals in the attached figures:

[0032] 1. Water spray device; 11. Blade heat dissipation; 12. Impeller blade; 13. Oil injection device; 14. Emergency start device; 15. Ignition device; 16. Air intake device; 17. Combustion chamber; 18. Compressed air intake; 19. Waste heat recovery; 16. Exhaust device; 2. Air inlet; 21. Air outlet; 3. Air inlet; 31. Exhaust outlet; 32. Housing; 33. Rotor; 34. Blade; 4. Exhaust outlet; 41. Sliding vane; 42. Air inlet; 43. Main sleeve; 5. Direct drive output shaft; 51. Bearing; 52. Sealing partition plate; 53. Impeller blade; 54. Engine housing; 55. Sealing partition plate; 56. Compressor housing; 57. Compressor rotor; 58. Centrifugal compressor housing; 59. Centrifugal compressor impeller. Detailed Implementation

[0033] To enable those skilled in the art to better understand the technical solution of the present invention, the present invention will be further described in detail below with reference to the accompanying drawings.

[0034] A disc-type impingement rotor engine includes a disc-type impingement rotor engine body, a compressor, an ignition and combustion stabilization mechanism, an emergency gas afterburning and restart mechanism, a power supply control module, a cooling mechanism, a water injection power enhancement mechanism, and an exhaust gas heat recovery mechanism. The ignition and combustion stabilization mechanism includes a plasma flame combustion stabilization unit and a spark plug ignition unit. The plasma flame combustion stabilization unit is used in high-end aerospace and military applications, while the spark plug ignition unit is used in general civilian ground applications. The power supply control module automatically switches between these units according to the application scenario. The entire engine is also equipped with a flame status sensor to collect combustion chamber flame signals in real time. When an unexpected flameout signal is detected, it is immediately fed back to the power supply control module to trigger the emergency restart logic.

[0035] The entire aircraft adopts an aerospace-grade integrated lightweight structural design. The power-to-weight ratio of this aerospace-specific model is as follows:

[0036] • 60kW class model: Total weight approximately 40 kg

[0037] • 100kW class model: Total weight approximately 70 kg

[0038] • 150kW class model: Total weight approximately 110 kg

[0039] When applied to civilian ground applications such as new energy vehicles, construction machinery, and ships, the addition of protective, shock-absorbing, and auxiliary structures will increase the overall weight accordingly, with reasonable fluctuations in weight.

[0040] This invention employs a disc-type impact rotor engine as its core power source. The machine utilizes impingement combustion, achieving instantaneous fuel injection, instantaneous ignition, and instantaneous detonation for power output, resulting in strong power delivery. Combined with an ignition and stabilization mechanism, it ensures continuous and stable combustion. The rotor engine's power airflow impacts the outer periphery of the rotor disc, allowing it to directly drive various equipment as an independent engine. It has no reciprocating moving parts or easily damaged sealing structures, resulting in low operating vibration, long service life, and significantly reduced maintenance costs. The single-sided directional direct jet impingement structure ensures stable and reliable power efficiency. Exhaust gas heat recovery heats the air entering the combustion chamber, raising the intake air temperature to 300℃~600℃, significantly reducing fuel consumption and increasing power output. The direct injection of fuel-air mixture into a small, sealed cavity enables instantaneous combustion for power output.

[0041] The compressor and disc-type impact rotor engine adopt a sealed, multi-chamber layout. The compressor and disc-type impact rotor engine body are integrated and cannot be independently separated. The multi-chamber layout isolates the compressor chamber and the power chamber, including but not limited to coaxial left and right, and top and bottom independent chambers. When arranged coaxially on the left and right, they operate synchronously with no power loss. When arranged top and bottom, they have independent shaft systems for precise transmission. The compressor side has dedicated compressed air, and the power side has dedicated impingement and combustion output power. Both sides are completely sealed and isolated, with no gas crossflow, no pressure interference, and no structural interference. The working principle of the disc-type impact rotor is as follows: the high-pressure gas after being pressurized by the compressor enters a small sealed combustion chamber and mixes instantaneously with the direct-injection fuel. The ignition and stabilization mechanism ignites the fuel to achieve instantaneous combustion. The high-pressure power airflow precisely impacts the working surface of the outer circumference of the rotor disc. The disc is driven to rotate at high speed by the unilateral directional direct injection high-pressure airflow, directly outputting shaft power. There is no reciprocating motion conversion or friction loss of seals. The power is directly converted and output from the impact of the outer circumference of the disc.

[0042] The engine is compatible with a variety of combustible fuels such as diesel, gasoline, kerosene, aviation kerosene, liquefied petroleum gas, methanol, and ethanol, meeting the supply needs of different scenarios and exhibiting extremely strong fuel adaptability.

[0043] This engine supports three independent compressor options, but only one type can be selected for use in a single unit:

[0044] 1. Medium and low speed operation: Scroll reciprocating compressor

[0045] 2. Medium and low speed operation: Rotary vane compressor

[0046] Both of the above are suitable for speeds of 3000r / min to 12000r / min.

[0047] 3. High-speed operation: Centrifugal compressor

[0048] Adapted to speeds of 10,000 r / min to 60,000 r / min

[0049] All three compressors can be individually adapted to the local rotary engine, perfectly matching the cooling and intake boosting requirements of different speeds and operating conditions;

[0050] The built-in ignition and combustion stabilization mechanism allows the plasma flame stabilization unit and spark plug ignition unit to work independently or in conjunction with the impingement combustion system, ensuring stable combustion throughout the combustion chamber, preventing accidental flameout, and providing high operational stability with no easily worn sealing components. A flame status sensor monitors the combustion condition in real time; if flameout is detected, it immediately sends a signal to the power supply control module, triggering an emergency gas-assisted combustion restart mechanism for a forced restart. An exhaust heat recovery mechanism is also included to recover and utilize the heat from the exhaust gas after the rotor engine's power output, further improving the overall energy efficiency. A redundant emergency gas-assisted combustion restart mechanism is implemented, and the lightweight design eliminates the need for additional counterweights, directly adapting to the lightweight, compact installation and direct drive requirements of non-multi-rotor manned and cargo drones, military drones, heavy-duty drones, aerospace vehicles, military tanks, special operations vehicles, ships, engineering machinery, new energy vehicles, and special mobile power supply applications.

[0051] Example 1 (High-speed model)

[0052] A high-speed disc-type impingement rotor engine, operating at speeds of 10,000 r / min-60,000 r / min and rated power of 100 kW-500 kW, includes a disc-type impingement rotor engine body, a centrifugal compressor, an ignition and combustion stabilization mechanism, an emergency gas combustion restart mechanism, a power supply control module, a cooling mechanism, a water injection power enhancement mechanism, and an exhaust heat recovery mechanism. The ignition and combustion stabilization mechanism employs a plasma flame combustion stabilization unit, suitable for high-end aerospace and military applications. The engine uses impingement combustion, achieving instantaneous fuel injection, instantaneous ignition, and instantaneous deflagration for power output. The plasma flame combustion stabilization unit continuously maintains flame stability in the combustion chamber. A flame status sensor monitors the combustion chamber condition in real time, automatically triggering an emergency restart logic in case of accidental flameout. The rotor impeller blades are all equipped with internal heat dissipation holes, designed for high-speed operation, and can be configured with a single-stage, two-stage, or multi-stage centrifugal compressor. It can flexibly select any combustible fuel such as diesel, gasoline, or aviation kerosene according to the application scenario, ensuring stable combustion and power output. It directly outputs shaft power, serving as a direct-drive engine for aerospace vehicles, military tanks, high-speed special operations vehicles, and ships, driving equipment operation. The exhaust heat recovery mechanism simultaneously recovers the heat from the rotor engine's exhaust gas, achieving waste heat utilization. The water injection power-enhancing mechanism sprays water during the combustion process, which is vaporized at high temperature to increase engine power. The cooling system can be either air-cooled or water-cooled to ensure efficient heat dissipation at high speeds. In the event of an unexpected rotor engine shutdown, the emergency gas re-ignition restart mechanism injects high-pressure combustible gas to achieve forced re-ignition and restart.

[0053] Example 2 (Medium and Low Speed ​​Model)

[0054] A medium-low speed disc-type impingement rotor engine, operating at speeds of 3000 r / min-12000 r / min and rated power of 30 kW-500 kW, is equipped with a rotary vane compressor to meet the requirements of stable high-pressure air intake at medium and low speeds. The engine adopts impingement combustion, and the ignition and stabilization mechanism uses a spark plug ignition unit, making it suitable for general civilian ground applications. It achieves instantaneous fuel injection, instantaneous ignition, and instantaneous detonation for power output, resulting in strong power output. The engine is equipped with a flame sensor and an electronic control system to achieve automatic flameout monitoring and restart, ensuring stable combustion. The remaining structure, working principle, fuel compatibility, restart mechanism, waste heat recovery, and water injection power enhancement are all consistent with Embodiment 1.

[0055] Example 3 (Medium and Low Speed ​​Model)

[0056] A medium-low speed disc-type impact rotor engine, operating at speeds of 3000 r / min-12000 r / min and rated power of 30 kW-500 kW, includes a disc-type impact rotor engine body, a rolling piston compressor, an ignition and combustion stabilization mechanism, an emergency gas combustion restart mechanism, a power supply control module, a cooling mechanism, a water injection power booster mechanism, and an exhaust heat recovery mechanism. The engine employs impact combustion, and the ignition and combustion stabilization mechanism can utilize spark plug ignition units to achieve instantaneous fuel injection, instantaneous ignition, and instantaneous combustion for power output. A flame sensor monitors the combustion status in real time, and the electronic control system automatically restarts the engine in conjunction with the emergency mechanism after flameout, ensuring stable combustion. The engine is designed for stable boosting conditions at medium and low speeds, and is equipped with a separate rolling piston compressor, providing good low-speed response and stable pressure. The cooling mechanism uses air cooling, achieving internal air cooling through heat dissipation holes in the blades. The water injection power booster mechanism sprays water to increase power during the impact combustion process. The exhaust heat recovery mechanism simultaneously recovers waste heat from the rotor engine's exhaust gas, improving overall engine efficiency.

[0057] The foregoing has only described certain exemplary embodiments of the present invention by way of illustration. Undoubtedly, those skilled in the art can modify the described embodiments in various ways without departing from the spirit and scope of the present invention. Therefore, the foregoing drawings and descriptions are illustrative in nature and should not be construed as limiting the scope of protection of the claims of the present invention.

Claims

1. A disc-type impact rotor engine, comprising an engine body, a compressor, an ignition and combustion stabilization mechanism, an emergency gas combustion restart mechanism, a power supply control module, a cooling mechanism, a water injection power enhancement mechanism, and an exhaust gas heat recovery mechanism, characterized in that: The engine body has mutually isolated and sealed compression chambers and power chambers. The compressor and rotor engine can be assembled in three layouts: coaxial left and right, independent top and bottom, and front and rear series. The compression side only compresses air, while the power side independently completes the combustion gas impact work. Both sides are completely sealed and isolated. The main body has an integrated molded disc impact impeller with an annular impact working surface on the outer edge and internal heat dissipation holes. It relies on the directional high-pressure airflow from one side of the combustion chamber to impact the outer circumference of the impeller to do work. The whole machine has no reciprocating moving parts, and the output shaft is rigidly directly connected to the load. The combustion chamber is a high-temperature resistant, pressure-bearing, sealed cavity, adopting a combustion mode of direct injection of fuel-air mixture, instantaneous fuel injection, instantaneous ignition, and instantaneous ramming and detonation. The engine is equipped with a full-condition adaptive electronic fuel injection system. The compressor is integrated into the body and cannot be externally placed. It can be selected from any of the rolling piston type, rotary vane type, and centrifugal type. When arranged coaxially on the left and right, the compressor and rotor rotate synchronously. When arranged in separate top and bottom chambers or in series front and rear, the compressor adopts an independent shaft drive. Low speed 3 It is suitable for rolling piston and rotary vane compressors for operating speeds of 000r / min to 12000r / min, and for centrifugal compressors for high-speed operating speeds of 10000r / min to 60000r / min. The ignition and stabilization mechanism integrates a plasma stabilization unit and a spark plug ignition unit, which can work independently or in conjunction, automatically switched by the power supply control module according to operating conditions. A flame sensor is included in the machine body. The emergency gas refueling and restart mechanism includes a high-pressure gas storage chamber and an electromagnetic injection valve. When the flame is extinguished, the electronic control module... The machine features block-controlled injection of combustible gas for re-ignition; the cooling system can be either air-cooled or jacketed water-cooled; the water-spraying power-enhancing mechanism injects water into the combustion chamber for vaporization and power enhancement; the waste gas heat recovery mechanism has heat exchange pipes built into the shell to recover waste heat and preheat the intake air to 300-500℃; the 60kW model weighs approximately 40kg, the 100kW model approximately 70kg, and the 150kW model approximately 110kg; for civilian applications, a shock-absorbing and protective structure can be added; all chambers, impellers, pipes, and combustion chambers are standardized independent components, separated by dedicated seals.

2. The disc-type impact rotor engine according to claim 1, characterized in that: The power supply control module is the main control unit of the whole machine, which uniformly controls the dual ignition unit, flame sensor, afterburner injection valve and electronic fuel injection system.

3. The disc-type impact rotor engine according to claim 1, characterized in that: The air compression chamber is only responsible for compressing air, while the power chamber independently completes the work done by the gas impact. The two chambers are completely sealed and isolated.

4. The disc-type impact rotor engine according to claim 1, characterized in that: The high-pressure gas is concentrated and acts on the annular working area on the outer periphery of the impeller.

5. The disc-type impact rotor engine according to claim 1, characterized in that: The three assembly layouts of the compressor and engine can be freely combined with three types of compressors.

6. The disc-type impact rotor engine according to claim 1, characterized in that: The power supply control module is electrically connected to the plasma stabilization unit and the spark plug ignition unit respectively. The power supply control module has a built-in operating condition judgment unit and ignition mode switching logic. It collects engine speed, load and intake air temperature operating parameters in real time. When the operating parameters are in the preset high operating condition threshold range, the plasma stabilization unit is activated. When the operating parameters are within the preset normal operating condition threshold range, the spark plug ignition unit is activated.

7. The disc-type impact rotor engine according to claim 1, characterized in that: The water is injected into the high-temperature combustion chamber via a water spray booster mechanism and rapidly vaporizes.

8. The disc-type impact rotor engine according to claim 1, characterized in that: The waste heat from the exhaust gas is recovered through an internal heat exchange pipeline to preheat the compressed air entering the combustion chamber.

9. The disc-type impact rotor engine according to claim 1, characterized in that: The machine has no reciprocating transmission structure and no seals that suffer long-term frictional wear.

10. The disc-type impact rotor engine according to claim 1, characterized in that: The modular and standardized component design of the whole machine allows for independent disassembly and replacement of each functional cavity and power component.

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