Axial jet ignition detonation system of rotary detonation engine and method of axial jet ignition detonation system

Abstract

The invention provides an axial jet ignition detonation system of a rotary detonation engine and a method of the axial jet ignition detonation system. The propellant supply system comprises fuel and oxidant supply equipment, a fuel nozzle, a circular seam and a fuel / oxidant premixing injection pipeline. The axial jet ignition system comprises an ignition plug, a pre-combustion chamber and an ignition jet device, the ignition plug is located at the bottom of the pre-combustion chamber, and the ignition jet device is connected with an outlet of the pre-combustion chamber. The engine body comprises a combustion chamber outer ring, a combustion chamber inner ring and a combustion chamber, the control system comprises a total monitoring controller and a sensor, and is used for monitoring and adjusting the flow of the fuel and the oxidant. By adjusting the intensity and angle of jet flow flame, quick and reliable detonation can be achieved, and the performance and reliability of an engine under various working conditions are improved. In addition, the arrangement mode of the jet ignition device is flexible and diversified, multiple times of repeated detonation can be effectively achieved, and stable operation of the engine under the complex working condition is guaranteed.

Description

Technical Field

[0001] The patent of the present invention relates to a new ignition system and working method for a rotary detonation engine, specifically an ignition and detonation device with axially adjustable jet flame intensity and angle. Background Art

[0002] As a new type of propulsion system, the rotating detonation engine has attracted widespread attention in recent years due to its unique working principle and significant advantages. Compared with traditional engines, the combustion process of the rotating detonation engine is close to isochoric combustion, which can produce a higher pressure of combustion products under the same intake pressure, thereby improving the cycle efficiency. This type of engine has a compact structure, small size and light weight, which is very suitable for applications such as aerospace that have strict requirements on space and weight.

[0003] However, the successful operation of a rotating detonation engine depends on an effective ignition and detonation process. Traditional ignition methods, such as pre-detonator detonators, are prone to uncontrollable collision double-wave phenomena and have complex equipment structures; the ignition energy of the glow plug detonator is limited and the position is single. Therefore, the development of a new, efficient and reliable ignition and detonation method is particularly important for the practical application of rotating detonation engines.

[0004] The axial jet ignition and detonation device shows significant advantages in the rotating detonation engine. It can produce a stable and controllable detonation wave pattern, ensure the efficient propagation of the detonation wave, and avoid the common problems in the traditional ignition method. In addition, the axial jet ignition and detonation device has sufficient ignition energy and high reliability, and is suitable for a variety of working conditions and fuel types. From the specific design point of view, the jet flame is distributed on both sides of the fuel inlet, making the rotating detonation engine structure more compact, reducing additional piping, simplifying the design, and thus reducing manufacturing and maintenance costs. By dynamically adjusting the injection parameters, the axial jet ignition and detonation device can not only achieve multiple repeated ignitions, but also optimize the ignition effect, further improving the performance and stability of the rotating detonation engine. These advantages make the axial jet ignition and detonation device an indispensable key technology in the practical application of rotating detonation engines. Summary of the invention

[0005] The purpose of the present invention is to provide an axial jet ignition and detonation system and method for a rotating detonation engine. The technical feature of the system is to ensure that the rotating detonation engine can be reliably detonated and stably propagated under various operating conditions by adjusting the intensity of the jet flame and the angle of the ignition jet device, thereby improving the overall performance and reliability of the engine.

[0006] The present invention is achieved through the following scheme:

[0007] An axial jet ignition and detonation system for a rotating detonation engine, comprising a propellant supply system, an axial jet ignition system, a rotating detonation engine body and a control system; specifically:

[0008] The rotating detonation engine body comprises an engine cover, a combustion chamber outer ring, a combustion chamber inner ring and a combustion chamber; the combustion chamber outer ring and the combustion chamber inner ring are both fixed to the right side of the engine cover; a combustion chamber is formed between the combustion chamber outer ring and the combustion chamber inner ring, one end of the combustion chamber is the engine cover, and the other end is an outlet;

[0009] The propellant supply system and the axial jet ignition system are located on the left side of the engine cover;

[0010] The propellant supply system comprises a fuel supply device, an oxidant supply device, a fuel nozzle, an annular seam, a fuel / oxidant premix injection pipeline and a one-way valve; the annular seam and the fuel / oxidant premix injection pipeline are coaxially and evenly arranged on the circumference of the left side of the engine cover; the annular seam is arranged at the inlet of the fuel / oxidant premix injection pipeline; a plurality of the fuel / oxidant premix injection pipelines are coaxially arranged and evenly distributed on the circumference of the annular seam; the fuel nozzle is arranged on the inlet wall of the fuel / oxidant premix injection pipeline; a plurality of one-way valves are evenly embedded in the engine cover along the circumferential direction; the end of the fuel / oxidant premix injection pipeline is connected to the one-way valve, and the outlet of the one-way valve is the combustion chamber;

[0011] The axial jet ignition system includes an ignition plug, a pre-combustion chamber and an ignition jet device, wherein the pre-combustion chamber is fixed to the left side of the engine cover; the ignition plug is arranged at the bottom of the pre-combustion chamber; the ignition jet device is embedded in the engine cover and connected to the outlet of the pre-combustion chamber;

[0012] The control system includes a general monitoring controller, a fuel solenoid valve, an oxidant solenoid valve, a jet ignition fuel / oxidant premixing solenoid valve and a temperature / pressure sensor, and the general monitoring controller is connected to the fuel solenoid valve, the oxidant solenoid valve, the jet ignition fuel / oxidant premixing solenoid valve, the ignition plug and the temperature / pressure sensor; wherein the inlet of the fuel solenoid valve is connected to the fuel supply equipment, and the outlet is divided into two paths, one path is connected to a plurality of the fuel nozzles, and the other path is connected to the inlet of the jet ignition fuel / oxidant premixing solenoid valve; the inlet of the oxidant solenoid valve is connected to the oxidant supply equipment, and the outlet of the oxidant solenoid valve is divided into two paths, one path is connected to the annular gap, and the other path is connected to the inlet of the jet ignition fuel / oxidant premixing solenoid valve; the outlet of the jet ignition fuel / oxidant premixing solenoid valve is connected to the inlet of the precombustion chamber;

[0013] Furthermore, a temperature / pressure sensor is arranged on the inner wall surface of the outer ring of the combustion chamber to monitor the temperature and pressure changes in the combustion chamber.

[0014] Further, the plurality of fuel nozzles are not connected to each other;

[0015] Further, the ignition jet device is connected to the overall monitoring controller, and the outlet of the ignition jet device is a combustion chamber;

[0016] Furthermore, the ignition jet device is arranged on both sides of the one-way valve or centrally arranged between two one-way valves.

[0017] Furthermore, the outlet of the ignition jet device is adjusted in angle by a master monitoring controller, and the adjustable angle is 20 to 90 degrees relative to the central axis.

[0018] The present invention is beneficial in that:

[0019] 1. The rotary detonation engine based on axial jet ignition and detonation technology described in the present invention enhances the compactness of the engine by axially arranging the ignition jet device. This design not only saves space, but also optimizes the airflow path and improves the overall efficiency. At the same time, the jet ignition system has a simple structure and is easy to maintain, which reduces the manufacturing and maintenance costs and simplifies the system design.

[0020] 2. The rotary detonation engine based on axial jet ignition and detonation technology described in the present invention changes the arrangement of the ignition jet device, arranges the ignition jet device on both sides of the one-way valve, and utilizes the interaction between the compression wave generated by the collision of the jet flames and the injected fuel to achieve rapid detonation.

[0021] 3. The rotary detonation engine based on axial jet ignition and detonation technology of the present invention changes the arrangement of the ignition jet device between the two one-way valves, and by adjusting the jet angle, the flame hits the inner wall of the outer ring of the combustion chamber, and the convergence effect of the wall cavity is used to generate a shock wave, which interacts with the injected fuel, thereby achieving rapid detonation. This design improves the flexibility and reliability of ignition and ensures the continuous and stable operation of the engine under complex working conditions.

[0022] 4. The rotary detonation engine based on axial jet ignition and detonation technology described in the present invention can achieve rapid detonation by adjusting the angle of each ignition jet flame device through the overall monitoring controller, accurately control the jet direction so that the flame quickly contacts the fuel, reduce ignition delay, and ensure rapid response of the rotary detonation engine during startup and acceleration.

[0023] 5. The rotary detonation engine based on axial jet ignition and detonation technology described in the present invention can flexibly adjust the jet flame intensity by adjusting the opening of the jet ignition fuel / oxidant premixing solenoid valve; at the same time, the jet flame intensity of each ignition jet flame device is adjusted by the overall monitoring controller, and the asymmetric jet flame intensity is adopted to achieve precise control of the detonation of the detonation wave and its stable propagation direction. This design ensures that the engine can be detonated efficiently under different working conditions, improves overall reliability, and optimizes the ignition effect.

[0024] 6. The rotary detonation engine based on axial jet ignition and detonation technology described in the present invention uses a temperature / pressure sensor to monitor the temperature and pressure changes in the combustion chamber in real time, and feeds the data back to the main monitoring controller, which dynamically adjusts the opening of the fuel solenoid valve and the oxidizer solenoid valve accordingly to ensure the stable propagation of the detonation wave and further improve the engine performance and safety.

[0025] 7. The rotary detonation engine based on the axial jet ignition and detonation technology of the present invention has high versatility and adaptability, and can ensure effective ignition and detonation when using different types of fuels. This feature makes it suitable for the design of various rotary detonation engines, making the rotary detonation engine have a wide range of application prospects in different application scenarios. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0027] Figure 2 It is a right view of the rotating detonation engine body in which the ignition jet device of the present invention is arranged on both sides of the one-way valve;

[0028] Figure 3 It is a right view of the rotating detonation engine body in which the ignition jet device of the present invention is arranged between two one-way valves;

[0029] Figure 4 Close-up of different ignition jet arrangements.

[0030] In the figure: 1-oxidant supply equipment; 2-fuel supply equipment; 3-oxidant solenoid valve; 4-fuel solenoid valve; 5-general monitoring controller; 6-jet ignition fuel / oxidant premixing solenoid valve; 7-fuel nozzle; 8-annular gap; 9-fuel / oxidant premixing injection pipe; 10-ignition plug; 11-precombustion chamber; 12-ignition jet device; 13-engine cover; 14-one-way valve; 15-temperature / pressure sensor; 16-combustion chamber outer ring; 17-combustion chamber inner ring; 18-combustion chamber. DETAILED DESCRIPTION

[0031] The present invention will be further described below in conjunction with the accompanying drawings and embodiments:

[0032] like Figure 1 As shown: an axial jet ignition and detonation device for a rotating detonation engine, comprising a control system, a propellant supply system, an axial jet ignition system and a rotating detonation engine body;

[0033] The rotating detonation engine body comprises an engine cover plate 13, a combustion chamber outer ring 16, a combustion chamber inner ring 17 and a combustion chamber 18; the combustion chamber outer ring 16 and the combustion chamber inner ring 17 are both fixed to the right side of the engine cover plate 13; the combustion chamber 18 is formed between the combustion chamber outer ring 16 and the combustion chamber inner ring 17, one end of the combustion chamber 18 is the engine cover plate 13, and the other end is an outlet;

[0034] The propellant supply system and the axial jet ignition system are located on the left side of the engine cover;

[0035] The propellant supply system comprises a fuel supply device 2, an oxidant supply device 1, a fuel nozzle 7, an annular gap 8, a fuel / oxidant premix injection pipeline 9 and a one-way valve 14; the annular gap 8 and the fuel / oxidant premix injection pipeline 9 are coaxially and evenly arranged on the circumference of the left side of the engine cover plate 13; a plurality of the fuel / oxidant premix injection pipelines 9 are coaxially arranged and evenly distributed on the circumference of the annular gap 8; the fuel nozzle 7 is arranged on the inlet wall of the fuel / oxidant premix injection pipeline 9; a plurality of the one-way valves 14 are evenly embedded in the engine cover plate 13 along the circumferential direction;

[0036] The axial jet ignition system includes an ignition plug 10, a pre-combustion chamber 11 and an ignition jet device 12, wherein the pre-combustion chamber 11 is fixed to the left side of the engine cover plate 13; the ignition plug 10 is arranged at the bottom of the pre-combustion chamber 11; the ignition jet device 12 is embedded in the engine cover plate 13 and connected to the outlet of the pre-combustion chamber 12;

[0037] The control system includes a general monitoring controller 5, a fuel solenoid valve 4, an oxidant solenoid valve 3, a jet ignition fuel / oxidant premixing solenoid valve 6 and a temperature / pressure sensor 15, and the general monitoring controller 5 is connected to the fuel solenoid valve 4, the oxidant solenoid valve 3, the jet ignition fuel / oxidant premixing solenoid valve 6, the ignition plug 10 and the temperature / pressure sensor 15; wherein the inlet of the fuel solenoid valve 4 is connected to the fuel supply device 2, and the outlet of the fuel solenoid valve 4 is divided into two paths, one of which is connected to a plurality of the fuel nozzles 7, and the other is connected to the jet ignition fuel / oxidant premixing solenoid valve 10. The inlet of the magnetic valve 6 is connected; the inlet of the oxidant solenoid valve 3 is connected to the oxidant supply equipment 1, and the outlet of the oxidant solenoid valve 3 is divided into two paths, one is connected to the annular gap 8, and the other is connected to the inlet of the jet ignition fuel / oxidant premixing solenoid valve 6; the jet ignition fuel / oxidant premixing solenoid valve 6 is connected to the fuel solenoid valve 4 and the oxidant solenoid valve 3, and the other end is connected to the inlet of the precombustion chamber 11; the temperature / pressure sensor 15 is arranged on the inner wall surface of the combustion chamber outer ring 16, which is used to monitor the temperature and pressure changes in the combustion chamber 18.

[0038] Further, the plurality of fuel nozzles 7 are not connected to each other; the end of the fuel / oxidant premix injection pipe 9 is connected to the one-way valve 14, and the outlet of the one-way valve 14 is the combustion chamber 18;

[0039] Furthermore, the outlet of the jet ignition fuel / oxidant premixing solenoid valve 6 is connected to the precombustion chamber 11 .

[0040] Furthermore, the outlet of the pre-combustion chamber 11 is connected to the inlet of the ignition jet device 12 , the outlet of the ignition jet device 12 is a combustion chamber, and the ignition jet device 12 is connected to the overall monitoring controller 5 .

[0041] Furthermore, the ignition jet device 12 is arranged on both sides of the one-way valve 14 or centrally arranged between two one-way valves 14 .

[0042] Furthermore, the outlet of the ignition jet device 12 is a jet device with an adjustable angle controlled by the overall monitoring controller 5. The angle relative to the central axis is 90°.

[0043] The working principle of the device of the present invention is described below:

[0044] (1) Preparation stage:

[0045] The fuel supply device 2 and the oxidant supply device 1 deliver fuel and oxidant to a plurality of fuel nozzles 7 and annular gaps 8 respectively, and at the same time, the fuel supply device 2 and the oxidant supply device 1 deliver fuel and oxidant to the pre-combustion chamber 11 .

[0046] The overall monitoring controller 5 adjusts the flow rates of the fuel and the oxidant through the fuel solenoid valve 4 and the oxidant solenoid valve 3 respectively to ensure a suitable equivalence ratio.

[0047] (2) Premixing stage:

[0048] The jet ignition fuel / oxidant premixing solenoid valve 6 is opened, allowing a small amount of fuel and oxidant to enter the precombustion chamber 11 for premixing to form a premixed gas;

[0049] The fuel and the oxidant are mixed in the fuel / oxidant premixing pipe 9 , and the premixed fuel and oxidant enter the combustion chamber 18 through the one-way valve 14 .

[0050] (3) Ignition stage:

[0051] The ignition plug 10 ignites the premixed gas in the precombustion chamber to generate a high-temperature and high-pressure jet.

[0052] The high temperature and high pressure jet enters the combustion chamber 18 of the rotating detonation engine through the ignition jet device 12, triggering a detonation wave;

[0053] (4) Detonation stage:

[0054] like Figure 2 and Figure 4 As shown in a, the ignition jet device 12 is arranged on both sides of the one-way valve 14, and the jet angle is adjusted to utilize the compression wave generated by the collision of the jet flames and the interaction of the premixed fuel injected by the one-way valve 14 to achieve detonation. Figure 3 and Figure 4 As shown in b, the ignition jet device 12 is arranged in the middle of the two one-way valves 14. By adjusting the jet angle of the ignition jet device 12, the jet flame hits the outer ring 16 of the combustion chamber, and the convergence effect of the outer ring 16 of the combustion chamber is utilized to generate a reflected shock wave. The reflected shock wave interacts with the premixed fuel injected by the one-way valve 14, thereby effectively realizing rapid detonation.

[0055] The engine cover plate 13 ensures the isolation between the jet ignition system and the main combustion chamber, prevents unstable factors during the ignition process from affecting the main combustion chamber, and fixes the fuel / oxidant premixing pipe 9, the combustion chamber inner ring 16 and the combustion chamber inner ring 17.

[0056] When the pressure in the combustion chamber 18 is greater than the premixed fuel injection pressure, the one-way valve 14 is closed to ensure that the gas in the combustion chamber 18 can only flow in one direction to prevent backfire.

[0057] (5) Monitoring and control stage:

[0058] The temperature / pressure sensor 15 monitors the temperature and pressure changes in the combustion chamber 18 in real time, and feeds the data back to the overall monitoring controller 5 .

[0059] The overall monitoring controller 5 dynamically adjusts the opening of the fuel solenoid valve 4 and the oxidant solenoid valve 3 according to the monitoring data to ensure the stable propagation of the detonation wave.

[0060] (6) Stable stage:

[0061] Once the detonation wave is formed and propagates stably, the overall monitoring controller maintains the stable propagation of the detonation wave by adjusting the flow rates of fuel and oxidizer.

[0062] The functions of the overall monitoring controller are as follows:

[0063] 1) Control the opening of the fuel solenoid valve 4 and the oxidant solenoid valve 3 to adjust the fuel ratio.

[0064] 2) Control the opening of the jet ignition fuel / oxidant premixing solenoid valve 6, and then control the intensity of the jet flame.

[0065] 3) Controlling the ignition plug 10 to generate a jet flame in the pre-combustion chamber 11 .

[0066] 4) According to the arrangement of different ignition jet devices, the ignition jet device 12 is controlled to select a suitable jet angle to spray flame, thereby achieving rapid detonation.

Claims

1. An axial jet ignition and detonation system for a rotating detonation engine, characterized in that: It includes a propellant supply system, an axial jet ignition system, a rotating detonation engine body and a control system; specifically: The rotating detonation engine body comprises an engine cover plate (13), a combustion chamber outer ring (16), a combustion chamber inner ring (17) and a combustion chamber (18); the combustion chamber outer ring (16) and the combustion chamber inner ring (17) are both fixed to the right side of the engine cover plate (13); a combustion chamber (18) is formed between the combustion chamber outer ring (16) and the combustion chamber inner ring (17); one end of the combustion chamber (18) is the engine cover plate (13), and the other end is an outlet; The propellant supply system and the axial jet ignition system are located on the left side of the engine cover plate (13); The propellant supply system comprises a fuel supply device (2), an oxidant supply device (1), a fuel nozzle (7), an annular slit (8), a fuel / oxidant premix injection pipeline (9) and a one-way valve (14); the annular slit (8) and the fuel / oxidant premix injection pipeline (9) are coaxially and evenly arranged on the circumference of the left side of the engine cover plate (13); the annular slit (8) is arranged at the inlet of the fuel / oxidant premix injection pipeline (9); a plurality of the fuel / oxidant premix injection pipelines (9) are coaxially arranged and evenly distributed on the circumference of the annular slit (8); the fuel nozzle (7) is arranged on the inlet wall of the fuel / oxidant premix injection pipeline (9); a plurality of one-way valves (14) are evenly embedded in the engine cover plate (13) along the circumferential direction; the end of the fuel / oxidant premix injection pipeline (9) is connected to the one-way valve (14), and the outlet of the one-way valve (14) is the combustion chamber (18); The axial jet ignition system comprises an ignition plug (10), a pre-combustion chamber (11) and an ignition jet device (12), wherein the pre-combustion chamber (11) is fixed to the left side of an engine cover plate (13); the ignition plug (10) is arranged at the bottom of the pre-combustion chamber (11); the ignition jet device (12) is embedded in the engine cover plate (13) and connected to the outlet of the pre-combustion chamber (11); The control system comprises a master monitoring controller (5), a fuel solenoid valve (4), an oxidant solenoid valve (3) and a jet ignition fuel / oxidant premixing solenoid valve (6), wherein the master monitoring controller (5) is connected to the fuel solenoid valve (4), the oxidant solenoid valve (3), the jet ignition fuel / oxidant premixing solenoid valve (6) and the ignition plug (10); wherein the inlet of the fuel solenoid valve (4) is connected to the fuel supply device (2), and the outlet is divided into two paths, one of which is connected to a plurality of the fuel nozzles (7), and the other is connected to the inlet of the jet ignition fuel / oxidant premixing solenoid valve (6); the inlet of the oxidant solenoid valve (3) is connected to the oxidant supply device (1), and the outlet of the oxidant solenoid valve (3) is divided into two paths, one of which is connected to the annular gap (8), and the other is connected to the inlet of the jet ignition fuel / oxidant premixing solenoid valve (6); and the outlet of the jet ignition fuel / oxidant premixing solenoid valve (6) is connected to the inlet of the precombustion chamber.

2. The axial jet ignition and detonation system of the rotating detonation engine according to claim 1, characterized in that: The ignition jet device (12) is connected to the overall monitoring controller (5), and the outlet of the ignition jet device (12) is a combustion chamber (18).

3. The axial jet ignition and detonation system of the rotating detonation engine according to claim 1, characterized in that: The ignition jet device (12) is arranged on both sides of the one-way valve (14) or centrally arranged between two one-way valves (14).

4. The axial jet ignition and detonation system of the rotating detonation engine according to claim 1, characterized in that: The outlet of the ignition jet device (12) is adjusted in angle by the main monitoring controller (5), and the adjustable angle is 20 to 90 degrees relative to the central axis.

5. The axial jet ignition and detonation system of the rotating detonation engine according to claim 1, characterized in that: The control system further comprises a temperature / pressure sensor (15), which is arranged on the inner wall surface of the combustion chamber outer ring (16) and is used to monitor the temperature and pressure changes in the combustion chamber (18).

6. The axial jet ignition and detonation system of the rotating detonation engine according to claim 1, characterized in that: The plurality of fuel nozzles (7) are not connected to each other.

7. The detonation method of the axial jet ignition and detonation system of the rotating detonation engine according to any one of claims 1 to 6, characterized in that: (1) Preparation stage: The fuel supply device (2) and the oxidant supply device (1) respectively deliver fuel and oxidant to a plurality of fuel nozzles (7) and annular gaps (8), and at the same time, the fuel supply device (2) and the oxidant supply device (1) deliver fuel and oxidant to a pre-combustion chamber (11); The overall monitoring controller (5) adjusts the flow rates of the fuel and the oxidant through the fuel solenoid valve (4) and the oxidant solenoid valve (3) respectively to ensure a suitable equivalence ratio; (2) Premixing stage: The jet ignition fuel / oxidant premixing solenoid valve (6) is opened to allow a small amount of fuel and oxidant to enter the precombustion chamber (11) for premixing to form a premixed gas; The fuel and the oxidant are mixed in the fuel / oxidant premixing pipe (9), and the premixed fuel and oxidant enter the combustion chamber (18) through the one-way valve (14); (3) Ignition stage: The ignition plug (10) ignites the premixed gas in the precombustion chamber (11) to generate a high-temperature and high-pressure jet; The high-temperature and high-pressure jet enters the combustion chamber (18) of the rotating detonation engine through the ignition jet device (12), thereby inducing a detonation wave; (4) Detonation stage: The ignition jet device (12) is arranged on both sides of the one-way valve (14), and the jet angle is adjusted to utilize the compression wave generated by the collision of the jet flames and the premixed fuel injected by the one-way valve (14) to achieve detonation; or the ignition jet device (12) is arranged between the two one-way valves (14), and the jet angle of the ignition jet device (12) is adjusted to enable the jet flame to hit the outer ring (16) of the combustion chamber, and the convergence effect of the outer ring (16) of the combustion chamber is utilized to generate a reflected shock wave, and the reflected shock wave interacts with the premixed fuel injected by the one-way valve (14), thereby effectively achieving rapid detonation; The engine cover plate (13) ensures the isolation between the jet ignition system and the main combustion chamber, prevents unstable factors in the ignition process from affecting the main combustion chamber, and fixes the fuel / oxidant premixing pipe (9), the combustion chamber outer ring (16) and the combustion chamber inner ring (17); When the pressure in the combustion chamber (18) is greater than the premixed fuel injection pressure, the one-way valve (14) is closed to ensure that the gas in the combustion chamber (18) can only flow in one direction, thereby preventing backfire; (5) Monitoring and control stage: The temperature / pressure sensor (15) monitors the temperature and pressure changes in the combustion chamber (18) in real time and feeds the data back to the overall monitoring controller (5); The overall monitoring controller (5) dynamically adjusts the openings of the fuel electromagnetic valve (4) and the oxidant electromagnetic valve (3) according to the monitoring data to ensure stable propagation of the detonation wave.

Images