Pulse detonation combustion chamber oil supply system

Abstract

The invention relates to the technical field of pulse detonation engine oil supply, in particular to a pulse detonation combustion chamber oil supply system which comprises a fuel oil filter, a flow regulating valve, a fuel oil flow meter, a fuel oil electric heater, an electromagnetic valve, a high-pressure direct-drive electronic fuel injector, a detonation chamber wall surface regeneration cooling mechanism and a fuel oil control system. Fuel oil is electrically heated in the starting process, an electric heater and the high-temperature wall face of the detonation chamber are used for heating the fuel oil within the full working condition range, the initial temperature of the fuel oil entering the pulse detonation combustion chamber is increased, the atomization mixing effect of the fuel oil in the pulse detonation combustion chamber is improved, and the combustion heat efficiency in the pulse detonation combustion chamber is improved; the regenerative cooling structure plays a role in heat exchange and detonation wave formation acceleration on the outer wall and the inner wall of the pulse detonation combustion chamber, the overall structure is simplified while the function is guaranteed, and the reliability of system operation is improved. And the requirements of the pulse detonation combustion chamber on stable oil supply flow under different working conditions and special conditions are met.

Description

Technical Field

[0001] The invention relates to the technical field of pulse detonation engine fuel supply, and in particular to a pulse detonation combustion chamber fuel supply system. Background Art

[0002] The pulse detonation engine is a power device that works periodically. According to whether it has its own oxidizer, the pulse detonation engine can be divided into air-breathing pulse detonation engine and rocket pulse detonation engine. Among them, the air-breathing pulse detonation engine can be further divided into pulse detonation ramjet engine and pulse detonation turbine engine.

[0003] A working cycle of an air-breathing pulse detonation engine can be divided into the steps of intake mixing and filling, ignition and detonation, exhaust, and refilling. First, after the incoming air passes through the intake ram of the intake duct or the compression of the compressor, the pressure and temperature of the air increase, and then enters the pulse detonation combustion chamber to mix with the fuel sprayed from the nozzle of the pulse detonation combustion chamber, and fills the pulse detonation combustion chamber. Then, the ignition system works to ignite and discharge the combustible mixture in the pulse detonation combustion chamber. The initial flame is continuously accelerated under the action of the pulse detonation combustion chamber explosion-assisting obstacles, and finally forms a detonation wave at the outlet of the pulse detonation combustion chamber. Subsequently, the exhaust process begins, and the high-temperature combustion products of the pulse detonation combustion chamber are continuously discharged, and the pressure in the detonation chamber begins to drop. When the pressure of the combustion products of the pulse detonation combustion chamber drops to a pressure lower than the pressure at the inlet of the detonation chamber, the air at the inlet of the detonation chamber refills the pulse detonation combustion chamber. During the filling process, the fuel system controls the fuel to enter the combustion chamber through the nozzle again to mix with the air, thereby preparing for the next ignition working cycle.

[0004] From the working process of the pulse detonation combustion chamber, it can be seen that the pulse detonation combustion chamber is a system that requires periodic supply of fuel and periodic ignition, unlike traditional aircraft engines, where fuel is continuously supplied to the combustion chamber and ignition only needs to be performed once, after which the flame can be stabilized in the combustion chamber. It is precisely because the pulse detonation combustion chamber requires periodic ignition that the ignition energy of its ignition system must be very small in order to reduce the weight of the entire ignition system, thereby improving the thrust-to-weight ratio of the entire engine.

[0005] The fuel supply system of the pulse detonation combustion chamber must not only meet the periodic fuel supply requirements of the pulse detonation combustion chamber under different working conditions, but also meet the requirements of sufficient atomization and mixing during low-energy ignition to ensure reliable ignition during the operation of the pulse detonation combustion chamber. Especially during the cold start ignition process of the pulse detonation combustion chamber, the incoming air temperature and pressure are low, and the atomization and mixing effect of the fuel injected into the combustion chamber by the fuel system is poor, making it difficult to ensure reliable ignition.

[0006] The existing fuel supply systems for pulse detonation combustors can be divided into two types: adaptive fuel supply and intermittent fuel supply with high-frequency solenoid valves. For the adaptive fuel supply system, the fuel supply completely relies on the interaction between the fuel supply pressure and the internal pressure of the detonation chamber. Premature fuel supply occurs when the pressure in the detonation chamber is relatively low during the late exhaust stage of the detonation chamber, resulting in fuel waste. During the test process, incomplete combustion, low combustion efficiency, and black smoke emission at the outlet of the detonation chamber often occur. For the intermittent fuel supply with high-frequency solenoid valves, the flow rate cannot meet the flow rate requirements under large operating conditions. Moreover, the pressure of the high-pressure fuel decreases after passing through the solenoid valve, and the atomization effect after spraying from the nozzle also fails to reach the expected effect, leading to problems such as incomplete combustion, low combustion efficiency, and black smoke emission at the outlet of the detonation chamber. When facing high-frequency operating conditions that require a relatively high fuel flow rate, the traditional solution is to use multiple solenoid valves in parallel and control the opening and closing of the solenoid valves according to a certain time sequence. Although the method of parallel solenoid valves can increase the fuel supply working frequency, it is still difficult to meet the demand for high fuel flow rate by supplying fuel through a single valve. It can be seen that in the existing technology, no matter which fuel supply system is used, there are problems such as poor atomization and mixing effect of fuel during the startup process, resulting in unreliable ignition during the startup process.

[0007] Some of the existing fuel supply systems use a regenerative cooling structure to achieve cooling while improving the atomization effect. However, there are structural problems in the existing regenerative cooling devices. When the fuel flows through the regenerative cooling structure, absorbing and utilizing the heat of the entire detonation chamber wall will cause the fuel to quickly heat up beyond the coking temperature, thereby causing fuel coking and blocking the fuel pipeline, resulting in damage to the regenerative cooling structure. Summary of the Invention

[0008] The purpose of the present invention is to avoid the deficiencies of the existing technology and provide a fuel supply system for a pulse detonation combustor. By heating the fuel, the atomization and mixing effect of the fuel and air in the pulse detonation combustor under different operating conditions is improved. A regenerative cooling device is designed to act as a spiral obstacle to accelerate the formation of detonation waves and at the same time can be used to avoid the influence of fuel coking on the fuel pipeline, thereby solving the technical problems in the existing technology.

[0009] To achieve the above object, the technical solution adopted by the present invention is as follows: The fuel supply system of a pulse detonation combustor includes a fuel filter, a flow regulating valve, a fuel flow meter, a fuel electric heater, solenoid valves, high-pressure direct-drive electronic fuel injection, a wall regenerative cooling mechanism for the detonation chamber, and a fuel control system; the solenoid valves include a first solenoid valve, a second solenoid valve, a third solenoid valve, a fourth solenoid valve, a fifth solenoid valve, and a sixth solenoid valve; the high-pressure direct-drive electronic fuel injection includes a first high-pressure direct-drive electronic fuel injection and a second high-pressure direct-drive electronic fuel injection; the fuel filter, the flow regulating valve, the fuel flow meter, the fuel electric heater, the third solenoid valve, the sixth solenoid valve, and the second high-pressure direct-drive electronic fuel injection are sequentially connected through fuel pipelines and then connected to the fuel inlet of the fuel nozzle at the front of the pulse detonation combustor; a wall regenerative cooling mechanism for the detonation chamber is arranged in the pulse detonation combustor, the fuel filter, the flow regulating valve, the fuel flow meter, the first solenoid valve, and the fourth solenoid valve are connected through fuel pipelines and then connected to the fuel inlet of the wall regenerative cooling mechanism for the detonation chamber, and the fuel outlet of the wall regenerative cooling mechanism for the detonation chamber is connected to the fifth solenoid valve and the first high-pressure direct-drive electronic fuel injection through a fuel pipeline and then connected to the fuel inlet of the fuel nozzle at the front of the pulse detonation combustor.

[0010] A first temperature sensor is further arranged on the fuel pipeline between the fuel electric heater and the third solenoid valve, and a second temperature sensor is further arranged on the fuel pipeline between the fuel outlet of the wall regenerative cooling mechanism for the detonation chamber and the fifth solenoid valve; the fuel control system is respectively connected to the flow regulating valve, the fuel flow meter, the first solenoid valve, the second solenoid valve, the third solenoid valve, the fourth solenoid valve, the fifth solenoid valve, the sixth solenoid valve, the first high-pressure direct-drive electronic fuel injection, the second high-pressure direct-drive electronic fuel injection, the first temperature sensor, and the second temperature sensor through control lines.

[0011] The wall regenerative cooling mechanism for the detonation chamber is a spiral groove structure formed by the inner depression of the wall of the pulse detonation combustor along a spiral line, and the spiral groove structure and the outer side wall sleeve of the pulse detonation combustor are enclosed and combined to form a regenerative cooling oil circuit spiraling around the combustion chamber wall.

[0012] A plurality of pulse detonation combustors are provided, and the plurality of pulse detonation combustors are arranged in parallel. One path of the fuel inlet of the fuel nozzle of each pulse detonation combustor is connected to the sixth solenoid valve through a fuel pipeline, and the other path of the fuel inlet of the fuel nozzle is connected to the fuel outlet of the wall regenerative cooling mechanism for the detonation chamber through a fuel pipeline. A high-pressure direct-drive electronic fuel injection and a solenoid valve are arranged on the fuel pipeline between the fuel inlet of the fuel nozzle and the sixth solenoid valve, and a high-pressure direct-drive electronic fuel injection, a solenoid valve, and a temperature sensor are arranged on the fuel pipeline between the fuel inlet of the fuel nozzle and the fuel outlet of the wall regenerative cooling mechanism for the detonation chamber; the fuel inlet of the wall regenerative cooling mechanism for the detonation chamber is connected to the first solenoid valve through a fuel pipeline, and a solenoid valve is arranged on the fuel pipeline between the fuel inlet of the wall regenerative cooling mechanism for the detonation chamber and the first solenoid valve.

[0013] Compared with the prior art, the present invention has the following technical effects: A fuel supply system for a pulse detonation combustor electrically heats the fuel during startup, designs a regenerative cooling mechanism on the wall of the pulse detonation combustor, and uses an electric heater and the high-temperature wall of the detonation chamber to heat the fuel within the entire operating range, increasing the initial temperature of the fuel entering the pulse detonation combustor, improving the atomization and mixing effect of the fuel within the pulse detonation combustor, enhancing the combustion thermal efficiency within the pulse detonation combustor. The regenerative cooling structure plays the roles of heat exchange on the outer and inner walls of the pulse detonation combustor and accelerating the formation of detonation waves, simplifies the overall structure while ensuring the function, and improves the reliability of system operation. It meets the requirements of the pulse detonation combustor for a stable fuel supply flow under different operating conditions and special circumstances. Description of the Drawings

[0014] Figure 1 is a schematic diagram of the system principle of the present invention; Figure 2 is a schematic diagram of the principle of an embodiment of multiple pulse detonation combustors of the present invention; Figure 3 is a schematic diagram of the regenerative cooling mechanism of the detonation chamber wall of the present invention.

[0015] In the figure, 1, fuel filter; 2, flow regulating valve; 3, fuel flow meter; 4, fuel electric heater; 5, first solenoid valve; 6, second solenoid valve; 7, third solenoid valve; 8, fourth solenoid valve; 9, fifth solenoid valve; 10, sixth solenoid valve; 11, first high-pressure direct drive electronic injection; 12, second high-pressure direct drive electronic injection; 13, first temperature sensor; 14, second temperature sensor; 15, regenerative cooling mechanism of the detonation chamber wall; 16, fuel control system; 17, fuel nozzle; 18, pulse detonation combustor. Detailed Embodiments

[0016] The principles and features of the present invention are described below in conjunction with the accompanying drawings; the examples given are only for explaining the present invention and are not intended to limit the scope of the present invention.

[0017] To achieve the above object, the present invention provides the following detailed embodiments: As Figure 1 and 3As shown in the figure, a fuel supply system for a pulse detonation combustor is characterized by including a fuel filter 1, a flow regulating valve 2, a fuel flowmeter 3, a fuel electric heater 4, electromagnetic valves, high-pressure direct-drive electronic fuel injection, a wall regenerative cooling mechanism 15 for the detonation chamber, and a fuel control system 16; the electromagnetic valves include a first electromagnetic valve 5, a second electromagnetic valve 6, a third electromagnetic valve 7, a fourth electromagnetic valve 8, a fifth electromagnetic valve 9, and a sixth electromagnetic valve 10; the high-pressure direct-drive electronic fuel injection includes a first high-pressure direct-drive electronic fuel injection 11 and a second high-pressure direct-drive electronic fuel injection 12; the fuel filter 1, the flow regulating valve 2, the fuel flowmeter 3, the fuel electric heater 4, the third electromagnetic valve 7, the sixth electromagnetic valve 10, and the second high-pressure direct-drive electronic fuel injection 12 are sequentially connected through a fuel pipeline and then connected to the oil inlet of a fuel nozzle 17 at the front of the pulse detonation combustor 18; a wall regenerative cooling mechanism 15 for the detonation chamber is arranged in the pulse detonation combustor 18, and the fuel filter 1, the flow regulating valve 2, the fuel flowmeter 3, the first electromagnetic valve 5, and the fourth electromagnetic valve 8 are connected through a fuel pipeline and then connected to the oil inlet of the wall regenerative cooling mechanism 15 for the detonation chamber, and the oil outlet of the wall regenerative cooling mechanism 15 for the detonation chamber is connected to the fifth electromagnetic valve 9 and the first high-pressure direct-drive electronic fuel injection 11 through a fuel pipeline and then connected to the oil inlet of the fuel nozzle 17 at the front of the pulse detonation combustor 18.

[0018] A first temperature sensor 13 is further arranged on the fuel pipeline between the fuel electric heater 4 and the third electromagnetic valve 7, and a second temperature sensor 14 is further arranged on the fuel pipeline between the oil outlet of the wall regenerative cooling mechanism 15 for the detonation chamber and the fifth electromagnetic valve 9; the fuel control system 16 is respectively connected to the flow regulating valve 2, the fuel flowmeter 3, the first electromagnetic valve 5, the second electromagnetic valve 6, the third electromagnetic valve 7, the fourth electromagnetic valve 8, the fifth electromagnetic valve 9, the sixth electromagnetic valve 10, the first high-pressure direct-drive electronic fuel injection 11, the second high-pressure direct-drive electronic fuel injection 12, the first temperature sensor 13, and the second temperature sensor 14 through control lines. By controlling the opening and closing of each valve through the fuel control system 16, there are multiple fuel supply paths to provide a stable fuel supply flow for the pulse detonation combustor 18 under full operating conditions.

[0019] The wall regenerative cooling mechanism 15 for the detonation chamber is a spiral groove structure formed by the inner depression of the wall of the pulse detonation combustor 18 along a spiral line. The spiral groove structure and the outer wall sleeve of the pulse detonation combustor 8 are hermetically combined to form a regenerative cooling oil path spiraling around the combustion chamber wall; at the same time, the protruding spiral structure formed on its inner wall can be used as a spiral obstacle to accelerate the formation of detonation waves.

[0020] The working process is as follows. During the cold-start ignition process, the fuel control system 16 controls the second solenoid valve 6 to the fifth solenoid valve 9 to open, the first high-pressure direct injection 11 to open, and the first solenoid valve 5 and the sixth solenoid valve 10 to close. The fuel coming from the high-pressure fuel tank or the fuel pump passes through the fuel filter 1, the flow regulating valve 2, and the fuel flow meter 3 in sequence, and then is heated to a high temperature state through the pipeline branch of the fuel heater 4. The heated fuel enters the fuel passage of the wall regenerative cooling mechanism 15 of the pulse detonation combustion chamber 18 through the fourth solenoid valve 8, and finally is intermittently supplied into the pulse detonation combustion chamber 18 through the fifth solenoid valve 9 and the first high-pressure direct injection 11. After being mixed with the high-pressure air coming from the intake passage or the compressor, it is ignited, and then a detonation wave is formed under the action of the detonation assisting obstacles in the pulse detonation combustion chamber 18. Due to the increase in the initial fuel temperature, the atomization and mixing effect of the fuel after entering the combustion chamber is greatly improved. The reliability of the cold-start ignition of the combustion chamber can be improved. When the pulse detonation combustion chamber 18 works stably and reliably, the temperature of the wall of the pulse detonation combustion chamber 18 gradually rises under the action of the high-temperature gas. The regenerative cooling structure 15 of the detonation chamber wall further heats the fuel flowing along the pipe wall to a higher temperature to further improve the atomization and mixing effect of the fuel in the detonation chamber, thereby improving the combustion efficiency of the pulse detonation combustion chamber 18. When the fuel temperature at the outlet of the detonation chamber regenerative cooling structure 15 reaches a certain temperature, the fuel control system 16 controls the second solenoid valve 6 and the third solenoid valve 7 to close, the first solenoid valve 5 to open, and at the same time cuts off the power supply of the fuel electric heater 4. The high-pressure fuel directly passes through the first solenoid valve 5 and the fourth solenoid valve 8 and enters the detonation chamber regenerative cooling structure 15. After the cold fuel exchanges heat with the wall regenerative cooling mechanism 15 of the detonation chamber, it is intermittently supplied into the detonation chamber through the first high-pressure direct injection 11 to improve the working reliability of the detonation chamber. As the ignition frequency of the working condition of the pulse detonation combustion chamber 18 increases, the fuel control system 16 controls the opening degree of the flow regulating valve 2 to meet the fuel flow demand of the detonation chamber. When the pulse detonation combustion chamber 18 works at a large flow rate and the first high-pressure direct injection 11 can no longer meet the fuel flow demand of the detonation chamber, the second high-pressure direct injection 12 opens and the first high-pressure direct injection 11 closes. The oil circuit where the second high-pressure direct injection 12, which can provide a larger fuel flow rate, supplies fuel to the pulse detonation combustion chamber 18 to meet the demand for a large fuel flow rate under high working conditions. During the working process of the pulse detonation combustion chamber 18, if a failure such as blockage or damage occurs in the wall regenerative cooling mechanism 15 of the detonation chamber or the second temperature sensor 14 measures that the fuel temperature at the outlet of the wall regenerative cooling mechanism 15 of the detonation chamber is about to reach the coking temperature, the fuel control system 16 can control the fourth solenoid valve 8 and the fifth solenoid valve 9 to close and open the emergency sixth solenoid valve 10, thereby ensuring that the fuel system can supply fuel to the pulse detonation combustion chamber 18 normally.

[0021] Specific Embodiment 2: A plurality of pulse detonation combustors 18 are provided, and the plurality of pulse detonation combustors 18 are arranged in parallel. The oil inlet of the fuel nozzle 17 of each pulse detonation combustor 18 is connected to the sixth solenoid valve 10 through a fuel pipeline in one path, and the oil inlet of the fuel nozzle 17 is connected to the outlet of the detonation chamber wall regenerative cooling mechanism 15 through a fuel pipeline in another path. A high-pressure direct drive electronic injection and solenoid valve are provided on the fuel pipeline between the oil inlet of the fuel nozzle 17 and the sixth solenoid valve 10. A high-pressure direct drive electronic injection, solenoid valve and temperature sensor are provided on the fuel pipeline between the oil inlet of the fuel nozzle 17 and the outlet of the detonation chamber wall regenerative cooling mechanism 15. The oil inlet of the detonation chamber wall regenerative cooling mechanism 15 is connected to the first solenoid valve 5 through a fuel pipeline, and a fourth solenoid valve 8 is provided on the fuel pipeline between the oil inlet of the detonation chamber wall regenerative cooling mechanism 15 and the first solenoid valve 5.

[0022] The working process is as follows. During the cold start of the multi-tube pulse detonation combustor 18, the fuel control system 16 controls the opening of the second solenoid valve 6 to the fifth solenoid valve 9, and at the same time opens the solenoid valve set on the fuel pipeline between the oil inlet of the detonation chamber wall regenerative cooling mechanism 15 of other pulse detonation combustors 18 and the first solenoid valve 5, the solenoid valve set on the fuel pipeline between the oil inlet of the fuel nozzle 17 and the oil outlet of the detonation chamber wall regenerative cooling mechanism 15, and the high-pressure direct drive electronic fuel injection 11 and the high-pressure direct drive electronic fuel injection set on the fuel pipeline between the oil inlet of the fuel nozzle 17 and the oil outlet of the detonation chamber wall regenerative cooling mechanism 15; the first solenoid valve 5 and the sixth solenoid valve 10 are closed, and at the same time the solenoid valve set on the fuel pipeline between the oil inlet of the fuel nozzle 17 and the sixth solenoid valve 10 is closed; the fuel passes through the fuel filter 1, the flow regulating valve 2, and the fuel flowmeter 3 in sequence, and then is heated to a high temperature state through the pipeline branch of the fuel heater 4. The heated fuel enters the fuel channel of the multi-tube pulse detonation wall regenerative cooling structure 15 through the fourth solenoid valve 8 and the solenoid valve set on the fuel pipeline between the oil inlet of the detonation chamber wall regenerative cooling mechanism 15 and the first solenoid valve 5, and finally passes through the fifth solenoid valve 9, the solenoid valve set on the fuel pipeline between the oil inlet of the fuel nozzle 17 and the oil outlet of the detonation chamber wall regenerative cooling mechanism 15, and the high-pressure direct drive electronic fuel injection set on the fuel pipeline between the oil inlet of the first high-pressure direct drive electronic fuel injection 11, the fuel nozzle 17 and the oil outlet of the detonation chamber wall regenerative cooling mechanism 15 is intermittently supplied into the pulse detonation combustor 18 to be mixed with air and ignited to form a detonation wave. When the fuel temperature at the outlet of the detonation chamber wall regenerative cooling mechanism 15 reaches a certain temperature, the fuel control system 16 controls the closing of the second solenoid valve 6 and the third solenoid valve 7, opens the first solenoid valve 5, and at the same time cuts off the power supply of the fuel electric heater 4. The high-pressure fuel directly enters the detonation chamber wall regenerative cooling mechanism 15 through the first solenoid valve 5, the fourth solenoid valve 8 and the solenoid valve set on the fuel pipeline between the oil inlet of the detonation chamber wall regenerative cooling mechanism 15 and the first solenoid valve 5. After the fuel exchanges heat with the detonation chamber wall regenerative cooling mechanism 15, it is intermittently supplied into the detonation chamber through the high-pressure direct drive electronic fuel injection set on the fuel pipeline between the oil inlet of the first high-pressure direct drive electronic fuel injection 11, the fuel nozzle 17 and the oil outlet of the detonation chamber wall regenerative cooling mechanism 15.When the high-pressure direct injection on the fuel pipeline between the first high-pressure direct injection 11 and the oil outlet of the knock chamber wall regenerative cooling mechanism 15 can no longer meet the fuel flow demand of the knock chamber, the high-pressure direct injection on the fuel pipeline between the second high-pressure direct injection 12 and the fuel nozzle 17's inlet and the sixth solenoid valve 10 is opened, and the high-pressure direct injection on the fuel pipeline between the first high-pressure direct injection 11 and the fuel nozzle 17's inlet and the oil outlet of the knock chamber wall regenerative cooling mechanism 15 is closed. The oil circuit where the high-pressure direct injection is set on the fuel pipeline between the second high-pressure direct injection 12, which can provide a larger fuel flow, and the fuel nozzle 17's inlet and the sixth solenoid valve 10 supplies fuel to the pulse detonation combustion chamber 18 to meet the demand for a large fuel flow under high operating conditions. During the operation of the pulse detonation combustion chamber 18, if a fault such as blockage or damage occurs in the knock chamber wall regenerative cooling mechanism 15, or the temperature sensor set on the fuel pipeline between the second temperature sensor 14 and the fuel nozzle 17's inlet and the oil outlet of the knock chamber wall regenerative cooling mechanism 15 measures that the fuel temperature at the outlet of the knock chamber wall regenerative cooling mechanism 15 is about to reach the coking temperature, the fuel control system 16 can control the fourth solenoid valve 8, the fifth solenoid valve 9, the solenoid valve set on the fuel pipeline between the inlet of the knock chamber wall regenerative cooling mechanism 15 and the first solenoid valve 5, and the solenoid valve set on the fuel pipeline between the fuel nozzle 17's inlet and the oil outlet of the knock chamber wall regenerative cooling mechanism 15 to close, and open the emergency sixth solenoid valve 10 and the solenoid valve on the fuel pipeline between the fuel nozzle 17's inlet and the sixth solenoid valve 10, so as to ensure that the fuel system can supply fuel to the pulse detonation combustion chamber 18 normally.

[0023] A fuel supply system for a pulse detonation combustor. Considering that the heater power required for fuel heating throughout the entire operating conditions is relatively large, which will lead to a relatively large size and weight of the heater, the present invention only uses an electromagnetic electric heater to heat the fuel during the startup process. After the pulse detonation combustor 18 ignites and operates normally, the detonation chamber wall regenerative cooling mechanism 15 provided uses the wall heat of the detonation chamber to heat the fuel, thereby greatly reducing the size and weight of the electric heater and reducing the engine's dependence on external energy. When the pulse detonation combustor 18 operates under high conditions, the oil circuit is switched, and an oil circuit that can provide a larger fuel flow rate is used to meet the large fuel flow supply demand. The detonation chamber wall regenerative cooling mechanism 15 plays the roles of heat exchange and accelerating the formation of detonation waves on the outer and inner walls of the pulse detonation combustor 18 respectively, simplifies the overall structure while ensuring the functions, and improves the reliability of the system operation. Moreover, compared with the traditional regenerative cooling structure, this new type of regenerative cooling structure has a smaller cross-sectional area of the oil pipeline heated by the remaining temperature of the detonation chamber wall, and the fuel flow rate is faster, which can effectively avoid the deposition and coking of fuel caused by slow flow rate in the traditional regenerative cooling structure. In short, the present invention comprehensively adopts the technical means of electrically heating the fuel during the startup process, using regenerative cooling during the working process, and switching to a large fuel supply flow rate oil circuit strategy during the high-condition working process to solve the problems existing in the existing fuel supply system of the pulse detonation combustor.

[0024] The above are only the preferred embodiments of the present invention; they are not intended to limit the present invention; any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A pulse detonation combustion chamber fuel supply system, characterized in that: It includes a fuel filter (1), a flow regulating valve (2), a fuel flow meter (3), a fuel electric heater (4), a solenoid valve, a high-pressure direct-drive electronic injection, a detonation chamber wall regeneration cooling mechanism (15) and a fuel control system (16); The solenoid valves include a first solenoid valve (5), a second solenoid valve (6), a third solenoid valve (7), a fourth solenoid valve (8), a fifth solenoid valve (9) and a sixth solenoid valve (10); the high-pressure direct-drive electronic injection system includes a first high-pressure direct-drive electronic injection system (11) and a second high-pressure direct-drive electronic injection system (12); The fuel filter (1), flow regulating valve (2), fuel flow meter (3), fuel electric heater (4), third solenoid valve (7), sixth solenoid valve (10), and second high-pressure direct-drive electronic injection (12) are connected in sequence through a fuel pipeline and then connected to the oil inlet of a fuel nozzle (17) at the front of a pulse detonation combustion chamber (18); a detonation chamber wall regeneration cooling mechanism (15) is provided in the pulse detonation combustion chamber (18); the fuel filter (1), flow regulating valve (2), fuel flow meter (3), first solenoid valve (5), and fourth solenoid valve (8) are connected through a fuel pipeline and then connected to the oil inlet of the detonation chamber wall regeneration cooling mechanism (15); the oil outlet of the detonation chamber wall regeneration cooling mechanism (15) is connected to the fifth solenoid valve (9) and the first high-pressure direct-drive electronic injection (11) through a fuel pipeline and then connected to the oil inlet of the fuel nozzle (17) at the front of the pulse detonation combustion chamber (18).

2. A pulse detonation combustion chamber fuel supply system as claimed in claim 1, characterized in that: A first temperature sensor (13) is also provided on the fuel pipeline between the fuel electric heater (4) and the third solenoid valve (7), and a second temperature sensor (14) is also provided on the fuel pipeline between the oil outlet of the detonation chamber wall regeneration cooling mechanism (15) and the fifth solenoid valve (9); The fuel control system (16) is respectively connected to the flow regulating valve (2), the fuel flow meter (3), the first solenoid valve (5), the second solenoid valve (6), the third solenoid valve (7), the fourth solenoid valve (8), the fifth solenoid valve (9), the sixth solenoid valve (10), the first high-pressure direct-drive electronic injection (11), the second high-pressure direct-drive electronic injection (12), the first temperature sensor (13) and the second temperature sensor (14) through control lines.

3. A pulse detonation combustion chamber fuel supply system as claimed in claim 1, characterized in that: The detonation chamber wall regeneration cooling mechanism (15) is a spiral groove structure formed by the pulse detonation combustion chamber wall being recessed inward along a spiral line, and the spiral groove structure is sealed and combined with the outer wall sleeve of the pulse detonation combustion chamber (18) to form a regeneration cooling oil path spiraling around the combustion chamber wall.

4. A pulse detonation combustion chamber fuel supply system according to any one of claims 1 to 3, characterized in that: The pulse detonation combustion chamber (18) is arranged in plurality, and the plurality of pulse detonation combustion chambers (18) are arranged in parallel. The fuel inlet of the fuel nozzle (17) of each pulse detonation combustion chamber (18) is connected to the sixth solenoid valve (10) through a fuel pipeline, and the fuel inlet of the fuel nozzle (17) is connected to the oil outlet of the detonation chamber wall regeneration cooling mechanism (15) through a fuel pipeline. A high-pressure direct-drive electronic injection and a solenoid valve are arranged on the fuel pipeline between the fuel inlet of the fuel nozzle (17) and the sixth solenoid valve (10), and a high-pressure direct-drive electronic injection, a solenoid valve and a temperature sensor are arranged on the fuel pipeline between the fuel inlet of the fuel nozzle (17) and the oil outlet of the detonation chamber wall regeneration cooling mechanism (15); the fuel inlet of the detonation chamber wall regeneration cooling mechanism (15) is connected to the first solenoid valve (5) through a fuel pipeline, and a solenoid valve is arranged on the fuel pipeline between the fuel inlet of the detonation chamber wall regeneration cooling mechanism (15) and the first solenoid valve (5).

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