Quick-start independent oil supply ignition system for micro turbojet engine

Abstract

The invention relates to a micro turbojet engine quick-start independent fuel supply ignition system which comprises a control unit, a fuel supply unit, a fuel supply unit and a fuel supply unit. The main oil supply unit is used for normally starting an engine on the ground; the ignition unit is used for ignition; the oxygen supplementing unit is used for supplying oxygen to an engine combustion chamber; the independent oil supply unit is used for quickly starting the engine; the independent oil supply unit comprises an independent oil pump which is independent of the main oil supply unit to supply oil; the independent electromagnetic valve controls the opening of the independent oil pump; the atomizing nozzle is ignited to atomize supplied oil in the independent oil pump; when quick / air starting / air secondary starting of the engine needs to be achieved, the main oil supply unit, the ignition unit, the oxygen supplementation unit and the independent oil supply unit need to be started at the same time. Through the independent oil supply unit, the ignition unit and the oxygen supplementation unit, the effects of ground conventional starting, ground quick starting, high-altitude starting, air flameout restarting or secondary starting can be achieved at the same time.

Description

Technical Field

[0001] The present application relates to the technical field of aerospace technology, and in particular to a micro turbojet engine rapid start independent fuel supply ignition system. Background Art

[0002] Micro-turbojet engines are complex and sophisticated thermal machines, primarily used to power drones, target aircraft, cruise missiles, and other equipment. Compared to solid- or liquid-propellant rockets, they offer advantages such as low fuel consumption, low cost, and reusability. With advances in powertrain technology, turbojet engines used in cruise missiles and high-altitude drones are increasingly required to offer rapid in-flight starts and quick restarts after flameout. This places higher technical demands on the engine's ignition and fuel supply systems, and conventional mechanical layouts and accessory designs are no longer sufficient.

[0003] The micro turbojet engine is mainly composed of a compressor, a combustion chamber, a turbine, and a tail nozzle. It is also equipped with a starting system, a fuel supply system, and an ignition system to ensure engine starting and operation.

[0004] The micro-turbojet engine ignition system mainly consists of the following structures: ignition head, electronic control unit, battery. The fuel supply system mainly consists of fuel supply pipeline, solenoid valve, fuel pump, and fuel injection ring.

[0005] When the engine starts, the starting system drives the engine rotor to rotate and inhale air. The oil pump starts working and the solenoid valve opens the oil circuit to spray oil. The igniter starts working and the fuel starts to burn after contacting the ignition head. The high-temperature gas drives the turbine and compressor to rotate, and the engine starts to run.

[0006] The above-mentioned related technologies have the following defects: the existing micro-turbojet engines have requirements for the temperature and speed of the air when starting. If the incoming air speed is too fast, the ignition head temperature will be low and ignition will be impossible. The flame will be unstable and extinguished during the starting process. Therefore, it can usually only be started on the ground, and the starting process takes a certain amount of time. Therefore, there are problems such as limited starting conditions and slow response speed. When the engine flies to a high altitude, the existing fuel supply system and ignition system are difficult to start in the air due to the high speed and low temperature of the oncoming airflow. When the engine is abnormally shut down, it cannot be restarted, which greatly reduces the reliability of the engine. At the same time, it cannot meet the special requirements of some equipment that need to be started in the air or start and stop multiple times in the air, which greatly limits the use and function of the micro-turbojet engine. Summary of the Invention

[0007] In order to improve the above problems, the present application provides a micro turbojet engine rapid start independent fuel supply ignition system.

[0008] The present application provides a micro-turbojet engine rapid start independent fuel supply ignition system adopts the following technical solutions: A micro turbojet engine rapid start independent fuel supply ignition system, comprising: A control unit, configured to execute an engine start instruction; Main fuel supply unit, used to realize conventional engine starting on the ground; an ignition unit, for ignition; an oxygen supply unit for supplying oxygen to the engine combustion chamber; and Independent fuel supply unit for quick engine starting; The independent oil supply unit comprises: Independent oil pump, which supplies oil independently from the main oil supply unit; Independent solenoid valve controls the opening of the independent oil pump; Ignition atomizing nozzle to atomize the oil supplied from the independent oil pump; When a quick / in-flight start / secondary in-flight start of the engine is required, the main fuel supply unit, ignition unit, oxygen supply unit and independent fuel supply unit need to be started simultaneously.

[0009] Furthermore, the main oil supply unit includes: Main oil supply pump, conventional oil supply; The fuel injection ring is used to connect the engine combustion chamber with the main fuel supply pump; Main solenoid valve, used to control the main oil supply pump on / off.

[0010] Furthermore, the ignition unit includes: Ignition nozzle, used to ignite the oil in the engine combustion chamber; The high-energy igniter is used to input high voltage electricity to the ignition nozzle and make the ignition nozzle generate electric sparks.

[0011] Furthermore, the oxygen supplementation unit includes: An oxygen supply tank and an oxygen supply jet ring, wherein the oxygen supply jet ring is used to connect the engine combustion chamber and the oxygen supply tank.

[0012] Furthermore, the oxygen-supplementing jet ring is provided with a chamber at a position connected to the engine combustion chamber, and the chamber is connected to a focused jet port and a diffuse jet port. The cross-sectional circular size of the focused injection port gradually decreases toward the engine combustion chamber, and the cross-sectional circular size of the diffuse injection port gradually increases toward the engine combustion chamber; The diffuse injection port is located above the focused injection port, and the diffuse injection port is directly facing the inlet of the main injection ring; The opening in the chamber is further provided with an adjustment unit, which is used to achieve a narrow-angle focused spray shape at low temperature and a wide-angle diffuse spray shape at hot state.

[0013] Furthermore, the adjustment unit includes: a slide plate, slidably disposed on a side wall of the chamber and provided with a vent hole, wherein the vent hole is adapted to the inlet of the focused injection port or the inlet of the diffuse injection port; Deformable mechanism, which is in its original shape when cold and contracts and deforms when hot; The transmission mechanism is used to convert the deformation of the deformable structure into power to control the swing of the baffle.

[0014] Furthermore, the transmission mechanism includes: a slider, sliding in the chamber along the direction of oxygen flow; An elastic member, used to realize elastic connection between the slider and the chamber; A transmission rod, one end of which is movably connected to the slider, the transmission rod is rotationally connected to the chamber, and the position where the transmission rod is rotationally connected to the chamber is close to the slider; The connecting piece is used to connect the other end of the transmission rod and the top of the skateboard.

[0015] Furthermore, the deformation mechanism includes: A memory alloy strip is fixedly connected to the slider, and the other end is fixedly connected to the inner wall of the chamber, and the elastic member is respectively provided at both ends of the slider; When the memory alloy strip is in a hot state, the vent holes on the slide plate move to the diffusion injection port.

[0016] Furthermore, the diffuse injection port is provided with an oblique cut with a tangential deflection angle, and the inner wall of the diffuse injection port is provided with a spiral micro guide groove.

[0017] As described above, the beneficial technical effects of this application are: 1. The present invention adds an independent ignition and fuel supply system and an oxygen supply system, which can greatly shorten the ground starting time and achieve rapid engine starting. At the same time, the system ensures the stability of the engine's high-altitude starting. The present invention removes the limitation that the micro-turbojet engine can only be started on the ground, and realizes the engine starting in the air, starting after flameout in the air, and secondary starting. The equipment using this invention can be equipped with cruise missiles and airborne start-type drones, thus expanding the application scenarios of the engine. A set of accessory systems is implemented to realize multiple engine starting schemes, so that one model of engine can meet the application requirements of ground target drones, ground start missiles, cruise missiles, and multiple equipment and scenarios, greatly improving the compatibility and versatility of the engine. 2. Micro turbojet engines have certain air temperature and velocity requirements during startup. Excessively high air velocity can cause the ignition head to be too cold for ignition, leading to unstable flames and flameout during startup. Therefore, to address these temperature and air velocity issues, an independent oil supply unit in this embodiment is used to inject oil mist, thereby addressing temperature constraints. The oxygen supply unit also addresses the issue of excessive air velocity, ensuring sufficient oxygen in the combustion chamber and ensuring complete combustion. 3. During the cold engine phase, just before engine ignition and when oxygen injection is required, the focused jet begins operating. In this embodiment, the focused jet is located closer to the ignition nozzle. When the focused jet begins operating, the high-pressure oxygen stream forms a highly concentrated jet, precisely targeting the core of the fuel mist sprayed from the ignition atomizing nozzle and the spark region of the ignition nozzle. This ensures extremely high oxygen concentrations in critical areas at the moment of ignition, significantly improving ignition success rates. During the hot engine phase, just as fuel combustion has begun within the combustion chamber, the diffuse jet faces the inlet of the main fuel injection ring. When the main fuel pump begins operating, the diffuse jet's high-pressure oxygen spray angle widens, providing a wider coverage area. This allows for more macroscopic and uniform mixing with the main fuel injected from the main fuel injection ring, promoting rapid expansion and stabilization of combustion, thereby rapidly generating large quantities of high-temperature combustion gas to drive the turbine. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of the overall structure of an embodiment of the present application; Figure 2 It is a cross-sectional view of the chamber and the adjustment unit of an embodiment of the present application.

[0019] Description of reference numerals: 01. Engine combustion chamber; 1. Control unit; 10. Ignition atomizing nozzle; 11. Fuel injection ring; 2. Main fuel supply pump; 90. Chamber; 91. Focusing injection port; 92. Diffusing injection port; 93. Slide plate; 94. Vent; 95. Slider; 96. Elastic part; 97. Transmission rod; 98. Connector; 99. Memory alloy strip; 3. Main solenoid valve; 4. Independent oil pump; 5. Independent solenoid valve; 6. Oxygen supply tank; 7. High-energy igniter; 8. Ignition nozzle; 9. Oxygen supply injection ring. DETAILED DESCRIPTION

[0020] The following will clearly and completely describe the technical solution of this application in conjunction with the accompanying drawings. Obviously, the embodiments described are only part of the embodiments of this application, not all of them. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making any creative efforts are within the scope of protection of this application.

[0021] The embodiment of the present application discloses a micro turbojet engine rapid start independent fuel supply ignition system. Figure 1-Figure 2 It includes a control unit 1 for executing the engine start instruction; a main fuel supply unit for realizing conventional engine start on the ground; an ignition unit for ignition; an oxygen supply unit for supplying oxygen to the engine combustion chamber 01; and an independent fuel supply unit for quickly starting the engine; in this embodiment, the control unit 1 uses an ECU, which mainly controls the main fuel supply unit, the ignition unit, the oxygen supply unit and the independent fuel supply unit to cooperate with each other, thereby achieving the effect of starting the engine. In this embodiment, it is mainly divided into conventional start, that is, start on the ground, quick start on the ground, start in the air or secondary start in the air. Therefore, the role of the control unit 1 is particularly important. It coordinates and controls the above-mentioned units to work together or as needed to complete the normal start of the engine under each working condition.

[0022] As mentioned in the above technical background, the micro turbojet engine has requirements for the temperature and speed of the air when starting. If the incoming air speed is too fast, the ignition head temperature will be low and ignition will be impossible. The flame will be unstable and extinguished during the starting process. Therefore, in order to solve the problems of temperature and air speed, the independent oil supply unit in this embodiment is used to realize oil mist injection, thereby solving the temperature problem, and the oxygen supply unit is used to solve the problem of excessive air flow rate, ensuring sufficient oxygen in the combustion chamber and thus sufficient combustion.

[0023] The independent fuel supply unit includes: an independent fuel pump 4, which performs fuel supply work independently of the main fuel supply unit; an independent solenoid valve 5, which controls the opening of the independent fuel pump 4; an ignition atomizing nozzle 10, which atomizes the fuel in the ignition fuel pump; the main fuel supply unit includes: a main fuel pump 2, which provides conventional fuel supply; a fuel injection ring 11, which is used to connect the engine combustion chamber 01 and the main fuel pump 2; a main solenoid valve 3, which is used to control the opening / closing of the main fuel pump 2. The main fuel pump 2 and the independent fuel pump are symmetrically arranged. The main solenoid valve 3 and the independent solenoid valve 5 have the same functions, but the main function of the ignition atomizing nozzle 10 is to atomize the fuel and quickly fill the combustion chamber with oil mist. The main fuel pump 2 mainly supplies oil to the engine combustion chamber 01 during normal startup, and it is in a normal starting state. When the oil mist is ignited first, the temperature of the combustion chamber can be quickly increased, and then the main fuel pump 2 is used to supply fuel to further increase the starting speed of the engine.

[0024] The ignition unit includes an ignition nozzle 8 for igniting the oil in the engine combustion chamber 01; a high-energy igniter 7 for inputting high voltage electricity to the ignition nozzle 8, causing it to produce a spark. The oxygen supply unit includes an oxygen supply tank 6 and an oxygen supply jet ring 9. The oxygen supply jet ring 9 connects the engine combustion chamber 01 to the oxygen supply tank 6. The oxygen supply tank 6 and the independent oil pump 4 are located on the same side. The oxygen supply jet ring 9 sprays oxygen from the oxygen supply tank 6 into the combustion chamber. To achieve a quick / in-flight start / secondary in-flight start of the engine, the main fuel supply unit, ignition unit, oxygen supply unit, and independent fuel supply unit must be started simultaneously.

[0025] During a conventional ground start, the main fuel supply system and the igniter operate together, while the oxygen supply unit and independent fuel supply unit are inoperative, achieving a conventional ground start. The specific process is as follows: After the engine receives the start command, the control unit 1 (ECU) begins operating and supplies power to the main fuel supply pump 2, which begins pumping fuel. The main solenoid valve 3 opens, and fuel is injected into the combustion chamber through the injection ring 11. Simultaneously, the ECU sends a command to the high-energy igniter 7, which feeds high voltage electricity to the ignition nozzle 8. The ignition nozzle 8 generates a spark, igniting the fuel entering the engine combustion chamber 01, successfully igniting the engine.

[0026] When the engine needs to be started quickly on the ground: after the engine receives the start command, the main fuel supply system, ignition unit, oxygen supply unit and independent fuel supply unit work simultaneously to achieve rapid start on the ground. The specific process is as follows: After the engine is started, the control unit 1ECU starts working and supplies power to the independent oil pump 4. The independent oil pump 4 starts to input fuel. The independent solenoid valve 5 opens, and the fuel is sprayed into the combustion chamber through the ignition atomizing nozzle 10. At the same time, the control unit 1ECU inputs a signal to the oxygen supply tank 6, the oxygen supply tank 6 opens, and oxygen enters the combustion chamber through the oxygen supply jet ring 9 and mixes with the fuel; at the same time, the ECU sends an instruction to the high-energy igniter 7, and the high-energy igniter 7 inputs high voltage electricity to the ignition nozzle 8. The ignition nozzle 8 generates an electric spark and ignites the fuel entering the engine combustion chamber 01. Then the control unit 1ECU supplies power to the main fuel supply pump 2, the main fuel supply pump 2 starts to input fuel, the main solenoid valve 3 opens, and the fuel is sprayed into the combustion chamber through the fuel injection ring 11. The fuel sprayed through the ignition atomizing nozzle 10 and the oxygen provided by the oxygen supply tank 6 are mixed and burned violently. The high-temperature gas continues to mix and burn with the fuel sprayed through the fuel injection ring 11. A large amount of high-temperature gas can be generated in a short time, which can quickly drive the turbine to rotate and achieve rapid engine start-up.

[0027] When air starting or air secondary starting is required: in the engine windmill state, the main fuel supply unit, ignition unit, oxygen supply unit and independent fuel supply unit work at the same time to realize air starting. The specific process is as follows: after the engine receives the starting command, the control unit 1ECU starts to work and supplies power to the independent oil pump 4. The independent oil pump 4 starts to input fuel. The independent solenoid valve 5 opens, and the fuel is sprayed into the combustion chamber through the ignition atomizing nozzle 10. At the same time, the control unit 1ECU inputs a signal to the oxygen supply tank 6, the oxygen supply tank 6 opens, and oxygen enters the combustion chamber through the oxygen supply jet ring 9 to mix with the fuel; at the same time, the control unit 1ECU sends a command to the high-energy igniter 7, and the high-energy igniter 7 inputs high voltage electricity to the ignition nozzle 8, and the ignition nozzle 8 produces After the electric spark is generated, the fuel entering the engine combustion chamber 01 is ignited. At the same time, the control unit 1ECU supplies power to the main fuel pump 2, and the main fuel pump 2 starts to input fuel. The main solenoid valve 3 opens, and the fuel is sprayed into the combustion chamber through the injection ring 11. The fuel sprayed through the ignition atomizing nozzle 10 is mixed with the oxygen provided by the oxygen supply tank 6 and burns violently. At the same time, the high-temperature combustion gas continues to be mixed and burned with the fuel sprayed through the injection ring 11. At high altitude, a large amount of high-speed air enters the engine, and the main fuel supply unit and the independent fuel supply ignition unit need to work together to input sufficient fuel in a short time. At the same time, the oxygen supply system inputs oxygen to help the ignition nozzle 8 ignite the fuel and promote combustion, solving the problem of thin oxygen at high altitude and low air temperature and difficulty in starting.

[0028] Of course, in order to further improve the engine ignition speed, the oxygen supplement jet ring 9 is provided with a chamber 90 at the connection position with the engine combustion chamber 01, and the chamber 90 is connected to a focused jet port 91 and a diffuse jet port 92. In this embodiment, the focused jet port 91 and the diffuse jet port 92 are located on the same vertical plane of the chamber 90, and the cross-sectional circular size of the focused jet port 91 gradually decreases toward the engine combustion chamber 01, and the cross-sectional circular size of the diffuse jet port 92 gradually increases toward the engine combustion chamber 01. The initial cross-sectional circular size of the diffuse jet port 92 and the focused jet port 91 is the same; the diffuse jet port 92 is located above the focused jet port 91, and the diffuse jet port 92 is directly opposite to the inlet of the main fuel injection ring 11; In this embodiment, the focused injection port 91 primarily operates during the cold state, that is, before the engine ignites and when oxygen injection is required. In this embodiment, the focused injection port 91 is located closer to the ignition nozzle 8. When the focused injection port 91 operates, the high-pressure oxygen stream forms a highly concentrated jet, precisely directed toward the core of the fuel mist field ejected by the ignition atomizing nozzle 10 and the spark region of the ignition nozzle 8. This ensures extremely high oxygen concentrations in the critical area at the moment of ignition, greatly improving the success rate of ignition. Furthermore, during the hot state, when the fuel has already begun to burn in the combustion chamber, the diffuse injection port 92 faces the inlet of the main fuel injection ring 11. When the main fuel supply pump 2 begins operating, the high-pressure oxygen injection angle of the diffuse injection port 92 increases, covering a wider range. This allows for more macroscopic and uniform mixing with the main fuel ejected from the main fuel injection ring 11, promoting rapid expansion and stabilization of combustion, thereby rapidly generating a large amount of high-temperature combustion gas to drive the turbine.

[0029] The opening in chamber 90 is also provided with an adjustment unit, which is used to achieve a narrow-angle focused jet shape at low temperatures and a wide-angle diffuse jet shape when hot. The adjustment unit includes: a slide 93, which is slidably mounted on the side wall of chamber 90 and is provided with a vent 94. The vent 94 is adapted to the inlet of the focused jet port 91 or the inlet of the diffuse jet port 92. Because the slide 93 slides against the inner wall of chamber 90, it can be set so that only one of the focused jet port 91 or the diffuse jet port 92 is in operation; a deformation mechanism, which maintains its original shape in the cold state and contracts and deforms in the hot state; and a transmission mechanism, which is used to convert the deformation of the deformation structure into power to control the swing of the baffle. Although chamber 90 protects the structure and components of the adjustment unit, the components of the adjustment unit must also be made of high-temperature resistant materials to avoid affecting its precise adjustment performance. In addition, when a cold state is required, high-pressure oxygen can be introduced into chamber 90, and heat can be exchanged through air flow, so that the adjustment unit is quickly cooled, forming a cold chamber effect to a certain extent.

[0030] The deformation mechanism is used to achieve the switching effect between the diffuse jet port 92 and the focused jet port 91 during the cold and hot states. In this embodiment, the deformation mechanism uses a memory alloy strip 99, and of course a memory alloy bundle can also be used; the memory alloy strip 99 is fixedly connected to the slider 95, and the other end is fixedly connected to the inner wall of the chamber 90, and is respectively provided with elastic members 96 at both ends of the slider 95; when the memory alloy strip 99 is in the hot state, the vent 94 on the slide 93 moves to the diffuse jet port 92; the transmission mechanism includes: a slider 95, which slides in the chamber 90 along the direction of oxygen flow; an elastic member 96, which is used to achieve the switching effect between the slider 95 and the chamber 90 is elastically connected; a transmission rod 97, one end of which is movably connected to the slider 95; a connecting piece 98 is used to connect the other end of the transmission rod 97 to the top of the slider 93. In this embodiment, a slider is fixedly connected in the chamber 90, and the slider 95 is sleeved and slid outside the slider. The elastic piece 96 adopts a high-temperature resistant spring, which is also sleeved outside the slider. One end of the spring is fixedly connected to the slider 95, and the other end is fixedly connected to the inner wall of the chamber 90. The spring is located at a position where the slider 95 is away from the focusing injection port 91, and the memory alloy belt 99 is located at one end of the slider 95 close to the focusing injection port 91. In the initial state, the spring is also in a compressed state.

[0031] Specifically, the transmission rod 97 is hinged with a hinge block, and the bottom of the slider 95 is also provided with a hinge groove for the sliding of the hinge block. The cross-sections of the hinge block and the hinge groove are both set to T-shaped, that is, the large-sized part of the hinge block slides on the large-sized part of the hinge groove. The position where the transmission rod 97 is hinged to the chamber 90 is close to the slider 95. The lever amplification principle is used here. Since the deformation of the memory alloy belt 99 is limited, it is necessary to convert the limited deformation of the memory alloy belt 99 into the movement of the slider 93 through the lever amplification principle. In this embodiment, the connecting member 98 can be connected by a flexible and hard material such as a wire rope. Therefore, during actual operation, in the initial state, the air vent on the slide 93 is connected to the focused injection port 91, and the high-pressure oxygen is ejected in a focused state. When combustion begins in the combustion chamber, the temperature in the chamber 90 also rises, exceeding the phase change temperature of the memory alloy strip 99. The memory alloy strip 99 transforms into the austenite phase and produces a strong contraction. The force is greater than the elastic force of the spring, and the slider 95 slides in the direction away from the slide 93. The transmission rod 97 and the connecting piece 98 swing upward, and the slide 93 slides upward until the air vent 94 is connected to the diffuse injection port 92, and the oxygen injection is switched to a diffuse form when the hot state is achieved.

[0032] The diffuse injection port 92 is provided with an oblique cut with a tangential deflection angle (not shown in the figure), and the inner wall of the diffuse injection port 92 is provided with a spiral micro-guide groove. The oblique cut with a tangential deflection angle means that the axis of the nozzle itself is not strictly pointing to the center of the combustion chamber (i.e., radially), but has an angle with the radial line, pointing in the tangential direction of the circumference. The oxygen jet ejected from this composite-shaped nozzle will have both an axial velocity component and a tangential velocity component. The rotating airflow itself has a strong axial momentum, i.e., the momentum in the downstream direction along the axis of the engine. Therefore, the overall forward-moving, rotating mixed gas mass is like an invisible, energy-filled piston. This "pneumatic piston" will forcefully propel the entire oil-gas mixture downstream (towards the turbine), ensuring that the combustion process quickly and without delay fills the entire effective volume of the combustion chamber, mainly solving the problem of insufficient momentum of the fuel spray itself and its inability to diffuse quickly.

[0033] The implementation principle of the independent fuel supply and ignition system for quick starting of a micro-turbojet engine in the embodiment of the present application is as follows: the micro-turbojet engine has requirements for the temperature and velocity of the air during starting. If the incoming air velocity is too fast, the ignition head temperature will be low and ignition will be impossible, and the flame will be unstable and flameout during the starting process. Therefore, in order to solve the problems of temperature and air velocity, the independent fuel supply unit in this embodiment is used to realize oil mist injection, thereby solving the problem of temperature, and the oxygen supply unit is used to solve the problem of excessive air velocity, ensuring sufficient oxygen in the combustion chamber and thus sufficient combustion; In the cold state, that is, before the engine ignites and oxygen injection is required, the focused injection port 91 begins operation. In this embodiment, the focused injection port 91 is located closer to the ignition nozzle 8. When the focused injection port 91 begins operation, the high-pressure oxygen flow forms a highly concentrated jet, precisely directed toward the core of the fuel mist field sprayed by the ignition atomizing nozzle 10 and the spark area of ​​the ignition nozzle 8. This ensures extremely high oxygen concentration in the critical area at the moment of ignition, greatly improving the ignition success rate. In the hot state, that is, when the fuel has begun to burn in the combustion chamber, because the diffuse injection port 92 is directly opposite the inlet of the main injection ring 11, if the main fuel supply pump 2 starts to operate, the high-pressure oxygen injection angle of the diffuse injection port 92 becomes larger, covering a wider range, and can achieve more macroscopic and uniform mixing with the main fuel injected by the main injection ring 11, promoting the rapid expansion and stabilization of combustion, thereby quickly generating a large amount of high-temperature combustion gas to drive the turbine.

[0034] Unless otherwise defined, the technical or scientific terms used in this application shall have the usual meanings understood by persons of ordinary skill in the field to which this application belongs. The words "first", "second", "third" and similar terms used in the specification and claims of this application do not indicate any order, quantity or importance, but are only used to distinguish different components. Words such as "one" or "a" do not indicate a quantity limitation, but rather indicate the existence of at least one. Words such as "include" or "comprise" mean that the elements or objects appearing before "include" or "comprises" cover the elements or objects listed after "include" or "comprises" and their equivalents, and do not exclude other elements or objects. "Up", "down", "left", "right" and the like are only used to indicate relative positional relationships. When the absolute position of the described object changes, the relative positional relationship may also change accordingly.

[0035] The above are all preferred embodiments of the present application, and are not intended to limit the scope of protection of the present application. Therefore, any equivalent changes made based on the structure, shape, and principle of the present application should be included in the scope of protection of the present application.

Claims

1. A micro turbojet engine rapid start independent fuel supply ignition system, characterized in that: include: A control unit, configured to execute an engine start instruction; Main fuel supply unit, used to realize conventional engine starting on the ground; an ignition unit, for ignition; An oxygen supply unit is used to supply oxygen to the engine combustion chamber; as well as Independent fuel supply unit for quick engine starting; The independent oil supply unit comprises: Independent oil pump, which supplies oil independently from the main oil supply unit; Independent solenoid valve controls the opening of the independent oil pump; Ignition atomizing nozzle to atomize the oil supplied from the independent oil pump; When a quick / in-flight start / secondary in-flight start of the engine is required, the main fuel supply unit, ignition unit, oxygen supply unit and independent fuel supply unit need to be started simultaneously.

2. A micro turbojet engine rapid start independent fuel supply ignition system according to claim 1, characterized in that: The main oil supply unit comprises: Main oil supply pump, conventional oil supply; The fuel injection ring is used to connect the engine combustion chamber with the main fuel supply pump; Main solenoid valve, used to control the main oil supply pump on / off.

3. A micro turbojet engine rapid start independent fuel supply ignition system according to claim 2, characterized in that: The ignition unit comprises: Ignition nozzle, used to ignite the oil in the engine combustion chamber; The high-energy igniter is used to input high voltage electricity to the ignition nozzle and make the ignition nozzle generate electric sparks.

4. A micro turbojet engine rapid start independent fuel supply ignition system according to claim 3, characterized in that: The oxygen supplementation unit comprises: An oxygen supply tank and an oxygen supply jet ring, wherein the oxygen supply jet ring is used to connect the engine combustion chamber and the oxygen supply tank.

5. A micro turbojet engine rapid start independent fuel supply ignition system according to claim 4, characterized in that: The oxygen-supplementing jet ring is provided with a chamber at a position connected to the engine combustion chamber, and the chamber is connected to a focusing jet port and a diffuse jet port. The cross-sectional circular size of the focused injection port gradually decreases toward the engine combustion chamber, and the cross-sectional circular size of the diffuse injection port gradually increases toward the engine combustion chamber; The diffuse injection port is located above the focused injection port, and the diffuse injection port is directly facing the inlet of the main injection ring; The opening in the chamber is further provided with an adjustment unit, which is used to achieve a narrow-angle focused spray shape at low temperature and a wide-angle diffuse spray shape at hot state.

6. A micro turbojet engine rapid start independent fuel supply ignition system according to claim 5, characterized in that: The adjustment unit includes: a slide plate, slidably disposed on a side wall of the chamber and provided with a vent hole, wherein the vent hole is adapted to the inlet of the focused injection port or the inlet of the diffuse injection port; Deformable mechanism, which is in its original shape when cold and contracts and deforms when hot; The transmission mechanism is used to convert the deformation of the deformable structure into power to control the swing of the baffle.

7. A micro turbojet engine rapid start independent fuel supply ignition system according to claim 6, characterized in that: The transmission mechanism comprises: a slider, sliding in the chamber along the direction of oxygen flow; An elastic member, used to realize elastic connection between the slider and the chamber; A transmission rod, one end of which is movably connected to the slider, the transmission rod is rotationally connected to the chamber, and the position where the transmission rod is rotationally connected to the chamber is close to the slider; The connecting piece is used to connect the other end of the transmission rod and the top of the skateboard.

8. A micro turbojet engine rapid start independent fuel supply ignition system according to claim 7, characterized in that: The deformation mechanism comprises: A memory alloy strip is fixedly connected to the slider, and the other end is fixedly connected to the inner wall of the chamber, and the elastic member is respectively provided at both ends of the slider; When the memory alloy strip is in a hot state, the vent holes on the slide plate move to the diffusion injection port.

9. A micro turbojet engine rapid start independent fuel supply ignition system according to claim 8, characterized in that: The diffuse injection port is provided with an oblique cut with a tangential deflection angle, and the inner wall of the diffuse injection port is provided with a spiral micro guide groove.

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