A quick start system and method applied to turbojet engines

Abstract

The application belongs to the technical field of turbojet engines, and discloses a quick starting system and method applied to a turbojet engine, which comprises an oil supply module, the outlet of the oil supply module supplies a main oil path and an ignition oil path respectively, an air starting module, the air starting module is arranged at the air inlet of the turbojet engine, the outlet of the air starting module is arranged in correspondence with the air compressor wheel of the turbojet engine, and an initiation integrated motor, which comprises a stator and a rotor arranged in correspondence, the stator is electrically connected with the control module of the turbojet engine, the stator is fixed to the diffuser of the turbojet engine, and the rotor is fixed to the back of the air compressor wheel. The application has the advantages of compact structure, convenient use, improved precision of oil supply, improved flame stability, increased speed of the rotation speed of the air compressor wheel, reduced time for the flame in the combustion chamber to reach stable combustion, improved starting speed, reverse replenishment of consumption after stable operation, convenient recycling, reduced maintenance cost and starting cost.

Description

Technical Field

[0001] The present invention belongs to the technical field of turbojet engines, and in particular relates to a rapid starting system and method applied to turbojet engines. Background Art

[0002] A turbojet engine is a turbine engine, the characteristic of which is that it completely relies on the flow of gas to generate thrust; the working process of the turbojet core engine is that the air is first compressed by the compressor impeller at the front end of the turbojet core engine, and then further decelerated and expanded through the diffuser, and the total temperature and total pressure of the compressed air both increase; then the air enters the combustion chamber and mixes with the atomized fuel to form a flammable gas-fuel mixture; the mixture is ignited by the ignition device installed on the combustion chamber, and the chemical energy in the fuel is extracted through combustion, and the gas temperature rises sharply to form high-temperature and high-pressure gas; the high-temperature and high-pressure gas drives the turbine to rotate, and the turbine expands and does work to drive the compressor to rotate, forming a complete heat engine cycle; the gas after flowing through the turbine expands and does work again through the nozzle to generate thrust.

[0003] Existing turbojet engine starting methods mainly include pyrotechnic starting and conventional starting. However, pyrotechnics are disposable consumable materials and cannot be used for continuous starting. If multiple starts are to be achieved, multiple sets are required, and the starting cost is relatively high. In addition, fireworks and gunpowder are both pyrotechnics, and there are safety risks in storage and transportation, which are not convenient for use in the civilian field. Conventional starting methods take a long time to start, generally about 60 seconds, which does not meet the overall design requirements of the aircraft under special working conditions.

[0004] Therefore, the present application designs a rapid starting system and method for a turbojet engine to solve the above technical problems. Summary of the Invention

[0005] In order to solve the above technical problems, the present invention proposes a rapid starting system and method for a turbojet engine, aiming to solve the problems of long starting time and complex structure of micro turbojet engines, as well as the high starting cost of disposable consumables.

[0006] To achieve the above object, the present invention provides a rapid starting system for a turbojet engine, comprising:

[0007] a fuel supply module, the fuel supply module being arranged on the turbojet engine, the inlet of the fuel supply module being connected to the fuel tank, the outlet of the fuel supply module supplying a main oil circuit and an ignition oil circuit respectively, the main oil circuit and the ignition oil circuit extending into the combustion chamber of the turbojet engine;

[0008] An air starting module, the air starting module being arranged at the air inlet of the turbojet engine, the outlet of the air starting module being arranged corresponding to the compressor wheel of the turbojet engine, and the inlet of the air starting module being in communication with the inner cavity of the combustion chamber;

[0009] The integrated motor includes a stator and a rotor that are correspondingly arranged. The stator is electrically connected to the control module of the turbojet engine, the stator is fixed to the diffuser of the turbojet engine, and the stator is fixed to the back of the compressor wheel.

[0010] Preferably, the oil supply module includes an independently arranged main oil pump and an ignition oil pump, the main oil pump and the ignition oil pump are respectively connected to the oil tank, the outlet of the ignition oil pump is connected to the ignition oil circuit, and the outlet of the main oil pump supplies oil to the inner cavity of the combustion chamber through the main oil circuit.

[0011] Preferably, the oil supply module also includes an oil supply base, the main oil pump and the ignition oil pump are respectively fixedly mounted on the oil supply base and are connected to independently arranged grooves in the oil supply base, and the main oil circuit and the ignition oil circuit are respectively connected to the grooves.

[0012] Preferably, the fuel supply module includes a fuel supply pump connected to the fuel tank, the outlet of the fuel supply pump is connected to a pressure differential valve, and the pressure differential valve is connected to the inner cavity of the combustion chamber through the main oil circuit and the ignition oil circuit respectively.

[0013] Preferably, the pressure differential valve includes a valve body, which is connected to an oil inlet, a first oil outlet and a second oil outlet, the first oil outlet is connected to the ignition oil circuit, the second oil outlet is connected to the main oil circuit, and the oil inlet is connected to the oil supply pump.

[0014] Preferably, a diaphragm is provided for sealing and sliding inside the valve body, and an adjusting spring is provided between the diaphragm and the inner cavity of the valve body; the second oil outlet is connected to the adjusting tube provided in the valve body, and the diaphragm is slidably sleeved outside the adjusting tube and is limited by the oil inlet groove on the adjusting tube.

[0015] Preferably, the air starting module includes an annular gas cylinder arranged around the compressor wheel, and a plurality of air outlets corresponding to the blades of the compressor wheel are arranged at equal intervals on the annular gas cylinder, and the inlet of the annular gas cylinder is connected to the combustion chamber.

[0016] A rapid starting method for a turbojet engine comprises the following steps:

[0017] Prepare for starting the turbojet engine and check the integrity of the oil circuit and electrical circuit;

[0018] A starting signal is issued, and the oil supply module, air starting module and the inspiration integrated motor start;

[0019] According to the starting working condition requirements, the air starting module and the starting motor drive the compressor wheel to rotate, so that the external air is pressurized and enters the combustion chamber;

[0020] The fuel supply module first supplies fuel to the combustion chamber through the ignition oil circuit, which mixes with the high-pressure air in the combustion chamber and ignites. At the same time, it continuously supplies fuel to the combustion chamber through the main oil circuit to maintain stable combustion operation in the combustion chamber.

[0021] Stop the output of the air starting module and the integrated inspiration motor. At the same time, the high-pressure air in the combustion chamber replenishes the high-pressure gas to the air starting module, and the integrated inspiration motor starts the power generation mode to generate electricity and store it for easy restart.

[0022] Preferably, when the oil supply module includes a main oil pump and an ignition oil pump, the main oil pump and the ignition oil pump operate independently, and after ignition is completed, the ignition oil pump stops running, while the main oil pump continues to run.

[0023] Preferably, when the oil supply module includes an oil supply pump and a pressure differential valve, the oil supply pump operates continuously.

[0024] Compared with the prior art, the present invention has the following advantages and technical effects: the present invention discloses a rapid starting system and method for a turbojet engine, the fuel supply module is used to supply fuel to the combustion chamber through the main fuel circuit and the ignition fuel circuit, which facilitates ignition and stable combustion in the combustion chamber, and the fuel supply module can also supply fuel to the ignition fuel circuit and the main fuel circuit separately and accurately, maintain flame stability, and improve the starting speed; the air starting module and the integrated inspiration motor are set up, which can be used separately or simultaneously to provide initial power for the starting of the turbojet engine, and the air starting module can provide high-pressure compressed air to blow to the compressor wheel, drive the compressor wheel to rotate, and compress the outside air into the combustion chamber, ensuring sufficient air and pressure for starting, and improving the starting speed. After the starting is completed, the excess air in the combustion chamber is reversely compressed and enters the air starting module to replenish the used compressed air. air, which is convenient for use when starting again; at the same time, the air starting module can also be filled with air with a high oxygen content, which is convenient for starting at high altitude or in areas with low oxygen content, and will further accelerate the starting speed; and when starting, the motor supplies power to the stator through the control module, and through the electromagnetic effect of the stator and the rotor, the rotor drives the compressor wheel to rotate, providing initial intake power for the starting of the turbojet engine. Combined with the design of the air starting module, it can quickly increase the speed of the compressor wheel, increase the intake volume of the combustion chamber, and improve the starting speed. After the start is completed, the compressor wheel is in a high-speed rotation state, and the electromagnetic effect between the rotor and the stator generates electricity in reverse to charge the power storage module of the turbojet engine, which is convenient for subsequent power supply. At the same time, it can recover part of the energy to provide electricity for the aircraft, reduce the aircraft's demand for batteries, and at the same time, improve the aircraft's load capacity.

[0025] The present invention has a compact structure and is easy to use. It improves the accuracy of oil supply and flame stability, while also increasing the speed increase rate of the compressor wheel, reducing the time it takes for the flame in the combustion chamber to reach stable combustion, and increasing the starting speed. Furthermore, after stable operation, it can reversely replenish consumption, facilitate recycling, reduce maintenance costs and starting costs, improve engine starting efficiency, reduce starting time, and achieve rapid starting. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The accompanying drawings, which constitute part of this application, are intended to provide a further understanding of this application. The exemplary embodiments and descriptions of this application are intended to explain this application and do not constitute an improper limitation on this application. In the accompanying drawings:

[0027] Figure 1 This is a flowchart of the existing single oil pump startup of the present invention;

[0028] Figure 2 Schematic diagram of a rapid starting system for a turbojet engine according to the present invention;

[0029] Figure 3 This is an axial view of an oil supply module according to a first embodiment of the present invention;

[0030] Figure 4 This is a front view of a fuel supply module according to an embodiment of the present invention;

[0031] Figure 5 This is a top view of a fuel supply module according to an embodiment of the present invention;

[0032] Figure 6 This is a control flow chart of the oil supply module of the present invention;

[0033] Figure 7 The present invention inspires the integrated motor control flow chart;

[0034] Figure 8 This is a schematic diagram of a pressure differential valve according to a second embodiment of the present invention;

[0035] Figure 9 This is a flow chart of a low-cost rapid start of a turbojet engine according to a second embodiment of the present invention;

[0036] Figure 10 This is a comparison diagram of the effects of the second embodiment of the present invention and the prior art;

[0037] In the figure: 1. Air inlet; 2. Compressor wheel; 3. Annular gas cylinder; 4. Gas cylinder solenoid valve; 5. Diffuser; 6. Main oil circuit; 7. Combustion chamber; 8. Shaft tube; 9. Main shaft; 10. Guide; 11. Turbine; 12. Fuel supply module; 13. Ignition oil circuit solenoid valve; 14. Rotor; 15. Stator; 16. Mounting bracket; 17. Ignition head; 18. Ignition oil circuit; 19. Ignition oil pump; 20. Main oil pump; 21. Fuel supply base; 22. Oil filter; 23. Fuel inlet nozzle; 24. Pressure differential valve; 25. Fuel supply pump; 26. Valve body; 27. Fuel inlet; 28. First oil outlet; 29. ​​Second oil outlet; 30. Diaphragm; 31. Adjusting spring; 32. Air inlet hole; 33. Oil inlet tank; 34. Adjusting pipe; 35. Main oil circuit solenoid valve. DETAILED DESCRIPTION

[0038] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0039] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0040] Example 1

[0041] Reference Figure 1-Figure 7 As shown, this embodiment provides a rapid starting system for a turbojet engine, comprising:

[0042] The fuel supply module 12 is provided on the turbojet engine. The inlet of the fuel supply module 12 is connected to the fuel tank. The outlet of the fuel supply module 12 supplies the main oil passage 6 and the ignition oil passage 18 respectively. The main oil passage 6 and the ignition oil passage 18 extend into the combustion chamber 7 of the turbojet engine.

[0043] An air starting module is provided at the air inlet 1 of the turbojet engine, an outlet of the air starting module is provided corresponding to the compressor wheel 2 of the turbojet engine, and an inlet of the air starting module is communicated with the inner cavity of the combustion chamber 7;

[0044] The integrated motor includes a stator 15 and a rotor 14 that are correspondingly arranged. The stator 15 is electrically connected to the control module of the turbojet engine. The stator 15 is fixed to the diffuser 5 of the turbojet engine. The stator 15 is fixed to the back of the compressor wheel 2.

[0045] The present invention discloses a rapid starting system and method for a turbojet engine, wherein the fuel supply module 12 is used to supply fuel to the combustion chamber 7 through the main oil circuit 6 and the ignition oil circuit 18, so as to facilitate ignition and stable combustion in the combustion chamber 7, and at the same time, the fuel supply module 12 can also supply fuel to the ignition oil circuit 18 and the main oil circuit 6 separately and accurately, so as to maintain flame stability and improve the starting speed; the setting of the air starting module and the integrated inspiration motor can be used separately or simultaneously to provide initial power for the starting of the turbojet engine, and the air starting module can provide high-pressure compressed air to blow to the compressor wheel 2, driving the compressor wheel 2 to rotate, so that the outside air is compressed into the combustion chamber 7, ensuring that there is sufficient air and pressure for starting, and improving the starting speed. After the starting is completed, the excess air in the combustion chamber 7 is reversely compressed and enters the air starting module to replenish the used compressed air, so as to facilitate starting again Use; at the same time, the air starting module can also be filled with air with a higher oxygen content, which is convenient for starting at high altitude or low oxygen content areas, and will further accelerate the starting speed; and when starting, the motor is powered by the control module to the stator 15, and the electromagnetic effect of the stator 15 and the rotor 14 is used to drive the compressor wheel 2 to rotate, providing initial intake power for the starting of the turbojet engine. Combined with the design of the air starting module, the speed of the compressor wheel 2 can be quickly increased, the intake volume of the combustion chamber 7 can be increased, and the starting speed can be improved. After the start is completed, the compressor wheel 2 is in a high-speed rotation state, and the electromagnetic effect between the rotor 14 and the stator 15 is reversed to generate electricity, charging the power storage module of the turbojet engine, facilitating subsequent power supply, and at the same time recovering part of the energy to provide electricity for the aircraft, reducing the aircraft's demand for batteries, and at the same time, improving the aircraft's load capacity. The present invention has a compact structure and is easy to use. It improves the accuracy of oil supply and flame stability, while increasing the speed increase rate of the compressor wheel 2, reducing the time for the flame in the combustion chamber 7 to reach stable combustion, and improving the starting speed. At the same time, it can reversely replenish consumption after stable operation, facilitate recycling, reduce maintenance costs and starting costs, improve engine starting efficiency, reduce starting time, and achieve rapid starting.

[0046] Furthermore, the compressor wheel 2 is rotatably connected to the air inlet 1, and the main shaft 9 is fixed to the compressor wheel 2; the diffuser 5 is located at the outlet of the compressor wheel 2, and the combustion chamber 7 is connected to the diffuser 5, and the main shaft 9 extends into the combustion chamber 7 after passing through the diffuser 5; the diffuser 5 is used to compress the air introduced by the compressor wheel 2, thereby increasing the temperature and pressure, and then forming a mixed gas with the injected fuel in the combustion chamber 7 to facilitate combustion.

[0047] Furthermore, after passing through the combustion chamber 7, the main shaft 9 again passes through the guide 10 fixed to the combustion chamber 7. The end of the main shaft 9 extends into the tail nozzle and is installed with a turbine 11. When the high-temperature and high-pressure gas generated in the combustion chamber 7 passes through the guide 10 and reverses, it drives the turbine 11 to rotate again. After passing through the turbine 11, it is ejected from the tail nozzle to provide thrust, and the turbine 11 drives the main shaft 9 to rotate stably, thereby driving the compressor wheel 2 to provide sufficient air for the turbojet engine.

[0048] Furthermore, a shaft tube 8 is provided in the combustion chamber 7 , and the main shaft 9 passes through the shaft tube 8 , thereby protecting the main shaft 9 .

[0049] Furthermore, the oil supply module 12 is fixed on the diffuser 5, which is convenient for fixation.

[0050] Furthermore, the stator 15 of this embodiment is fixed by a mounting bracket 16 , which is arranged in a ring shape as a whole and is arranged around the main shaft 9 .

[0051] Furthermore, the stator 15 of this embodiment uses a ring-shaped coil, and the coil is electrically connected to the power supply module. During startup, it is energized under the drive of the control module to generate magnetism; and the rotor 14 is a permanent magnet arranged on the back of the compressor wheel 2, and is coaxially connected to the turbojet engine; when the turbojet engine needs to be started, the turbojet engine serves as a load, and the starter-generator motor works as an electric motor, which consumes the electrical energy in the power supply module and converts it into mechanical energy, and drives the compressor wheel 2 to rotate through the main shaft 9; after starting is completed, the turbojet engine becomes the prime mover, and the starter-generator motor changes from the starting state to the power generation state, working as a generator, and the turbojet engine main shaft 9 rotates, thereby driving the rotor 14 to rotate, converting the mechanical energy into electrical energy, and performing rectification and voltage stabilization through the power converter to charge the battery or supply airborne equipment for use, thereby improving the towing efficiency and reducing the energy loss of the motor.

[0052] Furthermore, the use of an integrated motor can greatly reduce the number of mechanical components in the electrical system, reduce the onboard volume, and lighten the system mass.

[0053] Furthermore, this embodiment adopts a brushless DC motor with a starting power of up to 600W, which can drive the main shaft 9 to a speed of more than 10,000 within 2 seconds.

[0054] Further optimization scheme, the oil supply module 12 includes an independently set main oil pump 20 and ignition oil pump 19, the main oil pump 20 and the ignition oil pump 19 are respectively connected to the fuel tank, the outlet of the ignition oil pump 19 is connected to the ignition oil circuit 18, and the outlet of the main oil pump 20 is connected to the inner cavity of the combustion chamber 7 through the main oil circuit 6; the oil supply module 12 also includes an oil supply base 21, the main oil pump 20 and the ignition oil pump 19 are respectively fixedly installed on the oil supply base 21 and are connected to the independently set groove in the oil supply base 21, and the main oil circuit 6 and the ignition oil circuit 18 are respectively connected to the groove. Figure 1 In the existing ignition process shown in FIG, the existing turbojet engine supplies oil to the main oil circuit 6 and the ignition oil circuit 18 respectively through an oil pump; however, the single oil pump ignition structure has a design defect during the acceleration process due to the drop in oil pump voltage, which leads to unstable combustion inside the turbojet engine. This is manifested as after entering the acceleration stage, due to the main oil circuit solenoid valve 35 allocating part of the fuel flow, the oil pressure required for atomization of the ignition oil circuit 18 nozzle cannot be reached, and the main oil circuit 6 fuel entering the preheating tube cannot be evaporated and burned in time. At this time, the flame inside the turbojet engine burns In the case of unstable combustion, the exhaust temperature drops, affecting the starting time and starting envelope; the oil supply base 21 of the present application is installed on the diffuser 5, and the oil supply base 21 is provided with a number of independently set grooves for fuel flow, and the oil supply base 21 is provided with independently controlled main oil pump 20 and ignition oil pump 19, which are used to respectively deliver the fuel into the main oil circuit 6 and the ignition oil circuit 18 for fuel supply. Under the action of the turbojet controller, the ignition oil pump 19 and the main oil pump 20 have separate fuel pipelines, which provide accurate fuel flow to the corresponding oil circuits respectively.

[0055] Furthermore, an oil inlet nozzle 23 is provided on the oil supply base 21 , and the oil inlet nozzle 23 is communicated with the channel through an oil filter 22 fixed on the oil supply base 21 .

[0056] Furthermore, a main oil circuit solenoid valve 35 and an ignition oil circuit solenoid valve 13 are provided on the oil supply base 21. The main oil circuit solenoid valve 35 is provided between the main oil circuit 6 and the main oil pump 20, and the ignition oil circuit solenoid valve 13 is provided between the ignition oil circuit 18 and the ignition oil pump 19, which respectively control the on and off of the oil circuits.

[0057] Further, see the attached Figure 5 As shown in the flow chart of the fuel supply module 12, after successful ignition, the engine directly enters the acceleration stage. The ignition oil pump 19 maintains a 1.3V oil pump voltage and continuously provides fuel with a pressure greater than 0.2Mpa to the nozzle of the ignition oil circuit 18 to ensure stable combustion inside the combustion chamber 7. At the same time, the main oil pump 20 and the main oil circuit solenoid valve 35 are opened, and the fuel entering the evaporation tube is quickly atomized and fully mixed with the air to quickly form a combustible mixture, thereby maintaining a stable flame and increasing the starting speed.

[0058] To further optimize the solution, the air starting module includes an annular gas cylinder 3 arranged around the compressor wheel 2. A number of air outlets corresponding to the blades of the compressor wheel 2 are evenly spaced on the annular gas cylinder 3, and the inlet of the annular gas cylinder 3 is connected to the combustion chamber 7. The annular gas cylinder 3 is set in the air inlet 1, with an internal pressure of 0.3Mpa. It is connected through a pipeline. During the starting phase, the gas cylinder solenoid valve 4 is opened, and the high-pressure air inside the annular gas cylinder 3 directly blows the blades of the compressor wheel 2. Starting at high altitude can provide additional oxygen for the engine, and can instantly increase the speed of the engine main shaft 9 in a short time, thereby increasing the starting speed. After the engine is started, the high-pressure gas generated inside the combustion chamber 7 is reversely inflated to the annular gas cylinder 3, which is convenient for the next start and reduces the starting cost.

[0059] Furthermore, the annular gas cylinder 3 of this embodiment is an annular web, which is attached to the inner wall of the air inlet 1 to form a cavity for storing high-pressure air. It has a simple structure and also avoids affecting the air intake of the air inlet 1.

[0060] A rapid starting method for a turbojet engine comprises the following steps:

[0061] Prepare for starting the turbojet engine and check the integrity of the oil circuit and electrical circuit;

[0062] A starting signal is issued, and the oil supply module 12, the air starting module and the inspiration integrated motor are started;

[0063] According to the starting working condition requirements, the compressor wheel 2 is driven to rotate by the air starting module and the inspiration integrated motor, so that the external air is pressurized and enters the combustion chamber 7; in the starting stage of the turbojet engine, the cylinder solenoid valve 4 is opened, and the high-pressure air in the annular cylinder 3 is ejected toward the compressor wheel 2, directly blowing the blades of the compressor wheel 2, thereby driving the main shaft 9 to rotate, so that the external air is compressed and pressed into the combustion chamber 7; at this time, the inspiration integrated motor acts as a starting motor, dragging the turbojet engine main shaft 9 to rotate, and the stator 15 is energized to generate magnetism, which drives the rotor 14 to rotate through the electromagnetic effect, thereby accelerating the rotation of the compressor wheel 2 and pressing air into the combustion chamber 7. The air starting module and the inspiration integrated motor can be used alone or in combination according to actual starting requirements to increase the speed of the main shaft 9 and improve efficiency;

[0064] The fuel supply module 12 first supplies fuel to the combustion chamber 7 through the ignition oil circuit 18, which is then mixed with the high-pressure air in the combustion chamber 7 and ignited. At the same time, fuel is continuously supplied to the combustion chamber 7 through the main oil circuit 6 to maintain stable combustion operation in the combustion chamber 7; the main oil pump 20 and the ignition oil pump 19 are started respectively, and the ignition oil circuit solenoid valve 13 is opened, and oil mist is sprayed to the ignition head 17 position through the ignition oil circuit 18 to facilitate ignition. At the same time, the main oil circuit solenoid valve 35 is opened, and fuel is supplied to the evaporation tube of the combustion chamber 7 through the main oil circuit 6, so that the fuel is quickly atomized and fully mixed with the air to quickly form a combustible mixture and maintain stable combustion.

[0065] Stop the output of the air starting module and the inspiration integrated motor, and at the same time, the high-pressure air in the combustion chamber 7 replenishes the high-pressure gas to the air starting module, and the inspiration integrated motor starts the power generation mode to generate electricity and store it for easy restart and use; after the start is completed, the high-pressure air generated in the combustion chamber 7 is reversely filled into the annular gas cylinder 3 to replenish the air consumed in the start, which is convenient for recycling; at the same time, after the turbojet engine is started, since the rotor 14 is coaxial with the turbojet engine main shaft 9, the inspiration integrated motor is still driven by the compressor wheel 2 to cut the magnetic flux lines, generating three-phase alternating current, which is converted into direct current that can be used by the aircraft after rectification and voltage stabilization by external instruments.

[0066] In a further optimized solution, when the fuel supply module 12 includes a main fuel pump 20 and an ignition fuel pump 19, the main fuel pump 20 and the ignition fuel pump 19 operate independently. After ignition is completed, the ignition fuel pump 19 stops operating, while the main fuel pump 20 continues to operate. In this embodiment, the main fuel pump 20 and the ignition fuel pump 19 are independently controlled. After ignition is completed, the ignition fuel pump 19 stops operating and no longer supplies fuel, reducing energy consumption. The main fuel pump 20 continues to supply fuel, ensuring stable operation of the turbojet engine.

[0067] Example 2

[0068] Refer to the attached Figure 8 -Attached Figure 10 As shown, the difference between this embodiment and embodiment 1 is that the present application replaces the dual oil pump design of the main oil pump 20 and the ignition oil pump 19 with an oil supply pump 25 and a pressure differential valve 24. In order to avoid the problems of complex structure, slow response and high cost of the oil supply module 12 from the source, the design scheme of the oil supply module 12 is optimized.

[0069] In a further optimization scheme, the fuel supply module 12 includes a fuel supply pump 25 connected to the fuel tank. The outlet of the fuel supply pump 25 is connected to a pressure differential valve 24. The pressure differential valve 24 is connected to the inner cavity of the combustion chamber 7 through the main fuel line 6 and the ignition fuel line 18 respectively. The fuel supply pump 25 supplies fuel to both the main fuel line 6 and the ignition fuel line 18 simultaneously through the pressure differential valve 24, thereby ensuring that the fuel supply pressure of the ignition fuel line 18 is stable and does not drop due to the voltage drop of the fuel supply pump 25 or the partial fuel sharing of the main fuel line 6. The oil pressure meets the pressure requirement of the nozzle atomization, improving combustion stability and thus increasing the starting speed of the turbojet engine.

[0070] Further optimization scheme, the differential pressure valve 24 includes a valve body 26, the valve body 26 is connected with an oil inlet 27, a first oil outlet 28 and a second oil outlet 29, the first oil outlet 28 is connected to the ignition oil circuit 18, the second oil outlet 29 is connected to the main oil circuit 6, and the oil inlet 27 is connected to the oil supply pump 25; a diaphragm 30 is sealed and slidable in the valve body 26, and an adjustment spring 31 is provided between the diaphragm 30 and the inner cavity of the valve body 26; the second oil outlet 29 is connected to a regulating pipe 34 provided in the valve body 26, and the diaphragm 30 is slidably sleeved outside the regulating pipe 34 and is limited by the oil inlet groove 33 on the regulating pipe 34. Figure 8 As shown, under normal conditions, the fuel enters the inner cavity of the valve body 26 through the oil inlet 27 and is discharged through the first oil outlet 28 into the ignition oil circuit 18. As the fuel pressurized by the fuel supply pump 25 enters from the oil inlet 27, since the diameter of the ignition nozzle connected to the ignition oil circuit 18 is relatively small, about 0.3 mm, and the flow rate is about 100 g per minute, the flux is relatively small. The fuel generates high pressure in the lower half of the diaphragm 30 in the inner cavity of the valve body 26. When the pressure reaches the pressure required for atomization of the ignition nozzle, that is, 0.3-0.4 MPa, the diaphragm 30 is displaced under the action of the oil pressure and slides along the regulating tube 34, so that the fuel enters the regulating tube 34 from the oil inlet groove 33, and then enters the main oil circuit 6 through the second oil outlet 29. At this time, it is only necessary to continue to increase the voltage of the fuel supply pump 25 to stabilize the fuel supply, and the turbojet core engine can complete the entire process of ignition-preheating-acceleration, greatly improving the stability of the fuel supply, accelerating the starting efficiency of the turbojet engine, and reducing the starting time.

[0071] Furthermore, the ignition oil circuit solenoid valve 13 of this embodiment is disposed between the first oil outlet 28 and the ignition oil circuit 18 . After the start-up is completed, the ignition oil circuit solenoid valve 13 is closed so that the ignition oil circuit 18 no longer supplies oil.

[0072] Furthermore, an air inlet hole 32 is provided on the valve body 26 of the differential pressure valve 24 so that the area where the adjustment spring 31 is installed is connected to the outside, thereby preventing the air pressure change caused by the rise and fall of the diaphragm 30.

[0073] Further, see the attached Figure 9 and attached Figure 10 As shown, the differential pressure valve 24 is used for starting, and the control logic is clearer and simpler. The oil pump only needs to increase the power according to the speed and temperature. At the same time, the required structural parts are also streamlined, and one solenoid valve is reduced. Combined with a high-power starter generator, the starting envelope can be effectively improved.

[0074] According to a further optimized solution, when the oil supply module 12 includes the oil supply pump 25 and the pressure differential valve 24 , the oil supply pump 25 operates continuously.

[0075] In the description of the present invention, it should be understood that the terms "longitudinal", "transverse", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing the present invention, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0076] The embodiments described above are merely descriptions of preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Without departing from the spirit of the present invention, various modifications and improvements made to the technical solutions of the present invention by persons skilled in the art should fall within the scope of protection defined by the claims of the present invention.

Claims

1. A rapid starting system for a turbojet engine, characterized in that: include: An oil supply module (12), the oil supply module (12) being arranged on the turbojet engine, the inlet of the oil supply module (12) being connected to the oil tank, the outlet of the oil supply module (12) supplying oil to a main oil circuit (6) and an ignition oil circuit (18), respectively, the main oil circuit (6) and the ignition oil circuit (18) extending into a combustion chamber (7) of the turbojet engine; An air starting module, the air starting module being arranged at an air inlet (1) of the turbojet engine, the outlet of the air starting module being arranged corresponding to the compressor wheel (2) of the turbojet engine, the air starting module comprising an annular gas cylinder (3) arranged around the compressor wheel (2), a plurality of air outlets being arranged corresponding to blades of the compressor wheel (2) being arranged at equal intervals on the annular gas cylinder (3), and the inlet of the annular gas cylinder (3) being in communication with the combustion chamber (7); The integrated motor comprises a stator (15) and a rotor (14) which are arranged correspondingly, wherein the stator (15) is electrically connected to a control module of the turbojet engine, the stator (15) is fixed to a diffuser (5) of the turbojet engine, and the rotor (14) is fixed to the back of the compressor wheel (2); The working process of the rapid starting system applied to a turbojet engine comprises the following steps: Prepare for starting the turbojet engine and check the integrity of the oil and electrical circuits; A start signal is issued, and the oil supply module (12), the air start module and the inspiration integrated motor are started; According to the starting working condition requirements, the compressor wheel (2) is driven to rotate by the air starting module and the starting motor, so that the external air is pressurized and enters the combustion chamber (7); The oil supply module (12) first supplies oil to the combustion chamber (7) through the ignition oil circuit (18), and the oil is mixed with the high-pressure air in the combustion chamber (7) and then ignited. At the same time, the oil is continuously supplied to the combustion chamber (7) through the main oil circuit (6) to maintain stable combustion operation in the combustion chamber (7); The output of the air starting module and the inspiration integrated motor is stopped, and at the same time, the high-pressure air in the combustion chamber (7) replenishes the high-pressure gas to the air starting module, and the inspiration integrated motor starts the power generation mode to generate electricity and store it for easy restart and use.

2. The rapid starting system for a turbojet engine according to claim 1, characterized in that: The oil supply module (12) includes a main oil pump (20) and an ignition oil pump (19) which are independently arranged. The main oil pump (20) and the ignition oil pump (19) are respectively connected to the oil tank. The outlet of the ignition oil pump (19) is connected to the ignition oil circuit (18). The outlet of the main oil pump (20) supplies oil to the inner cavity of the combustion chamber (7) through the main oil circuit (6).

3. The rapid starting system for a turbojet engine according to claim 2, characterized in that: The oil supply module (12) further includes an oil supply base (21), the main oil pump (20) and the ignition oil pump (19) are respectively fixedly mounted on the oil supply base (21) and communicate with independently provided grooves in the oil supply base (21), and the main oil circuit (6) and the ignition oil circuit (18) are respectively communicated with the grooves.

4. The rapid starting system for a turbojet engine according to claim 1, characterized in that: The oil supply module (12) includes an oil supply pump (25) connected to the oil tank, the outlet of the oil supply pump (25) is connected to a pressure differential valve (24), and the pressure differential valve (24) is connected to the inner cavity of the combustion chamber (7) through the main oil circuit (6) and the ignition oil circuit (18).

5. The rapid starting system for a turbojet engine according to claim 4, characterized in that: The differential pressure valve (24) comprises a valve body (26), and the valve body (26) is connected to an oil inlet (27), a first oil outlet (28), and a second oil outlet (29), wherein the first oil outlet (28) is connected to the ignition oil circuit (18), the second oil outlet (29) is connected to the main oil circuit (6), and the oil inlet (27) is connected to the oil supply pump (25).

6. The rapid starting system for a turbojet engine according to claim 5, characterized in that: A diaphragm (30) is provided in a sealing and sliding manner in the valve body (26), and an adjusting spring (31) is provided between the diaphragm (30) and the inner cavity of the valve body (26); the second oil outlet (29) is communicated with a regulating pipe provided in the valve body (26), and the diaphragm (30) is slidably sleeved outside the regulating pipe and is limited by an oil inlet groove (33) on the regulating pipe.

7. The rapid starting system for a turbojet engine according to claim 1, characterized in that: When the oil supply module (12) includes a main oil pump (20) and an ignition oil pump (19), the main oil pump (20) and the ignition oil pump (19) operate independently. After ignition is completed, the ignition oil pump (19) stops operating, while the main oil pump (20) continues to operate.

8. The rapid starting system for a turbojet engine according to claim 1, characterized in that: When the oil supply module (12) includes the oil supply pump (25) and the pressure differential valve (24), the oil supply pump (25) operates continuously.

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