Visual turbojet engine annular combustion chamber experiment system for ignition cross-flame process research

Abstract

The invention provides a visual turbojet engine annular combustion chamber experiment system for ignition cross-flame process research. The visual turbojet engine annular combustion chamber experiment system comprises a high-speed camera, a visual combustion chamber, a fuel oil supply system, an air inlet system and a smoke exhaust device. The visual combustion chamber is placed on the optical platform and is used for providing a visual liquid fuel evaporation atomization coupling ignition operation process in the evaporation pipe; the fuel oil supply system and the gas inlet system are both connected with the visual combustion chamber, the fuel oil supply system is used for supplying fuel oil to the visual combustion chamber, and the gas inlet system is used for controlling gas entering the visual combustion chamber; the smoke exhaust device is arranged above the visual combustion chamber and used for exhausting smoke generated after ignition of the visual combustion chamber is completed. And the high-speed camera is used for observing the ignition cross-flame effect of the visual combustion chamber. According to the application, the visualization of fuel oil flow evaporation in the evaporation pipe before ignition can be realized, so that the ignition cross flame visualization under the non-premixing condition is realized, and a foundation is laid for the subsequent experimental research of different types of visual combustion chambers.

Description

Technical Field

[0001] The present application belongs to the field of turbojet engine ignition experiments, and in particular, relates to a visualized turbojet engine annular combustion chamber experimental system for studying the ignition and combined flame process. Background Art

[0002] Micro turbojet engines are currently seen as an emerging and promising alternative for small power generation, hybrid transportation systems and drone propulsion systems. Compared with traditional reciprocating piston engines, micro turbojet engines have a higher power-to-weight ratio, greater flexibility and a wider operating range. However, their overall efficiency is still low, which is the main factor hindering the widespread application of micro gas turbines. The combustion chamber is a key component in a turbojet engine that is used to burn fuel and directly affects the combustion efficiency. In a micro turbojet engine, air enters the outer annular cavity of the combustion chamber after being compressed by a centrifugal turbine, enters the combustion chamber through the main combustion holes, afterburning holes and mixing holes on the inner and outer walls of the combustion chamber, and is mixed with the fuel for combustion.

[0003] The ignition process of the combustion chamber is an extremely complex, multi-factor coupled transient development process. Due to the difficulties in measurement and high costs, it is difficult to carry out ignition experimental research on full-scale industrial-grade annular combustion chambers. For the micro-turbojet engine combustion chamber, due to its small size, it meets the laboratory-scale combustion chamber experimental standards, so it is necessary to design a visual turbojet engine combustion chamber for ignition process research.

[0004] The Chinese invention patent application with publication number CN113567143B discloses a visualized gas turbine combustion chamber experimental system, including a compressed air supply device, a natural gas supply device, a gas turbine combustion chamber experimental device, and a TDLAS measurement device. The invention uses the TDLAS device to measure parameters such as combustion chamber temperature, composition, and pressure to achieve real-time visualization of the flame tube flow field parameters. The patent focuses on the visualization of the steady-state combustion process of the axial section of the combustion chamber, and cannot achieve the visualization of the annular ignition and cross-flame process.

[0005] The Chinese invention patent application with publication number CN215411978U discloses a visualized three-head combustion chamber structure with adjustable main combustion holes and mixing holes. It includes an intake casing, a flame tube body and an exhaust casing connected in sequence; the head spacing ratio is changed by installing a removable swirler head mounting plate and a removable main combustion hole plate on the combustion chamber body. Due to its physical structure, the patented visual combustion chamber can only observe the three-head ignition and flame process, which has certain limitations and cannot realize the visualization study of the full-ring ignition and flame process.

[0006] Unlike the combustion chamber of a large aircraft engine, the combustion chamber of a micro turbojet engine generally adopts an evaporator tube annular combustion chamber structure, and the ignition position generally occurs at the outlet of the evaporator tube. Therefore, the existence of the evaporator tube will affect the visualization of the entire annular combustion chamber. At the same time, a certain amount of air needs to enter the evaporator tube to mix with the fuel, which is different from the axial intake of air / fuel in the same direction of large aircraft engines. The reverse intake mechanism will also increase the difficulty of designing a visible combustion chamber. Summary of the invention

[0007] In view of this, the present application aims to propose a visualized turbojet engine annular combustion chamber experimental system for studying the ignition and combined flame process, so as to solve at least one of the above problems.

[0008] To achieve the above purpose, the technical solution of this application is implemented as follows: The present application provides a visualized turbojet engine annular combustion chamber experimental system for studying the ignition and combined flame process, comprising a high-speed camera, a visible combustion chamber, a fuel supply system, an air intake system, and a smoke exhaust device; The visual combustion chamber is placed on an optical platform, and is used to provide a visual process of the evaporation, atomization, coupling and ignition of liquid fuel in the evaporation tube; The fuel supply system and the air intake system are both connected to the visible combustion chamber, the fuel supply system is used to supply fuel to the visible combustion chamber, and the air intake system is used to control the gas entering the visible combustion chamber; The smoke exhaust device is arranged above the visible combustion chamber and is used for exhausting smoke after the visible combustion chamber is ignited; The high-speed camera is used to observe the ignition and cross-flame effect of the visible combustion chamber.

[0009] Furthermore, the visible combustion chamber includes a fixed base, a first transparent cover, a second transparent cover, an evaporation tube, an oil injection mechanism, an ignition mechanism and an air intake mechanism; The first transparent cover shell and the second transparent cover shell are both mounted on the fixed base, and the second transparent cover shell is located outside the first transparent cover shell, and a combustion space is reserved between the first transparent cover shell and the second transparent cover shell; The air intake mechanism is arranged on the fixed base through a connecting piece, and is pressed and fixed to the top of the second transparent cover shell. The evaporation tube is arranged at the bottom of the air intake mechanism and is located in the combustion space. The air intake mechanism is connected to the air intake system and is used to provide compressed air to the evaporation tube. The fuel injection mechanism is arranged on the air intake mechanism, and one end of the fuel injection mechanism is connected to the fuel supply system, and the other end extends into the evaporation tube. The ignition mechanism is arranged at the bottom of the fixed base and is used for igniting the outlet of the evaporation tube.

[0010] Furthermore, a first slot and a second slot are formed on the upper end surface of the fixed base, the first slot and the second slot are concentrically arranged, and the first transparent cover shell and the second transparent cover shell are correspondingly plugged into the first slot and the second slot.

[0011] Further, the air intake mechanism includes a pressing plate and an end cover arranged on the pressing plate; The lower end surface of the pressing plate is provided with an inner groove for fixing the second transparent cover shell, and the pressing plate is provided with a plurality of through holes arranged in an annular manner, and the plurality of evaporation tubes are correspondingly installed in the through holes; The centers of the pressing plate and the end cover are both provided with openings, the upper end surface of the pressing plate is provided with a third slot around the opening, the end cover is inserted into the third slot, and is fixedly connected to the pressing plate by a fastener; The pressure plate cooperates with the end cover to form an air intake ring cavity, and an air inlet connected to the air intake ring cavity is circumferentially arranged on the end cover. Compressed air enters the air intake ring cavity through the air inlet, and the formed airflow flows in the air intake ring cavity and enters the evaporation tube.

[0012] Furthermore, the pressure plate is provided with a plurality of fastening holes, the inner wall of the end cover is provided with a convex edge, the convex edge is provided with connecting holes corresponding to the fastening holes, and the end cover is fixedly connected to the pressure plate by fastening screws.

[0013] Furthermore, a plurality of mounting holes are formed on the pressing plate in a circumferential direction, and the evaporating tube is fixed in the mounting holes by adhesive; The fuel injection mechanism includes a fuel injection pipe, a fuel inlet pipe connected to the fuel injection pipe, and a plurality of fuel injection needles. The fuel injection pipe is fixed in position by a support bracket arranged on the end cover. The fuel inlet pipe is connected to the fuel supply system. A through hole corresponding to the mounting hole is opened on the end cover. The fuel injection needle passes through the through hole and the mounting hole and extends into the evaporator tube.

[0014] Furthermore, a plurality of adjustment holes are provided on the edge of the end cover, the support bracket includes a support rod and a support plate arranged on the top of the support rod, the bottom of the support rod is provided with an external thread, the support rod is threadedly connected to the adjustment hole, and the support plate is used to support the fuel injection pipe.

[0015] Furthermore, the fixed base is fixedly connected to the end cover via a plurality of support studs provided thereon.

[0016] Furthermore, a built-in groove is provided at the bottom of the fixed base, and two groups of fixing holes communicating with the combustion space are provided on the top wall of the built-in groove; The ignition mechanism includes two ignition electrodes, the two ignition motors are correspondingly installed in the two groups of fixing holes, and the two ignition electrodes are located on both sides of one of the evaporation tubes to ignite the outlet of the central evaporation tube; The side wall of the built-in groove is also reserved with an inner hole for the connecting wires of the two groups of ignition electrodes and the ignition oil path to pass through.

[0017] Furthermore, the ignition electrode is a ceramic silicon nitride ignition electrode.

[0018] Compared with the prior art, the visualized turbojet engine annular combustion chamber experimental system for ignition and combined flame process research described in this application has the following beneficial effects: The present application describes a visualized turbojet engine annular combustion chamber experimental system for studying the ignition and coupled flame process. The system has a visualized design for the process of evaporation, atomization and coupled ignition operation of liquid fuel in the evaporator tube. The structure can realize the visualization of the evaporation of fuel flow in the evaporator tube before ignition, thereby achieving the visualization of ignition and coupled flame under non-premixed conditions, laying the foundation for subsequent experimental research on different types of visualized combustion chambers. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The drawings constituting a part of the present application are used to provide a further understanding of the present application. The illustrative embodiments and descriptions of the present application are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings: Figure 1 A schematic diagram of a visualized turbojet engine annular combustion chamber experimental system for studying the ignition and combined flame process described in an embodiment of the present application; Figure 2 This is a schematic diagram of the overall first angle structure of the ignition combustion chamber described in an embodiment of the present application; Figure 3 This is a second angle structural schematic diagram of the overall ignition combustion chamber according to an embodiment of the present application; Figure 4 This is a schematic diagram of the overall structure of the ignition combustion chamber according to the embodiment of the present application from a third angle; Figure 5 This is a cross-sectional view of the ignition combustion chamber described in the embodiment of the present application; Figure 6 This is a schematic diagram of the detailed structure of the ignition combustion chamber described in the embodiment of the present application; Figure 7 This is a schematic diagram of the fixed base structure described in an embodiment of the present application; Figure 8 This is a schematic diagram of the end cover structure described in an embodiment of the present application; Fig. 9 This is a schematic diagram of the support bracket structure described in an embodiment of the present application.

[0020] Description of reference numerals: 1-fixed base; 11-first slot; 12-second slot; 13-built-in groove; 14-fixing hole; 15-inner hole; 2-first transparent cover; 3-second transparent cover; 4-evaporator; 5-intake mechanism; 51-pressing plate; 52-end cover; 53-third slot; 54-intake ring cavity; 55-intake port; 56-fastening hole; 57-convex edge; 58-connecting hole; 59-mounting hole; 510-through hole; 511-adjusting hole; 6-injection mechanism; 61-injection pipe; 62-inlet pipe; 63-injection needle; 7-support bracket; 71-support support rod; 72-support plate; 8-support stud. DETAILED DESCRIPTION

[0021] In order to make the objectives, technical solutions and advantages of the present application more clearly understood, the present application is further described in detail below in combination with specific embodiments and with reference to the accompanying drawings.

[0022] It should be noted that, unless otherwise defined, the technical terms or scientific terms used in the embodiments of the present application should have the usual meanings understood by people with ordinary skills in the field to which the present application belongs. The words "first", "second" and similar words used in the embodiments of the present application do not indicate any order, quantity or importance, but are only used to distinguish different components. "Include" or "comprises" and other similar words mean that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, without excluding other elements or objects. "Connect" or "connected" and other similar words are not limited to physical or mechanical connections, but can be Including electrical connections, whether direct or indirect. "Up", "down", "left", "right", etc. are only used to indicate relative position relationships. When the absolute position of the object being described changes, the relative position relationship may also change accordingly.

[0023] See also Figure 1 As shown, this embodiment provides a visualized turbojet engine annular combustion chamber experimental system for studying the ignition and combined flame process, including a high-speed camera, a visible combustion chamber, a fuel supply system, an air intake system, and a smoke exhaust device; The visual combustion chamber is placed on the optical platform, and is used to provide visualization of the evaporation, atomization, coupled ignition operation process of the liquid fuel in the evaporation tube 4; The fuel supply system and the air intake system are both connected to the visible combustion chamber, the fuel supply system is used to supply fuel to the visible combustion chamber, and the air intake system is used to control the gas entering the visible combustion chamber; The smoke exhaust device is arranged above the visible combustion chamber and is used to discharge smoke after the visible combustion chamber is ignited; High-speed cameras are used to observe the ignition and cross-flame effects in the visible combustion chamber.

[0024] Specifically, in this embodiment, the experimental system includes a high-speed camera, a visible combustion chamber, a fuel supply system, an air intake system and a smoke exhaust device. The height and angle of the high-speed camera are adjustable to achieve the optimal ignition and flame observation effect. The fuel supply system adopts a compressed air extrusion fuel supply method, and is externally connected to a Coriolis fuel flow meter and a control solenoid valve to monitor and control the fuel flow. The air intake system is provided with a pressure-stabilizing tank, and an air flow meter is connected to the outlet of the pressure-stabilizing tank to meet the intake flow monitoring and control requirements. A smoke exhaust device is provided above the visible combustion chamber to ensure that smoke is discharged after ignition is completed.

[0025] The visualized turbojet engine annular combustion chamber experimental system for the study of the ignition and coupled flame process described in this embodiment has been designed to visualize the process of evaporation, atomization and coupled ignition operation of the liquid fuel in the evaporator tube 4. The structure can realize the visualization of the evaporation of the fuel flow in the evaporator tube 4 before ignition, thereby achieving the visualization of the ignition and coupled flame under non-premixed conditions, laying the foundation for subsequent experimental research on different types of visualized combustion chambers.

[0026] In some embodiments, the visible combustion chamber includes a fixed base 1, a first transparent cover shell 2, a second transparent cover shell 3, an evaporation tube 4, an oil injection mechanism 6, an ignition mechanism and an air intake mechanism 5; The first transparent cover shell 2 and the second transparent cover shell 3 are both mounted on the fixed base 1, and the second transparent cover shell 3 is located outside the first transparent cover shell 2, and a combustion space is reserved between the first transparent cover shell 2 and the second transparent cover shell 3; The air intake mechanism 5 is arranged on the fixed base 1 through a connecting piece, and is pressed and fixed to the top of the second transparent cover shell 3. The evaporation tube 4 is arranged at the bottom of the air intake mechanism 5 and is located in the combustion space. The air intake mechanism 5 is connected to the air intake system to provide compressed air to the evaporation tube 4. The fuel injection mechanism 6 is arranged on the air intake mechanism 5. One end of the fuel injection mechanism 6 is connected to the fuel supply system, and the other end extends into the evaporation tube 4. The ignition mechanism is arranged at the bottom of the fixed base 1 and is used to ignite the outlet of the evaporation tube 4 .

[0027] Specifically, in this embodiment, a visual design is performed based on a prototype of a micro turbojet engine combustion chamber. Figures 2 to 4 As shown, a complete visualized turbojet engine annular combustion chamber is assembled by a fixed base 1, a first transparent cover shell 2, a second transparent cover shell 3, an evaporator tube 4, a fuel injection mechanism 6, an ignition mechanism and an air intake mechanism 5, which can explore the ignition and flame-linking process of the evaporator tube 4-type annular combustion chamber.

[0028] Furthermore, by passing compressed air into the intake annular cavity 54, the air in the annular cavity continuously enters the evaporator tube 4, simulating the intake process of the evaporator tube 4 of the prototype micro-turbojet engine; at the same time, the fuel is supplied by the fuel co-supply system, and the fuel and the incoming compressed air are atomized, evaporated and mixed in the evaporator tube 4, and the evaporated and mixed oil mist is ignited at the outlet of the evaporator tube 4; the ignition process uses an ignition mechanism installed at the bottom of the fixed base 1 to ignite the evaporator tube 4, and then the ignition and flame-linking process of the entire annular combustion chamber can be observed through the transparent cover.

[0029] It should be noted that the first transparent cover shell 2 and the second transparent cover shell 3 in this embodiment are both transparent shells made of quartz glass, so as to facilitate the visualization of the ignition flame of the combustion chamber.

[0030] In some embodiments, Figure 5 and Figure 7 As shown, the upper end surface of the fixed base 1 is provided with a first slot 11 and a second slot 12, the first slot 11 and the second slot 12 are concentrically arranged, and the first transparent cover shell 2 and the second transparent cover shell 3 are correspondingly inserted into the first slot 11 and the second slot 12; The fixed base 1 is fixedly connected to the end cover 52 of the air intake mechanism 5 via a plurality of support studs 8 provided thereon.

[0031] Specifically, in this embodiment, Figure 5 As shown, two transparent covers made of quartz glass are respectively inserted into the slots of the fixed base 1, and the second transparent cover 3 located on the outside is subsequently pressed and fixed by the pressing plate 51, and the first transparent cover 2 located on the inside is inserted into the slot. The fixing of the whole device is as shown in FIG. Figures 2 to 4 As shown, four studs are used to press the end cover 52 and the fixed base 1 together, and at the same time, the second transparent cover shell 3 is further fixed.

[0032] In some embodiments, Figure 6 and Figure 8 As shown, the air intake mechanism 5 includes a pressing plate 51 and an end cover 52 disposed on the pressing plate 51; The lower end surface of the pressing plate 51 is provided with an inner groove for fixing the second transparent cover shell 3, and a plurality of through holes are arranged in an annular shape on the pressing plate 51, and a plurality of evaporation tubes 4 are correspondingly installed in the through holes; The center of the pressing plate 51 and the end cover 52 are both provided with an opening, and a third slot 53 is provided around the opening on the upper end surface of the pressing plate 51, and a plug-in portion is provided downward at the opening position of the end cover 52, which is correspondingly plugged into the third slot 53 and fixedly connected to the pressing plate 51 by fasteners; The pressure plate 51 cooperates with the end cover 52 to form an air intake annular cavity 54, and an air intake port 55 connected to the air intake annular cavity 54 is provided on the circumference of the end cover 52. Compressed air enters the air intake annular cavity 54 through the air intake port 55, and the formed air flow flows in the air intake annular cavity 54 and enters the evaporation tube 4; The pressing plate 51 is provided with a plurality of fastening holes 56 , the inner wall of the end cover 52 is provided with a convex edge 57 , the convex edge 57 is provided with connecting holes 58 corresponding to the fastening holes 56 , and the end cover 52 is fixedly connected to the pressing plate 51 by fastening screws.

[0033] Specifically, in this embodiment, Figure 5 As shown, the pressure plate 51 and the end cover 52 are fixed by fastening screws, and an intake ring cavity 54 is formed inside the two. Compressed air is connected to four intake ducts to allow air to enter the intake ring cavity 54, so that the airflow flows in the ring cavity and enters the evaporator tube 4, thereby ensuring the air intake demand inside the combustion chamber.

[0034] In some embodiments, a plurality of mounting holes 59 are formed on the pressing plate 51 in a circumferential direction, and the evaporation tube 4 is fixed in the mounting holes 59 by adhesive. The fuel injection mechanism 6 includes a fuel injection pipe 61, a fuel inlet pipe 62 connected to the fuel injection pipe 61, and a plurality of fuel injection needles 63. The fuel injection pipe 61 is fixed in position by a support bracket 7 arranged on the end cover 52. The fuel inlet pipe 62 is connected to the fuel supply system. A through hole 510 corresponding to the mounting hole 59 is opened on the end cover 52. The fuel injection needle 63 passes through the through hole 510 and the mounting hole 59 and extends into the evaporator tube 4. The edge of the end cover 52 is provided with a plurality of adjustment holes 511. Fig. 9 As shown, the support bracket 7 includes a support rod 71 and a support plate 72 arranged on the top of the support rod 71. The bottom of the support rod 71 is provided with an external thread. The support rod 71 is threadedly connected to the adjustment hole 511. The support plate 72 is used to support the fuel injection pipe 61.

[0035] Specifically, in this embodiment, Figure 6 As shown, AB glue is used to fix the evaporator tube 4 in the mounting hole 59 of the pressure plate 51. The fuel injection pipe 61 is arranged in a ring shape, and the fuel injection needle 63 arranged thereunder passes through the pressure plate 51 into the combustion space. The fuel enters the fuel injection pipe 61 from the fuel inlet pipe 62, and flows into different fuel injection needles 63 through the fuel injection pipe 61, thereby delivering the fuel to the evaporator tube 4.

[0036] In addition, the fuel injection pipe 61 uses a support bracket 7 with adjustable height to hold up the fuel injection ring, wherein the support rod 71 is connected to the end cover 52 by threads, and the subsequent test process can adjust the distance that the fuel injection ring penetrates into the evaporation tube 4.

[0037] In some embodiments, Figure 4 and Figure 7As shown, a built-in groove 13 is provided at the bottom of the fixed base 1, and two sets of fixing holes 14 communicating with the combustion space are provided on the top wall of the built-in groove 13; The ignition mechanism includes two ignition electrodes, which are ceramic silicon nitride ignition electrodes. Two ignition motors are correspondingly installed in two groups of fixing holes 14. The two ignition electrodes are located on both sides of one of the evaporation tubes 4 to ignite the outlet of the central evaporation tube 4. The side wall of the built-in groove 13 is also reserved with an inner hole 15 for the connecting wires of the two sets of ignition electrodes and the ignition oil circuit to pass through.

[0038] Specifically, in this embodiment, the ignition electrode adopts a ceramic silicon nitride ignition electrode specially used for micro-aircraft engines (the ignition electrode is not shown in the attached figure), and the outlet of the central evaporator tube 4 is ignited through two ignition electrodes to meet the ignition requirements of the visible annular combustion chamber; the tail of the ignition electrode passes through the side of the fixed base 1, and the connection position of the ignition oil circuit is also on the side of the base.

[0039] The present application can realize the disassembly and adjustment of each mechanism, and meet the experimental research of the ignition process of the evaporator tube 4-type annular combustion chamber under different types of structural parameters and boundary conditions.

[0040] The working principle of the ignition combustion chamber is as follows: First, the compressed air is introduced into the air inlet annular cavity 54, so that the airflow flows in the annular cavity and enters the evaporation tube 4 (such as Figure 2 As shown in FIG. 1 ), the intake air demand inside the combustion chamber is ensured. At the same time, the fuel enters from the fuel inlet pipe 62 and flows into different fuel injection needles 63 (as shown in FIG. 1 ) through the fuel injection pipe 61. Figure 6 As shown); To ensure the ignition requirement, two ignition electrodes are set at the base part, and the ignition work at the ignition rod position is completed by supplying oil to the ignition oil circuit and powering the ignition electrodes. Finally, under the joint action of the oil, gas and ignition electrodes of each evaporation tube 4, the joint flame process of the entire annular combustion chamber is completed.

[0041] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein by equivalents. These modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the present invention, and they should all be included in the scope of the claims and specification of the present invention.

[0042] The embodiments of the present application are intended to cover all such substitutions, modifications and variations that fall within the broad scope of the appended claims. Therefore, any omissions, modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the embodiments of the present application should be included in the scope of protection of the present application.

Claims

1. A visualized turbojet engine annular combustion chamber experimental system for ignition and combined flame process research, characterized by: Includes high-speed cameras, visual combustion chamber, fuel supply system, air intake system, and smoke exhaust device; The visual combustion chamber is placed on an optical platform, and is used to provide a visual process of the evaporation, atomization, coupling and ignition of liquid fuel in the evaporation tube; The fuel supply system and the air intake system are both connected to the visible combustion chamber, the fuel supply system is used to supply fuel to the visible combustion chamber, and the air intake system is used to control the gas entering the visible combustion chamber; The smoke exhaust device is arranged above the visible combustion chamber and is used for exhausting smoke after the visible combustion chamber is ignited; The high-speed camera is used to observe the ignition and cross-flame effect of the visible combustion chamber.

2. The system according to claim 1, characterized in that: The visible combustion chamber comprises a fixed base, a first transparent cover shell, a second transparent cover shell, an evaporation tube, an oil injection mechanism, an ignition mechanism and an air intake mechanism; The first transparent cover shell and the second transparent cover shell are both mounted on the fixed base, and the second transparent cover shell is located outside the first transparent cover shell, and a combustion space is reserved between the first transparent cover shell and the second transparent cover shell; The air intake mechanism is arranged on the fixed base through a connecting piece, and is pressed and fixed to the top of the second transparent cover shell. The evaporation tube is arranged at the bottom of the air intake mechanism and is located in the combustion space. The air intake mechanism is connected to the air intake system and is used to provide compressed air to the evaporation tube. The fuel injection mechanism is arranged on the air intake mechanism, and one end of the fuel injection mechanism is connected to the fuel supply system, and the other end extends into the evaporation tube. The ignition mechanism is arranged at the bottom of the fixed base and is used for igniting the outlet of the evaporation tube.

3. The system according to claim 2, characterized in that: The upper end surface of the fixed base is provided with a first slot and a second slot, the first slot and the second slot are concentrically arranged, and the first transparent cover shell and the second transparent cover shell are correspondingly plugged into the first slot and the second slot.

4. The system according to claim 2, characterized in that: The air intake mechanism comprises a pressing plate and an end cover arranged on the pressing plate; The lower end surface of the pressing plate is provided with an inner groove for fixing the second transparent cover shell, and the pressing plate is provided with a plurality of through holes arranged in an annular manner, and the plurality of evaporation tubes are correspondingly installed in the through holes; The centers of the pressing plate and the end cover are both provided with openings, the upper end surface of the pressing plate is provided with a third slot around the opening, the end cover is inserted into the third slot, and is fixedly connected to the pressing plate by a fastener; The pressure plate cooperates with the end cover to form an air intake ring cavity, and an air inlet connected to the air intake ring cavity is circumferentially arranged on the end cover. Compressed air enters the air intake ring cavity through the air inlet, and the formed airflow flows in the air intake ring cavity and enters the evaporation tube.

5. The system according to claim 4, characterized in that: The pressure plate is provided with a plurality of fastening holes, the inner wall of the end cover is provided with a convex edge, the convex edge is provided with connecting holes corresponding to the fastening holes, and the end cover is fixedly connected to the pressure plate by fastening screws.

6. The system according to claim 4, characterized in that: The pressing plate is provided with a plurality of mounting holes on its circumference, and the evaporating tube is fixed in the mounting holes by adhesive; The fuel injection mechanism includes a fuel injection pipe, a fuel inlet pipe connected to the fuel injection pipe, and a plurality of fuel injection needles. The fuel injection pipe is fixed in position by a support bracket arranged on the end cover. The fuel inlet pipe is connected to the fuel supply system. A through hole corresponding to the mounting hole is opened on the end cover. The fuel injection needle passes through the through hole and the mounting hole and extends into the evaporator tube.

7. The system according to claim 6, characterized in that: The edge of the end cover is provided with a plurality of adjustment holes, the support bracket includes a support rod and a support plate arranged on the top of the support rod, the bottom of the support rod is provided with an external thread, the support rod is threadedly connected to the adjustment hole, and the support plate is used to support the fuel injection pipe.

8. The system according to claim 4, characterized in that: The fixed base is fixedly connected to the end cover via a plurality of support studs arranged thereon.

9. The system according to claim 2, characterized in that: The bottom of the fixed base is provided with a built-in groove, and the top wall of the built-in groove is provided with two groups of fixing holes connected with the combustion space; The ignition mechanism includes two ignition electrodes, the two ignition motors are correspondingly installed in the two groups of fixing holes, and the two ignition electrodes are located on both sides of one of the evaporation tubes to ignite the outlet of the central evaporation tube; The side wall of the built-in groove is also reserved with an inner hole for the connecting wires of the two groups of ignition electrodes and the ignition oil path to pass through.

10. The system according to claim 9, characterized in that: The ignition electrode is a ceramic silicon nitride ignition electrode.

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