jet propulsion unit

Abstract

This invention relates to the technical field of power devices and discloses a jet power device, including a cylindrical body with a cavity, a main shaft in the cavity, a compressor and a turbine connected to the main shaft to form a rotor; a diffuser, a guide vane and a burner rotatably connected to the main shaft to form a stator; a tail cone fitted with a tail nozzle to form a tail nozzle channel; air is compressed into high-pressure gas by the compressor, and the high-pressure gas enters the combustion chamber through the diffuser; fuel is atomized into fuel gas through an evaporator, and the atomized fuel gas mixes with the high-pressure gas in the combustion chamber to form an oil-gas mixture, which burns in the combustion chamber to form high-pressure fuel gas, which drives the turbine to rotate after passing through the guide vane, and the fuel gas passing through the turbine is ejected at high pressure from the tail nozzle channel to generate forward thrust. The turbine's work drives the compressor to rotate through the main shaft, and continues to compress air into the air inlet, forming a compression-expansion cycle, which maintains stable operation on its own.

Description

Technical Field

[0001] This invention relates to the technical field of power devices, and more specifically, to jet power devices. Background Technology

[0002] Currently, drones, target drones, and loitering munitions are becoming increasingly widespread, and there are various types of power devices that drive drones, target drones, and loitering munitions to fly. At present, there are some jet-powered devices on the market that simulate jet propulsion and are used to drive drones to fly.

[0003] In the prior art, jet propulsion devices utilize the mixing of gas and fuel gas to form an oil-gas mixture, and use the combustion of the oil-gas mixture to eject high-pressure gas for propulsion. However, these jet propulsion devices suffer from low combustion efficiency and low driving efficiency. Summary of the Invention

[0004] The purpose of this invention is to provide a jet propulsion device that addresses the problem of low driving efficiency in existing jet propulsion devices.

[0005] The present invention is implemented as follows: a jet propulsion device includes a cylinder, the cylinder having a cavity, the cavity extending through the front end of the cylinder to form an air inlet, the cavity extending through the rear end of the cylinder to form an exhaust outlet; along the direction from the air inlet to the exhaust outlet, the cavity sequentially includes an air intake section, a combustion section and an exhaust section. The cylinder cavity is provided with a rotating main shaft, which extends from the intake section to the exhaust section and passes through the combustion section; a compressor and a diffuser are connected to the intake section, and the compressor has multiple compressor blades. The combustion section is equipped with a burner, which is fixedly connected to the combustion section. The burner has a ring-shaped combustion chamber, and the combustion chamber is equipped with multiple evaporation pipes that are connected to oil pipes. The multiple evaporation pipes are arranged around the circumference of the combustion chamber at intervals. The exhaust section is provided with a guide and a turbine. The guide is fixedly connected to the exhaust section. The guide has multiple guide blades and there is a guide interval between adjacent guide blades. The turbine has multiple turbine blades. The exhaust port has a tail cone in the middle. The diameter of the tail cone gradually decreases along the direction away from the exhaust port. The tail nozzle is fitted around the outer periphery of the tail cone and is connected to the cylinder. The tail cone and the tail nozzle extend outward away from the exhaust port, and the tail nozzle and the tail cone form an annular tail nozzle channel. After the main shaft drives the compressor to rotate, air enters the intake section through the intake port and is compressed by the rotating compressor blades to form high-pressure gas. The high-pressure gas is decelerated and guided by the diffuser and enters the combustion chamber. The fuel pipe discharges fuel into the evaporator tube, where it is heated and vaporized to form atomized gas. The atomized gas mixes with the high-pressure gas in the combustion chamber to form an oil-gas mixture. The oil-gas mixture burns in the combustion chamber to form high-pressure gas. The high-pressure gas passes through the guide gap and impacts the turbine blades to rotate. The turbine drives the main shaft to rotate in the opposite direction, so that the compressor continues to rotate and air continues to enter the intake section through the intake port. The high-pressure gas passing through the turbine is ejected at high pressure from the tail nozzle through the exhaust port to generate forward thrust. The evaporator tube has an evaporation chamber inside, and the end of the evaporation chamber is arranged in an open manner to form an outlet for the atomized gas to be discharged; the oil pipe has an end that passes through the evaporation chamber and is located in the evaporation chamber. The oil injection section sprays fuel onto the inner wall of the evaporation chamber. The fuel is heated and evaporated at high temperature to form the atomized gas. The atomized gas enters the combustion chamber through the outlet.

[0006] Furthermore, the air inlet is covered with a dustproof mesh to filter the air passing through it.

[0007] Furthermore, the air inlet is provided with a bracket, the bracket is provided with a base, and the base is provided with a starter. The starter is connected to the main shaft through a clutch, and the starter drives the main shaft from a stationary state to a rotating state.

[0008] Furthermore, there is a compressor gap between adjacent compressor blades, and the end of the compressor gap forms a compressor outlet; the diffuser is plate-shaped and arranged at the end of the compressor, and the diffuser is provided with multiple diffusion channels communicating with the combustion chamber, and the multiple diffusion channels are respectively connected to multiple compressor outlets; the high-pressure gas discharged from the compressor outlet enters the diffusion channel and is decelerated and guided by the diffusion channel into the combustion chamber.

[0009] Furthermore, the diffusion channel is arranged at an angle relative to the radial direction of the diffuser, and the diameter of the diffusion channel gradually increases along the flow direction of the high-pressure gas in the diffusion channel.

[0010] Furthermore, the evaporation chamber is provided with a rotating cylinder that rotates relative to the evaporation tube. The fuel injection section is placed in the rotating cylinder. The fuel injection section sprays fuel in the rotating cylinder. The fuel drives the rotating cylinder to rotate. The fuel passes through the rotating cylinder and enters the evaporation chamber in a centrifugal rotation, spraying onto the inner wall of the evaporation chamber. The rotating cylinder has a rotating cavity, the oil injection section extends into the rotating cavity, the end of the rotating cylinder is closed, and the outer periphery of the rotating cylinder is provided with a plurality of peripheral holes; the end of the oil injection section is bent and faces the inner wall of the rotating cavity. The fuel injected from the injection section impacts the inner side of the rotating cylinder, driving the rotating cylinder to rotate. The fuel in the rotating chamber rotates centrifugally and is sprayed into the evaporation chamber through multiple peripheral holes, and onto the inner wall of the evaporation chamber.

[0011] Furthermore, a plurality of curved pieces are protruding on the inner wall of the rotating cavity. The curved pieces are arranged to bend along the circumference of the rotating cavity, and the plurality of curved pieces are arranged at intervals along the circumference of the rotating cavity. The outer peripheral hole is formed between adjacent curved pieces. The end of the fuel injection section is bent to form multiple bent sections, which are arranged toward the bending plate. The fuel injected from the bent sections impacts the bending plate to drive the rotating cylinder to rotate.

[0012] Furthermore, the air outlet is covered with two fixed metal mesh layers, which are spaced apart to form a flat fixed cavity; the fixed cavity is provided with a movable metal mesh layer, and the atomized gas sprayed from the air outlet passes through the fixed metal mesh layer and the movable metal mesh layer, and the movable metal mesh layer is impacted and swings back and forth to disperse the atomized gas.

[0013] Furthermore, the outer periphery of the tail cone is provided with a plurality of external elastic plates, the front end of the external elastic plates is fixedly arranged, the middle part of the external elastic plates is arched and bent away from the tail cone, and the rear end of the external elastic plates extends backward to form an external movable end that movably abuts against the tail cone. The inner wall of the tail nozzle is provided with a plurality of inner elastic plates. The front end of the inner elastic plate is fixedly arranged, the middle part of the inner elastic plate is arched and bent away from the tail nozzle, and the rear end of the inner elastic plate extends backward to form an inner movable end that movably abuts against the tail nozzle. Multiple outer elastic plates are arranged at intervals around the tail cone in the circumferential direction, and multiple inner elastic plates are arranged at intervals around the tail nozzle in the circumferential direction. The inner elastic plates and outer elastic plates are staggered in the circumferential direction of the tail nozzle.

[0014] Furthermore, the arch height of the inner elastic sheet is greater than that of the outer elastic sheet, and the outer elastic sheet has a front end section facing the exhaust port. The front end section is provided with a guide groove, which extends along the length of the front end section.

[0015] Compared with the prior art, the jet propulsion device provided by the present invention forms an oil-gas mixture by mixing atomized gas with high-pressure gas, and the oil-gas mixture is burned to form high-pressure gas. The high-pressure gas is ejected at high speed from the tail nozzle to generate forward thrust and achieve driving effect. It has a simple structure and high driving efficiency. Secondly, the high-pressure gas drives the turbine to rotate, the turbine drives the main shaft to rotate in the opposite direction, and the main shaft drives the compressor to rotate, so that air continuously enters the compressor from the air inlet to achieve continuous operation and continuously generate forward thrust. Attached Figure Description

[0016] Figure 1 This is a three-dimensional schematic diagram of the jet propulsion device provided by the present invention; Figure 2 This is a three-dimensional schematic diagram of the jet propulsion device provided by the present invention; Figure 3 This is a partial three-dimensional schematic diagram of the jet propulsion device provided by the present invention; Figure 4 This is a partial three-dimensional schematic diagram of the jet propulsion device provided by the present invention; Figure 5 This is a partial cross-sectional schematic diagram of the jet propulsion device provided by the present invention; Figure 6 This is a schematic diagram of the interior of the rotating cylinder provided by the present invention; Figure 7 This is a schematic diagram of the interior of the rotating cylinder provided by the present invention; Figure 8 This is an internal schematic diagram of the tail cone and tail nozzle assembly provided by the present invention. Detailed Implementation

[0017] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention.

[0018] The implementation of the present invention will be described in detail below with reference to specific embodiments.

[0019] In the accompanying drawings of this embodiment, the same or similar reference numerals correspond to the same or similar components. In the description of this invention, it should be understood that if terms such as "upper," "lower," "left," and "right" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, they are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, the terms used to describe positional relationships in the drawings are only for illustrative purposes and should not be construed as limiting this invention. For those skilled in the art, the specific meaning of the above terms can be understood according to the specific circumstances.

[0020] Reference Figure 1-8 The image shows a preferred embodiment of the present invention.

[0021] The jet propulsion device is suitable for drones, target drones, loitering munitions, radio-controlled aircraft, etc. It includes a cylinder 100, which has a cavity. The cavity extends through the front end of the cylinder 100 to form an air inlet, and extends through the rear end of the cylinder 100 to form an exhaust outlet. Along the direction from the air inlet to the exhaust outlet, the cavity sequentially includes an air inlet section 104, a combustion section 105, and an exhaust section 106. That is to say, the cavity is arranged in a front-to-back through manner.

[0022] The cylinder cavity is provided with a rotating main shaft 204, which extends from the intake section 104 to the exhaust section 106 and passes through the combustion section 105; the intake section 104 is connected to a compressor 300 and a diffuser 400, and the compressor 300 has multiple compressor blades 301.

[0023] The combustion section 105 is equipped with a burner 500, which is fixedly connected to the combustion section 105. The burner 500 has a combustion chamber 502 arranged in a ring. The combustion chamber 502 is equipped with multiple evaporation pipes 501 that are connected to the oil pipe. The multiple evaporation pipes 501 are arranged around the circumference of the combustion chamber 502 at intervals.

[0024] The exhaust section 106 is provided with a guide 600 and a turbine 700. The guide 600 is fixedly connected to the exhaust section 106. The guide 600 has multiple guide blades and there is a guide interval between adjacent guide blades. The turbine 700 has multiple turbine blades 701.

[0025] A tail cone 102 is provided in the middle of the exhaust port. The diameter of the tail cone 102 gradually decreases along the direction away from the exhaust port. A tail nozzle 101 is fitted around the outer periphery of the tail cone 102. The tail nozzle 101 is connected to the cylinder 100. The tail cone 102 and the tail nozzle 101 are respectively arranged to extend outward away from the exhaust port. The tail nozzle 101 and the tail cone 102 enclose each other to form an annular tail nozzle channel 103. After the main shaft 204 drives the compressor 300 to rotate, air enters the intake section 104 through the intake port. It is compressed by the rotation of the compressor blades 301 to form high-pressure gas. The high-pressure gas is decelerated and guided by the diffuser 400 and enters the combustion chamber 502. The fuel pipe discharges fuel to the evaporator pipe 501, where it is heated and vaporized to form atomized gas. The atomized gas and the high-pressure gas mix in the combustion chamber 502 to form an oil-gas mixture. The oil-gas mixture burns in the combustion chamber 502 to form high-pressure gas. The high-pressure gas passes through the guide gap and impacts the turbine blades 701 to rotate. The turbine 700 drives the main shaft 204 to rotate in the opposite direction, so that the compressor 300 rotates continuously, and air continuously enters the intake section 104 through the intake port.

[0026] The high-pressure gas passing through the turbine 700 is ejected at high pressure through the exhaust port and the tailpipe 103 to generate forward thrust.

[0027] The evaporator pipe 501 has an evaporation chamber 503 inside, and the end of the evaporation chamber 503 is arranged in an open manner to form an outlet for the atomized gas to be discharged; the oil pipe has an injection section 508 that passes through the end of the evaporation chamber 503 and is located in the evaporation chamber 503. The injection section 508 sprays fuel onto the inner wall of the evaporation chamber 503. The fuel is heated and evaporated at high temperature to form atomized gas. The atomized gas enters the combustion chamber 502 through the outlet.

[0028] The jet propulsion device provided above mixes atomized gas with high-pressure gas to form an oil-gas mixture, which is then burned to form high-pressure gas. The high-pressure gas is ejected at high speed from the tail nozzle 103 to generate forward thrust and achieve driving effect. It has a simple structure and high driving efficiency. Secondly, the high-pressure gas drives the turbine 700 to rotate, and the turbine 700 drives the main shaft 204 to rotate in the reverse direction. The main shaft 204 drives the compressor 300 to rotate, so that air continuously enters the compressor 300 from the air inlet to achieve continuous working state and continuously generate forward thrust.

[0029] The compressor 300 and turbine 700 are connected to the main shaft 204 and rotate synchronously with the main shaft 204, forming the rotor of the jet propulsion unit. The main shaft 204 is connected to bushings at both ends via bearings. The bushings are connected to the diffuser 400 and the guide vane 600, respectively. The diffuser 400 and the guide vane 600 are connected to the combustor 500, respectively. In this way, the diffuser 400, the guide vane 600, and the combustor 500 can rotate relative to the main shaft 204. That is, when the main shaft 204 rotates, the diffuser 400, the guide vane 600, and the combustor 500 are in a fixed state, forming the stator of the jet propulsion unit.

[0030] In this embodiment, the air inlet is covered with a dustproof net 201 to filter the air passing through the air inlet, thereby ensuring the purity of the air entering the compressor 300 and improving the combustion efficiency of the oil-air mixture.

[0031] In this embodiment, a bracket 200 is provided on the air intake, a base 202 is provided on the bracket 200, and a starter 203 is provided in the base 202. The starter 203 is connected to the main shaft 204 through a clutch 205, and the starter 203 drives the main shaft 204 from a stationary state to a rotating state. The starter 203 is only used for the starting process of the jet power unit. After the jet power unit reaches a stable idling state, the starter 203 stops working.

[0032] The starter 203 is connected to the main shaft 204 via the clutch 205, thereby driving the main shaft 204 from a stationary state to a rotating state, so that the jet power unit enters the working state. When the high-pressure gas drives the turbine 700 to rotate, and the turbine 700 drives the main shaft 204 to rotate in the opposite direction, the starter 203 is disengaged from the main shaft 204.

[0033] In this embodiment, there is a compressor gap 302 between adjacent compressor blades 301, and the end of the compressor gap 302 forms a compressor outlet; the diffuser 400 is plate-shaped and arranged at the end of the compressor 300. The diffuser 400 is provided with a plurality of diffuser channels 401 that communicate with the combustion chamber 502, and the plurality of diffuser channels 401 are respectively connected to a plurality of compressor outlets; the high-pressure gas discharged from the compressor outlet enters the diffuser channel 401 and is decelerated and guided by the diffuser channel 401 into the combustion chamber 502.

[0034] During the rotation of compressor 300, air enters compressor 300 and is compressed into high-pressure gas as compressor 300 rotates. The high-pressure gas enters diffuser 401 from the compressor outlet. At this time, the high-pressure gas decelerates, converting power into pressure energy, thereby increasing the static pressure of the high-pressure gas. In other words, when the speed of the high-pressure gas decreases, its pressure increases.

[0035] In addition, the high-pressure gas can be uniformly introduced into the combustion chamber 502 by the guidance of multiple diffuser channels 401, so that the high-pressure gas and atomized gas can be mixed more evenly.

[0036] In this embodiment, the diffuser channel 401 is arranged at an angle relative to the radial direction of the diffuser 400, and the diameter of the diffuser channel 401 gradually increases along the flow direction of the high-pressure gas in the diffuser channel 401. This allows for better guidance of the high-pressure gas and further deceleration of the high-pressure gas to increase its pressure.

[0037] In this embodiment, the evaporation chamber 503 is provided with a rotating cylinder 504 that rotates relative to the evaporation tube 501. The fuel injection section 508 is placed in the rotating cylinder 504. The fuel injection section 508 injects fuel into the rotating cylinder 504. The fuel drives the rotating cylinder 504 to rotate and enters the evaporation chamber 503 in a centrifugal rotation. It is heated and vaporized by the evaporator to form atomized gas. The atomized gas enters the combustion chamber 502 through the gas outlet.

[0038] In this way, the fuel injection section 508 placed in the rotating cylinder 504 continuously drives the rotating cylinder 504 to rotate during the fuel injection process, so that the fuel in the rotating cylinder 504 enters the evaporator in a centrifugal rotation, thereby accelerating the vaporization of the fuel and making the fuel vaporization more uniform, which greatly improves the combustion efficiency of the fuel-air mixture and has high driving efficiency.

[0039] In this embodiment, the rotating cylinder 504 has a rotating cavity 506, the oil injection section 508 extends into the rotating cavity 506, the end of the rotating cylinder 504 is closed, and the outer periphery of the rotating cylinder 504 is provided with a plurality of outer peripheral holes 505; the end of the oil injection section 508 is bent and is arranged toward the inner wall of the rotating cavity 506. The fuel injected from the injection section 508 impacts the inner side of the rotating cylinder 504, driving the rotating cylinder 504 to rotate. The fuel in the rotating chamber 506 rotates centrifugally and is sprayed into the evaporation chamber 503 through multiple peripheral holes 505, and onto the inner wall of the evaporation chamber 503.

[0040] The rotating cylinder 504 is driven to rotate, and the fuel in the rotating chamber 506 rotates accordingly. Under the action of centrifugal force, the fuel enters the evaporation chamber 503 through multiple peripheral holes 505 in a centrifugal rotation, so as to achieve faster and more uniform vaporization of the fuel.

[0041] In addition, during the synchronous rotation of fuel in the rotating chamber 506, some of the fuel will be vaporized, thereby greatly improving the fuel vaporization efficiency.

[0042] In this embodiment, a plurality of curved pieces 507 are protruding on the inner sidewall of the rotating cavity 506. The curved pieces 507 are arranged to bend along the circumference of the rotating cavity 506. The plurality of curved pieces 507 are arranged at intervals along the circumference of the rotating cavity 506. The outer peripheral hole 505 is formed between adjacent curved pieces 507. The end of the fuel injection section 508 is bent to form multiple bent sections 509. The bent sections 509 are arranged toward the bending plate 507. The fuel injected from the bent sections 509 impacts the bending plate 507 to drive the rotating cylinder 504 to rotate.

[0043] By arranging multiple bending segments 507, the fuel sprayed from the bending section 509 impacts the bending segments 507, which can apply a circumferential driving force to the rotating cylinder 504, so that the rotating cylinder 504 can rotate better and continuously. In addition, arranging multiple bending segments 509 can realize multi-position drive, thereby accelerating the rotation speed of the rotating cylinder 504.

[0044] In this embodiment, a boss can be arranged in the burner 500, and one end of the rotating cylinder 504 can be rotatably connected to the boss. The way to achieve the rotatable arrangement of the rotating cylinder 504 can be diversified.

[0045] In this embodiment, the gas outlet is covered with two fixed metal mesh layers 510, which are arranged at intervals to form a flat fixed cavity 512. The fixed cavity 512 is provided with a movable metal mesh layer 511. The atomized gas sprayed from the gas outlet passes through the fixed metal mesh layer 510 and the movable metal mesh layer 511, and the movable metal mesh layer 511 is impacted and swings back and forth to disperse the atomized gas.

[0046] As the atomized gas exits the outlet, it first passes through a fixed metal mesh and enters the fixed cavity 512, where it drives the movable metal mesh to swing back and forth. It then passes through another fixed metal mesh and finally exits into the combustion chamber 502. The atomized gas is dispersed by the two fixed metal mesh layers 510 and the movable metal mesh layer 511, resulting in a more dispersed and evenly distributed atomized gas into the combustion chamber 502.

[0047] In addition, as the atomized gas passes through the outlet, it is blocked by the fixed metal mesh layer 510 and the movable metal mesh layer 511, so that it can be better heated in the evaporation chamber 503, thereby making the vaporization effect of the atomized gas better.

[0048] In this embodiment, a plurality of external elastic plates 1021 are provided on the outer periphery of the tail cone 102. The front end of the external elastic plate 1021 is fixedly arranged, the middle part of the external elastic plate 1021 is arched and bent away from the tail cone 102, and the rear end of the external elastic plate 1021 extends backward to form an external movable end that movably abuts against the tail cone 102. Multiple inner elastic plates 1011 are provided on the inner sidewall of the tail nozzle 101. The front end of the inner elastic plate 1011 is fixedly arranged. The middle part of the inner elastic plate 1011 is arched and bent away from the tail nozzle 101. The rear end of the inner elastic plate 1011 extends backward to form an inner movable end that movably abuts against the tail nozzle 101. Multiple outer elastic plates 1021 are arranged at intervals around the tail cone 102 in the circumferential direction, and multiple inner elastic plates 1011 are arranged at intervals around the tail nozzle 101 in the circumferential direction. The inner elastic plates 1011 and the outer elastic plates 1021 are staggered along the circumferential direction of the tail nozzle 103.

[0049] As the high-pressure gas passes through the tail nozzle 103, the presence of the inner elastic plate 1011 and the outer elastic plate 1021 reduces the area of ​​the tail nozzle 103, thereby causing the high-pressure gas to generate higher pressure and produce greater thrust.

[0050] Secondly, the rear ends of the inner elastic plate 1011 and the outer elastic plate 1021 are respectively arranged in a movable manner. As the high-pressure gas passes through the tail nozzle 103, it will simultaneously drive the elastic deformation of the inner elastic plate 1011 and the outer elastic plate 1021 to achieve elastic adjustment of thrust.

[0051] In addition, the inner elastic sheet 1011 and the outer elastic sheet 1021 are staggered so that the high-pressure gas can be uniformly ejected in the circumference as it passes through the tail nozzle 103, so that the thrust direction is centered.

[0052] In this embodiment, the arch height of the inner elastic sheet 1011 is greater than the arch height of the outer elastic sheet 1021. The outer elastic sheet 1021 has a front end section facing the exhaust port, and a guide groove is provided on the front end section. The guide groove extends along the length direction of the front end section.

[0053] In this way, the high-pressure gas can pass through the tail nozzle 103 in an inward contraction shape to generate greater thrust, and a guide groove is formed on the front end so that the high-pressure gas flows more along the outer periphery of the tail cone 102, so that the high-pressure gas is ejected in an inward contraction shape.

[0054] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A jet propulsion device, characterized in that, The device includes a cylindrical body, which has a cylindrical cavity. The cylindrical cavity extends through the front end of the cylindrical body to form an air inlet, and extends through the rear end of the cylindrical body to form an exhaust outlet. Along the direction from the air inlet to the exhaust outlet, the cylindrical cavity sequentially includes an air intake section, a combustion section, and an exhaust section. The cylinder cavity is provided with a rotating main shaft, which extends from the intake section to the exhaust section and passes through the combustion section; a compressor and a diffuser are connected to the intake section, and the compressor has multiple compressor blades. The combustion section is equipped with a burner, which is fixedly connected to the combustion section. The burner has a ring-shaped combustion chamber, and the combustion chamber is equipped with multiple evaporation pipes that are connected to oil pipes. The multiple evaporation pipes are arranged around the circumference of the combustion chamber at intervals. The exhaust section is provided with a guide and a turbine. The guide is fixedly connected to the exhaust section. The guide has multiple guide blades and there is a guide interval between adjacent guide blades. The turbine has multiple turbine blades. The exhaust port has a tail cone in the middle. The diameter of the tail cone gradually decreases along the direction away from the exhaust port. The tail nozzle is fitted around the outer periphery of the tail cone and is connected to the cylinder. The tail cone and the tail nozzle extend outward away from the exhaust port, and the tail nozzle and the tail cone form an annular tail nozzle channel. After the main shaft drives the compressor to rotate, air enters the intake section through the intake port and is compressed by the rotating compressor blades to form high-pressure gas. The high-pressure gas is decelerated and guided by the diffuser and enters the combustion chamber. The fuel pipe discharges fuel into the evaporator tube, where it is heated and vaporized to form atomized gas. The atomized gas mixes with the high-pressure gas in the combustion chamber to form an oil-gas mixture. The oil-gas mixture burns in the combustion chamber to form high-pressure gas. The high-pressure gas passes through the guide gap and impacts the turbine blades to rotate. The turbine drives the main shaft to rotate in the opposite direction, so that the compressor continues to rotate and air continues to enter the intake section through the intake port. The high-pressure gas passing through the turbine is ejected at high pressure from the tail nozzle through the exhaust port to generate forward thrust. The evaporator tube has an evaporation chamber inside, and the end of the evaporation chamber is arranged in an open manner to form an outlet for the atomized gas to be discharged; the oil pipe has an end that passes through the evaporation chamber and is located in the evaporation chamber. The oil injection section sprays fuel onto the inner wall of the evaporation chamber. The fuel is heated and evaporated at high temperature to form the atomized gas. The atomized gas enters the combustion chamber through the outlet.

2. The jet propulsion device as claimed in claim 1, characterized in that, The air inlet is covered with a dust filter to filter the air passing through it.

3. The jet propulsion device as described in claim 1, characterized in that, The air inlet is provided with a bracket, the bracket is provided with a base, and the base is provided with a starter. The starter is connected to the main shaft through a clutch, and the starter drives the main shaft from a stationary state to a rotating state.

4. The jet propulsion device as claimed in claim 1, characterized in that, There is a compressor gap between adjacent compressor blades, and the end of the compressor gap forms a compressor outlet; the diffuser is plate-shaped and arranged at the end of the compressor, and the diffuser is provided with multiple diffusion channels communicating with the combustion chamber, and the multiple diffusion channels are respectively connected to multiple compressor outlets; the high-pressure gas discharged from the compressor outlet enters the diffusion channel and is decelerated and guided by the diffusion channel into the combustion chamber.

5. The jet propulsion device as described in claim 4, characterized in that, The diffuser channel is arranged at an angle relative to the radial direction of the diffuser, and the diameter of the diffuser channel gradually increases along the flow direction of the high-pressure gas in the diffuser channel.

6. The jet propulsion device according to any one of claims 1 to 5, characterized in that, The evaporation chamber is provided with a rotating cylinder that rotates relative to the evaporation tube. The fuel injection section is placed in the rotating cylinder. The fuel injection section sprays fuel in the rotating cylinder. The fuel drives the rotating cylinder to rotate. The fuel passes through the rotating cylinder and enters the evaporation chamber in a centrifugal rotation, spraying onto the inner wall of the evaporation chamber. The rotating cylinder has a rotating cavity, the oil injection section extends into the rotating cavity, the end of the rotating cylinder is closed, and the outer periphery of the rotating cylinder is provided with a plurality of peripheral holes; the end of the oil injection section is bent and faces the inner wall of the rotating cavity. The fuel injected from the injection section impacts the inner side of the rotating cylinder, driving the rotating cylinder to rotate. The fuel in the rotating chamber rotates centrifugally and is sprayed into the evaporation chamber through multiple peripheral holes, and onto the inner wall of the evaporation chamber.

7. The jet propulsion device as claimed in claim 6, characterized in that, The inner wall of the rotating cavity is provided with a plurality of curved pieces, which are arranged to bend along the circumference of the rotating cavity. The plurality of curved pieces are arranged at intervals along the circumference of the rotating cavity, and the outer peripheral hole is formed between adjacent curved pieces. The end of the fuel injection section is bent to form multiple bent sections, which are arranged toward the bending plate. The fuel injected from the bent sections impacts the bending plate to drive the rotating cylinder to rotate.

8. The jet propulsion device according to any one of claims 1 to 5, characterized in that, The air outlet is covered with two fixed metal mesh layers, which are spaced apart to form a flat fixed cavity. The fixed cavity is provided with a movable metal mesh layer. The atomized gas sprayed from the air outlet passes through the fixed metal mesh layer and the movable metal mesh layer, and the movable metal mesh layer is impacted and swings back and forth to disperse the atomized gas.

9. The jet propulsion device according to any one of claims 1 to 5, characterized in that, The outer periphery of the tail cone is provided with a plurality of external elastic plates. The front end of the external elastic plates is fixedly arranged, the middle part of the external elastic plates is arched and bent away from the tail cone, and the rear end of the external elastic plates extends backward to form an external movable end that movably abuts against the tail cone. The inner wall of the tail nozzle is provided with a plurality of inner elastic plates. The front end of the inner elastic plate is fixedly arranged, the middle part of the inner elastic plate is arched and bent away from the tail nozzle, and the rear end of the inner elastic plate extends backward to form an inner movable end that movably abuts against the tail nozzle. Multiple outer elastic plates are arranged at intervals around the tail cone in the circumferential direction, and multiple inner elastic plates are arranged at intervals around the tail nozzle in the circumferential direction. The inner elastic plates and outer elastic plates are staggered in the circumferential direction of the tail nozzle.

10. The jet propulsion device as claimed in claim 9, characterized in that, The inner elastic sheet has a greater arch height than the outer elastic sheet. The outer elastic sheet has a front end section facing the exhaust port. The front end section is provided with a guide groove, which extends along the length of the front end section.

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