Water-air dual-purpose pump jet propeller

Abstract

The invention discloses a water-air dual-purpose pump spraying propeller, and relates to the technical field of propelling, the water-air dual-purpose pump spraying propeller comprises a shell, a core shaft and a driving device, the shell is cylindrical, the shell is arranged around the core shaft, and a flow channel for medium conveying is formed between the outer surface of the core shaft and the inner side face of the shell; a medium supercharging device is arranged along the flow channel, and the driving device is used for driving the mandrel to rotate. A combustion chamber in an original aero-engine is abandoned, single-runner axial flow supercharging propulsion is adopted, the problem that the combustion chamber part inevitably becomes dead weight during underwater propulsion is solved, and efficient propulsion work of different media in the air part and the underwater part is achieved by adjusting the rotating speed and the like.

Description

Technical Field

[0001] The invention relates to the field of propulsion technology, and in particular to a water-air dual-purpose pump-jet propeller. Background Art

[0002] Traditional strike plans based on single-medium aircraft are becoming increasingly difficult to achieve effective penetration; at the same time, the emergence of new combat styles such as distributed combat and multi-domain combat has put forward higher requirements on the aircraft's capabilities in multi-domain situational awareness, multi-dimensional information fusion, and cross-domain penetration and attack.

[0003] The cross-medium propulsion system is the fundamental support for the aircraft to achieve a comprehensive combat mode that takes into account both air flight and underwater navigation. Since the working principles and working methods of the propulsion system in different medium environments are quite different, the traditional propulsion method cannot adapt to the multi-medium working environment. Even if a solid / liquid rocket engine that is not restricted by the medium is used, its working characteristics in the air and underwater are also very different.

[0004] Most of the existing cross-medium aircraft solutions adopt a simple combination of two independent aerial and underwater propulsion systems, one working in the water and the other working in the air, with independent functions. A few other solutions integrate the aerial and underwater propulsion systems into one engine. There are many mechanical structures inside the engine, which can be controlled by electronic control to open and close the internal and external ducts, thereby achieving the purpose of cross-medium navigation.

[0005] Domestic researchers have done a lot of research on cross-media engines, but there are still some shortcomings. For the combination of two independent aerial and underwater propulsion systems, when working in the air, the underwater engine is closed and does not work, which becomes dead weight, increasing fuel consumption and reducing the range. When working underwater, the aerial engine is closed, which also becomes dead weight. Once water seeps in, the precision core components of the entire engine will be damaged. This method has problems such as large mass and low system integration. It is especially not suitable for small aircraft, tactical weapons and other aircraft with high requirements for volume, mass and cost-effectiveness. For the scheme of integrating the aerial and underwater propulsion systems into one engine, it is actually still two systems. Because of the combustion chamber, when running underwater, a complex mechanical structure must be used to seal the flow channel with the combustion chamber. This part does not work underwater, which also forms dead weight. In addition, its mechanical structure is too complicated, which increases the maintenance cost of the engine and increases the probability of its failure. Summary of the invention

[0006] The object of the present invention is to provide a water-air dual-purpose pump-jet propulsion device which can reduce or avoid the above-mentioned problems.

[0007] In order to solve the above technical problems, the present invention provides a water-air dual-purpose pump-jet propulsor, comprising a shell and a core shaft, wherein the shell is cylindrical and arranged around the core shaft, and a flow channel for medium transportation is formed between the outer surface of the core shaft and the inner side surface of the shell; a medium pressurizing device is arranged along the flow channel;

[0008] The medium boosting device comprises a single-stage or multi-stage boosting unit, and the boosting units of each stage are arranged in sequence from the first end to the second end; each stage of the boosting unit comprises a movable stage and a stator stage arranged alternately in front and back; the movable stage rotates with the core shaft and cooperates with the stator stage to boost the medium;

[0009] It also includes a driving device, which is used to drive the core shaft to rotate.

[0010] Optionally, the driving device is electrically driven; an induction coil or a permanent magnet is fixedly provided on the core shaft to serve as the rotor of the driving device; correspondingly, a stator is fixedly provided outside the rotor, and a power-carrying coil is wound around the stator, and the power-carrying coil is used to pass an alternating current to drive the rotor to rotate.

[0011] Optionally, the driving device is arranged at one end of the medium boosting device, and the stator has a streamlined shell, which is connected to the housing through a fixing member.

[0012] Optionally, the driving device is arranged on the outside of the shell or on the aircraft, and the driving device is fixedly connected to the shell by a connecting piece. The connecting piece is a hollow structure with a transmission piece inside. The transmission piece connects the driving device to the core shaft, and the transmission piece includes any one of a chain, a belt, and a gear.

[0013] Optionally, the drive device is electrically driven; the core shaft is a hollow shaft structure, the core shaft is a hollow shaft structure with a hollow cavity, the inner wall of the hollow shaft is provided with a permanent magnet to serve as the rotor of the drive device; a stator surrounded by an energized coil is provided in the hollow cavity; the end of the stator extends out of the hollow shaft and is connected to the shell through a fixing member.

[0014] Optionally, a sealed bearing is provided at the end of the stator for rolling connection between the hollow shaft structure and the end of the stator.

[0015] Optionally, any level of the mover stage is connected to the outer surface of the core shaft, and any level of the stator stage is fixedly connected to the inner side surface of the shell; the mover stage includes a plurality of mover blades extending radially outward along the core shaft, and the root of each mover blade is connected to the outer surface of the core shaft; the plurality of mover blades of the mover stage at any level are distributed in a ring shape.

[0016] Optionally, the medium flow cross-section of each of the boosting units converges step by step.

[0017] Optionally, a guide plate and a tail nozzle are also provided on the core shaft;

[0018] The guide plate includes a plurality of guide blades extending radially outward along the core shaft. The guide plate is arranged upstream of the medium pressurizing device along the flow channel to guide the flow direction of the medium entering the flow channel to be parallel to the axial direction of the core shaft; the tail nozzle is provided with a steering device to control the ejection direction of the medium in the flow channel.

[0019] Optionally, a fan assembly is further provided on the core shaft, and the fan assembly is provided at the inlet of the flow channel to suck the medium into the flow channel.

[0020] The present application provides a water-air dual-purpose pump-jet propeller, which contains a single flow channel, and a medium pressurizing device is arranged in the flow channel; when the driving device drives the core shaft to rotate, the medium pressurizing device pressurizes the medium, and then accelerates and ejects it from the outlet end of the flow channel, thereby generating thrust. It can be applied to air medium or water flow.

[0021] The present application provides a water-air dual-purpose pump-jet propulsion system, which has the following advantages:

[0022] 1. Efficient propulsion of different media in the air and underwater parts can be achieved by adjusting the rotation speed.

[0023] 2. The structure is simple, no combustion chamber is required, and single-channel axial flow booster propulsion is adopted to solve the problem that the combustion chamber part will inevitably become dead weight during underwater propulsion.

[0024] 3. It has a small size and mass, and uses electricity as its power source. It is suitable for small aircraft, tactical weapons and other aircraft that have high requirements on size, mass and economy.

[0025] 4. The structure is simple, without too many mechanical devices interacting with each other, and maintenance and management are relatively convenient. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the prior art and the drawings required for use in the embodiments are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0027] Figure 1 A schematic structural diagram of a water-air dual-purpose pump-jet propulsor provided by the present invention;

[0028] Figure 2 is a schematic diagram of a cross-sectional structure of a mandrel in another embodiment of the present invention;

[0029] Figure 3 for Figure 2 A schematic structural diagram of a core shaft end portion of a water-air dual-purpose pump-jet propulsor according to the embodiment shown;

[0030] Figure 4 for Figure 2 A schematic structural diagram of a core shaft end portion of a water-air dual-purpose pump-jet propulsor according to the embodiment shown;

[0031] Figure 5 A schematic structural diagram of a water-air dual-purpose pump-jet propulsor according to another embodiment of the present invention;

[0032] Figure 6 It is a schematic structural diagram of a water-air dual-purpose pump-jet propulsor provided with a fan assembly according to an embodiment of the present invention;

[0033] Figure 7 It is a schematic structural diagram of a moving stage of a medium boosting device of a water-air dual-purpose pump-jet propulsion system of the present invention;

[0034] Figure 8 The present invention is a schematic structural diagram of the stator stage of a medium boosting device of a water-air dual-purpose pump-jet propulsion system. DETAILED DESCRIPTION

[0035] The core of the present invention is to provide a pump-jet propulsion system for both water and air, which solves the problem of the inevitable dead weight of the combustion chamber of a cross-medium aircraft engine. The rotation speed of the fan can be controlled, and suitable power can be provided to the aircraft on which the engine is installed, thereby improving the power matching of the aircraft in different media such as on the water surface, underwater and in the air.

[0036] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are 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 creative work are within the scope of protection of the present invention.

[0037] Please refer to Figure 1 , Figure 1The present invention provides a schematic structural diagram of a dual-purpose pump-jet propulsor for water and air, which includes a shell 1, a core shaft 2 and a drive device 7. The drive device 7 is electrically driven to drive the core shaft 2 to rotate. The shell 1 is cylindrical and has a cavity. The shell 1 is arranged around the core shaft 2, and the shell 1 has a first end 11 and a second end 12 along the axial direction of the core shaft 2. A flow channel is formed between the outer surface of the core shaft 2 and the inner side surface of the shell 1, and the flow channel is used for conveying a medium (air or water, etc.). Figure 1 As shown, the diameter of the first end 11 of the housing 1 is greater than the diameter of the second end 12, and the medium enters the flow channel from the first end 11 and is ejected from the second end 12. The water-air dual-purpose pump-jet propulsor can be installed on an aircraft through an assembly portion (not shown in the figure).

[0038] From the first end 11 to the second end 12, the core shaft 2 is provided with a medium boosting device 5. The medium boosting device 5 includes a single-stage or multi-stage boosting unit. The boosting units of each stage are arranged in sequence from the first end 11 to the second end 12. Figure 1 , 7 As shown in Figure 8, each stage of the boosting unit includes a moving stage 51 and a stator stage 52 arranged alternately in front and back. The moving stage 51 and the stator stage 52 of each stage of the boosting unit are distributed in a ring shape in the flow channel, and two adjacent moving stages 51 and stator stages 52 distributed in a ring shape are a stage of the boosting unit. Figure 7 and Figure 8 In the structural diagram shown, it includes a five-stage boosting unit. The number of boosting units can be adaptively selected according to the specific application scenario. Any stage of the moving stage 51 is connected to the outer surface of the core shaft 2. Any stage of the stator stage 52 is fixedly connected to the inner side of the shell 1. In the process of the airflow passing through the medium boosting device 5, the boosting power is gradually accelerated, and the total temperature and total pressure of the airflow are gradually increased, and finally the exhaust speed is greater than the intake speed to generate the thrust required for flight.

[0039] The present invention provides a dual-purpose pump-jet propulsion device for water and air, which can realize efficient propulsion of different media in the air part and the underwater part. The principle is that when propulsion is performed in the air medium, under the action of the driving device 7, the core shaft 2 rotates, sucks air into the flow channel, and the core shaft 2 drives the medium boosting device 5 to compress the air, and the air is ejected from the second end 12 after compression to generate thrust. When propulsion is performed in water, under the action of the driving device 7, the core shaft 2 rotates, and the medium boosting device 5 drives the water flow to generate thrust. At the same time, the medium boosting device 5 can also compress the water flow, and the water flow is ejected from the second end 12 after compression to generate stronger thrust.

[0040] The electric energy driven jet aircraft engine provided in this embodiment is different from the traditional fuel turbojet engine, and the combustion chamber and turbine of the traditional fuel turbojet engine are eliminated. The power consumed by the medium supercharging device 5 does not come from the passive work driven by the turbine, but from the rotation work driven by the driving device 7 to drive the core shaft 2, which consumes electric energy. The high-speed intake air flow is decelerated and pressurized by electric energy, and the total temperature and total pressure of the intake air flow are increased step by step by step by step; finally, the air flow after supercharging is fully expanded and accelerated through the tail and discharged into the atmosphere. In this process of air expansion and acceleration, the reaction force generates thrust.

[0041] In a specific embodiment, Figure 1 As shown, the drive device 7 is electrically driven. An induction coil or a magnet is fixedly arranged on the core shaft 2 to serve as the rotor of the drive device 7 (not shown in the figure), and a stator (not shown in the figure) is fixedly arranged outside the corresponding rotor, and a power-carrying coil is surrounded by the stator, and the power-carrying coil is used to pass an alternating current to drive the rotor to rotate. The positions of the stator and the rotor are arranged in a one-to-one correspondence; the stator and the rotor together constitute an electromagnetic drive device. Optionally, the rotor is an induction coil or a permanent magnet. An power-carrying coil is surrounded by the stator, and the power-carrying coil is used to pass an alternating current to drive the rotor, and then drive the core shaft 2 connected to the rotor to rotate. The electromagnetically driven drive device 7 can conveniently adjust the rotation speed, which is convenient for realizing efficient propulsion of different media in the air part and the underwater part.

[0042] Optionally, the drive device 7 is arranged at one end of the medium boosting device 5. The stator has a streamlined shell 71, which can reduce the resistance during movement. The shell 71 is fixedly connected to the housing 1 through a fixing member 9. The power supply line of the drive device 7 can be passed through the inside of the fixing member 9 and then connected to the power supply in the aircraft.

[0043] In another specific embodiment, Figure 2-4 As shown, the driving device 7 is arranged inside the core shaft 2. Specifically, as Figure 2As shown, the core shaft 2 is a hollow shaft structure. The core shaft 2 is a hollow shaft structure with a hollow cavity. A permanent magnet 72 is fixedly arranged on the inner wall of the hollow shaft. The permanent magnet 72 is used as the rotor of the driving device 7. A stator 73 surrounding an energized coil is arranged in the hollow cavity. The end of the stator 73 extends out of the hollow shaft and is fixedly connected to the housing 1 through a fixing member 9. The part of the stator 73 in the hollow cavity is a "Y"-shaped structure, on which an energized coil is wound. The end of the stator 73 extends out of the hollow shaft and is cylindrical in shape, and a sealed bearing 10 is provided at the end of the stator 73. The sealed bearing 10 is used to connect the stator 73 and the hollow shaft structure of the core shaft 2, so that the hollow shaft structure is rollingly connected to the end of the stator 73. The provision of the sealed bearing 10 can prevent water, dust, etc. from entering the hollow cavity. The energized coil can be connected to the power supply of the aircraft via a wire, so that it generates a changing magnetic field when it is energized. Since the stator 73 is fixedly connected to the shell 1, the hollow shaft body serving as the rotor rotates under the action of the changing magnetic field, and finally drives the medium booster device 5 to rotate. With this structure, the drive device 7 is integrated into the interior of the core shaft 2, which can reduce the volume of the pump-jet propulsor and save space. Due to the need for the medium booster device 5, the flow channel of the medium gradually becomes smaller, causing the shell 1 to be squeezed inward or the core shaft 2 to expand; and in this embodiment, the drive device 7 can use the space occupied by the expansion of the core shaft 2, avoiding the volume occupied by the additional installation of the drive device 7 at other locations, reducing the obstruction to the medium, and improving the propulsion effect. For example, it can avoid the obstruction of the airflow or water flow when the drive device 7 is set in front of the flow channel.

[0044] like Figure 6 As shown, in another specific embodiment, a water-air dual-purpose pump-jet propulsor provided by the present invention may also include a fan assembly 3, a guide plate 4 and a tail nozzle 6. From the first end 11 to the second end 12, a fan assembly 3, a guide plate 4, a medium boosting device 5 and a tail nozzle 6 are sequentially arranged. A steering device (not shown in the figure) is also arranged at the tail nozzle 6, and the tail nozzle 6 and the steering device are used to control the ejection of the medium in the flow channel and the direction of the medium ejection, so that the direction of travel can be controlled. The fan assembly 3 is mounted on the core shaft 2 and is close to the first end 11. The fan assembly 3 is used to suck the medium into the flow channel so that more medium enters the flow channel at the same time, increasing the thrust of the pump-jet propulsor. The guide plate 4 is fixedly mounted on the inner side of the housing 1 and limits the core shaft 2. The guide plate 4 is arranged upstream of the medium boosting device 5 along the flow channel to guide the flow direction of the medium entering the flow channel to a direction parallel to the axis of the core shaft 2. Optionally, the guide plate 4 is used to control the flow direction of the medium entering the flow channel, so that the medium flows evenly toward the medium pressurizing device 5 .

[0045] like Figure 6The pump-jet propulsor shown in the figure can realize efficient propulsion of different media in the air part and the underwater part. When propulsion is performed in the air medium, the fan assembly 3 rotates with the core shaft 2 under the action of the driving device 7, sucks air into the flow channel, and the core shaft 2 drives the medium boosting device 5 to compress the air. After the air is compressed, it is ejected from the tail nozzle 6 at the second end 12 to generate thrust. When propulsion is performed in water, the fan assembly 3 rotates with the core shaft 2 under the action of the driving device 7, drives the water flow to generate thrust, and at the same time, the core shaft 2 drives the medium boosting device 5 to compress the water flow. After the water flow is compressed, it is ejected from the second end 12 to generate stronger thrust.

[0046] The fan assembly 3 includes a plurality of fan blades 31 extending radially outwardly along the core shaft 2. Optionally, the inclination angles of the plurality of fan blades 31 in the fan assembly 3 are adjustable to achieve adaptability to airflow or waterflow in different application scenarios, thereby improving the overall propulsion efficiency.

[0047] Generally, the drive device 7 can be driven not only by electric drive but also by other means, as long as it can provide sufficient power. The drive device 7 can also be arranged at other locations, such as other parts of the aircraft, as long as its power can be transmitted to the core shaft 2. Usually, a transmission member can be used to connect the core shaft 2. Generally, the transmission member can include any one of a chain, a belt, and a gear. Optionally, the drive device 7 is arranged on the outside of the housing 1 or on the aircraft (not shown in the figure). Figure 5 As shown, the driving device 7 is fixedly connected to the housing 1 through a connecting member 75. The connecting member 75 is a hollow structure, and a transmission member (not shown) is arranged inside the connecting member. The transmission member transmits and connects the driving device 7 to the core shaft 2. The transmission member can be any one of a chain, a belt, and a gear.

[0048] like Figure 1 and 6 As shown, the guide plate 4 includes a plurality of guide vanes extending radially outwardly along the core shaft 2. The center of the guide plate 4 is rotatably nested in the outer surface of the core shaft 2. The guide vanes are used to control the flow direction of the medium entering the flow channel. Generally, the guide vanes control the water flow or air flow to flow in a direction parallel to the axial direction of the core shaft 2, so that the water flow or air flow can flow evenly in the flow channel.

[0049] like Figure 7 and 8As shown, the mover stage 51 includes a plurality of mover blades extending radially outward along the core shaft 2, and the root of each mover blade is connected to the outer surface of the core shaft 2. The multiple mover blades of any one level of the mover stage 51 are distributed in an annular shape. The mover blades are at a certain inclination angle with the axial direction of the core shaft 2. The multiple mover blades of any one level of the mover stage 51 are fixedly connected to the outer surface of the core shaft 2. The stator stage 52 includes a plurality of stator blades extending radially inward along the core shaft 2, and the root of each stator blade is connected to the inner side of the shell 1. The multiple stator blades of any one level of the stator stage 52 are distributed in an annular shape. Along the air intake direction, the mover stage 51 is in front and the stator stage 52 is in the back, and they are arranged alternately in sequence. Preferably, the medium flow cross section of each level of the boosting unit of the medium boosting device 5 converges step by step. Wherein, the medium flow cross section refers to: the cross section of the air flow channel perpendicular to the axial flow direction.

[0050] In the present application, the working principle of the medium boosting device 5 can refer to the compressor of the aviation jet engine, which will not be described one by one here. However, the setting of its blades is different from that of the compressor of the aviation jet engine. Specifically, the thickness, angle, height, etc. of each blade setting of the multiple moving blades of any one level of the moving stage 51 and the multiple stator blades of the stator stage 52 are optimized and designed after multiple fluid dynamics (CFD) simulations and experimental verifications. The blade thickness is designed to be thinner to reduce medium resistance and improve compression efficiency; the angle of the blade includes the inlet angle and the outlet angle. The inlet angle affects the way the airflow enters the blade channel, and the outlet angle affects the direction and speed of the airflow when it leaves the blade. Preferably, the use of an appropriate angle can improve the flow direction and speed distribution of the medium in the blade channel, thereby increasing its compression effect and reducing flow losses. The height of the blade will affect the cross-sectional area of ​​the blade channel, and then affect the flow rate and compression ratio of the medium. Preferably, a higher blade height is used to ensure the flow rate requirements in the liquid medium. Through these optimized designs, it can not only pressurize the air medium, but also pressurize the liquid medium, making it more powerful when moving in the water.

[0051] The present application provides a dual-purpose pump-jet propulsor for water and air, which contains a single flow channel, a fan assembly is arranged in front of the flow channel, and a guide plate and a medium boosting device are arranged in sequence behind. When propulsing in the air, the fan assembly is driven to rotate by a driving device, and air is sucked into the flow channel. The core shaft rotates with the fan assembly, driving the medium boosting device to compress the air, and the compressed air is ejected from the tail nozzle to generate thrust; when propulsing underwater, the fan assembly is driven to rotate by a driving device, and water is ejected from the tail nozzle to generate thrust.

[0052] The present application provides a dual-purpose water and air pump-jet propulsion system, which solves the problem of the inevitable dead weight of the combustion chamber of a cross-medium aircraft engine; it has a small mass and volume, and uses electricity as a power source, making it more suitable for small aircraft and tactical weapons; an aircraft equipped with the rim-axial-flow booster pump-jet propulsion system can achieve cross-medium navigation functions such as high-speed flight in the air, energy-saving navigation on the surface, and stealth underwater; the rotation speed of the fan can be controlled, and appropriate power can be provided to the aircraft equipped with the engine, thereby improving the power matching of the aircraft in different media such as the surface, underwater and air.

[0053] It should be noted that, in this specification, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "comprise", "include" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, an element defined by the statement "comprises a ..." does not exclude the presence of other identical elements in the process, method, article or device including the element.

[0054] The above description of the disclosed embodiments enables those skilled in the art to implement or use the present invention. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention will not be limited to the embodiments shown herein, but rather to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A pump-jet propeller for water and air, characterized in that: include A shell and a core shaft, wherein the shell is cylindrical and arranged around the core shaft, and a flow channel for medium transportation is formed between the outer surface of the core shaft and the inner side surface of the shell; a medium pressurizing device is arranged along the flow channel; The medium boosting device comprises a single-stage or multi-stage boosting unit, and the boosting units of each stage are arranged in sequence from the first end to the second end; each stage of the boosting unit comprises a movable stage and a stator stage arranged alternately in front and back; the movable stage rotates with the core shaft and cooperates with the stator stage to boost the medium; It also includes a driving device, which is used to drive the core shaft to rotate.

2. The water-air dual-purpose pump-jet propulsion device according to claim 1, characterized in that: The driving device is electrically driven; an induction coil or a permanent magnet is fixedly arranged on the core shaft to serve as the rotor of the driving device; a stator is correspondingly fixedly arranged outside the rotor, and a power-carrying coil is wound around the stator, and the power-carrying coil is used to pass an alternating current to drive the rotor to rotate.

3. The water-air dual-purpose pump-jet propulsion device according to claim 2, characterized in that: The driving device is arranged at one end of the medium boosting device, and the stator has a streamlined shell, which is connected to the housing through a fixing member.

4. The water-air dual-purpose pump-jet propulsor according to claim 1, characterized in that: The driving device is arranged on the outside of the shell or on the aircraft. The driving device is fixedly connected to the shell through a connecting piece. The connecting piece is a hollow structure with a transmission piece inside. The transmission piece connects the driving device to the core shaft. The transmission piece includes any one of a chain, a belt, and a gear.

5. The water-air dual-purpose pump-jet propulsor according to claim 1, characterized in that: The driving device is electrically driven; the core shaft is a hollow shaft structure, and the core shaft is a hollow shaft structure with a hollow cavity, and the inner wall of the hollow shaft is provided with a permanent magnet to serve as the rotor of the driving device; a stator surrounding an energized coil is provided in the hollow cavity; the end of the stator extends out of the hollow shaft and is connected to the shell through a fixing member.

6. The water-air dual-purpose pump-jet propulsion device according to claim 5, characterized in that: The end of the stator is provided with a sealed bearing for rolling connection between the hollow shaft structure and the end of the stator.

7. The water-air dual-purpose pump-jet propulsion device according to any one of claims 1 to 6, characterized in that: Any level of the mover stage is connected to the outer surface of the core shaft, and any level of the stator stage is fixedly connected to the inner side surface of the shell; the mover stage includes a plurality of mover blades extending radially outward along the core shaft, and the root of each mover blade is connected to the outer surface of the core shaft; the plurality of mover blades of any level of the mover stage are distributed in a ring shape.

8. The water-air dual-purpose pump-jet propulsion device according to claim 7, characterized in that: The medium flow cross-section of each of the boosting units converges step by step.

9. The water-air dual-purpose pump-jet propulsion device according to claim 8, characterized in that: The core shaft is also provided with a guide plate and a tail nozzle; The guide plate includes a plurality of guide blades extending radially outward along the core shaft. The guide plate is arranged upstream of the medium pressurizing device along the flow channel to guide the flow direction of the medium entering the flow channel to be parallel to the axial direction of the core shaft; the tail nozzle is provided with a steering device to control the ejection direction of the medium in the flow channel.

10. The water-air dual-purpose pump-jet propulsion device according to claim 8 or 9, characterized in that: A fan assembly is also provided on the core shaft, and the fan assembly is provided at the inlet of the flow channel to suck the medium into the flow channel.

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