A water-air dual-use pump-jet propeller

Abstract

The present invention discloses a pump-jet thruster that can be used both in water and in air, which relates to the field of propulsion technology and includes a housing, a core shaft, and a driving device. The housing is in a cylindrical shape and is arranged around the core shaft. A flow channel for medium transportation is formed between the outer surface of the core shaft and the inner side surface of the housing. A medium pressurization device is arranged along the flow channel, and the driving device is used to drive the core shaft to rotate. This application abandons the combustion chamber in the original aeroengine and adopts single-channel axial flow pressurization propulsion to solve the problem that the combustion chamber part will inevitably become dead weight during underwater propulsion, and realizes efficient propulsion of different media in the air part and the underwater part by adjusting the rotation speed and other means.

Description

Technical Field

[0001] The present invention relates to the field of propulsion technology, and particularly to a pump-jet propeller that can be used both in water and in air. Background Art

[0002] Due to the significant differences in the working principles and modes of propulsion systems in different medium environments, traditional propulsion methods cannot adapt to multi-medium working environments. Even if solid / liquid rocket engines that are not restricted by media are used, there are still great differences in their working characteristics in the air and underwater.

[0003] Most of the existing cross-medium aircraft schemes currently adopt a simple combination of two independent air and underwater propulsion systems. One works in water and the other works in air, with independent functions. There are also a few schemes that integrate the air and underwater propulsion systems into one engine. Inside the engine, there are many mechanical structures. Through electronic control, these mechanical structures can be used to control the opening and closing of the inner and outer ducts, so as to achieve the purpose of cross-medium navigation.

[0004] When working underwater, the engine for use in the air is sealed and 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, and is particularly not suitable for aircraft such as small aircraft that have high requirements for volume, mass, and cost-effectiveness. For the scheme that integrates the air and underwater propulsion systems into one engine, in essence, it is still two systems. Due to the presence of the combustion chamber, when operating underwater, complex mechanical structures must be used to seal the flow path with the combustion chamber. This part does not work underwater and also forms dead weight. In addition, its mechanical structure is too complex, increasing the maintenance cost of the engine and the probability of its failure. Summary of the Invention

[0005] The purpose of the present invention is to provide a pump-jet propeller that can be used both in water and in air, which can reduce or avoid the above-mentioned problems.

[0006] To solve the above technical problems, the present invention provides a pump-jet propeller that can be used both in water and in air, including a housing and a core shaft. The housing is in a cylindrical shape and is arranged around the core shaft. A flow path for medium transportation is formed between the outer surface of the core shaft and the inner side surface of the housing. A medium pressurizing device is arranged along the flow path.

[0007] The medium pressurizing device includes single-stage or multi-stage pressurizing units. Each stage of the pressurizing units is arranged in sequence front and back along the direction from the first end to the second end. Any stage of the pressurizing unit includes a rotor stage and a stator stage that are arranged alternately front and back. The rotor stage rotates following the core shaft and cooperates with the stator stage to pressurize the medium.

[0008] It further includes a driving device for driving the mandrel to rotate.

[0009] Optionally, the driving device is electrically driven; an induction coil or a permanent magnet is fixedly arranged on the mandrel to serve as the rotor of the driving device; correspondingly, a stator is fixedly arranged outside the rotor, and a current-carrying coil is wound around the stator, and the current-carrying coil is used for passing an alternating current to drive the rotor to rotate.

[0010] Optionally, the driving device is arranged at one end of the medium pressurizing device, and the stator has a streamlined outer shell, and the outer shell is connected to the housing through a fixing member.

[0011] Optionally, the driving device is arranged outside the housing or on the aircraft, and the driving device is fixedly connected to the housing through a connecting member. The connecting member is of a hollow structure, and a transmission member is arranged inside it. The transmission member drives the connection between the driving device and the mandrel, and the transmission member includes any one of a chain, a belt, and a gear.

[0012] Optionally, the driving device is electrically driven; the mandrel is a hollow shaft structure, the mandrel is a hollow shaft body structure with a hollow cavity, and a permanent magnet is arranged on the inner wall of the hollow shaft body to serve as the rotor of the driving device; a stator surrounding a current-carrying coil is arranged in the hollow cavity; the end of the stator extends out of the hollow shaft body and is connected to the housing through a fixing member.

[0013] Optionally, a sealing bearing is arranged at the end of the stator for rolling connection between the hollow shaft body structure and the end of the stator.

[0014] Optionally, any stage of the mover stage is connected to the outer surface of the mandrel, and any stage of the stator stage is fixedly connected to the inner side surface of the housing; the mover stage includes a plurality of mover blades extending radially outward along the mandrel, and the roots of the mover blades are connected to the outer surface of the mandrel; the plurality of mover blades of any stage of the mover stage are annularly distributed.

[0015] Optionally, the medium flow cross-section of each pressurizing unit converges gradually.

[0016] Optionally, a flow deflector and a tail nozzle are further arranged on the mandrel;

[0017] The flow deflector includes a plurality of flow deflector blades extending radially outward along the mandrel. The flow deflector is arranged upstream of the medium pressurizing device along the flow channel for deflecting the flow direction of the medium entering the flow channel to be parallel to the axis direction of the mandrel; the tail nozzle is provided with a steering device for controlling the ejection direction of the medium in the flow channel.

[0018] Optionally, a fan assembly is further provided on the mandrel. The fan assembly is arranged at the inlet of the flow channel for sucking the medium into the flow channel.

[0019] A water-air dual-purpose pump-jet thruster provided by the present application includes a single flow channel, and a medium pressurizing device is arranged in the flow channel. When the driving device drives the mandrel 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.

[0020] A water-air dual-purpose pump-jet thruster provided by the present application has the following advantages:

[0021] 1. By adjusting the rotational speed, efficient propulsion of different media in the air part and the underwater part can be achieved.

[0022] 2. The structure is simple, without a combustion chamber, and single-flow channel axial flow pressurization propulsion is adopted to solve the problem that the combustion chamber part will inevitably become dead weight during underwater propulsion.

[0023] 3. It has a small volume and mass, and uses electric energy as the power source, which is suitable for small aircraft, tactical weapons and other aircraft with high requirements for volume, mass and economy.

[0024] 4. The structure is simple, there are not many mechanical device interactions, and maintenance and management are relatively convenient. Brief Description of the Drawings

[0025] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following will briefly introduce the drawings required to be used in the prior art and the embodiments. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0026] Figure 1 It is a schematic structural diagram of a water-air dual-purpose pump-jet thruster provided by the present invention;

[0027] Figure 2 It is a schematic cross-sectional structure diagram of the mandrel in another embodiment of the present invention;

[0028] Figure 3 For Figure 2 It is a schematic structural diagram of the end part of the mandrel of a water-air dual-purpose pump-jet thruster in the shown embodiment;

[0029] Figure 4 For Figure 2 It is a schematic structural diagram of the end part of the mandrel of a water-air dual-purpose pump-jet thruster in the shown embodiment;

[0030] Figure 5 Schematic structural diagram of a water-air dual-use pump-jet propulsor according to another embodiment of the present invention;

[0031] Figure 6 Schematic structural diagram of a water-air dual-use pump-jet propulsor provided with a fan assembly according to an embodiment of the present invention;

[0032] Figure 7 Schematic structural diagram of a rotor stage of a medium pressurizing device of a water-air dual-use pump-jet propulsor according to the present invention;

[0033] Figure 8 Schematic structural diagram of a stator stage of a medium pressurizing device of a water-air dual-use pump-jet propulsor according to the present invention. Detailed implementation manners

[0034] The core of the present invention is to provide a water-air dual-use pump-jet propulsor, which solves the problem that the combustion chamber of a cross-medium aeroengine inevitably becomes a dead weight, can control the rotation speed of the fan, can provide appropriate power for a vehicle equipped with this engine, and improves the power matching of the vehicle in different media such as on the water surface, underwater and in the air.

[0035] To make the objectives, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are some but not all of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0036] Please refer to Figure 1 , Figure 1 Schematic structural diagram of a water-air dual-use pump-jet propulsor provided by the present invention. The water-air dual-use pump-jet propulsor includes a housing 1, a core shaft 2 and a driving device 7. The driving device 7 is electrically driven to drive the core shaft 2 to rotate. Among them, the housing 1 is cylindrical and has a cavity. The housing 1 is arranged around the core shaft 2, and the housing 1 has a first end 11 and a second end 12 in 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 housing 1, and this flow channel is used for the transportation of a medium (such as air or water). As Figure 1 shown, the diameter of the first end 11 of the housing 1 is larger than that of the second end 12, and the medium enters the flow channel at the first end 11 and is ejected from the second end 12. The water-air dual-use pump-jet propulsor can be installed on an aircraft through an assembly part (not shown in the figure).

[0037] In the direction from the first end 11 to the second end 12, a medium pressurizing device 5 is provided on the mandrel 2. The medium pressurizing device 5 includes single-stage or multi-stage pressurizing units. Each stage of pressurizing unit is arranged in sequence front and back in the direction from the first end 11 to the second end 12. As Figure 1 , 7 , as shown in 8, any stage of pressurizing unit includes a mover stage 51 and a stator stage 52 arranged alternately front and back. The mover stage 51 and the stator stage 52 of each stage of pressurizing unit are annularly distributed in the flow channel, and two adjacent annularly distributed mover stage 51 and stator stage 52 are a stage of pressurizing unit. In Figure 7 and Figure 8 In the shown structural schematic diagram, it is a structure including five stages of pressurizing units. The number of stages of the pressurizing unit can be adaptively selected according to specific application scenarios. Any stage of mover stage 51 is connected to the outer surface of the mandrel 2. Any stage of stator stage 52 is fixedly connected to the inner side surface of the housing 1. During the process of the air flow passing through the medium pressurizing device 5, it is accelerated, pressurized, and work-added stage by stage. The total temperature and total pressure of the air flow increase stage by stage, and finally the exhaust speed is greater than the intake speed to generate the thrust required for flight.

[0038] A water-air dual-use pump-jet thruster provided by the present invention can achieve efficient propulsion work for different media in the air part and the underwater part. Its principle is that when propulsion is carried out in the air medium, under the action of the driving device 7, the mandrel 2 rotates, sucks air into the flow channel, the mandrel 2 drives the medium pressurizing device 5 to compress the air, and the compressed air is ejected from the second end 12 to generate thrust. When propulsion is carried out in water, under the action of the driving device 7, the mandrel 2 rotates, the medium pressurizing device 5 drives the water flow to generate thrust, and at the same time, the medium pressurizing device 5 can also compress the water flow, and the compressed water flow is ejected from the second end 12 to generate stronger thrust.

[0039] The electric energy-driven jet aviation engine provided in this embodiment is different from the traditional fuel turbine jet engine, and cancels the combustion chamber and turbine of the traditional fuel turbine jet engine. The power consumed by the medium pressurizing device 5 part does not come from the passive work driven by the turbine, but from the rotational work of the driving device 7 driving the mandrel 2, consuming electric energy. Through electric energy drive, the high-speed intake air flow is decelerated and pressurized, and work is done on the intake air flow stage by stage to make its total temperature and total pressure increase stage by stage; finally, the pressurized air flow is discharged into the atmosphere through complete and full expansion and acceleration at the tail, and thrust is generated through the reaction force during this air expansion and acceleration process.

[0040] In a specific embodiment, as Figure 1As shown, the driving device 7 is electrically driven. An induction coil or a magnet is fixedly arranged on the mandrel 2 to serve as the rotor of the driving device 7 (not shown in the figure). Corresponding to this, a stator is fixedly arranged outside the rotor (not shown in the figure). An energized coil is wound around the stator. The energized 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 one-to-one correspondence; the stator and the rotor together form an electromagnetic driving device. Optionally, the rotor is an induction coil or a permanent magnet. An energized coil is wound around the stator. The energized coil is used to pass an alternating current to drive the rotor and then drive the mandrel 2 connected to the rotor to rotate. The driving device 7 using electromagnetic drive can conveniently adjust the rotation speed and is convenient for realizing efficient propulsion work in different media in the air part and the underwater part.

[0041] Optionally, the driving device 7 is arranged at one end of the medium pressurizing device 5. The stator has a streamlined outer shell 71, which can reduce the resistance during movement. The outer shell 71 is fixedly connected to the housing 1 through a fixing member 9. The power line of the driving device 7 can pass through the inside of the fixing member 9 and then be connected to the power supply inside the aircraft.

[0042] In another specific embodiment, as Figures 2-4 shown, the driving device 7 is arranged inside the mandrel 2. Specifically, as Figure 2 shown, the mandrel 2 is a hollow shaft structure. The mandrel 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 body. The permanent magnet 72 serves as the rotor of the driving device 7. A stator 73 around which an energized coil is wound is arranged in the hollow cavity. The end of the stator 73 extends out of the hollow shaft body and is fixedly connected to the housing 1 through a fixing member 9. The part of the stator 73 in the hollow cavity is of a "Y"-shaped structure, on which an energized coil is wound. The end of the stator 73 is cylindrical after extending out of the hollow shaft body, and a sealing bearing 10 is arranged at the end of the stator 73. The sealing bearing 10 is used to connect the hollow shaft body structure of the stator 73 and the mandrel 2, so that the hollow shaft body structure is in rolling connection with the end of the stator 73. The arrangement of the sealing 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 as to generate a changing magnetic field after being energized. Since the stator 73 is fixedly connected to the housing 1, the hollow shaft body serving as the rotor rotates under the action of the changing magnetic field, and finally drives the medium pressurizing device 5 to rotate. With this structure, the driving device 7 is integrated inside the mandrel 2, which can reduce the volume of the pump-jet propeller and save space. Due to the need of the medium pressurizing device 5, the flow channel of the medium gradually becomes smaller, resulting in the housing 1 needing to be squeezed inward or the mandrel 2 expanding; in this embodiment, the driving device 7 can utilize the space occupied by the expansion of the mandrel 2, avoiding the volume occupation of installing the driving device 7 additionally at other positions, reducing the blockage of the medium, and improving the propulsion effect. For example, it can avoid the blocking effect on the airflow or water flow when the driving device 7 is arranged in front of the flow channel.

[0043] 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 .

[0044] like Figure 6 The 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.

[0045] 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.

[0046] 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 5As shown, the driving device 7 and the housing 1 are fixedly connected by a connecting member 75. The connecting member 75 has a hollow structure, and a transmission member (not shown in the figure) is provided inside it. The transmission member drives and connects the driving device 7 and the mandrel 2. The transmission member can be any one of a chain, a belt, and a gear.

[0047] As Figure 1 and 6 shown, the deflector 4 includes a plurality of deflector vanes extending radially outward along the mandrel 2. The center of the deflector 4 is rotatably nested on the outer surface of the mandrel 2. The deflector vanes are used to control the flow direction of the medium entering the flow channel. Generally, the deflector vanes control the water flow or air flow to flow in a direction parallel to the axial direction of the mandrel 2, so that the water flow or air flow can flow evenly in the flow channel.

[0048] As Figure 7 and 8 shown, the rotor stage 51 includes a plurality of rotor vanes extending radially outward along the mandrel 2, and the roots of the rotor vanes are connected to the outer surface of the mandrel 2. The plurality of rotor vanes of any rotor stage 51 are annularly distributed. The rotor vanes form a certain inclination angle with the axis direction of the mandrel 2. The plurality of rotor vanes of any rotor stage 51 are fixedly connected to the outer surface of the mandrel 2. The stator stage 52 includes a plurality of stator vanes extending radially inward along the mandrel 2, and the roots of the stator vanes are connected to the inner side surface of the housing 1. The plurality of stator vanes of any stator stage 52 are annularly distributed. Along the intake direction, the rotor stage 51 is in front and the stator stage 52 is behind, and they are arranged alternately in sequence. Preferably, the medium flow cross-sections of the pressurization units of each stage of the medium pressurization device 5 gradually converge. Among them, the medium flow cross-section refers to: the cross-section of the air flow channel perpendicular to the axial flow direction.

[0049] In this application, the working principle of the medium pressurization device 5 can be referred to that of the compressor of an aviation jet engine, which will not be elaborated here one by one. However, the setting of its blades is different from that of the compressor of an aviation jet engine. Specifically, for the multiple rotor blades of any rotor stage 51 and the multiple stator blades of the stator stage 52, the thickness, angle, height, etc. of each blade are optimized through multiple computational fluid dynamics (CFD) simulations and experimental verifications. The blade thickness is designed to be thinner to reduce the medium resistance and improve the compression efficiency. The angles of the blades, including the inlet angle and the outlet angle, the inlet angle affects the way the air flow enters the blade channel, and the outlet angle affects the direction and speed of the air flow when it leaves the blade. Preferably, adopting appropriate angles can improve the flow direction and speed distribution of the medium in the blade channel, thereby increasing its compression effect and reducing the flow loss. The height of the blade affects the cross-sectional area of the blade channel, and further affects the flow rate and compression ratio of the medium. Preferably, adopting a higher blade height can ensure the flow rate requirement in the liquid medium. Through these optimized designs, it can not only pressurize the air medium, but also boost the liquid medium, making it more powerful when traveling in water.

[0050] A water-air dual-purpose pump-jet thruster provided by this application includes a single flow channel. A fan assembly is arranged in front of the flow channel, followed by a guide vane and a medium pressurization device in sequence. When propelling in the air, the fan assembly is driven to rotate by a driving device, sucking air into the flow channel. The core shaft rotates with the fan assembly, driving the medium pressurization device to compress the air. After compression, the air is ejected from the tail nozzle to generate thrust. When propelling underwater, the fan assembly is driven to rotate by a driving device, ejecting water flow from the tail nozzle to generate thrust.

[0051] A water-air dual-purpose pump-jet thruster provided by this application solves the problem that the combustion chamber of a cross-medium aeroengine inevitably becomes a dead weight; it is small in mass and volume, and uses electric energy as the power source, making it more suitable for small watercraft and tactical weapons; the watercraft equipped with this rim axial-flow supercharged pump-jet thruster can achieve cross-medium navigation functions such as high-speed flight in the air, energy-saving navigation on the water surface, and stealthy underwater navigation; the rotation speed of the fan can be controlled, which can provide appropriate power for the watercraft equipped with this engine, improving the power matching of the watercraft in different media such as on the water surface, underwater, and in the air.

[0052] It should be noted that in this specification, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the term "comprising", "including" or any other variation thereof is intended to cover non-exclusive inclusion, such that a process, method, article or device comprising a series of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article or device. Without further limitation, an element defined by the phrase "comprising a..." does not exclude the presence of additional identical elements in the process, method, article or device comprising the said element.

[0053] The foregoing 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 readily 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 is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A pump-jet propeller that can be used both in water and in air, characterized in that, including a housing and a mandrel, wherein the housing is cylindrical, the housing is arranged around the mandrel, and a flow channel for medium transportation is formed between the outer surface of the mandrel and the inner side surface of the housing; a medium pressurizing device is arranged along the flow channel; the medium is air or water; the medium pressurizing device includes single-stage or multi-stage pressurizing units, and each stage of the pressurizing units are arranged in sequence from the first end to the second end; any stage of the pressurizing unit includes a rotor stage and a stator stage which are arranged alternately front and back; the rotor stage rotates with the mandrel and cooperates with the stator stage to pressurize the medium; it further includes a driving device for driving the mandrel to rotate; the driving device is driven by electricity; the mandrel is a hollow shaft body structure with a hollow cavity, and permanent magnets are arranged on the inner wall of the hollow shaft body to serve as the rotor of the driving device; a stator surrounding the energized coil is arranged in the hollow cavity; the end of the stator extends out of the hollow shaft body and is connected to the housing through a fixing member; a sealing bearing is arranged at the end of the stator for the rolling connection between the hollow shaft body structure and the end of the stator.

2. The water-air dual-use pump-jet thruster according to claim 1, characterized in that, Any stage of the rotor stage is connected to the outer surface of the mandrel, and any stage of the stator stage is fixedly connected to the inner side surface of the housing; the rotor stage includes a plurality of rotor blades extending radially outward along the mandrel, and the roots of the rotor blades are connected to the outer surface of the mandrel; the plurality of rotor blades of any stage of the rotor stage are annularly distributed.

3. The water-air dual-use pump-jet thruster according to claim 2, characterized in that, The medium flow cross-section of each of the pressurizing units converges gradually.

4. The water-air dual-use pump-jet propeller according to claim 3, wherein A deflector and a tail nozzle are further arranged on the mandrel; the deflector includes a plurality of deflector blades extending radially outward along the mandrel, and the deflector is arranged upstream of the medium pressurizing device along the flow channel for deflecting the flow direction of the medium entering the flow channel to be parallel to the axis direction of the mandrel; a steering device is arranged at the tail nozzle for controlling the ejection direction of the medium in the flow channel.

5. The water-air dual-use pump-jet thruster according to claim 3 or 4, characterized in that A fan assembly is further arranged on the mandrel, and the fan assembly is arranged at the entrance of the flow channel for sucking the medium into the flow channel.

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