A rim-type axial-flow booster pump-jet propeller

Abstract

The present invention discloses a rim-type axial-flow booster pump-jet propulsor, which relates to the field of propulsion technology, and includes a shell, a core shaft, and a driving device. The shell is cylindrical, and the shell 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 shell; a fan assembly, a guide plate, a medium booster device, and a tail nozzle are sequentially arranged along the flow channel; and the driving device is used to drive the fan assembly to rotate. This application abandons the combustion chamber in the original aircraft engine and adopts a single-flow channel axial-flow booster propulsion to solve the problem that the combustion chamber part will inevitably become a 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 methods.

Description

Technical Field

[0001] The invention relates to the field of propulsion technology, and in particular to a rim-type axial-flow booster pump-jet propeller. Background Art

[0002] In recent years, with the development of military confrontation technology in various countries, the regional anti-missile capabilities of the world's major military powers have been increasingly enhanced, and traditional strike plans based on single-medium aircraft have become 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 rim-type axial-flow booster pump-jet propeller which can reduce or avoid the above-mentioned problems.

[0007] In order to solve the above technical problems, the present invention provides a rim-type axial-flow booster pump-jet propulsor, which includes 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 fan assembly, a guide plate, a medium boosting device and a tail nozzle are sequentially arranged along the flow channel; and

[0008] A driving device, mounted on the housing, for driving the fan assembly to rotate;

[0009] Wherein, the fan assembly is mounted on the core shaft and is used to draw the medium into the flow channel;

[0010] The guide plate is fixedly mounted on the inner side of the shell and limits the core shaft. The guide plate is used to control the flow direction of the medium entering the flow channel.

[0011] 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;

[0012] The tail nozzle is provided with a steering device for controlling the ejection of the medium in the flow channel.

[0013] Optionally, the fan assembly includes a plurality of fan blades extending radially outward along the core shaft, and the inclination angles of the plurality of fan blades in the fan assembly are adjustable.

[0014] Optionally, the driving device is electrically driven;

[0015] A rotor is fixedly arranged on the top of each fan blade of the fan assembly, and each of the rotors forms a ring-shaped structure; a stator is arranged on the outer side wall of the shell, and the positions of the stator and the rotor are arranged in a one-to-one correspondence;

[0016] The rotor is an induction coil or a permanent magnet;

[0017] The stator is surrounded by an energized coil, which is used to pass an alternating current to drive the rotor, and then drive the fan assembly connected to the rotor to move.

[0018] Optionally, the fan assembly and the core shaft are connected via a clutch structure; the clutch structure is used to selectively disconnect or connect the power between the fan assembly and the core shaft;

[0019] Wherein, the clutch structure is configured as follows:

[0020] When propelling in the air, the fan assembly and the core shaft are engaged through the clutch structure, and the fan assembly drives the core shaft to rotate together under the action of the driving device to suck air into the flow channel, and the core shaft drives the medium boosting device to compress the air, and the compressed air is ejected from the second end to generate thrust;

[0021] When propelling in water, the fan assembly and the core shaft are separated by the clutch structure, and the fan assembly drives the water flow to generate thrust under the action of the driving device.

[0022] Optionally, the driving device is drivingly connected to the core shaft, and the fan assembly is fixedly mounted on the core shaft.

[0023] 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.

[0024] Optionally, a plurality of mover blades of any one of the mover stages are fixedly connected to the outer surface of the core shaft;

[0025] The stator stage comprises a plurality of stator blades extending radially inwardly along the core shaft, and the root of each stator blade is connected to the inner side surface of the shell; the plurality of stator blades of the stator stage at any level are distributed in a ring shape.

[0026] Optionally, roots of a plurality of mover blades of any one of the mover stages are fixedly connected to an annular member, and the annular member is rotatably nested on the core shaft.

[0027] Optionally, the medium flow cross-section of each of the boosting units converges step by step.

[0028] Optionally, the guide plate includes a plurality of guide blades extending radially outward along the core shaft, and the center of the guide plate is rotatably nested in the outer surface of the core shaft.

[0029] The present application provides a rim-type axial-flow booster pump-jet propulsor, which contains a single flow channel, a fan assembly is arranged in front of the flow channel, and a guide plate and a medium booster device are arranged in sequence behind. When propulsing in the air, the fan assembly is driven to rotate by a driving device to suck air into the flow channel, and the core shaft rotates with the fan assembly to drive the medium booster 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 to eject water from the tail nozzle to generate thrust.

[0030] The present application provides a rim-type axial-flow booster pump-jet propeller, which has the following advantages:

[0031] 1. Efficient propulsion of different media in the air and underwater parts can be achieved by adjusting the rotation speed.

[0032] 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.

[0033] 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.

[0034] 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

[0035] 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.

[0036] Figure 1 A schematic structural diagram of a rim-type axial-flow booster pump-jet propulsor provided by the present invention;

[0037] Figure 2 A schematic diagram of the structure of a driving device and a fan assembly of a rim-type axial-flow booster pump-jet propulsor provided by the present invention;

[0038] Figure 3 A schematic structural diagram of a guide plate of a rim-type axial-flow booster pump-jet propulsor provided by the present invention;

[0039] Figure 4 A schematic structural diagram of a moving stage of a medium boosting device of a rim-type axial-flow booster pump-jet thruster provided by the present invention;

[0040] Figure 5 A schematic structural diagram of a stator stage of a medium pressurizing device of a rim-type axial-flow booster pump-jet thruster provided by the present invention. DETAILED DESCRIPTION

[0041] The core of the present invention is to provide a rim-type axial-flow booster pump-jet propulsor, which solves the problem of the inevitable dead weight of the combustion chamber of a cross-medium aircraft engine, can control the rotation speed of the fan, can provide appropriate power to the aircraft installed with the engine, and improve the power matching of the aircraft in different media on the water surface, underwater and in the air.

[0042] 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.

[0043] Please refer to Figure 1 , Figure 1 The present invention provides a schematic structural diagram of a rim-type axial-flow booster pump-jet propulsor, which includes a shell 1, a core shaft 2, a fan assembly 3, a guide plate 4, a medium boosting device 5, a tail nozzle 6 and a driving device 7. 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 .

[0044] 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. 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. The guide plate 4 is fixedly mounted on the inner side of the shell 1 and limits the core shaft 2. The guide plate 4 is used to control the flow direction of the medium entering the flow channel so that the medium flows evenly to the 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. Any boosting unit of each stage includes a moving stage 51 and a stator stage 52 arranged alternately from front to 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 constitute a first stage of the boosting unit. Figure 4 and Figure 5In 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.

[0045] The present invention provides a rim-type axial flow booster pump jet propulsor, 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, the fan assembly 3 drives the core shaft 2 to rotate together under the action of the driving device 7, sucks air into the flow channel, and the core shaft 2 drives the medium booster 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 drives the water flow to be ejected from the tail nozzle 6 at the second end 12 under the action of the driving device 7 to generate thrust.

[0046] 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 boosting device 5 does not come from the passive work driven by the turbine, but from the electric energy driven work driven by the drive device 7 to drive the fan assembly 3, which consumes electric energy. The high-speed intake air flow is decelerated and pressurized by electric energy drive, 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 passes through the tail nozzle 6, that is, the exhaust duct system, and is fully expanded and accelerated and then discharged into the atmosphere. In this air expansion and acceleration process, the reaction force generates thrust.

[0047] 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 facilitate adaptability to airflow or waterflow in different application scenarios, thereby improving the overall propulsion efficiency. In a specific embodiment, the drive device 7 is electrically driven. Specifically, as Figure 1 and 2As shown, a rotor 71 is fixedly arranged on the top of each fan blade 31 of the fan assembly 3. Each rotor 71 together forms a ring-shaped structure. A stator 72 is arranged on the outer wall of the housing 1. The positions of the stator 72 and the rotor 71 are arranged one by one; the stator 72 and the rotor 71 together constitute an electromagnetic drive device. Optionally, the rotor 71 is an induction coil or a permanent magnet. An energized coil is surrounded by the stator 72, and the energized coil is used to pass an alternating current to drive the rotor 71, and then drive the fan assembly 3 connected to the rotor 71 to move. 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.

[0048] In an optional embodiment, the fan assembly 3 can also be connected to the core shaft 2 through a clutch structure (not shown in the figure). The power between the fan assembly 3 and the core shaft 2 is disconnected or connected by the clutch structure. The choice of the clutch structure can be selected according to the application scenario. Specifically, the clutch structure is configured as follows: when propelling in the air, the fan assembly 3 and the core shaft 2 are engaged through the clutch structure, and the fan assembly 3 drives the core shaft 2 to rotate together under the action of the driving device 7, and the air is sucked into the flow channel. The core shaft 2 drives the medium boosting device 5 to compress the air, and the air is compressed and ejected from the tail nozzle 6 of the second end 12 to generate thrust; when propelling in water, the fan assembly 3 and the core shaft 2 are separated by the clutch structure, and the fan assembly 3 drives the water flow to be ejected from the tail nozzle 6 of the second end 12 under the action of the driving device 7 to generate thrust. That is, when propelling in water, the power connection between the fan assembly 3 and the core shaft 2 is disconnected by the clutch structure, so that the core shaft 2 no longer rotates with the fan assembly 3, and the medium boosting device 5 no longer works, thereby reducing the resistance of the medium boosting device 5 to the water flow and further improving the propulsion efficiency in water.

[0049] In an optional embodiment, the driving device 7 can also be connected to the core shaft 2. The fan assembly 3 is fixedly mounted on the core shaft 2. In this case, the driving device 7 can be set at other positions, and the power is transmitted to the core shaft 2 through the transmission member, so that the core shaft 2 drives the fan assembly 3 to rotate, thereby driving the air or water flow, thereby generating thrust.

[0050] like Figure 1 and 3 As shown, the guide plate 4 includes a plurality of guide vanes 41 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 41 are used to control the flow direction of the medium entering the flow channel. Generally, the guide vanes 41 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.

[0051] like Figure 4 and 5 As 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. Optionally, the roots of the multiple mover blades of any one level of the mover stage 51 are fixedly connected to an annular member 512, and the annular member 512 is rotatably nested on the core shaft 2. Preferably, the medium flow cross-sections of each level of the boosting unit of the medium boosting device 5 converge step by step. The medium flow cross section refers to the cross section of the air flow channel perpendicular to the axial flow direction.

[0052] 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.

[0053] The present application provides a rim-type axial-flow booster pump-jet propulsor, which contains a single flow channel, a fan assembly is arranged in front of the flow channel, and a guide plate and a medium booster device are arranged in sequence behind. When propulsing in the air, the fan assembly is driven to rotate by a driving device to suck air into the flow channel, and the core shaft rotates with the fan assembly to drive the medium booster 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 to eject water from the tail nozzle to generate thrust.

[0054] The present application provides a rim-type axial-flow booster pump-jet propulsor, 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-type axial-flow booster pump-jet propulsor 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, so that 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 in the air.

[0055] 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.

[0056] 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 rim-type axial-flow booster pump-jet propeller, characterized in that: include A shell and a core shaft, wherein the shell is cylindrical and arranged around the core shaft, and a single flow channel for medium transportation is formed between the outer surface of the core shaft and the inner side surface of the shell; a fan assembly, a guide plate, a medium pressurizing device and a tail nozzle are arranged in sequence along the flow channel; and A driving device, mounted on the housing, the driving device is electrically driven to drive the fan assembly to rotate; Wherein, the fan assembly is fixedly mounted on the core shaft and is used to suck the medium into the flow channel; The guide plate is fixedly mounted on the inner side of the shell and limits the core shaft. The guide plate is used to control the flow direction of the medium entering 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 is fixedly connected to the core shaft, and the movable stage rotates with the core shaft and cooperates with the stator stage to boost the medium; the medium flow cross section of each boosting unit converges step by step; The tail nozzle is provided with a steering device for controlling the ejection of the medium in the flow channel.

2. The rim-type axial-flow booster pump-jet propeller according to claim 1, characterized in that: The fan assembly includes a plurality of fan blades extending radially outward along a core shaft, and the inclination angles of the plurality of fan blades in the fan assembly are adjustable.

3. The rim-type axial-flow booster pump-jet propeller according to claim 1 or 2, characterized in that: A rotor is fixedly arranged on the top of each fan blade of the fan assembly, and each of the rotors forms a ring-shaped structure; a stator is arranged on the outer side wall of the shell, and the positions of the stator and the rotor are arranged in a one-to-one correspondence; The rotor is an induction coil or a permanent magnet; The stator is surrounded by an energized coil, which is used to pass an alternating current to drive the rotor, and then drive the fan assembly connected to the rotor to move.

4. The rim-type axial-flow booster pump-jet propeller according to claim 1 or 2, characterized in that: The driving device is drivingly connected to the core shaft, and the fan assembly is fixedly mounted on the core shaft.

5. The rim-type axial-flow booster pump-jet propeller according to claim 1, 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.

6. The rim-type axial-flow booster pump-jet propeller according to claim 5, characterized in that: A plurality of moving blades of any moving stage are fixedly connected to the outer surface of the core shaft; The stator stage comprises a plurality of stator blades extending radially inwardly along the core shaft, and the root of each stator blade is connected to the inner side surface of the shell; the plurality of stator blades of the stator stage at any level are distributed in a ring shape.

7. The rim-type axial-flow booster pump-jet propeller according to claim 5, characterized in that: The roots of the multiple moving blades of any moving stage are fixedly connected to an annular member, and the annular member is rotatably embedded in the core shaft.

8. The rim-type axial-flow booster pump-jet propeller according to claim 1, characterized in that: The guide plate comprises a plurality of guide blades extending radially outwardly along the core shaft, and the center of the guide plate is rotatably nested in the outer surface of the core shaft.

Images