CN217125119U

CN217125119U - Magnetic suspension propeller and turbojet engine applying same

Info

Publication number: CN217125119U
Application number: CN202220286608.5U
Authority: CN
Inventors: 汪海波
Original assignee: Beijing Jinlu Oriental United Logistics Co ltd
Current assignee: Beijing Jinlu Oriental United Logistics Co ltd
Priority date: 2022-02-12
Filing date: 2022-02-12
Publication date: 2022-08-05
Anticipated expiration: 2032-02-12

Abstract

The utility model provides a magnetic suspension screw and turbojet engine of using thereof relates to aeroengine's technical field. The magnetic suspension type magnetic suspension device comprises a main shaft, rotating blades and a magnetic suspension driving mechanism, wherein the magnetic suspension driving mechanism comprises a suspension mechanism and a transmission mechanism, the transmission mechanism comprises an inner stator sleeved on the main shaft and an outer rotor matched with the inner stator, and the outer rotor is connected with the rotating blades; the suspension mechanism comprises two groups of suspension magnet groups which have the same polarity and are respectively arranged on the inner stator and the main shaft, and a suspension gap is arranged between the suspension magnet groups. It can reduce the friction loss under the rotational speed prerequisite of guaranteeing to change the blade to reduce the demand to power, and apply this technique to in the turbojet engine simultaneously, make the turbojet engine reduce the demand to power.

Description

Magnetic suspension propeller and turbojet engine applying same

Technical Field

The utility model relates to an aeroengine's technical field particularly, relates to a magnetic suspension screw and turbojet engine of using thereof.

Background

At present, in both propeller and turbojet engines, the losses due to the friction of rotation are extremely large, and particularly in the turbojet engines, the fans are directly driven by the low-pressure turbine; generally, a 3-5-stage supercharging compressor (sometimes called a low-pressure compressor) is arranged behind a fan rotor to increase the total pressure ratio of the engine and the air flow of the engine. However, the design has the inherent defects that the fan is connected with the low-pressure turbine shaft, and the fan is internally provided with the booster compressor, so that the rotating speed of the fan cannot be very low in order to take account of the boosting ratio and the rotating speed of the content, and the rotating speed of the booster compressor and the low-pressure turbine is greatly lower than the optimal working rotating speed of the booster compressor and the low-pressure turbine because the fan (additionally provided with the booster compressor) is directly driven by the low-pressure turbine; in order to meet the overall design requirement of the engine, the number of stages of the booster compressor and the low-pressure turbine is increased. The booster compressor and the low-pressure turbine do not work at the optimal rotating speed, so that the number of stages of the engine is increased, the friction force of the rotating blades is extremely high when the rotating blades rotate, and the loss of power is extremely serious, so that a magnetic suspension propeller and a turbojet engine applying the magnetic suspension propeller are urgently needed.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a magnetic suspension screw, it can reduce the loss under the rotational speed prerequisite of guaranteeing the rotation leaf to reduce the demand to engine flabellum rotation power.

The embodiment of the utility model is realized like this:

the embodiment of the application provides a magnetic suspension propeller, which comprises a main shaft, rotating blades and a magnetic suspension driving mechanism, wherein the magnetic suspension driving mechanism comprises a suspension mechanism and a transmission mechanism, the transmission mechanism comprises an inner stator and an outer rotor, the inner stator is sleeved on the main shaft, the outer rotor is matched with the inner stator, and the outer rotor is connected with the rotating blades; the suspension mechanism comprises two groups of suspension magnet groups which have the same polarity and are respectively arranged on the inner stator and the main shaft, and a suspension gap is arranged between the suspension magnet groups.

In some embodiments of the utility model, be equipped with the stator magnet group around inner stator main part evenly distributed in the inner stator, be equipped with the rotor magnet group with stator magnet group adaptation in the outer rotor, adjacent magnet polarity is opposite in the rotor magnet group, and the outer wall and the rotating vane of outer rotor are connected.

In some embodiments of the present invention, the stator magnet assembly includes a stator coil wound around the main shaft and a plurality of coils wound around the stator coil.

In some embodiments of the present invention, the plurality of coils are evenly distributed on the stator spool.

In some embodiments of the present invention, the stator spool includes a ring member sleeved on the main shaft and a winding post connected to the ring member, and the coil is wound on the winding post.

In some embodiments of the present invention, the wrapping post is T-shaped.

The utility model discloses an in some embodiments, still include spacing magnet group, spacing magnet group is including setting up the first spacing magnet on the rotor and setting up the spacing magnet of the epaxial second of main, and first spacing magnet is the same with the spacing magnet polarity of second, and first spacing magnet is equipped with the isolation clearance with the spacing magnet of second.

The embodiment of the application provides a magnetic suspension turbojet engine, which comprises a shell, a main shaft arranged in the shell, and an air inlet fan, an air compressor, a combustion chamber and a turbine which are sequentially arranged on the main shaft, wherein the air inlet fan, the air compressor, the combustion chamber and the turbine are all provided with rotating blades; the rotating blade is connected with the main shaft through a magnetic suspension driving mechanism.

In some embodiments of the present invention, the spoiler is streamlined on the side thereof away from the isolation gap.

In some embodiments of the present invention, any one of the magnets may be a permanent magnet or an electromagnet.

Compared with the prior art, the embodiment of the utility model has following advantage or beneficial effect at least:

a magnetic suspension propeller comprises a main shaft 3, a rotating blade 7 and a magnetic suspension driving mechanism 6, wherein the magnetic suspension driving mechanism 6 comprises a suspension mechanism 61 and a transmission mechanism 62, the transmission mechanism 62 comprises an inner stator 621 and an outer rotor 622, the inner stator 621 is sleeved on the main shaft 3, the outer rotor 622 is matched with the inner stator 621, and the outer rotor 622 is connected with the rotating blade 7; the suspension mechanism 61 includes two sets of suspension magnet groups 611 with the same polarity and respectively disposed on the inner stator 621 and the spindle 3, and a suspension gap 612 is disposed between the suspension magnet groups 611.

When the propeller rotates, the rotation friction of the propeller is the largest factor of power consumption, and the fundamental reason is that the hub of the propeller is complex and numerous, so that the direct friction and the indirect friction are caused, the friction force is increased, and the loss of parts is caused. Therefore, most of the friction force comes from the hub, and the design adopts the principle of magnetic suspension, so that the structure is simplified, and the friction force of parts in the hub is reduced. Therefore, on the premise of ensuring the rotating speed, the loss is reduced, and the requirement of the rotating blades of the propeller hub on the rotating power is reduced. In the specific embodiment, two sets of suspension magnet groups 611 having the same polarity and respectively disposed on the inner stator 621 and the spindle 3 are used, and a suspension gap 612 is disposed between the suspension magnet groups 611. The rotor is suspended by the principle of like poles repelling each other, and because of gravity, the magnetic force of the upper magnet should be set to be larger and the magnetic force of the lower magnet should be set to be smaller. In addition, the magnet is selected differently according to different application places of the engine, the load and the self weight of the aircraft engine are large, and therefore the magnet adopts the electromagnet, and the magnetic force can be adjusted according to the requirement of the aircraft. And for small airplanes or toy aircrafts, the permanent magnet can be directly adopted. The operation is that the magnetic poles of the magnets on the stator and the rotor are as shown in figure 5, and the principle is the same as that of a magnetic suspension train.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention, and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.

Fig. 1 is a schematic view of an external structure of a magnetic suspension propeller according to the present invention;

fig. 2 is a schematic structural view of a magnetic suspension driving mechanism of the present invention;

FIG. 3 is a schematic view of the position of the transmission structure and the rotating blades of the present invention;

fig. 4 is a schematic structural view of the transmission structure of the present invention;

FIG. 5 is an enlarged view of a portion A of FIG. 3;

fig. 6 is an external structural schematic diagram of a magnetic levitation turbojet engine according to the present invention;

fig. 7 is a schematic structural diagram of the magnetic suspension driving mechanism applied in the turbojet engine according to the present invention;

fig. 8 is a schematic structural diagram of another view angle of the magnetic levitation driving mechanism applied to the turbojet engine according to the present invention.

Icon: 1. an air intake fan; 2. a gas compressor; 3. a main shaft; 4. a combustion chamber; 5. a turbine; 6. a magnetic suspension driving mechanism; 61. a suspension mechanism; 611. a suspension magnet group; 612. a suspension gap; 62. a transmission mechanism; 621. an inner stator; 6211. a stator magnet group; 6212. a stator spool; 6213. a coil; 6214. an annular member; 6215. a winding post; 622. an outer rotor; 623. a rotor magnet group; 7. a rotor blade; 8. a limiting magnet group; 9. a spoiler.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, 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, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention, as generally described and illustrated in the figures herein, may be arranged and designed in a wide variety of different configurations.

Thus, the following detailed description of the embodiments of the present invention, presented in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.

It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.

In the description of the embodiments of the present invention, it should be noted that, if the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" and the like indicate the position or positional relationship based on the position or positional relationship shown in the drawings, or the position or positional relationship which is usually placed when the product of the present invention is used, the description is only for convenience of description of the present invention and simplification, but the indication or suggestion that the device or element to be referred must have a specific position, be constructed and operated in a specific position, and therefore, the present invention should not be construed as being limited thereto. Furthermore, the terms "first," "second," "third," and the like are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.

Furthermore, the terms "horizontal", "vertical", "suspended" and the like do not require that the components be absolutely horizontal or suspended, but may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.

In the description of the embodiments of the present invention, "a plurality" means at least 2.

In the description of the embodiments of the present invention, it should be further noted that unless explicitly stated or limited otherwise, the terms "disposed," "mounted," "connected," and "connected" should be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.

Example 1

Referring to fig. 1, fig. 2, fig. 3, fig. 4 and fig. 5, a magnetic suspension propeller is provided for the present embodiment, which includes a main shaft 3, a rotating blade 7 and a magnetic suspension driving mechanism 6, the magnetic suspension driving mechanism 6 includes a suspension mechanism 61 and a transmission mechanism 62, the transmission mechanism 62 includes an inner stator 621 sleeved on the main shaft 3 and an outer rotor 622 adapted to the inner stator 621, the outer rotor 622 is connected to the rotating blade 7; the suspension mechanism 61 includes two sets of suspension magnet groups 611 with the same polarity and respectively disposed on the inner stator 621 and the spindle 3, and a suspension gap 612 is disposed between the suspension magnet groups 611.

In some embodiments of the present invention, when the propeller rotates, the rotational friction is the largest factor of power consumption, and the root cause thereof is that the hub of the propeller has a complex structure and numerous structures, and the direct friction and the indirect friction brought by the complex structure result in an increase in friction force, and also result in loss of parts. Therefore, most of the friction force comes from the hub, and the design adopts the principle of magnetic suspension, so that the structure is simplified, and the friction force of parts in the hub is reduced. On the premise of ensuring the rotating speed, the loss is reduced, and the requirement of the rotating blades 7 of the propeller hub on the rotating power is reduced. In the specific embodiment, two sets of suspension magnet groups 611 having the same polarity and respectively disposed on the inner stator 621 and the spindle 3 are used, and a suspension gap 612 is disposed between the suspension magnet groups 611. The rotor is suspended by the principle of like poles repelling each other, and because of gravity, the magnetic force of the upper magnet should be set to be larger and the magnetic force of the lower magnet should be set to be smaller. In addition, the magnet is selected differently according to different application places of the engine, the load and the self weight of the aircraft engine are large, and therefore the magnet adopts the electromagnet, and the magnetic force can be adjusted according to the requirement of the aircraft. And for small airplanes or toy aircrafts, the permanent magnet can be directly adopted. The operation is that the magnetic poles of the magnets on the stator and the rotor are as shown in figure 5, and the principle is the same as that of a magnetic suspension train.

Example 2

Referring to fig. 2, 3 and 4, the present embodiment proposes, based on the technical solution of embodiment 1, that a stator magnet group 6211 uniformly distributed around a stator body is disposed in an inner stator 621, a rotor magnet group 623 adapted to the stator magnet group 6211 is disposed in an outer rotor 622, adjacent magnets in the rotor magnet group 623 have opposite polarities, and an outer wall of the outer rotor 622 is connected to a rotor blade 7.

The utility model discloses an in some embodiments, owing to adopt the mode of magnetic suspension, so rotor blade 7's drive just no longer adopts current mechanical rotation mode, adopts electromagnetic induction's mode to drive rotor blade 7, and for the annular rotor blade 7 of adaptation, the relevant device of electromagnetic induction also need carry out the annular setting, sets up the stator magnet group 6211 around inner stator 621 main part evenly distributed in this inner stator 621, thereby makes electromagnetic induction more even, has improved stability.

Example 3

Referring to fig. 4, the present embodiment proposes based on the technical solution of embodiment 2 that the stator magnet assembly 6211 includes a stator coil 6212 sleeved on the spindle 3 and a plurality of coils 6213 wound on the stator coil 6212.

The utility model discloses an in some embodiments, what this embodiment adopted is that the mode of electro-magnet drives, and it can be through the magnetic induction volume of the effectual control coil 6213 of control current to make rotor blade 7 and inside turbojet engine not have direct mechanical connection, with the simple structure of easily making, realize its rotational speed real-time adjustment.

Example 4

Referring to fig. 4, the present embodiment provides based on the technical solution of embodiment 3 that a plurality of coils 6213 are uniformly distributed on a stator winding disc 6212.

The utility model discloses an in some embodiments, the magnet reason is the same with on the stator, owing to adopt the mode of magnetic suspension, so rotor blade 7's drive just no longer adopts current mechanical rotation mode, adopts electromagnetic induction's mode to drive rotor blade 7 to reduce the direct mechanical connection with the engine. And the annular arrangement is also needed to adapt to the rotation of the rotor, so that the stability is improved.

Example 5

Referring to fig. 4, the present embodiment proposes based on the technical solution of embodiment 3 that the stator winding disc 6212 includes a ring element 6214 sleeved on the main shaft 3 and a winding post 6215 connected to the ring element 6214, and the coil 6213 is wound on the winding post 6215.

In some embodiments of the present invention, in order to wind the coil 6213 as much as possible, the stator bobbin 6212 is designed based on the principle of the motor similar to the outer rotor 622, the stator is fixed to the main shaft 3 by the ring 6214, and the vertical column is provided on the outer wall of the ring 6214 for winding the coil 6213, thereby achieving the purpose of fixing the stator.

Example 6

The present embodiment proposes that the winding post 6215 is T-shaped based on the technical solution of embodiment 5.

In some embodiments of the present invention, the winding post 6215 is configured to be T-shaped when winding the coil 6213 in order to avoid the coil 6213 being detached from the winding post 6215. It aims to limit the coil 6213 by the T-shaped protruding structure, thereby improving the stability.

Example 7

Referring to fig. 2, the embodiment is provided based on the technical solution of embodiment 1, and further includes a limit magnet group 8, where the limit magnet group 8 includes a first limit magnet disposed on the rotor and a second limit magnet disposed on the spindle 3, the first limit magnet and the second limit magnet have the same polarity, and an isolation gap is formed between the first limit magnet and the second limit magnet.

In some embodiments of the present invention, only the friction in the radial direction is solved in the above embodiments, so that although the friction can be reduced, when the aircraft flies, the rotating blade 7 of the engine can receive the thrust from the air, so that the rotating blade 7 applies a larger force to the tail of the engine, and thus the rotating blade 7 receives the pressure in the axial direction, and still has a larger friction. In particular, the rotary blades 7 in the intake fan 1 and the high-pressure gas compressor 2 generate the highest frictional force and are worn most severely due to the high pressure. Therefore, in order to solve this problem, the present embodiment provides the limit magnet group 8, and utilizes the principle of the same polarity to repel the rotor and the main shaft 3, thereby generating an isolation gap. When the pressure in flight is responded, the electromagnet is adopted as the magnet for the large-scale aviation aircraft, so that the repulsive force between the magnets is controlled, the rotor is not contacted with the main shaft 3, the friction is reduced, and the energy loss is reduced.

Example 8

Referring to fig. 2, the present embodiment is provided based on the technical solution of embodiment 7, and further includes a spoiler 9 for covering the isolation gap, where the spoiler 9 is connected to the main shaft 3, and the spoiler 9 is disposed right above the isolation gap.

In some embodiments of the present invention, after the magnetic levitation technique is adopted, the generation of the levitation gap 612 and the isolation gap may cause the air flow to flow along the two gaps, thereby causing the vortex condition in the engine. In order to avoid the problem, the design adopts the spoiler arranged on the isolation gap, so that most of air flow cannot directly flow into the isolation gap, and the generation of air inlet vortex is reduced; thereby improving the stability of the engine.

Example 9

Referring to fig. 2, the present embodiment provides based on the technical solution of embodiment 8 that a side of the spoiler 9 away from the isolation gap is streamlined.

In some embodiments of the present invention, the resistance to the object moving in the gas is caused by two reasons, internal friction and vortex. At very low speeds, the amount of drag is largely determined by internal friction. At higher velocities the swirl is mainly determined, the faster the velocity the greater the effect of the swirl. In order to effectively reduce the resistance, it is necessary to avoid the formation of vortices. The side of the spoiler 9 remote from the separation gap is thus arranged in a streamline shape to reduce the vortex effect or to avoid the formation of vortices, thus greatly reducing the same resistance of the gas to the engine.

In some embodiments of the utility model, to the difference in engine application place, the chooseing for use of magnet is also different, and to aeroengine, its load and self weight are great, and the magnet adopts the electromagnet from this, and such mode can be adjusted magnetic force according to the needs of aircraft. And for small airplanes or toy aircrafts, the permanent magnet can be directly adopted.

Example 10

Referring to fig. 6, 7 and 8, for the magnetic suspension turbojet engine provided by the present invention, the magnetic suspension turbojet engine includes a housing, a main shaft 3 disposed in the housing, and an air intake fan 1, an air compressor 2, a combustion chamber 4 and a turbine 5 sequentially disposed on the main shaft 3, wherein the air intake fan 1, the air compressor 2, the combustion chamber 4 and the turbine 5 are all provided with rotating blades 7; the rotor blade 7 is connected to the spindle 3 via the above-mentioned magnetic levitation drive 6.

In some embodiments of the present invention, the rotational friction of the engine is further increased for increasing the number of stages of the engine, which is highly required for the power of the aircraft. The fundamental reason for this is that the components of the intake fan 1, the gas compressor 2, the combustion chamber 4 and the turbine 5 that process the air are all rotating blades (i.e., the rotor blades 7), as shown in fig. 6; therefore, most of friction force comes from the above, the design adopts the principle of magnetic suspension, so that the friction among the air inlet fan 1, the air compressor 2, the combustion chamber 4, the turbine 5 and parts in the engine is reduced, the loss is reduced on the premise of ensuring the rotating speed, and the requirement on the rotating power of the fan blades of the engine is reduced. In the specific embodiment, two sets of suspension magnet groups 611 having the same polarity and respectively disposed on the inner stator 621 and the spindle 3 are used, and a suspension gap 612 is disposed between the suspension magnet groups 611. The rotor is suspended by the principle of like poles repelling each other, and because of gravity, the magnetic force of the upper magnet should be set to be larger and the magnetic force of the lower magnet should be set to be smaller. In addition, the magnet is selected differently according to different application places of the engine, the load and the self weight of the aircraft engine are large, and therefore the magnet adopts the electromagnet, and the magnetic force can be adjusted according to the requirement of the aircraft. And for small airplanes or toy aircrafts, the permanent magnet can be directly adopted. The operation is that the magnetic poles of the magnets on the stator and the rotor are shown in figure 7, the structure is shown in figure 8, and the principle is the same as that of a magnetic suspension train.

To sum up, the embodiment of the present invention provides a magnetic suspension propeller, which includes a main shaft 3, a rotating blade 7 and a magnetic suspension driving mechanism 6, a suspension mechanism 61 and a transmission mechanism 62 of the magnetic suspension driving mechanism 6, wherein the transmission mechanism 62 includes an inner stator 621 sleeved on the main shaft 3 and an outer rotor 622 adapted to the inner stator 621, and the outer rotor 622 is connected to the rotating blade 7; the suspension mechanism 61 includes two sets of suspension magnet groups 611 with the same polarity and respectively disposed on the inner stator 621 and the spindle 3, and a suspension gap 612 is disposed between the suspension magnet groups 611.

When the propeller rotates, the rotation friction of the propeller is the largest factor of power consumption, and the fundamental reason is that the hub of the propeller is complex and numerous, so that the direct friction and the indirect friction are caused, the friction force is increased, and the loss of parts is caused. Therefore, most of the friction force comes from the hub, and the design adopts the principle of magnetic suspension, so that the structure is simplified, and the friction force of parts in the hub is reduced. This reduces losses while ensuring a rotational speed, so that the requirement for the rotational power of the rotor blades 7 connected to the hub is reduced. In the specific embodiment, two sets of suspension magnet groups 611 having the same polarity and respectively disposed on the inner stator 621 and the spindle 3 are used, and a suspension gap 612 is disposed between the suspension magnet groups 611. The rotor is suspended by the principle of like poles repelling each other, and because of gravity, the magnetic force of the upper magnet should be set to be larger and the magnetic force of the lower magnet should be set to be smaller. In addition, the magnet is selected differently according to different application places of the engine, the load and the self weight of the aircraft engine are large, and therefore the magnet adopts the electromagnet, and the magnetic force can be adjusted according to the requirement of the aircraft. And for small airplanes or toy aircrafts, the permanent magnet can be directly adopted. The operation is that the magnetic poles of the magnets on the stator and the rotor are as shown in figure 5, and the principle is the same as that of a magnetic suspension train.

The above description is only a preferred embodiment of the present application and is not intended to limit the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.

It will be evident to those skilled in the art that the present application is not limited to the details of the foregoing illustrative embodiments, and that the present application may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the application being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.

Claims

1. A magnetic suspension propeller is characterized by comprising a main shaft, rotating blades and a magnetic suspension driving mechanism, wherein the magnetic suspension driving mechanism comprises a suspension mechanism and a transmission mechanism, the transmission mechanism comprises an inner stator sleeved on the main shaft and an outer rotor matched with the inner stator, and the outer rotor is connected with the rotating blades; the suspension mechanism comprises two groups of suspension magnet groups which have the same polarity and are respectively arranged on the inner stator and the main shaft, and a suspension gap is arranged between the suspension magnet groups.

2. The magnetic suspension propeller as claimed in claim 1, wherein a stator magnet set is disposed in the inner stator and evenly distributed around the main body of the inner stator, a rotor magnet set is disposed in the outer rotor and adapted to the stator magnet set, adjacent magnets in the rotor magnet set have opposite polarities, and the outer wall of the outer rotor is connected to the rotating blades.

3. The magnetically levitated propeller of claim 2, wherein the stator magnet assembly includes a stator wire spool sleeved on the main shaft and a plurality of coils wound on the stator wire spool.

4. A magnetically levitated propeller as claimed in claim 3, wherein a plurality of said coils are evenly distributed on said stator spool.

5. The magnetically levitated propeller of claim 3, wherein the stator coil comprises a ring member sleeved on the main shaft and a winding post connected to the ring member, and the coil is wound on the winding post.

6. The magnetically levitated propeller of claim 5, wherein said winding post is T-shaped.

7. The magnetically suspended propeller of claim 1, further comprising a limit magnet assembly, wherein the limit magnet assembly comprises a first limit magnet disposed on the rotor and a second limit magnet disposed on the main shaft, the first limit magnet and the second limit magnet have the same polarity, and the first limit magnet and the second limit magnet are provided with an isolation gap.

8. The magnetically levitated propeller of claim 7, further comprising a spoiler for covering the isolation gap, the spoiler being connected to the main shaft, the spoiler being disposed directly above the isolation gap.

9. The magnetically levitated propeller of claim 8, wherein a side of said spoiler remote from said isolation gap is streamlined.

10. A magnetic suspension turbojet engine comprises a shell, a main shaft arranged in the shell, and an air inlet fan, an air compressor, a combustion chamber and a turbine which are sequentially arranged on the main shaft, wherein the air inlet fan, the air compressor, the combustion chamber and the turbine are all provided with rotating blades; characterized in that the rotor blade is connected to the spindle by means of a magnetic levitation drive as claimed in claim 1.