CN114368472A - Magnetic suspension propeller and turbojet engine applying same - Google Patents
Magnetic suspension propeller and turbojet engine applying same Download PDFInfo
- Publication number
- CN114368472A CN114368472A CN202210130799.0A CN202210130799A CN114368472A CN 114368472 A CN114368472 A CN 114368472A CN 202210130799 A CN202210130799 A CN 202210130799A CN 114368472 A CN114368472 A CN 114368472A
- Authority
- CN
- China
- Prior art keywords
- suspension
- magnet
- main shaft
- stator
- propeller
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000000725 suspension Substances 0.000 title claims abstract description 87
- 230000007246 mechanism Effects 0.000 claims abstract description 43
- 230000005540 biological transmission Effects 0.000 claims abstract description 15
- 238000004804 winding Methods 0.000 claims description 18
- 238000002955 isolation Methods 0.000 claims description 14
- 238000002485 combustion reaction Methods 0.000 claims description 9
- 238000005339 levitation Methods 0.000 claims description 8
- 238000000034 method Methods 0.000 abstract description 5
- 238000010586 diagram Methods 0.000 description 5
- 230000005674 electromagnetic induction Effects 0.000 description 4
- 230000005484 gravity Effects 0.000 description 4
- 230000001846 repelling effect Effects 0.000 description 4
- 230000015572 biosynthetic process Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/02—Hub construction
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02N—ELECTRIC MACHINES NOT OTHERWISE PROVIDED FOR
- H02N15/00—Holding or levitation devices using magnetic attraction or repulsion, not otherwise provided for
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides a magnetic suspension propeller and a turbojet engine using the same, and relates to the technical field of aero-engines. 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
Technical Field
The invention relates to the technical field of aircraft engines, in particular to a magnetic suspension propeller and a turbojet engine applying the same.
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.
Disclosure of Invention
The invention aims to provide a magnetic suspension propeller which can reduce loss on the premise of ensuring the rotating speed of a rotating blade, so that the requirement on the rotating power of a fan blade of an engine is reduced.
The embodiment of the invention is realized by the following steps:
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 present invention, a stator magnet group is uniformly distributed around the inner stator main body in the inner stator, a rotor magnet group adapted to the stator magnet group is arranged in the outer rotor, adjacent magnets in the rotor magnet group have opposite polarities, and the outer wall of the outer rotor is connected with the rotating vanes.
In some embodiments of the present invention, the stator magnet assembly includes a stator spool sleeved on the spindle and a plurality of coils wound on the stator spool.
In some embodiments of the 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 invention, the winding post is T-shaped.
In some embodiments of the present invention, the spindle further includes a limit magnet assembly, the limit magnet assembly includes a first limit magnet disposed on the rotor and a second limit magnet disposed on the spindle, 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.
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 invention, a side of the spoiler remote from the isolation gap is streamlined.
In some embodiments of the present invention, either magnet may be a permanent magnet or an electromagnet.
Compared with the prior art, the embodiment of the invention has at least the following advantages or beneficial effects:
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 needed 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 diagram of an external structure of a magnetically levitated propeller in the present invention;
FIG. 2 is a schematic structural diagram of a magnetic levitation driving mechanism according to the present invention;
FIG. 3 is a schematic view of the position of the transmission structure and the rotor blade of the present invention;
FIG. 4 is a schematic structural view of a transmission structure according to the present invention;
FIG. 5 is an enlarged view of a portion A of FIG. 3;
FIG. 6 is a schematic diagram of an external structure of a magnetic levitation turbojet engine according to the present invention;
FIG. 7 is a schematic structural diagram of a magnetic levitation drive mechanism in a turbojet engine according to the present invention;
fig. 8 is a schematic structural diagram of another view angle of the magnetic levitation drive mechanism applied to the turbojet engine in the 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 technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the 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 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 figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within 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", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings or the orientations or positional relationships that the products of the present invention are usually placed in when used, the orientations or positional relationships are only used for convenience of describing the present invention and simplifying the description, but the terms do not indicate or imply that the devices or elements indicated must have specific orientations, be constructed in specific orientations, and operate, and therefore, should not be construed as limiting the present invention. 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", "overhang" and the like do not require that the components be absolutely horizontal or overhang, 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" represents at least 2.
In the description of the embodiments of the present invention, it should be further noted that unless otherwise explicitly stated or limited, 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 meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
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, the rotation friction of the propeller is the largest factor of power consumption when the propeller rotates, and the root cause is that the hub of the propeller is complex and numerous, and the direct friction and the indirect friction are caused by the complex structure, so that the friction force is increased, and the part loss 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. 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.
In some embodiments of the present invention, because of the magnetic suspension, the driving of the rotating blade 7 does not use the existing mechanical rotation method, but uses the electromagnetic induction method to drive the rotating blade 7, and in order to adapt to the annular rotating blade 7, the electromagnetic induction related device also needs to be arranged annularly, so that the stator magnet groups 6211 uniformly distributed around the main body of the inner stator 621 are arranged in the inner stator 621, thereby making the electromagnetic induction more uniform and improving the 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.
In some embodiments of the present invention, the present embodiment is driven by an electromagnet, which can effectively control the magnetic induction of the coil 6213 by controlling the current, so that the rotating blade 7 is not directly mechanically connected to the internal turbojet engine, and the rotating speed of the rotating blade is adjusted in real time by a simple and easily manufactured structure.
Example 4
Referring to fig. 4, the present embodiment proposes that a plurality of coils 6213 are uniformly distributed on a stator winding disc 6212 based on the technical solution of embodiment 3.
In some embodiments of the present invention, as the magnet on the stator is used for the same reason, because the magnetic suspension mode is used, the driving of the rotating blade 7 does not use the existing mechanical rotating mode, and the electromagnetic induction mode is used for driving the rotating blade 7, so that the direct mechanical connection with the engine is reduced. 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 facilitate the winding of the coil 6213 as much as possible, the stator winding disc 6212 is designed by using a principle similar to that of the outer rotor 622 motor, the stator is fixed with the main shaft 3 by using the ring 6214, and the outer wall of the ring 6214 is provided with a vertical wire column 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 provided in a T-shape when winding the coil 6213 in order to avoid the coil 6213 from 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 force in the radial direction is solved in the above embodiments, so that although the friction force can be reduced, when the aircraft is in flight, the rotating blades 7 of the engine can be subjected to the thrust from the air, so that the rotating blades 7 apply a larger force to the tail of the engine, thereby the rotating blades 7 are subjected to the pressure in the axial direction, and the larger friction still exists. 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, the generation of the levitation gap 612 and the isolation gap after the magnetic levitation technique causes the air flow to flow along the two gaps, thereby causing a vortex situation 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 movement of the object in the gas is due to both 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 present invention, either magnet may be a permanent magnet or an electromagnet.
In some embodiments of the present invention, the magnet is selected differently according to the application of the engine, and for the aircraft engine, the load and the self weight of the aircraft engine are large, so that the magnet adopts an 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.
Example 10
Referring to fig. 6, 7 and 8, the magnetic suspension turbojet engine provided by the present invention includes a housing, a main shaft 3 disposed in the housing, and an intake fan 1, an air compressor 2, a combustion chamber 4 and a turbine 5 sequentially disposed on the main shaft 3, wherein the 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 is further increased for an increased number of engine stages, which places a higher demand on aircraft power. 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.
In summary, the embodiment of the present invention provides a magnetic suspension propeller, which includes a main shaft 3, a rotating blade 7, 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 (10)
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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210130799.0A CN114368472A (en) | 2022-02-12 | 2022-02-12 | Magnetic suspension propeller and turbojet engine applying same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210130799.0A CN114368472A (en) | 2022-02-12 | 2022-02-12 | Magnetic suspension propeller and turbojet engine applying same |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114368472A true CN114368472A (en) | 2022-04-19 |
Family
ID=81146518
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210130799.0A Pending CN114368472A (en) | 2022-02-12 | 2022-02-12 | Magnetic suspension propeller and turbojet engine applying same |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114368472A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118238996A (en) * | 2024-05-09 | 2024-06-25 | 四川天舜动力科技有限公司 | Magnetic suspension power rotor system driven by disc type motor and aircraft with magnetic suspension power rotor system |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040080234A1 (en) * | 2002-03-15 | 2004-04-29 | David Arel | Permanent magnet alternator for a gas turbine engine |
| CN101197520A (en) * | 2006-12-07 | 2008-06-11 | 通用电气公司 | Double-sided starter-generator for aircraft |
| CN103236759A (en) * | 2013-04-22 | 2013-08-07 | 南京工业大学 | Magnetic suspension bearing disc type precise air-conditioning fan |
| CN107013265A (en) * | 2017-04-25 | 2017-08-04 | 黄绍忠 | It is a kind of vertical to magnetic swimming vortex turbine |
| CN108791813A (en) * | 2018-05-31 | 2018-11-13 | 江苏常探机器人有限公司 | Rear single vortex-spraying type composite wing cargo aircraft with solar energy additional fin |
| CN109441635A (en) * | 2018-12-18 | 2019-03-08 | 王立芳 | Three axis triple channels become duct variable diameter in series and parallel and adaptively recycle to turning jet engine |
| CN212047864U (en) * | 2020-03-18 | 2020-12-01 | 郑红刚 | Magnetic suspension electric propeller |
| CN217125119U (en) * | 2022-02-12 | 2022-08-05 | 北京金璐东方联合物流有限公司 | Magnetic suspension propeller and turbojet engine applying same |
-
2022
- 2022-02-12 CN CN202210130799.0A patent/CN114368472A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040080234A1 (en) * | 2002-03-15 | 2004-04-29 | David Arel | Permanent magnet alternator for a gas turbine engine |
| CN101197520A (en) * | 2006-12-07 | 2008-06-11 | 通用电气公司 | Double-sided starter-generator for aircraft |
| CN103236759A (en) * | 2013-04-22 | 2013-08-07 | 南京工业大学 | Magnetic suspension bearing disc type precise air-conditioning fan |
| CN107013265A (en) * | 2017-04-25 | 2017-08-04 | 黄绍忠 | It is a kind of vertical to magnetic swimming vortex turbine |
| CN108791813A (en) * | 2018-05-31 | 2018-11-13 | 江苏常探机器人有限公司 | Rear single vortex-spraying type composite wing cargo aircraft with solar energy additional fin |
| CN109441635A (en) * | 2018-12-18 | 2019-03-08 | 王立芳 | Three axis triple channels become duct variable diameter in series and parallel and adaptively recycle to turning jet engine |
| CN212047864U (en) * | 2020-03-18 | 2020-12-01 | 郑红刚 | Magnetic suspension electric propeller |
| CN217125119U (en) * | 2022-02-12 | 2022-08-05 | 北京金璐东方联合物流有限公司 | Magnetic suspension propeller and turbojet engine applying same |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118238996A (en) * | 2024-05-09 | 2024-06-25 | 四川天舜动力科技有限公司 | Magnetic suspension power rotor system driven by disc type motor and aircraft with magnetic suspension power rotor system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9143023B1 (en) | Electromagnetic propulsive motor | |
| EP2613033B1 (en) | Magnetically coupled contra-rotating propulsion stages | |
| US8752787B2 (en) | Electrical driven flying saucer based on magnetic suspension | |
| WO2021164549A1 (en) | Electric energy-driven jet aircraft engine and aircraft | |
| US9963981B2 (en) | Pitch change mechanism for shrouded fan with low fan pressure ratio | |
| US11414198B2 (en) | Aircraft propulsion system | |
| GB2565886B (en) | Electric engine | |
| US20130170985A1 (en) | Electrical powered tail rotor of a helicopter | |
| CN108488082B (en) | Electric drive torque self-balancing shaftless ducted fan or shaftless ducted blade for aircraft | |
| US9181900B1 (en) | Fully advanced superconducting segmented turbo-electric rotormachine (fasster) | |
| US11739694B2 (en) | Embedded electric motor assembly | |
| CN201176263Y (en) | Magnetic flying saucer | |
| US11884386B2 (en) | System, assemblies and methods for mechanical-thrust power conversion multifans | |
| CN217125119U (en) | Magnetic suspension propeller and turbojet engine applying same | |
| CN114368472A (en) | Magnetic suspension propeller and turbojet engine applying same | |
| CN101633408A (en) | Flying disk | |
| GB2601209A (en) | Electrically powered fan engine | |
| US20230303262A1 (en) | Electric vertical takeoff and landing (evtol) aircraft lift motor with air cooling | |
| CA2794077C (en) | Electrical powered tail rotor of a helicopter | |
| CN111852915A (en) | Ducted fan | |
| GB2370922A (en) | Electro-magnetic propulsion engine | |
| CN201254294Y (en) | Novel flying saucer | |
| CN101381001A (en) | Magneto-flying saucer | |
| CN113978703B (en) | Rim drive formula duct propeller of aviation usefulness | |
| CN107313950A (en) | Electromagnetic drive fan device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20220419 |