CN115395690A - Annular permanent magnet motor for directly driving aircraft engine fan with medium-to-large bypass ratio - Google Patents

Abstract

The invention provides an annular permanent magnet motor for directly driving an aircraft engine fan with a medium-high bypass ratio, which comprises an inner ring of a motor rotor and a stator core of an outer ring, wherein the inner ring of the motor rotor is internally provided with the aircraft engine fan; and a rotor iron core is tightly fixed on the outer ring of the inner ring of the motor rotor. The invention can make the diameter of the rotor of the annular permanent magnet motor larger than that of the rotor of the traditional motor, and make the power of the annular permanent magnet motor higher, thereby meeting the high power requirement required by the fan applied to a medium-large bypass ratio aircraft engine; meanwhile, the armature calculation length is increased by the installation mode of each rotor iron core on the annular motor and the permanent magnet on the rotor, so that the power of the motor is further increased.

Description

A Ring Permanent Magnet Motor Directly Driving Medium and Large Bypass Ratio Aeroengine Fans

technical field

The invention relates to an annular permanent magnet motor which directly drives a fan of an aeroengine with a medium and large bypass ratio.

Background technique

As shown in FIG. 2 , in a traditional permanent magnet motor, the rotor core 3 is directly installed on the motor shaft 8 . Restricted by conditions such as the size of the motor space, the diameter of the stator ring (that is, the diameter of the armature) and the length of the stator winding (that is, the calculated length of the armature) are limited. Under the condition of other control conditions and certain materials used in the motor, it is difficult to further increase the power of the motor .

Contents of the invention

In order to solve the above-mentioned technical problems, the present invention provides a ring permanent magnet motor that directly drives the fan of an aeroengine with a medium and large bypass ratio. The ring permanent magnet motor that directly drives the fan of an aeroengine with a medium and large bypass ratio can The diameter of the rotor is larger than that of the traditional motor, so that the power of the annular permanent magnet motor is higher, which meets the high power demand required for the application of medium and large bypass ratio aeroengine fans.

The present invention is achieved through the following technical solutions.

The present invention provides a ring-shaped permanent magnet motor that directly drives a medium and large bypass ratio aero-engine fan, including a stator core and an inner ring of the motor rotor located inside the stator core. The aero-engine fan is installed in the inner ring of the motor rotor. There are permanent magnets clamped and distributed in the annular space between the inner ring of the rotor of the motor and the iron core of the stator; the outer ring of the inner ring of the rotor of the motor is closely attached to and fixed with the rotor iron core.

The inner ring of the motor rotor is the main installation ring of the fan.

The rotor core is an annular body covering the inner and outer ring surfaces of the motor rotor.

Stator teeth are closely attached to and fixed on the inner ring of the stator iron core, and stator windings are wound on the stator teeth.

The permanent magnets are evenly distributed along the annular space.

The stator teeth are evenly distributed along the inner ring of the stator iron core, and the stator teeth and the permanent magnets are alternately distributed; the stator teeth and the permanent magnets are parallel.

The aero-engine fan is coaxially fixed to the motor shaft.

On the vertical projection plane of the permanent magnet, the centerline of the permanent magnet is inclined relative to the axis line of the inner ring of the motor rotor.

The inclination angle of the permanent magnet is 5°-25°.

The number of the permanent magnets is 24, 36, 48 or 60.

The beneficial effect of the present invention is that: the rotor diameter of the annular permanent magnet motor can be made larger than that of the traditional motor rotor, so that the power of the annular permanent magnet motor is higher, which can meet the high power demand required by the fans of medium and large bypass ratio aeroengines; at the same time The installation method of each rotor iron core on the ring motor and the permanent magnet on the rotor increases the calculated length of the armature, further increasing the power of the motor.

Description of drawings

Fig. 1 is a schematic diagram of a three-dimensional structure;

Fig. 2 is a schematic diagram of a two-dimensional cross-sectional structure of a conventional permanent magnet motor in the prior art;

FIG. 3 is a schematic partial cross-sectional top view of FIG. 1 .

In the figure: 1-aeroengine fan, 2-motor rotor inner ring, 3-rotor core, 4-permanent magnet, 5-stator winding, 6-stator teeth, 7-stator core, 8-motor shaft.

Detailed ways

The technical solution of the present invention is further described below, but the scope of protection is not limited to the description.

Example 1

As shown in Figure 1, a ring permanent magnet motor that directly drives the fan of an aeroengine with a medium and large bypass ratio includes a stator core 7 and a motor rotor inner ring 2 positioned at the inner side of the stator core 7, and the motor rotor inner ring 2 is installed The aero-engine fan 1 has permanent magnets 4 sandwiched and distributed in the annular space between the inner ring 2 of the motor rotor and the stator core 7;

Example 2

Based on Embodiment 1, the inner ring 2 of the motor rotor is the main installation ring of the fan.

Example 3

Based on Embodiment 1, the rotor core 3 is an annular body covering the outer ring surface of the inner ring 2 of the motor rotor.

Example 4

Based on the first embodiment, the inner ring of the stator core 7 is tightly fixed with the stator teeth 6 , and the stator winding 5 is wound on the stator teeth 6 .

Example 5

Based on Embodiment 1, the permanent magnets 4 are evenly distributed along the annular space.

Example 6

Based on Embodiment 4, as shown in FIG. 3 , the stator teeth 6 are evenly distributed along the inner ring of the stator core 7 , and the stator teeth 6 and the permanent magnets 4 are alternately distributed; the stator teeth 6 and the permanent magnets 4 are parallel.

Example 7

Based on Embodiment 1, the aeroengine fan 1 is coaxially fixed to the motor shaft 8 .

Example 8

Based on Embodiment 1, on the vertical projection plane of the permanent magnet 4 , the center line of the permanent magnet 4 is inclined relative to the axis line of the inner ring 2 of the motor rotor.

Example 9

Based on Embodiment 8, the inclination angle of the permanent magnet 4 is 5°-25°.

Example 10

Based on Embodiment 1, the number of permanent magnets 4 is 24, 36, 48 or 60.

Example 11

Based on the above embodiments, it mainly includes a rotor mechanism containing permanent magnets, a stator winding mechanism for generating a magnetic field and other system components, as shown in FIG. 1 . The rotor mechanism is located outside the aeroengine fan 1 and the main fan installation ring 2, supported by the fan 1 and the fan main installation ring 2, and rotates around the axis of the fan installation ring 2. It is composed of rotor core 3 and permanent magnet 4, etc. The magnet 4 is installed in the axially distributed installation groove of the rotor core 3; the stator mechanism is located outside the rotor mechanism and is mainly composed of stator winding 5, stator teeth 6 and stator core 7. The stator teeth 6 are distributed in the direction, and the stator winding 5 is wound around the periphery of the stator teeth 6 . In addition, the permanent magnet 4 can be provided with a ring protection mechanism. When the motor is working, the rotor mechanism rotates under the action of the magnetic field of the stator mechanism.

Example 11

Based on the preferred solution of the above-mentioned embodiment, the outer diameter of the armature (i.e. the outer diameter of the stator) is 1080mm, the inner diameter of the armature (i.e. the inner diameter of the stator) is 1006mm, the outer diameter of the rotor is 1004mm, and the number of pole pairs on the rotor is 18 (corresponding to 36 permanent magnets), The number of stator core teeth is 101, the running air gap between the permanent magnet and the stator core is 1mm, the radial length of the permanent magnet on the iron core and the stator core is 150mm, the thickness of the permanent magnet is 8mm, the installation angle of the permanent magnet and the stator core is 10°, The outer sheath thickness of the permanent magnet is 2mm.

Therefore, according to the formula for the relationship between the power and size of the ring permanent magnet motor:

When calculating the pole arc coefficient α _i , the air gap magnetic field model coefficient K _Nm , the armature winding coefficient K _dp , the number of ampere conductors (referred to as line load) A of the rotating machine along the unit length of the armature circumference, and the air gap magnetic density B Under certain conditions such as _δ , constant k, motor speed n and other parameters, the present invention makes the ring permanent magnet motor stator diameter (or armature diameter) D larger than the traditional motor rotor diameter with a larger outer ring size, which can make the ring permanent magnet motor The motor power P is higher. In addition, each rotor core on the ring motor and the permanent magnets on the rotor are synchronously inclined at a certain angle α with respect to the power output shaft on the concentric ring surface (see the schematic diagram), and the length l of the permanent magnets (calculated length of the armature) is increased. The power of the ring permanent magnet motor is further increased. To meet the high power requirements of aero-engine fans with medium and large bypass ratios.

Claims (10)

1. The utility model provides an annular permanent-magnet machine of big bypass ratio aeroengine fan in direct drive, includes stator core (7) and is located the inboard electric motor rotor inner ring (2) of stator core (7), its characterized in that: an aircraft engine fan (1) is arranged in the motor rotor inner ring (2), and a permanent magnet (4) is clamped and distributed in an annular space between the motor rotor inner ring (2) and the stator core (7); and a rotor iron core (3) is tightly fixed on the outer ring of the motor rotor inner ring (2).

2. The direct drive, high bypass ratio aircraft engine fan ring permanent magnet machine according to claim 1, wherein: the inner ring (2) of the motor rotor is a main fan mounting ring.

3. The direct drive, high bypass ratio aircraft engine fan ring permanent magnet machine according to claim 1, wherein: the rotor iron core (3) is an annular body and covers the outer annular surface of the inner ring (2) of the motor rotor.

4. The direct drive, high bypass ratio aircraft engine fan ring permanent magnet machine according to claim 1, wherein: stator teeth (6) are tightly attached and fixed on the inner ring of the stator core (7), and stator windings (5) are wound on the stator teeth (6).

5. The direct drive, high bypass ratio aircraft engine fan ring permanent magnet machine according to claim 1, wherein: the permanent magnets (4) are uniformly distributed along the annular space.

6. The direct drive, high bypass ratio aircraft engine fan ring permanent magnet machine according to claim 4, wherein: the stator teeth (6) are uniformly distributed along the inner ring of the stator core (7), and the stator teeth (6) and the permanent magnets (4) are distributed in a staggered manner; the stator teeth (6) are parallel to the permanent magnet (4).

7. The direct drive, high bypass ratio aircraft engine fan ring permanent magnet machine according to claim 1, wherein: the aero-engine fan (1) is coaxially fixed on the motor shaft (8).

8. The direct drive, high bypass ratio aircraft engine fan ring permanent magnet machine according to claim 1, wherein: on the vertical projection plane of the permanent magnet (4), the center line of the permanent magnet (4) is inclined relative to the axial lead of the motor rotor inner ring (2).

9. The direct drive, high bypass ratio aircraft engine fan ring permanent magnet machine according to claim 8, wherein: the inclination angle of the permanent magnet (4) is 5-25 degrees.

10. The direct drive, high bypass ratio aircraft engine fan ring permanent magnet machine according to claim 1, wherein: the number of the permanent magnets (4) is 24, 36, 48 or 60.

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