CN115467852A

CN115467852A - Rotor shafting structure, rotor subassembly and air compressor machine

Info

Publication number: CN115467852A
Application number: CN202211282067.XA
Authority: CN
Inventors: 王红; 李玲玉; 张玉松; 关占帅; 牛树潭; 杜天意; 周敏
Original assignee: Hebei Kingston Technology Co ltd
Current assignee: Hebei Kingston Technology Co ltd
Priority date: 2022-10-19
Filing date: 2022-10-19
Publication date: 2022-12-13

Abstract

The invention provides a rotor shaft system structure, a rotor assembly and an air compressor, belonging to the technical field of air compressors and comprising a radial shaft, a thrust shaft, a sheath and rotor magnetic steel, wherein the rotor magnetic steel is arranged in the sheath, and the radial shaft and the thrust shaft are oppositely arranged; the radial shaft is sequentially provided with a first shaft section, a second shaft section, a third shaft section and a fourth shaft section from outside to inside, and the outer diameters of the first shaft section, the second shaft section, the third shaft section and the fourth shaft section are sequentially decreased; the thrust shaft is sequentially provided with a fifth shaft section, a sixth shaft section, a seventh shaft section and an eighth shaft section from outside to inside, and the outer diameters of the fifth shaft section, the sixth shaft section, the seventh shaft section and the eighth shaft section are sequentially decreased; the first shaft section and the fifth shaft section penetrate through two ports of the sheath respectively and are fixedly arranged and are pressed at two ends of the rotor magnetic steel respectively, and the fourth shaft section and the eighth shaft section are threaded sections. The rotor shafting structure provided by the invention has a more reasonable structure, can ensure the stable installation of the rotor magnetic steel and ensure that the air compressor has higher working efficiency.

Description

Rotor shafting structure, rotor subassembly and air compressor machine

Technical Field

The invention belongs to the technical field of air compressors, and particularly relates to a rotor shafting structure, a rotor assembly and an air compressor.

Background

The air compressor is an air compressor for short, and is used for a fuel cell system to compress clean air and provide the compressed clean air to a fuel cell stack so as to improve the operating efficiency of the fuel cell system.

The rotor is a core component of the air compressor, is positioned between the compressor and the turbine and is matched with the stator to realize autorotation by mounting a belt magnet on the rotor. In the prior art, the structure of the rotor and the structure of the rotor provided with the magnets are often unreasonable, and the working efficiency of the whole air compressor can be directly related.

Disclosure of Invention

The invention aims to provide a rotor shafting structure, which improves the reasonability of the structure of a rotor and the structure of mounting the rotor with magnets and ensures the working efficiency of an air compressor.

In order to achieve the purpose, the invention adopts the technical scheme that: the rotor shaft system structure comprises a radial shaft, a thrust shaft, a sheath and rotor magnetic steel, wherein the rotor magnetic steel is arranged in the sheath, and the radial shaft and the thrust shaft are arranged oppositely;

the radial shaft is sequentially provided with a first shaft section, a second shaft section, a third shaft section and a fourth shaft section from outside to inside, and the outer diameters of the first shaft section, the second shaft section, the third shaft section and the fourth shaft section are sequentially decreased;

the thrust shaft is sequentially provided with a fifth shaft section, a sixth shaft section, a seventh shaft section and an eighth shaft section from outside to inside, and the outer diameters of the fifth shaft section, the sixth shaft section, the seventh shaft section and the eighth shaft section are sequentially decreased;

the first shaft section and the fifth shaft section respectively penetrate through two ports of the sheath to be fixedly arranged and are respectively pressed at two ends of the rotor magnetic steel, and the fourth shaft section and the eighth shaft section are both threaded sections.

In a possible implementation manner, a first weight-reduction chamber is arranged inside the radial shaft, is arranged along the axial direction of the radial shaft, and has one end located on the end face of the first shaft section; and a second weight reduction chamber is arranged in the thrust shaft, is arranged along the axial direction of the thrust shaft, and has one end positioned on the end surface of the fifth shaft section.

In one possible implementation, a first step is formed between the first shaft section and the second shaft section, a second step is formed between the fifth shaft section and the sixth shaft section, and the first step and the second step are flush with two ports of the sheath.

In a possible implementation manner, a first inclined surface is arranged between the third shaft section and the fourth shaft section, and a second inclined surface is arranged between the seventh shaft section and the eighth shaft section.

In a possible implementation manner, the radial shaft, the thrust shaft, and the sheath are all made of nickel-based high-temperature alloy, and the rotor magnetic steel is made of rare earth cobalt permanent magnet alloy.

The rotor shafting structure provided by the invention has the beneficial effects that: compared with the prior art, the radial shaft comprises a first shaft section, a second shaft section, a third shaft section and a fourth shaft section, wherein the outer diameters of the first shaft section, the second shaft section, the third shaft section and the fourth shaft section are sequentially decreased. The thrust shaft comprises a fifth shaft section, a sixth shaft section, a seventh shaft section and an eighth shaft section, wherein the outer diameters of the fifth shaft section, the sixth shaft section, the seventh shaft section and the eighth shaft section are sequentially decreased progressively. The rotor magnetic steel is installed in the sheath, the first shaft section of the radial shaft and the fifth shaft section of the thrust shaft are arranged oppositely, penetrate into the rotor magnetic steel from two ports of the sheath respectively and are pressed at two ends of the rotor magnetic steel respectively, and the first shaft section and the fifth shaft section are fixed at the two ports of the sheath respectively, so that the rotor magnetic steel is stably installed in the sheath. The second shaft section, the third shaft section and the fourth shaft section of the radial shaft, the sixth shaft section, the seventh shaft section and the eighth shaft section of the thrust shaft and a stepped table surface formed between the adjacent shaft sections can provide a mounting surface and a positioning surface for a matched structural member. In addition, the seventh shaft section and the eighth shaft section which are far away from the sheath are respectively threaded sections and are used for installing and positioning the power structural part. The rotor shafting structure provided by the invention has a more reasonable structure, can ensure the stable installation of the rotor magnetic steel and ensure that the air compressor has higher working efficiency.

The invention also provides a rotor assembly which comprises the rotor shaft structure, the third shaft section is sequentially sleeved with a pressure end sealing element and a pressure end impeller from inside to outside, the seventh shaft section is sequentially sleeved with a vortex end sealing element and a vortex end impeller from inside to outside, the third shaft section or the seventh shaft section is sleeved with a thrust disc, the thrust disc is pressed on the inner side of the pressure end sealing element or the vortex end sealing element, and the outer ends of the fourth shaft section and the eighth shaft section are respectively provided with a locking nut.

The rotor assembly provided by the invention has the beneficial effects that: compared with the prior art, pressure end sealing member and pressure end impeller install on the third shaft section in proper order from inside to outside, and vortex end sealing member and vortex end impeller install on the seventh shaft section in proper order from inside to outside, and the outer end of fourth shaft section and eighth shaft section all is equipped with lock nut to respectively will press end impeller and pressure end sealing member to compress tightly in proper order, and compress tightly vortex end impeller and vortex end sealing member in proper order. The thrust disc can be arranged on the third shaft section or the seventh shaft section and is arranged on the inner side of the pressure end sealing element or the vortex end sealing element in a pressing mode.

When the thrust disc is installed on the third shaft section, because the axial force direction of rotor is from turbine end impeller finger pressure end impeller department, so during normal operation, footstep bearing pastes tight thrust bearing seat, and the axial elongation begins to calculate from thrust disc department, because this structure pressure end impeller is nearer from the thrust disc, so the shaft section heat elongation from thrust disc to pressure end impeller department is less negligible, so pressure end impeller and clearance when volute design clearance approximately equals the normal operation of host computer, can guarantee pressure end impeller and pressure end volute clearance like this, can guarantee air compressor machine compressor's compression efficiency.

When the thrust disc is arranged on the seventh shaft section, the mass of the pressure end impeller is larger than that of the vortex end impeller, the thrust bearing and the thrust disc are arranged at the vortex end impeller, the weight of the impeller is balanced, the vibration of the whole machine is reduced, the temperature of the vortex end side is relatively low, the heat dissipation of the thrust bearing is facilitated, and the service life of the thrust bearing is prolonged.

The invention also provides an air compressor comprising the rotor assembly.

The air compressor provided by the invention has the beneficial effects that: compared with the prior art, the air compressor provided by the invention mainly comprises a compressor end, a turbine end and the rotor assembly, wherein the compressor and the turbine are coaxial. The tail gas of the fuel cell with certain pressure enters the end of the turbine to push the turbine to rotate, so as to drive the shaft of the air compressor to rotate, and further drive the impeller at the pressure end to rotate to compress air. The tail gas energy of the fuel cell system is fully utilized, and the system efficiency is improved.

The air compressor provided by the invention also comprises a motor, wherein an output shaft of the motor is coaxial with the compressor and the turbine, the motor rotates to drive the impeller of the compressor to rotate so as to compress air, an air inlet of the turbine is connected with tail gas of the fuel cell, and the tail gas of the fuel cell pushes the impeller of the turbine to rotate to assist in pushing the motor shaft to rotate, so that the energy consumption of the motor is reduced, and the efficiency of the air compressor is further improved.

Drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed for the embodiments or the prior art descriptions will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.

Fig. 1 is a cross-sectional structural view of a rotor shafting structure provided in an embodiment of the present invention;

FIG. 2 is a cross-sectional structural view of a rotor shafting structure according to another embodiment of the present invention;

FIG. 3 is a schematic diagram of a thrust plate installed at a compression end according to an embodiment of the present invention;

fig. 4 is a schematic structural diagram of a thrust disk installed at a scroll end according to an embodiment of the present invention.

Description of the reference numerals:

100. rotor magnetic steel; 110. positioning a block; 200. a sheath; 300. a radial axis; 310. a first shaft section; 320. a second shaft section; 330. a third shaft section; 340. a fourth shaft section; 350. a first weight-reduction chamber; 360. a first step table; 370. a third terrace; 380. a first inclined surface; 400. a thrust shaft; 410. a fifth shaft section; 420. a sixth shaft section; 430. a seventh shaft section; 440. an eighth shaft segment; 450. a second weight-reduction chamber; 460. a second step; 470. a fourth step; 480. a second inclined surface; 500. a press end seal; 600. a pressure end impeller; 700. a scroll end seal; 800. a vortex end impeller; 900. a thrust plate; 1000. and locking the nut.

Detailed Description

In order to make the technical problems, technical solutions and advantageous effects to be solved by the present invention more clearly apparent, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

Referring to fig. 1 and fig. 2, a rotor shaft structure according to the present invention will now be described. The rotor shafting structure comprises a radial shaft 300, a thrust shaft 400, a sheath 200 and rotor magnetic steel 100, wherein the rotor magnetic steel 100 is arranged in the sheath 200, and the radial shaft 300 and the thrust shaft 400 are oppositely arranged; the radial shaft 300 is sequentially provided with a first shaft section 310, a second shaft section 320, a third shaft section 330 and a fourth shaft section 340 from outside to inside, and the outer diameters of the first shaft section 310, the second shaft section 320, the third shaft section 330 and the fourth shaft section 340 are sequentially decreased progressively; the thrust shaft 400 is sequentially provided with a fifth shaft section 410, a sixth shaft section 420, a seventh shaft section 430 and an eighth shaft section 440 from outside to inside, and the outer diameters of the fifth shaft section 410, the sixth shaft section 420, the seventh shaft section 430 and the eighth shaft section 440 are sequentially decreased progressively; the first shaft section 310 and the fifth shaft section 410 respectively penetrate through two ports of the sheath 200 to be fixedly arranged and are respectively pressed on two ends of the rotor magnetic steel 100, and the fourth shaft section 340 and the eighth shaft section 440 are both threaded sections.

Compared with the prior art, the rotor shafting structure provided by the invention has the advantages that the radial shaft 300 comprises a first shaft section 310, a second shaft section 320, a third shaft section 330 and a fourth shaft section 340, wherein the outer diameters of the first shaft section 310, the second shaft section 320, the third shaft section 330 and the fourth shaft section 340 are sequentially decreased in a descending manner. Thrust shaft 400 includes fifth shaft segment 410, sixth shaft segment 420, seventh shaft segment 430 and eighth shaft segment 440, which have successively decreasing outer diameters. The rotor magnetic steel 100 is installed inside the sheath 200, the first shaft section 310 of the radial shaft 300 and the fifth shaft section 410 of the thrust shaft 400 are oppositely arranged, penetrate into the sheath 200 from two ports of the sheath 200 respectively and are pressed at two ends of the rotor magnetic steel 100 respectively, and the first shaft section 310 and the fifth shaft section 410 are fixed at two ports of the sheath 200 respectively, so that the rotor magnetic steel 100 is stably installed in the sheath 200. The second, third and

fourth shaft segments

320, 330, 340 of the radial shaft 300, the sixth, seventh and

eighth shaft segments

420, 430, 440 of the thrust shaft 400, and the stepped lands formed between adjacent shaft segments can provide mounting and locating surfaces for mating structural members. In addition, the seventh shaft segment 430 and the eighth shaft segment 440 away from the sheath 200 are respectively threaded segments for installing and positioning the power structural member. The rotor shaft system structure provided by the invention has a more reasonable structure, can ensure the stable installation of the rotor magnetic steel 100, and ensures that the air compressor has higher working efficiency.

Specifically, the radial shaft 300, the thrust shaft 400, and the sheath 200 are all made of nickel-based high-temperature alloy, and the rotor magnetic steel 100 is made of rare earth cobalt permanent magnet alloy. The sheath 200 connects the thrust shaft 400 of the radial shaft 300 and the rotor magnetic steel 100 into a whole.

The thrust shaft 400, the radial shaft 300 and the sheath 200 are made of GH4169, and the rotor magnetic steel 100 is made of SM-30U rare earth cobalt permanent magnet material. Because rotor magnet steel 100 can not be welded, so sheath 200, thrust shaft 400 and radial shaft 300 select for use the same material, when the welding, fixes rotor magnet steel 100 in the inner chamber of sheath 200, makes it keep stable.

The GH4169 material is a precipitation-strengthened nickel-based high-temperature alloy, has good comprehensive performance within the temperature range of-253-650 ℃, has the yield strength below 650 ℃ at the first position of the deformation high-temperature alloy, and has good fatigue resistance, radiation resistance, oxidation resistance, corrosion resistance, processability and welding performance.

The good welding performance of the GH4169 material itself ensures good welding of the thrust shaft 400, the radial shaft 300, and the sheath 200. When the thrust shaft 400, the radial shaft 300 and the sheath 200 are welded, the first shaft section 310 of the radial shaft 300 is inserted into one port of the sheath 200, and the first step 360 formed by the first shaft section 310 and the second shaft section 320 is flush with the port of the sheath 200, so that a groove can be formed at an annular welding seam for welding. Similarly, the fifth shaft section 410 of the thrust shaft 400 is inserted into another port of the sheath 200, and the second step 460 formed by the fifth shaft section 410 and the sixth shaft section 420 is flush with the port of the sheath 200, so that a groove can be formed at the circumferential weld for welding. After the thrust shaft 400, the radial shaft 300 and the sheath 200 are welded, the first step 360 and the second step 460 are ground and polished.

In addition, when the rotor works, the circumferential direction of the rotor has a large torsional force, especially when the rotor suddenly accelerates, decelerates or changes the steering direction, in order to further ensure the stability of the thrust shaft 400, the radial shaft 300 and the sheath 200 and avoid the situation that the connection structure of the three is unstable in structure and causes circumferential relative displacement after being used for a long time, the positioning block 110 is arranged at the position, close to the port, of the inner wall of the sheath 200, and similarly, the first shaft section 310 and the fifth shaft section 410 are provided with corresponding clamping grooves so as to realize the dual connection relationship that the radial shaft 300, the thrust shaft 400 and the sheath 200 form clamping and combined welding.

Referring to fig. 1 and 2, a first inclined surface 380 is disposed between the third shaft segment 330 and the fourth shaft segment 340, a second inclined surface 480 is disposed between the seventh shaft segment 430 and the eighth shaft segment 440, and the first inclined surface 380 and the second inclined surface 480 are transition surfaces disposed in a circumferential direction, so as to form a tapered platform capable of cooperating with a dynamic structural member, such as a central hole of an impeller. Preferably, the first inclined surface 380 and the second inclined surface 480 are inclined at 45 degrees, and the two inclined sides of the section of the tapered platform form an included angle a and b of 90 degrees.

Referring to fig. 2, the first weight-reducing chamber 350 is formed inside the radial shaft 300 in the axial direction, one end of the first weight-reducing chamber 350 extends to the end surface of the first shaft section 310, and the other end extends to the position of the second shaft section 320 close to the third shaft section 330, and in order to increase the self-weight of the radial shaft 300, the width of the first weight-reducing chamber 350 may be set to the same size as the outer diameter of the third shaft section 330. Similarly, the second weight-reducing chamber 450 is disposed inside the thrust shaft 400 along the circumferential direction thereof, and the structure and the arrangement thereof are the same as those of the first weight-reducing chamber 350, and are not described herein again.

In addition, the first weight-reducing chamber 350 is a prismatic chamber, a protruding block is arranged at the end of the rotor magnetic steel 100, the protruding block is matched with the inner cavity of the prismatic chamber, the radial shaft 300 is in inserted fit with the protruding block through the first weight-reducing chamber 350, the radial shaft 300 and the rotor magnetic steel 100 are coaxially arranged, and coaxiality of the rotor magnetic steel 100 and the sheath 200 can be ensured. In order to ensure that the first weight-reducing chamber 350 can be smoothly sleeved on the protruding block, a guiding inclined plane is arranged at the end part of the first weight-reducing chamber 350, and a matching inclined plane matched with the guiding inclined plane is arranged on the protruding block. Similarly, the second weight-reducing chamber 450 is also a prismatic chamber, which has the same structure and assembly manner as the first weight-reducing chamber 350, and is not described herein again.

Referring to fig. 3, the present invention further provides a rotor assembly, including the above-mentioned rotor shafting structure, the third shaft section 330 is sequentially sleeved with a pressure end sealing element 500 and a pressure end impeller 600 from inside to outside, the seventh shaft section 430 is sequentially sleeved with a vortex end sealing element 700 and a vortex end impeller 800 from inside to outside, the third shaft section 330 or the seventh shaft section 430 is sleeved with a thrust disk 900, the thrust disk 900 is press-mounted on the inner side of the pressure end sealing element 500 or the vortex end sealing element 700, and the outer ends of the fourth shaft section 340 and the eighth shaft section 440 are respectively provided with a locking nut 1000.

Compared with the prior art, the rotor shaft system structure provided by the invention has the advantages that the pressure end sealing element 500 and the pressure end impeller 600 are sequentially arranged on the third shaft section 330 from inside to outside, the vortex end sealing element 700 and the vortex end impeller 800 are sequentially arranged on the seventh shaft section 430 from inside to outside, and the outer ends of the fourth shaft section 340 and the eighth shaft section 440 are respectively provided with the locking nut 1000, so that the pressure end impeller 600 and the pressure end sealing element 500 are respectively and sequentially compressed, and the vortex end impeller 800 and the vortex end sealing element 700 are sequentially compressed. The thrust disk 900 is further mounted on the rotor shaft system structure, and the thrust disk 900 may be mounted on the third shaft section 330 or the seventh shaft section 430 and press-fitted on the third step 370 inside the pressure end seal 500 or the fourth step 470 inside the scroll end seal 700.

When the thrust disk 900 is installed on the third shaft section 330, since the axial force direction of the rotor is from the turbine-end impeller 800 to the pressure-end impeller 600, during normal operation, the thrust bearing is attached to the thrust bearing seat, and the axial elongation is calculated from the thrust disk 900, since the pressure-end impeller 600 is close to the thrust disk 900, the heat elongation of the shaft section from the thrust disk 900 to the pressure-end impeller 600 is negligible, so the designed clearance between the pressure-end impeller 600 and the volute is about equal to the clearance during normal operation of the host machine, thus the clearance between the pressure-end impeller 600 and the pressure-end volute can be ensured, and the compression efficiency of the air compressor can be ensured.

When the thrust disk 900 is installed on the seventh shaft section 430, since the mass of the pressure end impeller 600 is greater than that of the vortex end impeller 800, the thrust bearing and the thrust disk 900 are placed at the vortex end impeller 800, the weight of the impeller is balanced, so that the vibration of the whole machine is reduced, the temperature of the vortex end side is relatively low, the heat dissipation of the thrust bearing is facilitated, and the service life of the thrust bearing is prolonged.

The material of the pressure end impeller 600 is aluminum, and the material of the vortex end impeller 800 is stainless steel, and the diameter of the pressure end impeller 600 is larger than that of the vortex end impeller 800. The pressure end impeller 600 is an aluminum impeller, and the vortex end impeller 800 is a stainless steel impeller, so that the weight of the two ends of the rotor can be balanced. In addition, because the turbine end is directly connected with the hydrogen fuel reactor tail gas, the reaction tail gas contains a large amount of water vapor, the water vapor has a certain water erosion effect on the vortex-end impeller 800, the reactor tail gas is weakly acidic and has a certain corrosion effect on the vortex-end impeller 800, and in order to avoid the corrosion of the vortex-end impeller 800, the vortex-end impeller 800 is made of stainless steel impellers.

The turbine impeller 800 can be made of 17-4PH stainless steel, and the corrosion resistance is superior to that of an aluminum impeller. Meanwhile, a plating layer and a corrosion-resistant plating layer are sequentially attached to the surface of the vortex-end impeller 800. The adhesion coating can increase the outer surface adhesion of the vortex end impeller 800, and facilitates the coating of the corrosion-resistant coating. The adhesion coating is made of CrAl, the corrosion-resistant coating is a nitride coating made of TiAlN or CRSiN, surface hardness can be increased, the outer surface hardness of the vortex-end impeller 800 can reach 2000Hv, the surface friction coefficient of the impeller is reduced, and the corrosion resistance of the impeller is improved.

In addition, the blade of pressure end impeller 600 includes two kinds, one kind is short blade, one kind is long blade, and long blade and short blade interval are arranged in turn, realize balanced drainage, improve the effect of drainage. Similarly, the number of the gas guide vanes can be increased and the pressure ratio can be increased on the premise of ensuring the gas flow.

The pressure end sealing element 500 and the vortex end sealing element 700 are in the form of sealing ring sealing or labyrinth sealing, and the pressure end sealing element 500 and the vortex end sealing element 700 are made of 17-4PH stainless steel, so that the corrosion resistance is improved.

The invention also provides an air compressor using the rotor assembly.

The air compressor provided by the invention mainly comprises a compressor end, a turbine end and the rotor assembly, wherein the compressor and the turbine are coaxial. The end of the fuel cell exhaust gas with a certain pressure enters the turbine end to push the turbine to rotate, so as to drive the air compressor shaft to rotate, and further drive the pressure end impeller 600 to rotate to compress air. The tail gas energy of the fuel cell system is fully utilized, and the system efficiency is improved.

The air compressor provided by the invention also comprises a motor, wherein the output shaft of the motor is coaxial with the compressor and the turbine, the motor rotates to drive the impeller of the compressor to rotate so as to compress air, the air inlet of the turbine is connected with the tail gas of the fuel cell, and the tail gas of the fuel cell pushes the impeller of the turbine to rotate to assist in pushing the motor shaft to rotate, so that the energy consumption of the motor is reduced, and the efficiency of the air compressor is further improved.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.

Claims

1. The rotor shafting structure is characterized by comprising a radial shaft (300), a thrust shaft (400), a sheath (200) and rotor magnetic steel (100), wherein the rotor magnetic steel (100) is arranged inside the sheath (200), and the radial shaft (300) and the thrust shaft (400) are arranged oppositely;

the radial shaft (300) is sequentially provided with a first shaft section (310), a second shaft section (320), a third shaft section (330) and a fourth shaft section (340) from outside to inside, and the outer diameters of the first shaft section (310), the second shaft section (320), the third shaft section (330) and the fourth shaft section (340) are sequentially decreased progressively;

the thrust shaft (400) is sequentially provided with a fifth shaft section (410), a sixth shaft section (420), a seventh shaft section (430) and an eighth shaft section (440) from outside to inside, and the outer diameters of the fifth shaft section (410), the sixth shaft section (420), the seventh shaft section (430) and the eighth shaft section (440) are sequentially decreased progressively;

the first shaft section (310) and the fifth shaft section (410) penetrate into two ports of the sheath (200) respectively and are fixedly arranged and tightly pressed at two ends of the rotor magnetic steel (100) respectively, and the fourth shaft section (340) and the eighth shaft section (440) are threaded sections.

2. Rotor shafting structure according to claim 1, wherein said radial shaft (300) is internally provided with a first weight-reduction chamber (350), said first weight-reduction chamber (350) being arranged in the axial direction of said radial shaft (300) with one end on the end face of said first shaft section (310); a second weight reduction chamber (450) is arranged inside the thrust shaft (400), the second weight reduction chamber (450) is arranged along the axial direction of the thrust shaft (400), and one end of the second weight reduction chamber is located on the end face of the fifth shaft section (410).

3. The rotor shafting structure as in claim 1, wherein a first step (360) is formed between the first shaft section (310) and the second shaft section (320), and a second step (460) is formed between the fifth shaft section (410) and the sixth shaft section (420), and the first step (360) and the second step (460) are flush with two ports of the jacket (200).

4. A rotor shaft system structure according to claim 1, characterised in that a first inclined surface (380) is provided between said third shaft section (330) and said fourth shaft section (340), and a second inclined surface (480) is provided between said seventh shaft section (430) and said eighth shaft section (440).

5. The rotor shafting structure according to any one of claims 1 to 4, wherein the radial shaft (300), the thrust shaft (400) and the sheath (200) are all made of nickel-based high-temperature alloy, and the rotor magnetic steel (100) is made of rare earth cobalt permanent magnet alloy.

6. A rotor assembly, comprising a rotor shafting structure according to any one of claims 1 to 5, wherein the third shaft section (330) is sleeved with a pressure end seal (500) and a pressure end impeller (600) in sequence from inside to outside, the seventh shaft section (430) is sleeved with a vortex end seal (700) and a vortex end impeller (800) in sequence from inside to outside, the third shaft section (330) or the seventh shaft section (430) is sleeved with a thrust disk (900), the thrust disk (900) is pressed on the inner side of the pressure end seal (500) or the vortex end seal (700), and the outer ends of the fourth shaft section (340) and the eighth shaft section (440) are provided with locking nuts (1000).

7. The rotor assembly of claim 6, wherein the nose impeller (600) is aluminum, the vortex impeller (800) is stainless steel, and the diameter of the nose impeller (600) is greater than the diameter of the vortex impeller (800).

8. The rotor assembly of claim 6, wherein the surface of the turbine wheel (800) is provided with an adhesion coating and a corrosion resistant coating in sequence.

9. An air compressor, characterized by comprising the rotor assembly of any one of claims 6 to 8.