CN211343141U

CN211343141U - Rotor system and micro gas turbine generator set

Info

Publication number: CN211343141U
Application number: CN201922357500.1U
Authority: CN
Inventors: 靳普; 刘慕华
Original assignee: Xunling Tengfeng Automotive Power Technology Beijing Co ltd
Current assignee: Yongxu Tengfeng New Energy Power Technology Beijing Co ltd; Zhiyue Tengfeng Technology Group Co ltd
Priority date: 2019-12-25
Filing date: 2019-12-25
Publication date: 2020-08-25
Anticipated expiration: 2029-12-25

Abstract

The utility model provides a rotor system and miniature gas turbine generating set, include: the rotating shaft is of an integrally formed structure; the integrated bearing, the motor, the radial bearing, the compressor and the turbine are sequentially arranged on the rotating shaft; the integrated bearing and the motor are provided with a first air inlet channel which penetrates through the integrated bearing and the motor along the axial direction, and the first air inlet channel is communicated with the air inlet of the air compressor. In the system, the bearing shell and the stator part of the generator are provided with air inlet channels, air inlet of the air compressor can enter the air compressor through the air inlet channels in the bearing shell and the stator of the generator, on one hand, the air inlet of the air compressor can cool a coil winding of the stator of the generator, on the other hand, the air inlet of the air compressor does not need to go around, the axial length of a rotor system does not need to be increased, and sufficient air inlet of the air compressor can be ensured.

Description

Rotor system and micro gas turbine generator set

Technical Field

The utility model relates to a rotor dynamics technical field especially relates to a rotor system and miniature gas turbine generating set.

Background

In the field of micro gas turbine power generation, a micro gas turbine power generator set generally includes a coaxially mounted generator and a micro gas turbine. Specifically, the micro gas turbine mainly comprises three parts, namely a compressor, a combustion chamber and a turbine. The air is compressed into high-temperature and high-pressure air after entering the air compressor, then the high-temperature and high-pressure air is supplied to the combustion chamber to be mixed and combusted with fuel, the generated high-temperature and high-pressure gas expands in the turbine to do work, the turbine is pushed to rotate, and the generator is driven to generate electricity. Because the magnetic components and coil windings in the generator are not resistant to high temperature, the generator cannot be installed at the hot end of the rotor system, namely, at the turbine side. In the prior art, a generator is generally installed at an air inlet end of a micro gas turbine, namely an air inlet end of a compressor. However, the generator is arranged at the air inlet end of the rotor system, so that air inlet of the air compressor is easily blocked, the air inlet of the air compressor is insufficient, and the overall efficiency of the micro gas turbine generator set is further influenced. In the prior art, the air inlet of the air compressor is arranged at the outer side of the generator, namely, the air bypasses the stator of the generator and enters the air compressor; or in the axial direction, the generator and the compressor are spaced at a certain distance to ensure sufficient air inlet of the compressor. The first scheme easily causes the technical problems of unsmooth and insufficient operation of the gas compressor, poor heat dissipation of the generator and the like; and the second scheme can cause the axial length of the whole rotor system to be lengthened, and the lengthened axial length of the rotor system can influence the running stability of the whole rotor system.

SUMMERY OF THE UTILITY MODEL

In order to solve the technical problem, an object of the utility model is to provide a rotor system and miniature gas turbine generating set, in this system, the stator part of its bearing housing and generator is provided with the intake duct, the intake duct in the stator of the accessible bearing housing of admitting air of compressor and generator gets into the compressor, the coil winding of generator stator can be cooled off in admitting air of compressor on the one hand, the air inlet of on the other hand compressor also need not be walked around, also need not increase rotor system's axial length, and can guarantee the sufficient of compressor and admit air.

The technical scheme of the utility model as follows:

according to an aspect of the present invention, there is provided a rotor system, comprising:

the rotating shaft is of an integrally formed structure;

the integrated bearing, the motor, the radial bearing, the compressor and the turbine are sequentially arranged on the rotating shaft;

the integrated bearing and the motor are provided with a first air inlet channel which penetrates through the integrated bearing and the motor along the axial direction, and the first air inlet channel is communicated with the air inlet of the air compressor.

Furthermore, the rotating shaft comprises a first shaft section and a second shaft section, the diameter of the first shaft section is larger than that of the second shaft section, and a step surface is formed at the transition position of the first shaft section and the second shaft section;

the integrated bearing, the motor and the radial bearing are arranged on the first shaft section, the compressor and the turbine are arranged on the second shaft section, and one end of the compressor is abutted to the step surface.

Further, the integrated bearing is an integrated air bearing, which includes:

the thrust disc is fixedly connected with the rotating shaft or integrally formed;

the thrust disc is sleeved on the rotating shaft, the first bearing body and the second bearing body are positioned on two sides of the thrust disc, the first bearing body is provided with a radial bearing part and a thrust bearing part which are integrally formed, the radial bearing part and the rotating shaft have a preset radial gap in the radial direction, the thrust bearing part and the thrust disc are installed in an opposite mode in the axial direction and have a preset first axial gap, and the second bearing body and the thrust disc are installed in an opposite mode in the axial direction and have a preset second axial gap;

the first bearing shell covers the peripheries of the first bearing body, the thrust disc and the second bearing body;

the first bearing end cover is arranged at one end of the second bearing body of the rotating shaft and is used for fixing the second bearing body in the axial direction;

the first air inlet passage penetrates through a first bearing shell of the integrated bearing.

Further, the radial bearing part of the integrated bearing is installed towards one end far away from the motor;

alternatively, the radial bearing portion of the integrated bearing is mounted toward one end close to the motor.

Further, a first anti-rotation member is arranged between the first bearing housing and the first bearing body and/or between the first bearing housing and the second bearing body, and the first anti-rotation member is used for circumferentially fixing the first bearing body relative to the first bearing housing and/or the second bearing body relative to the first bearing housing.

Further, the radial bearing is any one of a dynamic pressure gas bearing, a static pressure gas bearing or a dynamic and static pressure gas bearing;

the radial bearing comprises a third bearing body, a second bearing shell and a second bearing end cover, wherein the second bearing shell cover is arranged on one axial end face and the periphery of the third bearing body, the second bearing end cover is sleeved on the rotating shaft and abutted against one end face of the second bearing shell, a second anti-rotation component is arranged between the second bearing shell and the third bearing body, and the second anti-rotation component is used for fixing the third bearing body in the circumferential direction relative to the second bearing shell.

Further, the motor comprises a motor stator and a motor shell;

the motor stator is sleeved on the rotating shaft and keeps a certain gap with the rotating shaft in the radial direction, and the motor shell is covered on the periphery of the motor stator;

the first air inlet channel penetrates through the motor stator.

Further, the motor stator comprises a stator core and a stator winding;

the stator core is cylindrical, and a through hole for mounting the rotating shaft is formed in the center of the cylinder;

a plurality of outer wire grooves which extend along the axial direction of the cylinder and are uniformly distributed along the circumferential direction of the cylinder are formed on the outer diameter side of the stator core, and a plurality of inner wire grooves which extend along the axial direction of the cylinder and are uniformly distributed along the circumferential direction of the cylinder are formed on the inner diameter side of the stator core;

the stator winding is wound in the outer wire slot and the inner wire slot along the axial direction of the cylinder, and the first air inlet channel is formed in the inner wire slot.

Further, still be provided with the second intake duct between the motor stator of motor and the motor casing, the second intake duct communicates with the admitting air of compressor.

Furthermore, a reinforcing ring is arranged between the compressor and the turbine.

According to another aspect of the present invention, a micro gas turbine generator set is provided, which comprises the above rotor system, the motor casing, the gas turbine casing and the combustion chamber;

the gas turbine engine comprises a motor, a gas turbine, a gas compressor, a gas turbine, a motor casing, a gas turbine, a gas compressor, a gas turbine;

the combustion chamber is connected with the gas turbine casing, the air inlet of the combustion chamber is connected with the air outlet of the air compressor, and the air outlet of the combustion chamber is connected with the air inlet of the turbine.

Furthermore, a diffuser is arranged between the exhaust port of the air compressor and the air inlet of the combustion chamber.

Compared with the prior art, the utility model discloses following beneficial effect has:

1. the utility model discloses a rotor system's the mode of admitting air and the setting of intake duct position for the heat dissipation that the abundant and be favorable to the motor of admitting air of compressor, whole rotor system's axial dimensions is short, and rotor system's dynamic characteristic is good.

2. The utility model discloses a rationally distributed of each part among the rotor system, rotor operation stationarity is good.

3. The utility model discloses an integral type bearing of rotor system's simple structure, and machining precision and assembly precision are high.

4. The utility model discloses a motor among the rotor system is provided with the intake duct, and the heat dissipation is good, and axial dimensions is short.

5. The utility model discloses an air bearing among the rotor system can prevent the rotation of bearing body under the high-speed rotatory condition, operates steadily, and the bearing is longe-lived.

6. Use the utility model discloses a rotor system's miniature gas turbine generating set, it is low to machining precision and assembly accuracy requirement, with low costs, be fit for engineering batch production.

Drawings

Fig. 1 is a schematic diagram of a rotor system structure according to the present invention.

Fig. 2 is a structural diagram of an integrated gas bearing according to an embodiment of the present invention.

Fig. 3 is a front view of a first bearing body according to an embodiment of the present invention.

Fig. 4 is a left side view of a first bearing body according to an embodiment of the present invention.

Fig. 5 is a structural diagram of an annular groove according to an embodiment of the present invention.

Fig. 6 is a first air tank structure diagram according to an embodiment of the present invention.

Fig. 7 is a structural view of a second air tank according to an embodiment of the present invention.

Fig. 8 is a schematic diagram of another rotor system structure according to the present invention.

Fig. 9 is a motor structure diagram according to a second embodiment of the present invention.

Fig. 10 is a half-sectional view of a motor according to a second embodiment of the present invention.

Fig. 11 is a structural view of a motor stator core according to a second embodiment of the present invention.

Fig. 12 is a structural view of a silicon steel sheet according to a second embodiment of the present invention.

Fig. 13 is a structural view of an end face wire slot according to a second embodiment of the present invention.

Fig. 14 is a first structure view of an anti-rotation member according to a third embodiment of the present invention.

Fig. 15 is a cross-sectional view taken along a-a in fig. 14.

Fig. 16 is a second structure view of an anti-rotation member according to a third embodiment of the present invention.

Fig. 17 is a cross-sectional view taken along a-a in fig. 16.

Fig. 18 is a third structure view of an anti-rotation member according to a third embodiment of the present invention.

Fig. 19 is a cross-sectional view taken along a-a in fig. 18.

Fig. 20 is a fourth structural view of an anti-rotation member according to a third embodiment of the present invention.

Fig. 21 is a cross-sectional view taken along a-a in fig. 20.

Fig. 22 is a fifth structural view of an anti-rotation member according to a third embodiment of the present invention.

Fig. 23 is a cross-sectional view taken along a-a in fig. 22.

Fig. 24 is a sixth structural view of an anti-rotation member according to a third embodiment of the present invention.

Fig. 25 is a cross-sectional view taken along a-a in fig. 24.

Fig. 26 is a first structure view of an anti-rotation member according to a fourth embodiment of the present invention.

Fig. 27 is a cross-sectional view taken along a-a of fig. 26.

Fig. 28 is a second structure view of an anti-rotation member according to a fourth embodiment of the present invention.

Fig. 29 is a cross-sectional view taken along a-a in fig. 28.

Fig. 30 is a third structural view of an anti-rotation member according to a fourth embodiment of the present invention.

Fig. 31 is a cross-sectional view taken along a-a in fig. 30.

Fig. 32 is a fourth structure view of an anti-rotation member according to a fourth embodiment of the present invention.

Fig. 33 is a cross-sectional view taken along a-a in fig. 32.

Fig. 34 is a fifth structural view of an anti-rotation member according to a fourth embodiment of the present invention.

Fig. 35 is a cross-sectional view taken along a-a in fig. 34.

Fig. 36 is a sixth structural view of an anti-rotation member according to a fourth embodiment of the present invention.

Fig. 37 is a cross-sectional view taken along a-a in fig. 36.

Detailed Description

In order to better understand the technical solution of the present invention, the present invention will be further explained with reference to the following specific embodiments and the accompanying drawings.

According to an aspect of the present invention, a rotor system is provided.

As shown in fig. 1, it includes:

the rotating shaft 100, the rotating shaft 100 includes a first shaft segment 110 and a second shaft segment 120 which are integrally formed, the diameter of the first shaft segment 110 is greater than that of the second shaft segment 120, and a step surface 130 is formed at the transition position of the first shaft segment 110 and the second shaft segment 120;

the integrated bearing 200, the motor 400, the radial bearing 300, the compressor 500 and the turbine 600 are sequentially arranged on the rotating shaft 100, wherein the integrated bearing 200, the motor 400 and the radial bearing 300 are arranged on the first shaft section 110, the compressor 500 and the turbine 600 are arranged on the second shaft section 120, and one end of the compressor 500 is abutted to the step surface 130;

the integrated bearing 200 and the motor 400 are provided with a first air inlet channel P1, and the first air inlet channel P1 is communicated with the air inlet of the compressor 500.

Through the layout of the rotor system and the arrangement of the air inlet channel on the integrated bearing 200 and the motor 400, the structure of the rotor system of the utility model is compact and simple; and the installation of the bearing and the motor can not block the air inlet of the compressor 500, and meanwhile, the axial dimension of the rotor system is short, and the running stability of the rotor system is good.

Example one

In the present embodiment, a structure of the integrated bearing 200 is provided. The integrated bearing 200 is an integrated air bearing that provides both radial and axial support.

As shown in fig. 2 and 3, the integrated bearing 200 includes: a first bearing body 2200, a thrust disc 2300, a second bearing body 2400; the thrust disc 2300 is fixedly connected with the rotating shaft 100 or integrally formed; the first bearing body 2200 and the second bearing body 2400 are both sleeved on the rotating shaft 100 and located on two sides of the thrust disc 2300; the first bearing body 2200 has a radial bearing portion 2210 and a thrust bearing portion 2220 which are integrally formed, the radial bearing portion 2210 and the rotating shaft 100 have a predetermined radial gap S1 in the radial direction, and the thrust bearing portion 2220 is mounted opposite to the thrust disk 2300 in the axial direction and has a predetermined first axial gap S2; the second bearing body 2400 is mounted axially opposite the thrust disk 2300 with a predetermined second axial gap S3; the integrated bearing 200 further includes a first bearing housing 2500 and a first bearing end cover 2600, the first bearing housing 2500 is covered on the peripheries of the first bearing body 2200, the thrust disc 2300 and the second bearing body 2400, the first bearing end cover 2600 is mounted on one end of the second bearing body 2400 of the rotating shaft 100, the second bearing body 2400 is fixed in the axial direction, and the first bearing housing 2500 is in transition fit with the first bearing housing 2600.

The first inlet passage P1 is provided in the first bearing housing 2500 of the integrated bearing.

Specifically, the integrated gas bearing of the present embodiment may be any one of a static pressure gas bearing, a dynamic pressure gas bearing, or a hybrid dynamic and static pressure gas bearing.

When the first bearing body 2200 is provided as a static pressure gas bearing, a first annular air chamber 2230 is provided between the outer periphery of the radial bearing portion 2210 of the first bearing body 2200 and the first bearing housing 2500, and a first through hole 2240 penetrating the first annular air chamber 2230 and the radial gap S1 is provided at the bottom of the first annular air chamber 2230;

a second annular air cavity 2250 is disposed between the thrust bearing portion 2220 of the first bearing body 2200 and the first bearing housing 2500, and a second through hole 2260 penetrating through the second annular air cavity 2250 and the first axial gap S2 is disposed at the bottom of the second annular air cavity 2250;

a third annular air cavity 2270 is arranged between the second bearing body 2400 and the first bearing end cover 2600, and a third through hole 2280 penetrating through the third annular air cavity 2270 and a second axial gap S3 is arranged at the bottom of the third annular air cavity 2270;

meanwhile, the first bearing housing 2500 is also provided with a first air inlet 2510 and a second air inlet 2520 which are used for communicating the first annular air cavity 2230 and the second annular air cavity 2250 with an external air source, and the first bearing end cover 2600 is provided with a third air inlet 2610 which is used for communicating the third annular air cavity 2270 with the external air source.

Preferably, as shown in fig. 3, in this embodiment, the first through hole 2240, the second through hole 2260, and the third through hole 2280 are all set as step holes, specifically: the diameter of one side of the stepped hole, which is far away from the gap, is large, the diameter of one side of the stepped hole, which is close to the gap, is small, and the section of the reducing part of the stepped hole can be funnel-shaped or conical. This facilitates machining without affecting the gas pressure in the gap. Because the aperture of the air inlet hole needs to be smaller than a certain value in order to satisfy the air pressure in the gap, the air inlet hole with a small diameter is difficult to process and is easy to block.

Meanwhile, as shown in fig. 4, an annular groove 2241 is circumferentially provided on an inner wall of the first bearing body 2200 of the present embodiment, and the first through hole 2240 partially or entirely intersects with the annular groove 2241.

Preferably, the width W of the annular groove 2241 > the diameter D of the first through hole 2240, the first through hole 2240 is located in the annular groove 2241, or the first through hole 2240 is tangent to one side of the annular groove 2241, or the first through hole 2240 partially intersects the annular groove 2241.

Preferably, the annular groove 2241 has a width W equal to the diameter D of the first through hole 2240, and the first through hole 2240 is tangent to both sides of the annular groove 2241.

Preferably, the width W of the annular groove 2241 < the diameter D of the first through hole 2240, and the first through hole 2240 partially intersects the annular groove 2241.

Preferably, the depth H of the annular groove 2241 is larger than or equal to the diameter D of the first through hole 2240.

Because the first through holes 2240 of the embodiment are partially or completely sunk into the annular groove 2241, when the shaft and the inner wall of the radial bearing generate friction, the first through holes 2240 in the annular groove 2241 cannot be worn, so that the first through holes 2240 are prevented from being blocked, and the pneumatic lubrication effect is improved; the annular groove 2241 can increase the position clearance of the throttling hole, and the throttling hole oxidation caused by high temperature is effectively avoided while the rigidity of the whole bearing is ensured.

Preferably, the first through holes 2240 of the present embodiment are provided in plural, and are uniformly distributed in the circumferential direction of the radial bearing portion 2210, so as to form a stable pressure gas film in the circumferential direction of the rotating shaft 100, and more smoothly support the rotating shaft 100 in the circumferential direction.

Preferably, the second through holes 2260 of the present embodiment are provided in plural numbers, and are uniformly distributed on the end surface of the thrust bearing portion 2220 around the axis of the rotating shaft 100, so as to more stably support the rotating shaft 100 and the rotor system in the axial direction. As shown in fig. 5, fig. 5 is a left side view of the first bearing body 2200.

Preferably, the third through holes 2280 of the present embodiment are provided in plural numbers, and are uniformly distributed on the end surface of the second bearing body 2400 with the axis of the rotating shaft 100 as the center, so as to more stably support the rotating shaft 100 and the rotor system in the axial direction.

When the integrated gas bearing of the present embodiment is provided as a dynamic pressure bearing, a dynamic pressure generating groove is provided on an inner diameter surface of the radial bearing portion 2210 of the first bearing body 2200 or a portion of the rotating shaft 100 where the radial bearing portion 2210 is mounted; a dynamic pressure generating groove is provided in an end surface of the thrust bearing portion 2220 of the first bearing body 2200 facing the thrust disk 2300 or an end surface of the thrust disk surface 2300 facing the thrust bearing portion 2220; a dynamic pressure generating groove is provided on an end surface of the second bearing body 2400 facing the thrust disk 2300 or an end surface of the thrust disk 2300 facing the second bearing body 2400.

Preferably, as shown in fig. 6 and 7, in the present embodiment, a first air groove 2700 is provided on the side of the thrust bearing portion 2220 facing the thrust disk 2300, on the side of the thrust disk 2300 facing the thrust bearing portion 2220, on the side of the second bearing body 2400 facing the thrust disk 2300, or on the side of the thrust disk 2300 facing the second bearing body 2400; a second air groove 2800 is formed in the inner wall of the radial bearing portion 2210 in the circumferential direction or the circumferential surface of the rotary shaft 100 to which the radial bearing portion 2210 is attached, to increase the air flow rate. When the rotating shaft 100 rotates and gradually accelerates, the flowing gas existing in the bearing gap is pressed into the second air groove 2800 and rapidly flows through the second air groove 2800, so that the directional high-speed circulation of the gas is realized, and under the condition that the bearing air pressure load is met, the rotating shaft 100 and the air bearing can better dissipate heat and guide flow.

Preferably, the first air grooves 2700 are arc-shaped grooves which are uniformly distributed in the circumferential direction and are centrosymmetric, one end of each arc-shaped groove is adjacent to the circle center, and the other end of each arc-shaped groove is adjacent to or intersected with the circumference. The number of the arc-shaped grooves is set according to the rotating speed of the rotating shaft 100, so that the air flow rate and the pressure reach reasonable proportion, the rigidity and the load capacity of the bearing can be kept to be high under the condition that the rotating shaft 100 rotates in the forward direction or in the reverse direction, the air through flow is smooth, and the air can be prevented from being blocked in the flow channel.

Preferably, when the rotating shaft 100 rotates clockwise as viewed from the air intake direction, the arc-shaped grooves on the end surfaces of the second bearing body 2400 and the thrust bearing portion 2220 are left concave arcs, the arc-shaped grooves on the end surfaces of the thrust disk 2300 are right concave arcs, and when the rotating shaft 100 rotates counterclockwise, the arc-shaped grooves on the end surfaces of the second bearing body 2400 and the thrust bearing portion 2220 are right concave arcs, and the arc-shaped grooves on the end surfaces of the thrust disk 2300 are left concave arcs, so that air flows through the rotating shaft from left to right in the axial direction.

Preferably, the first air groove 2700 may be formed by forging, rolling, etching, or stamping; meanwhile, the thrust disc 2300 may be made of a stainless steel material to facilitate the processing of the first air groove 2700.

Preferably, the second air groove 2800 is in the shape of a parallel diagonal groove or a helical groove that has a smaller flow capacity than the parallel diagonal groove but can increase axial damping compared to the parallel diagonal groove. The circulation of air in-process, when the pitch is less, the air flow can the pressure boost that slows down, and when the pitch is great, the air flow can the acceleration rate step-down, therefore can set up the helicla flute parameter according to the rotation axis rotational speed, when the rotation axis rotational speed is high, sets up the helicla flute and be coarse pitch, and the helix clearance is loose, and when the rotation axis rotational speed was low, it is little pitch to set up the helicla flute, and the helix clearance is fine and close.

Preferably, said parallel chutes are continuous or discontinuous; the lead angle of the spiral groove is alpha, the thread pitch is P, the depth of the spiral groove is HL, the diameter of the rotating shaft is DL, 30 degrees < alpha <60 degrees, 1/2 degrees < DL < P <5 DL; p-3 DL, α -45 °; the helical groove makes half a turn or 1/3 turns around the shaft.

The parallel chute or the spiral groove is arranged in a position which can keep the rigidity and the load capacity of the bearing to be strong under the condition that the rotating shaft rotates in the positive direction or the reverse direction, the air can flow smoothly, and the air can be prevented from being blocked in the flow channel.

Preferably, the second air grooves 2800 in the radial bearing portion 2210 are provided in the middle portion of the rotary shaft 100 corresponding to the position where the inner wall of the radial bearing portion 2210 is installed, or in two independent portions symmetrically distributed on both sides of the middle portion.

Preferably, the air inlet end of the parallel chute or spiral groove on the rotating shaft 100 is adjacent to the annular groove 2241.

Preferably, when the rotating shaft 100 rotates clockwise as viewed from the air intake direction, the inclined direction of the parallel diagonal grooves or the helical grooves is inclined to the left, and when the rotating shaft 100 rotates counterclockwise, the inclined direction of the parallel diagonal grooves or the helical grooves is inclined to the right, so that air flows through the rotating shaft from the left to the right in the axial direction.

Preferably, the shape of the second air groove 2800 further includes a chevron shape, a V shape, and a chevron-shaped groove, or a V-shaped groove is set such that the bearing can support the rotating shaft 100 in a desired manner in a non-contact manner under the condition that the rotating shaft 100 rotates in the forward direction or in the reverse direction, and has high load capacity and good stability; splayed grooves, herringbone grooves or V-shaped grooves are arranged at the positions of the rotating shaft 100 with larger load or insufficient rigidity, parallel inclined grooves or spiral grooves are arranged at the positions with insufficient through-flow, and the splayed grooves, the herringbone grooves, the V-shaped grooves and/or the parallel inclined grooves and the spiral grooves are arranged at intervals.

The ventilation efficiency of the second air groove 2800 varies depending on the angle, the groove width, the number of grooves, the length, the depth, and the flatness of the second air groove 2800, and the ventilation speed is related to the rotation speed of the rotating shaft 100 and the bearing gap. Further, in reality, the cross section of the rotating shaft 100 cannot be an ideal circle, and when the out-of-roundness affects the pressure of the air film during rotation, the gap between the rotating shaft 100 and the radial bearing portion 2210 is unevenly distributed radially, and the pressure of the space with a small gap becomes large and the pressure of the place with a large gap becomes small. The second air slot 2800 and the annular slot 2241 may be matched according to actual conditions.

Preferably, the air grooves are engraved on the thrust disc 2300, the rotation shaft 100 or the bearing surface in the same direction, and preferably, the air grooves are engraved on the rotation shaft 100, and since the rotation shaft 100 is hard and relatively wear-resistant, the air grooves are not easily deformed and worn by impact, wherein the air grooves are engraved on one end, both ends or a specific position of the rotation shaft 100.

Because the shaft length is longer when the rotor system is at low speed, the low-speed zero-crossing rigidity is larger, and the shaft length is longer when the rotor system is at high speed, the resistance is larger and multiplied, after grooving, the shaft rigidity is not influenced at low speed, the thrust is unchanged, the dynamic pressure working capacity is reduced when the rotor system is at high speed, air can flow to an air groove, the rigidity is reduced, the dynamic pressure actual working length is the length of the shaft minus the length of the groove, the resistance is reduced, and the length of the shaft can be increased; the flow guide is realized without reducing the rigidity of the shaft, after the air grooves are arranged, the air is guided to form directional flow at low speed, and the airflow still flows directionally when the dynamic pressure is switched at high speed, so that the impact airflow is not formed; meanwhile, after the bearing is provided with the air groove, the capacity of resisting the rotor from being disturbed and eccentrically colliding with the wall can be improved, and therefore the bearing capacity of the bearing is also improved.

When the integrated gas bearing of the present embodiment is provided as a hybrid bearing of dynamic and static pressures, it has both the features of the hydrostatic bearing and the dynamic pressure bearing.

In the present embodiment, since the first bearing body 2200 includes both the radial bearing portion 2210 and the thrust bearing portion 2220, it is sufficient to ensure perpendicularity between the axial direction and the action surface of the thrust bearing portion 2220 by machining the thrust bearing portion 2220 with the axial direction as a reference, or to ensure perpendicularity between the action surface of the thrust bearing portion 2220 and the axial direction by machining the inner diameter of the radial bearing portion 2210 with the action surface of the thrust bearing portion 2220 as a reference, in the machining process. The processing technology is simple and easy to operate, the processing precision is high, meanwhile, the precision of combined assembly is not required to be considered in the assembly process, and the assembly technology is simple.

As a preferable solution of this embodiment, an end of the first bearing body 2200 near the thrust disc 2200 is provided with a thrust disc receiving groove 2290, see fig. 3. During installation, thrust disc 2200 is placed in thrust disc receiving groove 2290, and the terminal surface of second bearing body 2400 and thrust disc receiving groove 2290's terminal surface butt. The design of this kind of structure, the installation of being convenient for, and installation accuracy is high.

The integrated bearing 200 can be installed in the rotor system of the present invention in two installation manners, fig. 1 shows a first installation manner, and the radial bearing portion 2210 of the integrated bearing 200 is installed toward the end far away from the motor 400; the arrangement of the installation mode is convenient for assembly, and as for the whole rotor system, one radial bearing is positioned at the leftmost end of the rotor system, and the second radial bearing is positioned between the motor 400 and the gas compressor 500, the axial weight distribution is uniform, and the stability of the rotor system is good; and the thrust bearing is positioned between the two radial bearings, and when the weight of the thrust bearing is larger, the stability of the whole rotor system is not influenced, so that the thrust bearing is suitable for the rotor system with high rotating speed and larger axial force.

Fig. 8 shows a second mounting manner, in which the radial bearing portion 2210 of the integrated bearing 200 is mounted toward the end close to the motor 400, and the thrust bearing portion is located at the leftmost end of the entire rotor system. Due to the arrangement of the installation mode, for the whole rotor system, the two radial bearings are positioned between the stator of the motor 400 and the rotating shaft 100, the axial length of the rotor system is greatly shortened compared with that of the first installation mode, and the dynamic characteristic of the rotor system is further improved. However, this solution requires an air inlet channel of the air bearing to be formed on the winding of the motor 400, and the manufacturing process of the motor 400 is complicated.

Therefore, the two schemes have the advantages and can be reasonably selected according to specific design conditions and use scenes.

Example two

In this embodiment, a structure of the motor 400 is provided, in which the motor 400 forms the first air inlet P1 on the stator of the motor by using a back winding method.

Specifically, as shown in fig. 9, the motor 400 includes: the air inlet structure comprises a motor stator 410, a motor rotor (not shown in the figure) and a motor shell 430, wherein the motor stator 410 is sleeved on the rotating shaft 100 and radially keeps a certain gap with the rotating shaft 100, the motor shell 430 is covered on the periphery of the motor stator 410, a plurality of air inlet channels 440 axially penetrating through the motor stator 410 are arranged on the motor stator 410, and the air inlet channels 440 are first air inlet channels P1.

Due to the arrangement of the air inlet channel 440, the air inlet of the compressor 500 can enter the compressor 500 through the air inlet channel 440, so that the air inlet of the compressor 500 is more sufficient, and meanwhile, the normal-temperature air passing through the air inlet channel 440 can play a certain cooling role on the motor stator 410.

Specifically, the formation of the air inlet 440 may be achieved by the following structure and winding manner. Referring to fig. 10, a half-sectional view of the motor is shown; and fig. 11, a structural view of the motor stator core 411.

The motor stator 410 includes a stator core 411 and a stator winding 412, the stator core 411 is cylindrical, and a through hole 4111 for installing the rotating shaft 100 is formed in the center of the cylinder; stator core 411's external diameter side is formed with a plurality of first winding baffles 4112 that extend along the axial of cylinder and radial outside, along the circumference equipartition of cylinder, stator core 411's internal diameter side is formed with a plurality of second winding baffles 4113 that extend along the axial of cylinder and radial inboard, along the circumference equipartition of cylinder, the one end that second winding baffle 4113 is close to the cylinder centre of a circle forms through-hole 4111. First winding baffle 4112 and second winding baffle 4113 are arranged oppositely on the outer diameter side and the inner diameter side of the cylinder, the outer peripheral surfaces of two adjacent first winding baffles 4112 and the cylinder form an outer wire groove 4114, the inner peripheral surfaces of two adjacent second winding baffles 4113 and the cylinder form an inner wire groove 4115, the stator winding 412 is wound in the outer wire groove 4114 and the inner wire groove 4115 along the axial direction of the cylinder, and the stator winding 412 and two adjacent second winding baffles 4113 form an air inlet passage 440.

Alternatively, the stator core 411 is formed by laminating and pressing a plurality of silicon steel sheets 4116 with the same shape in the axial direction of the cylinder, and the structure of the silicon steel sheets is as shown in fig. 12.

Through the setting of above-mentioned stator core 411 structure for stator winding 412 can twine in stator core 411's outer wire groove 4114 and inner wire groove 4115, has still been formed with intake duct 440 in the inner wire groove 4115 interior wiring stator winding back of laying out simultaneously. Therefore, in the present structure, the stator winding 412 of the motor 400 is mostly located in the slot, and only a little stator winding leaks out at both ends of the stator core 411. And conventional motor adopts conventional wire winding mode, and whole winding is located stator core's inboard, because of stator core inboard space is limited, hardly forms regular intake duct, even if form the intake duct, its intake duct is also very narrow, is unfavorable for gaseous passing through to both ends at stator core can be formed with mushroom-shaped winding. Compared with the prior art, the motor 400 with the structure has the advantages that the length in the axial direction is shortened, and the whole volume is reduced. Therefore, when the motor 400 with the structure is used for a rotor system, the axial length of the whole rotor system can be greatly shortened, and the running stability of the rotor system is improved. Meanwhile, the motor 400 of the structure is provided with the air inlet channel 440 for air or cooling air to pass through on the motor stator 410, which is beneficial to heat dissipation of the motor stator 410 and the rotating shaft 100, and meanwhile, when the motor 400 is used at the front end of a compressor or other equipment needing air inlet, air inlet of rear-end equipment cannot be blocked, and the axial length of a rotor system cannot be increased.

Optionally, as shown in fig. 13, the structure of the stator core 411 may be further optimized, that is, the end face wire slots 4117 are disposed at the positions corresponding to the outer wire slots 4114 and the inner wire slots 4115 at the two ends of the stator core 411, so that the whole winding may be disposed in the wire slots, and the whole wiring of the motor 400 is neater and cleaner.

Alternatively, the surface of the stator core 411 is coated with an insulating layer or painted with an insulating varnish.

Optionally, the first winding separator 4112 and the second winding separator 4113 are arranged in 10, 16, 18, 24, etc.

Optionally, in order to facilitate heat dissipation of the motor stator 410 and the rotating shaft 100 and air intake of the air intake duct 440, end covers may not be disposed at both ends of the motor 400 in this structure, or end covers may be disposed at both ends, but mesh-shaped air holes are disposed on the end covers at both ends.

The air inlet channel of the integrated bearing 200 is opposite to the air inlet channel of the motor 400 and is communicated with the air inlet of the compressor 500. This allows the inlet air to the compressor 500 to be more unobstructed while the inlet air to the compressor 500 cools the stator windings 412 of the motor 400.

Further, a second air inlet passage P2 may be provided between the motor stator 410 and the motor housing 430 of the motor 400. In the case of a large intake demand, both intake ducts can be simultaneously charged. This allows for adequate air intake of the compressor 500, while the air intake of the compressor 500 further cools the motor housing 430, the motor stator 410, and the stator windings 412 of the motor.

EXAMPLE III

In the present embodiment, an anti-rotation structure for the integrated bearing 200 of the second embodiment is provided. A first anti-rotation member 2900 is provided between the first bearing housing 2500 and the first bearing body 2200, and/or between the first bearing housing 2500 and the second bearing body 2400, and the first anti-rotation member 2900 is used for circumferentially fixing the first bearing body 2200 with respect to the first bearing housing 2500 and/or the second bearing body 2400 with respect to the first bearing housing 2500.

Specifically, one end of the first anti-rotation member 2900 is fixedly connected or integrally formed with the first bearing housing 2500, and the other end of the first anti-rotation member 2900 is detachably connected with the first bearing body 2200 or the second bearing body 2400; alternatively, one end of the first rotation prevention member 2900 is detachably connected to the first bearing housing 2500, and the other end of the first rotation prevention member 2900 is fixedly connected to or integrally formed with the first bearing body 2200 or the second bearing body 2400; the first anti-rotation member 2900 may be provided in one or more.

The connection between the first anti-rotation member 2900 and the bearing may be the connection with the first bearing body 2200 or the second bearing body 2400, and since the first bearing body 2200 and the second bearing body 2400 are fixedly connected, the first anti-rotation member 2900 can prevent the bearing body from rotating circumferentially regardless of which bearing body is connected.

The specific structure of the first anti-rotation member 2900 of the present invention is further explained below, and this description is only for the thrust bearing portion of the present integrated gas bearing, and it should be understood by those skilled in the art that the specific structure of the first anti-rotation member 2900 is equally applicable to the radial bearing portion of the integrated gas bearing.

As shown in fig. 14 and 15, the first rotation prevention member 2900 may be configured as a pin and fixedly mounted on the end surface of the first bearing body 2200, and the first bearing housing 2500 is provided with a corresponding first receiving hole 2910.

Alternatively, as shown in fig. 16 and 17, the first rotation preventing member 2900 may be provided as a pin and fixedly mounted on an end surface of the first bearing housing 2500 facing the first bearing body 2200, and the first bearing body 2200 is provided with a corresponding second receiving hole 2920.

Alternatively, as shown in fig. 18 and 19, the first rotation preventing member 2900 may be provided as a pin or a dowel, the first rotation preventing member 2900 is installed from the outer circumference of the first bearing housing 2500 in the radial direction of the first bearing housing 2500, one end of the first rotation preventing member 2900 is fixed to the first bearing housing 2500, the other end is inserted into the outer circumference of the first bearing body 2200, and the outer circumference of the first bearing body 2200 is provided with a corresponding third receiving hole 2930.

Alternatively, as shown in fig. 20 and 21, the first rotation prevention member 2900 may be configured as a key and fixedly mounted to the end surface of the first bearing body 2200 or integrally formed with one end surface of the first bearing body 2200, and the first bearing housing 2500 is provided with a corresponding first key groove 2940.

Alternatively, as shown in fig. 22 and 23, the first rotation prevention member 2900 may be configured as a key and fixedly mounted on the inner diameter surface of the first bearing housing 2500, or integrally formed with the inner diameter surface of the first bearing housing 2500, and the first bearing body 2200 may be provided with a corresponding second key groove 2950.

Alternatively, as shown in fig. 24 and 25, the first rotation prevention member 2900 may be provided with a spherical body and fixedly mounted on the end surface of the first bearing body 2200, and the first bearing housing 2550 is provided with a corresponding hemispherical groove.

Alternatively, as shown in fig. 24 and 25, the first rotation prevention member 2900 may be provided with a spherical body and fixedly mounted on an end surface of the first bearing housing 2500 facing the first bearing body 2200, and the first bearing body 2200 is provided with a corresponding hemispherical groove.

The integral type bearing is provided with prevents changeing the component, and the bearing body can not be rotatory along with the pivot, long service life, operation stability.

Example four

In the present embodiment, an anti-rotation structure of the radial bearing 300 is provided.

The radial bearing 300 includes a third bearing body 320, a second bearing housing 330, a second bearing end cap 340, and a second rotation-preventing member 350, the third bearing body 320 is sleeved on the rotating shaft 100 and keeps a predetermined gap with the rotating shaft 100, the second bearing housing 330 is covered on an axial end surface and an outer periphery of the third bearing body 320, and the second bearing end cap 340 is sleeved on the rotating shaft 100 and abuts against an end surface of the second bearing housing 330; the second rotation preventing member 350 is disposed between the second bearing housing 330 and the third bearing body 320 and connects them to fix the third bearing body 320 in the circumferential direction.

In this structure, one end of the second rotation-preventing member 350 is fixedly connected or integrally formed with the second bearing housing 330, and the other end of the second rotation-preventing member 350 is detachably connected with the third bearing body 320;

alternatively, one end of the second rotation-preventing member 350 is detachably connected to the second bearing housing 330, and the other end of the second rotation-preventing member 350 is fixedly connected to the third bearing body 320 or integrally formed therewith. This connection of the second anti-rotation member 350 enables the second anti-rotation member 350 to be mounted very conveniently.

Specifically, the second anti-rotation member 350 may be provided in one or more.

With respect to the present anti-rotation radial bearing structure, several example structures of the second anti-rotation member 350 are provided as follows.

As shown in fig. 26 and 27, the second rotation preventing member 350 is provided as a pin and is fixedly mounted on the end surface of the third bearing body 320, and the second bearing housing 330 is provided with a corresponding first receiving hole 331, which is used to circumferentially position the third bearing body 320.

Alternatively, as shown in fig. 28 and 29, the second rotation preventing member 350 is provided as a pin and is fixedly mounted on the end surface of the second bearing housing 330 facing the third bearing body 320, and the third bearing body 320 is provided with a corresponding second receiving hole 321, and circumferential positioning of the third bearing body 320 is achieved by the pin.

Alternatively, as shown in fig. 30 and 31, the second rotation preventing member 350 is provided as a pin or a dowel, the second rotation preventing member 350 is installed from the outer periphery of the second bearing housing 330 in the radial direction of the second bearing housing 330, one end of the second rotation preventing member 350 is fixed to the second bearing housing 330, the other end is inserted into the outer periphery of the third bearing body 320, the outer periphery of the third bearing body 320 is provided with a corresponding third accommodating hole 322, and circumferential positioning of the third bearing body 320 is achieved by the pin or the dowel.

Alternatively, as shown in fig. 32 and 33, the second rotation-preventing member 350 is provided as a key and is fixedly mounted on the end surface of the third bearing body 320 or integrally formed with one end surface of the third bearing body 320, and the second bearing housing 330 is provided with a corresponding first key groove 332, so that the circumferential positioning of the third bearing body 320 is realized by the key.

Alternatively, as shown in fig. 34 and 35, the second rotation-preventing member 350 is provided as a key and is fixedly mounted on the inner diameter surface of the second bearing housing 330, or is integrally formed with the inner diameter surface of the second bearing housing 330, and the third bearing body 320 is provided with a corresponding second key groove 323, so that the circumferential positioning of the third bearing body 320 is realized by the key.

Alternatively, as shown in fig. 36 and 37, the second rotation-preventing member 350 is provided as a spherical body and is fixedly mounted on the end surface of the third bearing body 320, and the second bearing housing 330 is provided with a corresponding hemispherical groove, so that the circumferential positioning of the third bearing body 320 is realized by the spherical body.

Alternatively, as shown in fig. 36 and 37, the second rotation-preventing member 350 may be provided with a spherical body and fixedly mounted on the end surface of the second bearing housing 330 facing the third bearing body 320, and the third bearing body 320 is provided with a corresponding hemispherical groove, so that the circumferential positioning of the third bearing body 320 is realized by the spherical body.

In the operation process of the rotor, through the structure of the radial bearing, the third bearing body works stably, cannot rotate along with the improvement of the rotating speed of the rotating shaft, and is reliable in performance, long in service life and simple in structure.

As a preferred embodiment of the present invention, a reinforcing ring 700 is disposed between the compressor 500 and the turbine 600 of the rotor system. For rotor dynamics, the shaft 100 is lighter and lighter, and the diameter of the shaft 100 is smaller and lighter, but the strength of the shaft 100 is highly required during high-speed rotation of the rotor system. In order to take both the rotor dynamics and the strength of the rotating shaft 100 into consideration, the shaft diameter of the second shaft section 120 may be set thin while a reinforcing ring 700 is installed between the compressor 500 and the turbine 600 to satisfy the rotor rigidity requirement.

The utility model provides a rotor system it has following advantage: because the bearing shell and the motor stator are provided with the air inlet channels, the air inlet of the air compressor can be met, and meanwhile, the air inlet of the air compressor can cool the bearing and the winding of the motor, so that the use performance of the motor is improved. Additionally, the utility model discloses a motor is short in the axial direction size, can improve rotor system's stability ability, and with low costs.

According to the utility model discloses an on the other hand, the utility model discloses still provide a miniature gas turbine generating set who uses above-mentioned rotor system, this generator unit includes:

the rotor system, motor case 810, gas turbine case 820, and combustor 830 described above; the motor case 810 covers the outer periphery of the motor 300, the gas turbine case 820 covers the outer peripheries of the compressor 500 and the turbine 600, and is connected to the motor case 810, the combustion chamber 830 is connected to the gas turbine case 820, an air inlet of the combustion chamber 830 is connected to an air outlet of the compressor 500, and an air outlet of the combustion chamber 830 is connected to an air inlet of the turbine 600.

Preferably, a diffuser 840 is disposed between an exhaust port of the compressor 500 and an intake port of the combustion chamber 830 to further increase the pressure of the high-temperature and high-pressure gas entering the turbine 600 to perform work.

The utility model discloses an among the miniature gas turbine generating set, all bearings are all set up in motor machine casket 810, only need guarantee in this machine casket like this be used for setting up the machining precision at the position of bearing stator can, the position that is used for connecting the bearing stator in this machine casket when the assembly can be accomplished through the processing of once adorning the card, and is visible, the utility model discloses reduce miniature gas turbine generating set's machining precision and assembly precision, the cost is reduced is fit for engineering batch production. And simultaneously, the utility model discloses a miniature gas turbine generating set admits air abundant and the axial direction of pivot 100 goes up the size short, and miniature gas turbine generating set's operation stationarity is good.

The micro gas turbine is a small heat engine which is newly developed, the single-machine power range of the micro gas turbine is 25-300 kW, and the basic technical characteristics are that a radial-flow impeller machine and a regenerative cycle are adopted. The micro gas turbine has a simple and compact structure, saves the installation space, is convenient for quick installation and transportation, and can well meet the small-scale and distributed requirements of distributed power supply; the moving parts are few, the structure is simple and compact, and therefore the reliability is good, and the manufacturing cost and the maintenance cost are low; good environmental adaptability and high power supply quality.

The whole system only has one moving part and adopts an air bearing, the operation reliability of the system is as high as 99.996%, and the average annual downtime and overhaul time is not more than 2 hours. The utility model discloses a bearing/rotor system can be used to the miniature gas turbine of 10 ~ 100KW models, like the 15/30/45KW model.

Single micro gas turbine:

the rotating speed of a 15KW micro-combustion engine with a heat regenerator is 0-140000 RPM, and when the fuel is kerosene, the oil consumption is 50-600 g/kWh; when the fuel is natural gas, the consumption of the natural gas is 0.15m³/kWh～0.5m³/kWh. The rotating speed of a 15KW micro-combustion engine without a heat regenerator is 0-140000 RPM, and when the fuel is kerosene, the oil consumption is 400-1000 g/kWh; when the fuel is natural gas, the consumption of the natural gas is 0.4m³/kWh～1m³/kWh。

The rotating speed of a 45KW micro-combustion engine with a heat regenerator is 0-80000 RPM, and when the fuel is kerosene, the oil consumption is 200-500 g/kWh; when the fuel is natural gas, the consumption of the natural gas is 0.2m³/kWh～0.5m³/kWh. 45KW without beltThe rotation speed of a micro-combustion engine of the heat regenerator is 0-80000 RPM, and when the fuel is kerosene, the oil consumption is 400-900 g/kWh; when the fuel is natural gas, the consumption of the natural gas is 0.5m³/kWh～1m³/kWh。

The above description is only a preferred embodiment of the invention and is intended to illustrate the technical principles applied. It will be understood by those skilled in the art that the scope of the present invention is not limited to the specific combination of the above-mentioned features, but also covers other embodiments formed by any combination of the above-mentioned features or their equivalents without departing from the spirit of the present invention. For example, the above features have similar functions to (but not limited to) those disclosed in the present invention.

Claims

1. A rotor system, comprising:

the rotating shaft is of an integrally formed structure;

2. The rotor system of claim 1, wherein the shaft includes a first shaft section and a second shaft section, the first shaft section having a diameter greater than a diameter of the second shaft section, a step surface being formed at a transition of the first shaft section and the second shaft section;

3. The rotor system of claim 1, wherein the integrated bearing is an integrated air bearing comprising:

4. The rotor system of claim 3, wherein the radial bearing portion of the integrated bearing is mounted toward an end away from the electric machine;

5. A rotor system according to claim 3, characterised in that a first anti-rotation member is provided between the first bearing housing and the first bearing body and/or between the first bearing housing and the second bearing body for circumferential fixing of the first bearing body relative to the first bearing housing and/or of the second bearing body relative to the first bearing housing.

6. The rotor system of claim 1, wherein the radial bearing is any one of a hydrodynamic gas bearing, a hydrostatic gas bearing, or a hydrodynamic gas bearing;

7. The rotor system of claim 1, wherein the electric machine comprises a machine stator, a machine housing;

the first air inlet channel penetrates through the motor stator.

8. The rotor system of claim 7, wherein the motor stator includes a stator core and a stator winding;

9. The rotor system according to claim 7 or 8, wherein a second air inlet channel is further arranged between the motor stator of the motor and the motor shell, and the second air inlet channel is communicated with the air inlet of the compressor.

10. A rotor system according to claim 1, wherein a reinforcing ring is provided between the compressor and the turbine.

11. A micro gas turbine power plant comprising a rotor system, a motor case, a gas turbine case, and a combustor according to any one of claims 1 to 10;

12. A micro gas turbine power plant according to claim 11, wherein a diffuser is provided between the compressor discharge and the combustion chamber inlet.