CN211343130U

CN211343130U - Rotor system and micro gas turbine

Info

Publication number: CN211343130U
Application number: CN201922359289.7U
Authority: CN
Inventors: 靳普; 刘慕华
Original assignee: Zhiyue Tengfeng Technology Group Co ltd
Current assignee: Liu Muhua
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, wherein rotor system includes: the rotating shaft is of an integrated structure, the rotating shaft is horizontally or vertically arranged, and a motor, a radial bearing, a gas compressor, a thrust bearing and a turbine are arranged on the rotating shaft; the radial bearing and the thrust bearing are both air bearings, a first air groove is arranged in the thrust bearing, and a second air groove is arranged in the rotating shaft and/or the radial bearing. The utility model discloses can not reduce the rigidity of axle when realizing the water conservancy diversion.

Description

Rotor system and micro gas turbine

Technical Field

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

Background

The micro gas turbine mainly comprises three parts of a gas compressor, a combustion chamber and a turbine. After entering the compressor, the air is compressed into high-temperature and high-pressure air, and then the high-temperature and high-pressure air is supplied to the combustion chamber to be mixed and combusted with fuel, and the generated high-temperature and high-pressure gas expands in the turbine to do work. A radial bearing and a thrust bearing are required to be installed in a rotor system of a micro gas turbine to stably support a rotating shaft in a radial direction and an axial direction.

When the radial bearing and the thrust bearing used in the prior art rotor system are air bearings, the prior art rotor system has the following defects: for a radial air bearing, the radial air bearing is used when the rigidity is insufficient, air can be stored through the splayed groove, the bearing capacity of the shaft can be improved when the radial air bearing is applied at low speed, but air blockage can be caused at high speed, high-frequency vibration can be generated due to high-speed rotation of the shaft when the air is blocked, the blocked air becomes an energy absorber, the temperature can be rapidly increased, the temperature can be increased to thousands of degrees of high temperature, the shaft/shaft sleeve is melted, the shaft and the shaft sleeve are adhered and clamped, meanwhile, the air of the bearing is refilled, and an air channel is further blocked,

in the case of a thrust bearing, the stiffness is excessive but the throughflow is insufficient in the case of a conventional rotor dynamic structure. Air is easy to block at a corner position, the rotating resistance of the shaft is large, air in the middle of the thrust bearing can be extruded out of a bearing gap due to the blocking of a bearing stator, so that air is refilled, the flowing direction is changed, the airflow of an air channel is disturbed, and particularly when dynamic pressure is switched at a high speed, the airflow impact is larger, and larger turbulence is formed.

SUMMERY OF THE UTILITY MODEL

In order to solve the above technical problem, an object of the present invention is to provide a rotor system and a micro gas turbine.

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 integrated structure, the rotating shaft is horizontally or vertically arranged, and a motor, a radial bearing, a gas compressor, a thrust bearing and a turbine are arranged on the rotating shaft;

the radial bearing and the thrust bearing are both air bearings, a first air groove is arranged in the thrust bearing, and a second air groove is arranged in the rotating shaft and/or the radial bearing.

Further, an air groove bevel angle is arranged in the thrust bearing.

Furthermore, the thrust bearing comprises a second thrust disc, a second stator, a first stator and a first thrust disc, and the second thrust disc, the second stator, the first stator and the first thrust disc are sequentially sleeved on the rotating shaft;

the end face of the second stator facing one side of the second thrust disc or the end face of the second thrust disc facing one side of the second stator is provided with the first air groove, the end face of the first stator facing one side of the first thrust disc or the end face of the first thrust disc facing one side of the first stator is provided with the first air groove, a gap is formed between the second stator and the second thrust disc, a gap is formed between the first stator and the first thrust disc, and the second thrust disc and the first thrust disc are fixedly connected with the rotating shaft or integrally formed with the rotating shaft;

the first air grooves 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.

Furthermore, a suction type first air groove is arranged on one side of the thrust bearing, and a throwing type first air groove is arranged on the other side of the thrust bearing.

Further, the air-intake direction is, as viewed from the air-intake direction,

when the rotating shaft rotates clockwise, the arc-shaped grooves on the end surfaces of the second thrust disc and the first thrust disc are left concave arcs, and the arc-shaped grooves on the end surfaces of the second stator and the first stator are right concave arcs;

when the rotating shaft rotates anticlockwise, the arc-shaped grooves of the end faces of the second thrust disc and the first thrust disc are right concave arcs, and the arc-shaped grooves of the end faces of the second stator and the first stator are left concave arcs.

Furthermore, the radial bearing comprises a bearing body, the bearing body is sleeved on the rotating shaft, a gap is kept between the bearing body and the rotating shaft, and the second air groove is formed in the circumferential surface of the rotating shaft corresponding to the position where the bearing body is installed or in the circumferential direction on the inner wall of the bearing body.

Further, the second air groove is a parallel inclined groove or a spiral groove.

Furthermore, 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,

wherein 30 ° < α <60 °, 1/2DL < P <5 DL.

Further, the air-intake direction is, as viewed from the air-intake direction,

when the rotating shaft rotates clockwise, the inclination direction of the parallel chute or the spiral groove is left inclination;

when the rotating shaft rotates anticlockwise, the inclination direction of the parallel chute or the spiral groove is right-inclined.

Further, the second air groove also comprises a herringbone shape and/or a splayed shape and/or a V-shaped shape.

Furthermore, the second air groove in the bearing body is arranged in the middle part of the rotating shaft corresponding to the inner wall of the bearing body, or is symmetrically distributed on two sides of the middle part and is mutually independent.

Further, the radial bearing comprises a first radial bearing and a second radial bearing, and the thrust bearing, the first radial bearing, the motor, the second radial bearing, the compressor and the turbine are sequentially arranged on the rotating shaft;

or, the radial bearing comprises a first radial bearing and a second radial bearing, and the first radial bearing, the motor, the second radial bearing, the compressor, the thrust bearing and the turbine are sequentially arranged on the rotating shaft.

According to another aspect of the present invention, there is provided a micro gas turbine, comprising the rotor system described above.

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

1. in the rotor system, the longer the shaft length is at low speed, the higher the low-speed zero-crossing rigidity is, and the longer the shaft length is at high speed, the higher the resistance is, and the multiplied increase is, so that after the air groove is arranged, the shaft rigidity is not influenced at low speed, the thrust is unchanged, the dynamic pressure working capacity is reduced at high speed, air can flow to the air groove, the rigidity is reduced, the actual dynamic pressure 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; flow guidance is achieved without reducing the stiffness of the shaft.

2. After the air groove is arranged, the air is guided to form directional flow at low speed, and airflow still flows directionally when dynamic pressure is switched at high speed, so that impact airflow cannot be formed.

3. After the bearing is provided with the air groove, the capacity of resisting the disturbance of the rotor to collide with the wall eccentrically can be improved, so that the bearing capacity of the bearing is also improved; the radial bearing and the thrust bearing work cooperatively, the integration level is high, the processing and the installation are easy, the coaxiality of the radial bearing and the thrust bearing is effectively ensured, the comprehensive performance of the bearing is improved, and the dynamic performance and the stability of the bearing in a high-speed running state are improved; the structure is simple, the operation is simple and convenient, the precision requirement is not high, the practicability is strong, and the economic cost is low; compared with the traditional structure adopting a single gas bearing, the gas bearing has high response speed.

Drawings

Fig. 1 is a first structural diagram of the rotor system of the present invention.

Fig. 2 is a second structure diagram of the rotor system of the present invention.

Fig. 3 is a schematic view of the thrust bearing assembly of the present invention.

Fig. 4 is a schematic structural view of the first air groove of the present invention.

Fig. 5 is a schematic view of the radial bearing assembly of the present invention.

Fig. 6 is a schematic structural view of a second air tank according to the present invention.

Fig. 7 is a structure diagram of the second air tank assembly of the present invention.

Fig. 8 is a front view of the ring groove air bearing structure of the present invention.

Fig. 9 is a cross-sectional view taken along line a-a of fig. 8.

Fig. 10 is a partially enlarged view of a bearing orifice according to the present invention.

Fig. 11 is a first structural view of an anti-rotation member of the thrust bearing of the present invention.

Fig. 12 is a cross-sectional view taken along line a-a of fig. 11.

Fig. 13 is a second structural view of the anti-rotation component of the thrust bearing of the present invention.

Fig. 14 is a cross-sectional view taken along line a-a of fig. 13.

Fig. 15 is a third structural view of an anti-rotation member of the thrust bearing of the present invention.

Fig. 16 is a cross-sectional view taken along line a-a of fig. 15.

Fig. 17 is a fourth structural view of the anti-rotation component of the thrust bearing of the present invention.

Fig. 18 is a cross-sectional view taken along line a-a of fig. 17.

Fig. 19 is a fifth structural view of an anti-rotation member of the thrust bearing of the present invention.

Fig. 20 is a cross-sectional view taken along line a-a of fig. 19.

Fig. 21 is a sixth structural view of an anti-rotation member of the thrust bearing of the present invention.

Fig. 22 is a cross-sectional view taken along line a-a of fig. 21.

Fig. 23 is a first structural view of an anti-rotation member of the radial bearing of the present invention.

Fig. 24 is a cross-sectional view taken along line a-a of fig. 23.

Fig. 25 is a second structural view of the anti-rotation member of the radial bearing of the present invention.

Fig. 26 is a cross-sectional view taken along line a-a of fig. 25.

Fig. 27 is a third structural view of the anti-rotation component of the radial bearing of the present invention.

Fig. 28 is a cross-sectional view taken along line a-a of fig. 27.

Fig. 29 is a fourth structural view of the anti-rotation component of the radial bearing of the present invention.

Fig. 30 is a cross-sectional view taken along line a-a of fig. 29.

Fig. 31 is a fifth structural view of the anti-rotation component of the radial bearing of the present invention.

Fig. 32 is a cross-sectional view taken along line a-a of fig. 31.

Fig. 33 is a sixth structural view of an anti-rotation member of the radial bearing of the present invention.

Fig. 34 is a sectional view taken along a-a in fig. 33.

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, the rotor system includes a rotating shaft 110, a shaft body of the rotating shaft 110 is an integral structure, the rotating shaft 110 is horizontally or vertically disposed, and a thrust bearing 100, a first radial bearing 200, a motor 300, a second radial bearing 400, a compressor 500, and a turbine 600 are sequentially sleeved on the rotating shaft 110.

As shown in fig. 2, the rotor system includes a rotating shaft 110, a shaft body of the rotating shaft 110 is an integral structure, the rotating shaft 110 is horizontally or vertically disposed, and a first radial bearing 200, a motor 300, a second radial bearing 400, a compressor 500, a thrust bearing 100, and a turbine 600 are sequentially sleeved on the rotating shaft 110.

For the rotor system shown in fig. 1, the side surface of the rotating shaft 110 is easily worn, air is easily accumulated at the worn position after the wear, and the temperature is increased to 800-.

For the rotor system shown in fig. 2, 4 right-angle bends exist in the shaft system, and the air flow channel resistance is severe.

In order to solve the problems of the rotor system, the present invention provides a first air groove 800 in the thrust bearing 100, and a second air groove 900 in the rotating shaft 110 and/or the radial bearing to improve the air circulation rate; meanwhile, the air groove oblique angle is arranged at the position of the thrust bearing 100, so that active flow guide of gas can be realized.

In the present embodiment, a structure of the thrust bearing 100 is provided, as shown in fig. 3, the thrust bearing 100 includes a second thrust disk 121, a second stator 140, a first stator 130, and a first thrust disk 122, the second stator 140 and the first stator 130 form a bearing stator 180, and the second thrust disk 121 and the first thrust disk 122 form a thrust disk 120. The second thrust disc 121, the second stator 140, the first stator 130, and the first thrust disc 122 are sequentially sleeved on the rotating shaft 110, the end surface of the second stator 140 facing the second thrust disc 121 side or the end surface of the second thrust disc 121 facing the second stator 140 side is provided with a first air groove 800, the end surface of the first stator 130 facing the first thrust disc 122 side or the end surface of the first thrust disc 122 facing the first stator 130 side is provided with a first air groove 800, a gap is formed between the second stator 140 and the second thrust disc 121, a gap is formed between the first stator 130 and the first thrust disc 122, and the second thrust disc 121, the first thrust disc 122, and the rotating shaft 110 are fixedly connected. A sealing ring may be disposed on an end surface of the second stator 140 adjacent to the first stator 130, and an elastic member 190 may be disposed between the second stator 140, the first stator 130, and the bearing housing. The utility model discloses an among the above-mentioned thrust bearing 100 structure, as shown in FIG. 4, first air groove 800 is the arc wall, arc wall circumference equipartition and central symmetry, arc wall one end is adjacent with the centre of a circle, and the other end is adjacent with the circumference or intersects.

The number of the arc-shaped grooves is set according to the rotating speed of the rotating shaft 110, 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.

In the arc-shaped groove structure of the thrust bearing 100, when the rotating shaft 110 rotates clockwise as seen from the air inlet direction, the arc-shaped grooves on the end surfaces of the second thrust disc 121 and the first thrust disc 122 are left concave arcs, the arc-shaped grooves on the end surfaces of the second stator 140 and the first stator 130 are right concave arcs, when the rotating shaft 110 rotates counterclockwise, the arc-shaped grooves on the end surfaces of the second thrust disc 121 and the first thrust disc 122 are right concave arcs, and the arc-shaped grooves on the end surfaces of the second stator 140 and the first stator 130 are left concave arcs, so that the air flows through from left to right along the axial direction. Namely, the suction type first air groove 800 is arranged on the left side of the thrust bearing 100, and the throw type first air groove 800 is arranged on the right side of the thrust bearing, so that the rapid through flow of air in the bearing can be realized, the gas of the compressor can be conducted, and the air blockage and accumulation can be prevented.

Preferably, the first air groove 800 may be formed by forging, rolling, etching, or punching.

Preferably, the second thrust disk 121 and the first thrust disk 122 are made of a stainless steel material, which facilitates the machining of the first air groove 800.

In the present embodiment, a radial bearing structure is provided, which is suitable for the first radial bearing 200 and the second radial bearing 400.

As shown in fig. 5, the radial bearing includes a bearing body 220, and a second air groove 900 is formed in a circumferential surface of the rotating shaft 110 corresponding to a position where the bearing body 220 is mounted or in a circumferential direction of an inner wall of the bearing body 220. When the rotating shaft 110 rotates and gradually accelerates, the flowing gas existing in the bearing gap is pressed into the second air groove 900 and rapidly flows through the second air groove 900, so that the directional high-speed circulation of the gas is realized, and under the condition of meeting the bearing air pressure load, the rotating shaft 110 and the radial bearing can better dissipate heat and guide flow.

Preferably, the second air groove 900 may be formed by forging, rolling, etching, or punching.

Preferably, as shown in fig. 6, the secondary air slot 900 is in the shape of a parallel diagonal slot or a spiral slot having a smaller flow capacity than the parallel diagonal slot but increased axial damping than the parallel diagonal slot. 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, the parallel chutes are continuous or discontinuous.

Preferably, the helical groove has a lead angle α, a pitch P, a depth HL, a diameter DL of the rotation axis, 30 ° < α <60 °, 1/2DL < P <5DL,

preferably, P is 3DL and α is 45 °.

Preferably, the helical groove makes half a turn or 1/3 turns around the shaft.

Preferably, the parallel inclined grooves or the spiral grooves are positioned such that the rigidity and the load capacity of the bearing are maintained when the rotating shaft 110 rotates in the forward direction or in the reverse direction, and air flows smoothly, thereby preventing air from being blocked in the flow passage.

Preferably, the second air groove 900 of the bearing body 220 is provided at a middle portion of the rotation shaft 100 corresponding to a position where the inner wall of the bearing body 220 is installed, or provided at two independent portions symmetrically distributed at both sides of the middle portion.

Preferably, the air inlet end of the parallel inclined groove or the spiral groove on the rotating shaft 110 is adjacent to an annular groove (the annular groove is arranged on the circumference of the inner wall of the bearing body 220, and the specific reference will be made to the following description).

Preferably, when the rotating shaft 110 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 110 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, as shown in fig. 7, the shape of the second air groove 900 further includes a chevron shape, a figure eight shape, a V shape, a chevron shape groove, or a V shape groove, and the bearing is configured to support the rotating shaft 110 in a desired manner in a non-contact manner under the condition that the rotating shaft 110 rotates in a forward direction or a 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 110 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.

Preferably, the first radial bearing 200, the second radial bearing 400, and the thrust bearing 100 are one of a hydrostatic bearing, a hydrodynamic bearing, and a hybrid dynamic-static bearing.

In the present invention, the ventilation efficiency of the second air groove 900 varies according to the angle, the groove width, the number of grooves, the length, the depth, and the flatness of the second air groove 900, and the ventilation speed is related to the rotation speed of the rotating shaft 110 and the bearing gap. In addition, in reality, the cross section of the rotating shaft 110 cannot be an ideal circle, when the out-of-roundness affects the pressure of the air film during rotation, the radial distribution of the gap between the rotating shaft 110 and the bearing body 220 is not uniform, 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 groove 900 and the annular groove may be arranged in a matching manner according to actual conditions.

Preferably, the same direction air grooves are engraved on the thrust disc 120, the rotating shaft 110 or the bearing body 220, wherein the air grooves are engraved on the rotating shaft or the shaft sleeve surface equivalently.

Preferably, the air groove is engraved on the rotating shaft 110, and since the rotating shaft 110 is hard and wear-resistant, the air groove is not easily deformed and worn when receiving impact, wherein the air groove is engraved at one end, both ends, or a specific position of the rotating shaft.

The embodiment of the utility model provides a radial bearing to rotor system, the embodiment of the utility model provides a bearing structure.

As shown in fig. 8, 9 and 10, the radial bearing includes a second bearing housing 230 and a bearing body 220 which are sequentially nested from outside to inside, the rotating shaft 110 is arranged in the bearing body 220, the bearing body 220 is an annular cylinder, a throttle hole 270 is radially arranged on the bearing body 220, the throttle hole 270 is a diameter-variable hole, the opening of the throttle hole 270 on the outer wall of the bearing body 220 is larger than the opening of the throttle hole 270 on the inner wall, an annular groove 260 is circumferentially arranged on the inner wall of the bearing body 220, and the opening of the throttle hole 270 on the inner wall partially or wholly intersects with the.

Preferably, the air bearing may be one of a hydrostatic bearing, a hydrodynamic bearing, or a hybrid bearing of dynamic and static pressure.

Preferably, the cross section of the diameter-variable portion of the orifice 270 is funnel-shaped or conical.

Preferably, the throttle holes 270 are plural and are uniformly distributed in one or more circles along the circumferential direction of the bearing body 220.

Preferably, the orifice 270 is positioned at an axial load so that the air film pressure in the bearing gap in the axial direction is uniformly distributed.

Preferably, the width W of the annular groove 260 is larger than the diameter D of the inner wall throttle opening, and the throttle hole 270 is located in the annular groove 260, or the throttle hole 270 is tangent to one side of the annular groove 260, or the throttle hole 270 partially intersects the annular groove 260.

Preferably, the width W of the annular groove 260 is equal to the inner wall throttling orifice diameter D, and the throttling orifice 6 is tangent to both sides of the annular groove 4.

Preferably, the annular groove 260 has a width W < the inner wall orifice diameter D, and the orifice hole 270 partially intersects the annular groove 260.

Preferably, the depth H of the annular groove 260 is more than or equal to the diameter D of the throttling orifice of the inner wall.

Preferably, a width of a bearing gap between the bearing body 220 and the rotating shaft 110 is w, D < w <3D, and preferably, w is 1.5D.

In the bearing structure provided by the utility model, because the throttling hole 270 is partially or completely sunk into the annular groove 260, when the shaft and the inner wall of the radial bearing generate friction, the throttling hole 270 in the annular groove can not be worn, so that the throttling hole is prevented from being blocked, and the pneumatic lubrication effect is improved; the annular groove 260 can increase the position clearance of the throttling hole 270, and the throttling hole oxidation caused by high temperature is effectively avoided while the rigidity of the whole bearing is ensured.

The embodiment of the utility model provides a thrust bearing 100, first journal bearing 200, second journal bearing 400 to rotor system still provides a thrust bearing and journal bearing's anti-rotation structure for stability when guaranteeing the bearing and using.

The anti-rotation thrust bearing 100 of the present embodiment is adapted to be mounted to the rotating shaft 110 to support the rotating shaft 110 in the axial direction. The anti-rotation thrust air bearing 100 comprises a thrust disc 120, a first stator 130, a second stator 140, a first bearing shell 150, a first bearing end cover 160 and a first anti-rotation component 170, wherein the thrust disc 120 is fixedly installed on the rotating shaft 110 or integrally formed with the rotating shaft 110, the first stator 130 is sleeved on the rotating shaft 110 and is positioned on one side of the thrust disc 120, a preset gap is reserved between the first stator 130 and the thrust disc 120, the second stator 140 is sleeved on the rotating shaft 110 and is positioned on the other side of the thrust disc 120, a preset gap is reserved between the second stator 140 and the thrust disc 120, and the first bearing shell 150 is sleeved on the peripheries of the first stator 130 and the second stator 140 and the end face of the first stator 130; the first bearing end cap 160 is sleeved on the rotating shaft 110, is positioned on one side of the second stator 140, and is abutted against the end surface of the second stator 140, and the first stator 130 and the second stator 140 are fixedly connected to form a bearing stator 180; the first rotation preventing member 170 is disposed between the first bearing housing 150 and the bearing stator 180 and connects the two to fix the bearing stator 180 in the circumferential direction.

In an embodiment, one end of the first anti-rotation member 170 is fixedly connected or integrally formed with the first bearing housing 150, and the other end of the first anti-rotation member 170 is detachably connected with the bearing stator 180;

alternatively, one end of the first rotation-preventing member 170 is detachably connected to the first bearing housing 150, and the other end of the first rotation-preventing member 170 is fixedly connected to the bearing stator 180 or integrally formed therewith. This connection of the first anti-rotation member 170 enables the first anti-rotation member 170 to be mounted very conveniently.

Specifically, the first anti-rotation member 170 may be provided in one or more.

The connection between the first anti-rotation member 170 and the bearing stator 180 may be with the first stator 130 or with the second stator 140, and because the first stator 130 and the second stator 140 are fixedly connected, the first anti-rotation member 170 can prevent the bearing stator 180 from rotating circumferentially regardless of which stator is connected.

The present embodiment provides the following specific structure for the first anti-rotation member 170.

As shown in fig. 11 and 22, in the present embodiment, the first rotation-preventing member 170 is provided as a pin and is fixedly mounted on the end surface of the bearing stator 180, and the first bearing housing 150 is provided with a corresponding first receiving hole 151, and circumferential positioning of the bearing stator 180 is achieved by the pin.

As shown in fig. 13 and 14, in the present embodiment, the first rotation-preventing member 170 is provided as a pin and is fixedly mounted on the end surface of the first bearing housing 150 facing the bearing stator 180, and the bearing stator 180 is provided with a corresponding second receiving hole 181, and circumferential positioning of the bearing stator 180 is achieved by the pin.

As shown in fig. 15 and 16, in the present embodiment, the first rotation-preventing member 170 is provided as a pin or a dowel, the first rotation-preventing member 170 is installed from the outer periphery of the first bearing housing 150 in the radial direction of the first bearing housing 150, one end of the first rotation-preventing member 170 is fixed to the first bearing housing 150, the other end is inserted into the outer periphery of the bearing stator 180, and the outer periphery of the bearing stator 180 is provided with a corresponding third receiving hole 182, and circumferential positioning of the bearing stator 180 is achieved by the pin or the dowel.

As shown in fig. 17 and 18, in the present embodiment, the first rotation-preventing member 170 is provided as a key and is fixedly mounted on an end surface of the bearing stator 180 or is integrally formed with one end surface of the bearing stator 180, and the first bearing housing 150 is provided with a corresponding first key groove 152, so that the circumferential positioning of the bearing stator 180 is realized by the key.

As shown in fig. 19 and 20, in the present embodiment, the first rotation-preventing member 170 is configured as a key and is fixedly mounted on the inner diameter surface of the first bearing housing 150, or is integrally formed with the inner diameter surface of the first bearing housing 150, and the bearing stator 180 is provided with a corresponding second key groove 183, so that the circumferential positioning of the bearing stator 180 is realized by the key.

As shown in fig. 21 and 22, in the present embodiment, the first rotation-preventing member 170 is provided as a spherical body and is fixedly mounted on the end surface of the bearing stator 180, and the first bearing housing 150 is provided with a corresponding first hemispherical groove, and circumferential positioning of the bearing stator 180 is achieved by the spherical body.

As shown in fig. 21 and 22, in the present embodiment, the first rotation-preventing member 170 is provided as a spherical body and is fixedly mounted on the end surface of the first bearing housing 150 facing the bearing stator 180, and the bearing stator 180 is provided with a corresponding semi-spherical groove, and circumferential positioning of the bearing stator 180 is achieved by the spherical body.

In the present invention, the specific forms of the anti-rotation members of the above embodiments are merely illustrative of the preferred structures of the anti-rotation members, and do not limit the present invention. Meanwhile, the above structures are directed to the structure in which the thrust disk 120 is located between the bearing stators 180, and the above anti-rotation member is also applicable to the structure in which the bearing stators 180 are located between the thrust disks 120. It should be understood that any component that is disposed between the bearing housing and the bearing stator and that can prevent the bearing stator from rotating in the circumferential direction belongs to the protection scope of the present invention.

The utility model discloses a thrust air bearing is suitable for high-speed and the rotatory rotor system of hypervelocity, perhaps the great rotor system of diameter of axle, and at the operation in-process of rotor, bearing stator job stabilization can not take place to rotate along with the improvement of pivot 110 and thrust disc 120 rotational speed, the dependable performance, long service life, and simple structure.

The anti-rotation radial bearing 200 of the present embodiment is used to be mounted to the rotating shaft 110 to support the rotating shaft 110 in the radial direction. The radial bearing 200 includes a bearing body 220, a second bearing housing 230, a second bearing end cap 240, and a second anti-rotation member 250, wherein the bearing body 220 is sleeved on the rotating shaft 110 and keeps a predetermined gap with the rotating shaft 110, the second bearing housing 230 is covered on an axial end surface and an outer periphery of the bearing body 220, and the second bearing end cap 240 is sleeved on the rotating shaft 110 and abuts against an end surface of the second bearing housing 230; the second rotation preventing member 250 is disposed between the second bearing housing 230 and the bearing body 220 and connects them to fix the bearing body 220 in the circumferential direction.

In this embodiment, one end of the second anti-rotation member 250 is fixedly connected to or integrally formed with the second bearing housing 230, and the other end of the second anti-rotation member 250 is detachably connected to the bearing body 220;

alternatively, one end of the second rotation-preventing member 250 is detachably connected to the second bearing housing 230, and the other end of the second rotation-preventing member 250 is fixedly connected to the bearing body 220 or integrally formed therewith. This manner of attachment of the second anti-rotation member 250 can make installation of the second anti-rotation member 250 very convenient.

Specifically, the second anti-rotation member 250 may be provided in one or more.

The present embodiment provides the following specific structure for the second anti-rotation member 250.

As shown in fig. 23 and 24, in the present embodiment, the second rotation-preventing member 250 is provided as a pin and is fixedly mounted on the end surface of the bearing body 220, and the second bearing housing 230 is provided with a corresponding fourth receiving hole 231, so that the circumferential positioning of the bearing body 220 is realized by the pin.

As shown in fig. 25 and 26, in the present embodiment, the second rotation-preventing member 250 is provided as a pin and is fixedly mounted on the end surface of the second bearing housing 230 facing the bearing body 220, and the bearing body 220 is provided with a corresponding fifth receiving hole 221, so that the circumferential positioning of the bearing body 220 is realized by the pin.

As shown in fig. 27 and 8, in the present embodiment, the second rotation-preventing member 250 is provided as a pin or a dowel, the second rotation-preventing member 250 is installed from the outer periphery of the second bearing housing 230 in the radial direction of the second bearing housing 230, one end of the second rotation-preventing member 250 is fixed to the second bearing housing 230, the other end is inserted into the outer periphery of the bearing body 220, the outer periphery of the bearing body 220 is provided with a corresponding sixth receiving hole 222, and circumferential positioning of the bearing body 220 is achieved by the pin or the dowel.

As shown in fig. 29 and 30, in the present embodiment, the second rotation-preventing member 250 is provided as a key and is fixedly mounted on the end surface of the bearing body 220 or is integrally formed with one end surface of the bearing body 220, and the second bearing housing 230 is provided with a corresponding third key groove 232, so that the circumferential positioning of the bearing body 220 is realized by the key.

As shown in fig. 31 and 32, in the present embodiment, the second rotation-preventing member 250 is provided as a key and is fixedly mounted on the inner diameter surface of the second bearing housing 230, or is integrally formed with the inner diameter surface of the second bearing housing 230, and the bearing body 220 is provided with a corresponding fourth key groove 223, so that the circumferential positioning of the bearing body 220 is realized by the key.

As shown in fig. 33 and 34, in the present embodiment, the second rotation-preventing member 250 is provided as a spherical body and is fixedly mounted on the end surface of the bearing body 220, and the second bearing housing 230 is provided with a corresponding hemispherical groove, so that the circumferential positioning of the bearing body 220 is achieved by the spherical body.

As shown in fig. 33 and 34, in the present embodiment, the second rotation-preventing member 250 may be provided with a spherical body and fixedly mounted on the end surface of the second bearing housing 230 facing the bearing body 220, and the bearing body 220 is provided with a corresponding semi-spherical groove, and the circumferential positioning of the bearing body 220 is realized by the spherical body.

In the present invention, the specific form of the anti-rotation members of the above embodiments is only an exemplary illustration of the preferred structure of the anti-rotation members, and does not constitute a limitation of the present invention, it should be understood that any member that is disposed between the bearing housing and the bearing body can prevent the bearing body from rotating along the circumferential direction belongs to the protection scope of the present invention.

The utility model discloses a radial air bearing is suitable for high-speed and hypervelocity rotatory rotor system, perhaps the great rotor system of shaft diameter, and at the operation in-process of rotor, bearing body job stabilization can not take place to rotate along with the improvement of the 110 rotational speeds of pivot, the dependable performance, long service life, and simple structure.

The utility model discloses in, still provide a miniature gas turbine who uses above-mentioned rotor system, have the advantage that the operation is stable, dependable performance, long service life.

The micro gas turbine applied to the rotor system is a newly developed small heat engine, 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. The utility model discloses a miniature gas turbine can be with step power, step rotational speed operation, and the highest rotational speed reaches 140000RPM, and the fuel quantity is few.

The above description is only a preferred embodiment of the application and is illustrative of the principles of the technology employed. 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 features described above have similar functions to (but are not limited to) those disclosed in this application.

Claims

1. A rotor system, comprising:

2. The rotor system of claim 1, wherein an air slot bevel is further disposed within the thrust bearing.

3. The rotor system according to claim 1, wherein the thrust bearing comprises a second thrust disc, a second stator, a first stator and a first thrust disc, and the second thrust disc, the second stator, the first stator and the first thrust disc are sequentially sleeved on the rotating shaft;

4. The rotor system of claim 3, wherein the thrust bearing includes a suction first air slot on one side and a throw first air slot on the other side.

5. A rotor system according to claim 4, wherein, viewed in the direction of the inlet air,

6. The rotor system according to claim 1, wherein the radial bearing comprises a bearing body, the bearing body is sleeved on the rotating shaft and keeps a gap with the rotating shaft, and the second air groove is circumferentially arranged on a circumferential surface of the rotating shaft corresponding to a position where the bearing body is installed or on an inner wall of the bearing body.

7. The rotor system of claim 6, wherein the second air slot is a parallel skewed slot or a spiral slot.

8. A rotor system according to claim 7, wherein the helical groove has a lead angle of α, a pitch of P, a depth of HL, and a diameter of the rotation shaft of DL,

wherein 30 ° < α <60 °, 1/2DL < P <5 DL.

9. A rotor system according to claim 7, wherein, viewed in the direction of the inlet air,

10. The rotor system of claim 7, wherein the second air slot further comprises a chevron and/or a splay and/or a V-shape.

11. The rotor system according to claim 6, wherein the second air slot in the bearing body is disposed in a middle portion of the rotating shaft corresponding to the inner wall of the bearing body, or disposed in two independent portions symmetrically disposed on two sides of the middle portion.

12. The rotor system according to any one of claims 1-11, wherein the radial bearing comprises a first radial bearing and a second radial bearing, and the thrust bearing, the first radial bearing, the motor, the second radial bearing, the compressor and the turbine are arranged on the rotating shaft in sequence;

13. A micro gas turbine comprising a rotor system according to any one of claims 1 to 12.