CN110552746A

CN110552746A - Rotor system and gas turbine generator set

Info

Publication number: CN110552746A
Application number: CN201810558569.8A
Authority: CN
Inventors: 靳普
Original assignee: To Yue Teng Wind Technology Investment Group Ltd
Current assignee: Liu Muhua
Priority date: 2018-06-01
Filing date: 2018-06-01
Publication date: 2019-12-10
Anticipated expiration: 2038-06-01
Also published as: CN110552746B

Abstract

the invention provides a rotor system and a gas turbine generator set, wherein the rotor system comprises: the shaft body of the rotating shaft is of an integrated structure; the first radial bearing, the motor, the second radial bearing, the compressor and the turbine are sequentially arranged on the rotating shaft, an auxiliary thrust disc is arranged between the compressor and the turbine, a first gap is formed between the compressor and the auxiliary thrust disc, and a second gap is formed between the turbine and the auxiliary thrust disc; the thrust bearing is arranged on the rotating shaft, the thrust bearing is arranged on one side of the gas compressor, which is far away from the turbine, and the arrangement position of the thrust bearing can enable the gravity center of the rotor system to be positioned between the first radial bearing and the second radial bearing; the thrust bearing, the first radial bearing and the second radial bearing are all non-contact bearings. In the invention, an auxiliary thrust disc is arranged between a compressor and a turbine of a rotor system, so that an auxiliary gas thrust bearing is formed. In this way, the load of the main thrust bearing in the rotor system can be reduced.

Description

Rotor system and gas turbine generator set

Technical Field

the invention relates to the technical field of rotors, in particular to a rotor system and a gas turbine generator set.

background

the 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. When the rotor rotates at a high speed, the rotor is subjected to a force in the radial direction and a force in the axial direction. In order to limit the radial and axial movement of the rotating shaft, a radial bearing and a thrust bearing are required to be installed in the rotor system. The traditional radial bearing and the thrust bearing are both common contact type bearings, and along with the increase of the rotating speed of the rotor, especially when the rotating speed of the rotor exceeds 40000 revolutions per minute, the common contact type bearings cannot meet the requirement of the working rotating speed due to the existence of large mechanical abrasion. On the basis, the non-contact bearing is adopted to replace the original contact bearing.

However, as the rotational speed of the rotor is further increased, the linear velocity of the outer periphery of the thrust disc of the thrust bearing is also increased, and when the linear velocity of the outer periphery of the thrust disc reaches or exceeds the sonic velocity, a shock wave phenomenon occurs. After the shock wave is generated, the gas state of the periphery of the thrust disc is suddenly changed, and the resistance of the thrust bearing is greatly increased, so that the efficiency and the stability of the whole rotor system are reduced. In order to avoid the supersonic velocity of the linear velocity at the outer periphery of the thrust disk, the diameter of the thrust disk is usually small, but when the diameter of the thrust disk is small, the thrust force which can be borne in the axial direction of the rotor is also small, so that the axial force from the gas turbine rotor cannot be borne.

It can be seen that there is a need to provide a new rotor system to solve the above-mentioned problems of the existing gas turbine power generation assemblies.

Disclosure of Invention

The invention provides a rotor system and a gas turbine generator set, which are used for solving the problems of the conventional gas turbine generator set.

in one aspect, the present invention provides a rotor system comprising:

The shaft body of the rotating shaft is of an integrated structure;

the first radial bearing, the motor, the second radial bearing, the compressor and the turbine are sequentially arranged on the rotating shaft, an auxiliary thrust disc is arranged between the compressor and the turbine, a first gap is formed between the compressor and the auxiliary thrust disc, and a second gap is formed between the turbine and the auxiliary thrust disc;

The thrust bearing is arranged on the rotating shaft, the thrust bearing is arranged on one side of the compressor, which is far away from the turbine, and the arrangement position of the thrust bearing can enable the gravity center of the rotor system to be positioned between the first radial bearing and the second radial bearing;

Wherein the thrust bearing, the first radial bearing and the second radial bearing are all non-contact bearings.

On the other hand, the invention also provides a gas turbine generator set which comprises an air inlet channel, a combustion chamber and the rotor system, wherein the air inlet channel is communicated with the air inlet of the air compressor, the air outlet of the air compressor is communicated with the air inlet of the combustion chamber, and the air outlet of the combustion chamber is communicated with the air inlet of the turbine.

In the invention, an auxiliary thrust disc is arranged between a compressor and a turbine of a rotor system, so that an auxiliary gas thrust bearing is formed. Therefore, the load of the main thrust bearing in the rotor system can be reduced, the diameter of the thrust disc of the main thrust bearing can be reduced, the limit rotating speed of the rotating shaft when the peripheral linear speed of the thrust disc of the main thrust bearing reaches the sonic speed can be improved, and the overall power and the efficiency of the rotor system are improved.

Drawings

in order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required to be used in the description of the embodiments of the present invention will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without inventive exercise.

FIG. 1 is a schematic structural diagram of a rotor system according to an embodiment of the present invention;

FIG. 2 is a schematic structural diagram of another rotor system provided in accordance with an embodiment of the present invention;

FIG. 3 is a schematic structural diagram of another rotor system provided in accordance with an embodiment of the present invention;

fig. 4 is a schematic structural diagram of a locking device provided in a rotor system according to an embodiment of the present invention;

FIG. 5 is a schematic structural diagram of another locking device provided in a rotor system according to an embodiment of the present invention;

FIG. 6 is a schematic view of the structure of FIG. 5 in the direction C-C;

FIG. 7 is a schematic structural diagram of a rotating shaft coated with a wear-resistant coating according to an embodiment of the present invention;

FIG. 8 is a schematic structural diagram of a gas turbine power plant provided by an embodiment of the invention;

FIG. 9 is a schematic flow chart diagram illustrating a method for controlling a gas turbine generator set according to an embodiment of the present invention;

FIG. 10 is a schematic flow chart diagram illustrating another method for controlling a gas turbine power plant according to an embodiment of the present invention;

FIG. 11 is a schematic flow chart illustrating a method for controlling a rotor system according to an embodiment of the present invention;

FIG. 12 is a schematic flow chart diagram illustrating another method for controlling a rotor system according to an embodiment of the present invention;

Fig. 13 to 16 are schematic structural views of a foil type gas-magnetic hybrid thrust bearing provided in an embodiment of the present invention;

Fig. 17 to 23 are schematic structural diagrams of a groove type air-magnetic hybrid thrust bearing provided in an embodiment of the present invention;

fig. 24 to 32 are schematic structural views of an air-magnetic hybrid thrust bearing provided by an embodiment of the present invention;

FIGS. 33-40 are schematic structural views of a groove type air-magnetic hybrid radial bearing provided by an embodiment of the present invention;

Fig. 41 to 50 are schematic structural views of an integrated bearing according to an embodiment of the present invention.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

As shown in fig. 1 to 3, an embodiment of the present invention provides a rotor system, including:

The rotating shaft 100, the shaft body of the rotating shaft 100 is an integral structure;

The first radial bearing 500, the motor 400, the second radial bearing 600, the compressor 300 and the turbine 200 are sequentially arranged on the rotating shaft 100, an auxiliary thrust disc 810 is arranged between the compressor 300 and the turbine 200, a first gap is formed between the compressor 300 and the auxiliary thrust disc 810, and a second gap is formed between the turbine 200 and the auxiliary thrust disc 810;

and a thrust bearing 700 disposed on the rotating shaft 100, the thrust bearing 700 being disposed on a side of the compressor 300 away from the turbine 200, the thrust bearing 700 being disposed at a position such that a center of gravity of the rotor system is located between the first radial bearing 500 and the second radial bearing 600;

the thrust bearing 700, the first radial bearing 500, and the second radial bearing 600 are all non-contact bearings.

In the embodiment of the present invention, the thrust bearing 700 is a bearing for restricting the movement of the rotating shaft 100 in the axial direction, and the radial bearing is a bearing for restricting the movement of the rotating shaft 100 in the radial direction.

With the increase of the rotating speed of the rotor, the common contact type bearing can not meet the requirement of the high-rotating-speed rotor. Therefore, in order to meet the development requirement of high-speed rotation of the rotor in the embodiment of the present invention, the thrust bearing 700 and the radial bearing may adopt non-contact bearings.

In the embodiment of the present invention, the shaft body of the rotating shaft 100 is an integral structure, and it can be understood that the shaft body of the rotating shaft 100 is an integral shaft, or the shaft body of the rotating shaft 100 is formed by rigidly connecting a plurality of shaft sections. Since the shaft body of the rotating shaft 100 is an integral structure, the strength of the shaft body is consistent everywhere on the rotating shaft 100, which makes the arrangement position of the thrust bearing 700 on the rotating shaft 100 not limited.

in the embodiment of the present invention, the rotating shaft 100 may be horizontally disposed, and therefore, it can be understood that the rotor system of the embodiment of the present invention is a horizontal rotor system, which may be suitable for a horizontal unit that needs to use the horizontal rotor system, such as a horizontal gas turbine generator set.

In the embodiment of the present invention, the rotating shaft 100 may also be vertically disposed, and therefore, it can be understood that the rotor system of the embodiment of the present invention is a vertical rotor system, which may be suitable for a vertical unit that needs to use the vertical rotor system, such as a vertical gas turbine generator set.

In the embodiment of the present invention, the thrust bearing 700 is disposed on the side of the compressor 300 away from the turbine 200, for example, the thrust bearing 700 may be disposed at a position between the compressor 300 and the second radial bearing 600, the thrust bearing 700 may be disposed at a position between the second radial bearing 600 and the motor 400, the thrust bearing 700 may be disposed at a position between the motor 400 and the first radial bearing 500, the thrust bearing 700 may be disposed at a side of the first radial bearing 500 away from the motor 400, and so on.

For example, when the mass of the turbine 200 is large, such as the turbine 200 is made of a metal material, the embodiment shown in fig. 1 or fig. 2 may be adopted in order to locate the center of gravity of the entire rotor system between the first radial bearing 500 and the second radial bearing 600. When the mass of the turbine 200 is small, for example, the material of the turbine 200 is a ceramic material or a ceramic fiber composite material, the embodiment shown in fig. 3 may be adopted in order to locate the center of gravity of the entire rotor system between the first radial bearing 500 and the second radial bearing 600.

In the embodiment of the present invention, the setting position of the thrust bearing 700 may be flexibly adjusted according to the setting position of each radial bearing and the parameters such as the mass of each component in the entire rotor system (including the mass of the thrust bearing 700 itself), so that the center of gravity of the entire rotor system is located between two radial bearings. Therefore, the whole rotor system forms a spindle structure, and is different from the traditional cantilever type structure, so that the whole rotor system can keep stable structure when rotating at high speed. Preferably, the thrust bearing 700 is positioned such that the center of gravity of the entire rotor system is located on the compressor 300.

when the thrust bearing 700 needs to be disposed at a position between the compressor 300 and the motor 400, the thrust bearing 700 having a smaller thrust disk diameter may be used to prevent the thrust disk of the thrust bearing 700 from blocking the air inlet of the compressor 300. The thrust bearing 700 with the smaller thrust disk diameter can bear less thrust in the axial direction of the rotor than the thrust bearing 700 with the larger thrust disk diameter, which may result in the thrust bearing not being able to better bear the axial force from the gas turbine rotor.

In view of the above, in the embodiment of the present invention, the auxiliary thrust disk 810 is disposed between the compressor 300 and the turbine 200, and a first gap is formed between the compressor 300 and the auxiliary thrust disk 810, and a second gap is formed between the turbine 200 and the auxiliary thrust disk 810; specifically, a first clearance is provided between the impeller of the compressor 300 and the auxiliary thrust disk 810, and a second clearance is provided between the impeller of the turbine 200 and the auxiliary thrust disk 810. Thus, the auxiliary thrust disc 810 and the compressor 300 and the turbine 200 form an auxiliary thrust bearing 800, and the auxiliary thrust bearing 800 is a gas thrust bearing.

As such, the rotor system of the embodiment of the present invention is provided with a dual thrust bearing including the thrust bearing 700 and the auxiliary thrust bearing 800. The axial force of the rotor system can be received by the thrust bearing 700 together with the auxiliary thrust bearing 800, so that the load of the thrust bearing 700 can be reduced. Since the load of the thrust bearing 700 is reduced, the diameter of the thrust disk of the thrust bearing 700 can be reduced. Because the diameter of the thrust disc is reduced, the peripheral linear velocity of the thrust disc is correspondingly reduced under the same rotor rotating speed, so that the limit rotating speed of the rotating shaft 100 when the peripheral linear velocity of the thrust disc reaches the sound speed can be improved, and the overall power and the efficiency of a rotor system are improved. In addition, the diameter of the thrust disc of the thrust bearing 700 is reduced, which can reduce the manufacturing cost of the thrust bearing 700 and the processing difficulty of the thrust disc.

In addition, in embodiments of the present invention, thrust bearing 700 is located at the cold end of the rotor system (i.e., the end away from turbine 200) and secondary thrust bearing 800 is located at the hot end of the rotor system (i.e., the end near turbine 200). On one hand, the gravity center of the rotor system is easier to be positioned between the two radial bearings, and the stability of the rotor system is improved. On the other hand, the thrust bearing 700 is arranged at the cold end of the rotor system, so that the thrust bearing 700 can be arranged as a gas-magnetic hybrid thrust bearing, and the control of the rotor system can be better realized by utilizing the magnetic bearing in the thrust bearing 700, thereby further improving the stability of the rotor system.

In the embodiment of the present invention, the auxiliary thrust disk 810 may be fixedly connected to the rotating shaft 100, and in this case, the thrust bearing 700 is disposed at a position considering the weight of the auxiliary thrust disk 810, so that the center of gravity of the entire rotor system is located between the two radial bearings.

optionally, the auxiliary thrust disk 810 is connected to a housing of the rotor system, a through hole is formed in the center of the auxiliary thrust disk 810, the auxiliary thrust disk 810 is disposed on the rotating shaft 100 in a penetrating manner, and a third gap is formed between the auxiliary thrust disk 810 and the rotating shaft 100.

Through the above arrangement, the weight of the auxiliary thrust disk 810 is borne by the casing of the rotor system, so that the weight of one side of the rotor system turbine 200 is not increased while the axial support is provided for the rotor system, the thrust bearing 700 is arranged at one end of the rotor system, and the compressor 300 and the turbine 200 are arranged at the other end of the rotor system, so that the problem of poor stability of the rotor system caused by the shift of the center of gravity of the rotor system can be avoided.

in the embodiment of the present invention, the auxiliary thrust bearing 800 may be a gas dynamic pressure thrust bearing, a gas static pressure thrust bearing, or a gas dynamic and static pressure thrust bearing.

When the auxiliary thrust bearing 800 selects the aerodynamic thrust bearing 700, the end surface of the auxiliary thrust disk 810 facing the compressor 300, or the end surface of the impeller of the compressor 300 facing the auxiliary thrust disk 810 may be provided with a first hydrodynamic generating groove.

Thus, when the rotating shaft 100 is started to rotate, the rotating shaft 100 drives the impeller of the compressor 300 to rotate, and a dynamic pressure air film is formed between the auxiliary thrust disc 810 and the impeller of the compressor 300, so that the rotor system is axially supported.

Similarly, the end surface of the auxiliary thrust disk 810 facing the turbine 200, or the end surface of the impeller of the turbine 200 facing the auxiliary thrust disk 810, may be provided with a second dynamic pressure generating groove.

Thus, when the impeller of the turbine 200 rotates, a dynamic pressure air film is formed between the auxiliary thrust disk 810 and the impeller of the turbine 200, thereby supporting the rotor system in the axial direction.

in the case where both the first dynamic pressure generating groove and the second dynamic pressure generating groove are provided, the auxiliary thrust bearing 800 can support the rotor system in both directions in the axial direction, thereby further improving the bearing performance of the auxiliary thrust disk 810 in the axial direction.

When the auxiliary power bearing 800 selects the aerostatic thrust bearing 700, the rotor system may be provided with a static pressure air intake throttling pipe communicated with both the first gap and the second gap, and the static pressure air intake throttling pipe is used for conveying a pressure air source into the first gap and the second gap.

Wherein, the static pressure air inlet throttling pipeline can be communicated with an external pressure air source.

Considering that the compressor 300 is disposed in the rotor system, the compressed gas output from the compressor 300 can provide a gas source for the gas hydrostatic thrust bearing 700. Based on this, in the embodiment of the present invention, a static pressure air intake throttling pipeline may be communicated with the air outlet of the compressor 300, and the static pressure air intake throttling pipeline is used for conveying the compressed air output by the compressor 300 into the first gap and the second gap.

Thus, a small portion of the high-temperature and high-pressure gas compressed by the compressor 300 may enter a first gap between the back end surface of the impeller of the compressor 300 and the auxiliary thrust disk 810 and a second gap between the back end surface of the impeller of the turbine 200 and the auxiliary thrust disk 810 through the static pressure inlet throttle pipe to form the gas static pressure thrust bearing 700.

The gas source of the gas hydrostatic thrust bearing 700 is high-temperature and high-pressure gas compressed by the compressor 300, so that an external pressure gas source is omitted; on the other hand, since the sound propagation speed increases with an increase in temperature and increases with an increase in pressure, the sound propagation speed is faster in a high-temperature and high-pressure environment, and the local sound speed in the working environment of the compressor 300 and the turbine 200 is further increased by the gas. Therefore, the diameters of the compressor 300 and the turbine 200 can be further increased at a constant rotation speed to increase the power of the entire rotor system.

In order to adjust the axial bearing capacity of the gas static pressure thrust bearing, the static pressure air inlet throttling pipeline can be provided with a control valve, for example, the static pressure air inlet throttling pipeline can be provided with a switch valve for controlling air inlet, a flow control valve for adjusting air inlet flow and pressure and a pressure adjusting valve.

Alternatively, the inner circumferential surface of the auxiliary thrust disk 810 facing the rotating shaft 100, or the outer circumferential surface of the rotating shaft 100 facing the auxiliary thrust disk 810, may be provided with a third dynamic pressure generating groove.

Thus, when the rotating shaft 100 is started to rotate, a dynamic pressure air film can be formed between the auxiliary thrust disc 810 and the rotating shaft 100, so that the rotor system can be radially supported. Therefore, with the above arrangement, the auxiliary thrust disk 810 of the embodiment of the present invention can also function as a gas radial bearing.

In order to improve the wear resistance of both end surfaces of the auxiliary thrust disk 810, the auxiliary thrust disk 810 may be made of copper or a copper alloy; alternatively, the auxiliary thrust disk 810 may be made of a common steel material, and both end surfaces of the auxiliary thrust disk 810 are coated with babbitt metal plating; alternatively, the auxiliary thrust disk 810 may be made of a general steel material, and support members 820 made of copper or a copper alloy are provided at both sides of the auxiliary thrust disk 810, respectively.

In the embodiment of the invention, the compressor 300 can be a centrifugal compressor, and the turbine 200 can be a centrifugal turbine; the motor 400 may be a dynamic pressure bearing motor, and a fourth dynamic pressure generating groove may be formed at a portion of the rotating shaft 100 corresponding to a bearing of the motor 400.

Further, the motor 400 may also be a starter-integral motor.

Thus, at the initial starting time of the rotor system, the motor 400 may be started in a starting mode to rotate the rotor system, and after the rotation speed of the rotor system is increased to a preset rotation speed, the operating mode of the motor 400 may be switched to a power generation mode.

when the rotor system of the present application is used in a mobile device, such as an extended range electric vehicle, the shaft 100 is in direct contact with the bearing when the rotor system is not in operation. During the running of the automobile, the rotating shaft 100 moves in the radial direction or the axial direction relative to the bearing due to the jolt or vibration, so that abrasion is generated between the rotating shaft 100 and the bearing, and the precision and the service life of the bearing are further influenced.

Therefore, in order to solve the above-mentioned problems, the rotor system of the embodiment of the present invention is provided with a locking device for locking the rotation shaft 100 when the rotor system is not operated.

In the embodiment of the present invention, the structural form and the arrangement manner of the locking device are not exclusive, and for easy understanding, the two embodiments will be specifically described below with reference to the accompanying drawings.

In one embodiment, as shown in fig. 4, the locking device 110 includes a telescopic tightening unit 111, a connecting rod 112 and a fixing part 113, one end of the connecting rod 112 is connected to the fixing part 113, the other end is connected to the telescopic tightening unit 111, the telescopic tightening unit 111 faces an end surface of the rotating shaft 100 far away from the turbine 200, and the other end of the fixing part 113 is fixedly connected to a housing for mounting the rotor system of the present application.

When the rotor system is stopped, the telescopic jacking unit 111 of the locking device acts and pushes the rotating shaft 100 along the axial direction of the rotating shaft 100, so that the stator of the thrust bearing 700 is in contact with the thrust disc, the rotating shaft 100 is axially fixed, and meanwhile, the rotating shaft 100 is radially fixed by using the friction force between the stator of the thrust bearing 700 and the thrust disc.

further, the telescopic tightening unit 111 is provided with a tip portion (not shown), and an end surface of the rotating shaft 100 at an end far from the turbine 200 is provided with a tip hole (not shown). In the locked state, the apex portion pushes into the apex hole of the rotating shaft 100, so that the rotating shaft 100 can be better fixed, and the rotating shaft 100 and the bearing are prevented from being worn and damaged in the driving process of the vehicle.

In another embodiment, as shown in fig. 5-6, the locking device may also be configured as a locking device in the form of ferrule 122. Specifically, the locking device includes a telescopic unit 121 and a ferrule 122, and the ferrule 122 is coupled to a telescopic end of the telescopic unit 121. The ferrule 122 may be a semi-circular ferrule having a radius equal to or slightly larger than the radius of the rotary shaft 100, the axis of the ferrule 122 is disposed in parallel with the axis of the rotary shaft 100, and the telescopic unit 121 is mounted to a substantially axial middle position of the rotary shaft 100 and is fixedly connected to a housing in which the rotor system of the present application is mounted.

when the rotor system is stopped, the telescopic unit 121 is extended to make the ferrule 122 seize the rotating shaft 100 and push the rotating shaft 100 to contact with the radial bearing, thereby radially fixing the rotating shaft 100 and axially fixing the rotating shaft 100 by using the friction force of the radial bearing and the rotating shaft 100.

Further, the telescopic unit 121 may be a piston cylinder or a hydraulic cylinder, which can perform telescopic control.

In this embodiment, the location of the locking device on the rotating shaft 100 may not be limited, and preferably, the locking device is disposed between two radial bearings in the rotor system.

it should be noted that the locking devices in fig. 4 and fig. 6 are both arranged based on the rotor system shown in fig. 1, and the locking devices arranged in the rotor systems according to other embodiments of the present invention are not described one by one here.

In the embodiment of the present invention, by providing the locking device, when the rotor system does not work, the locking device can lock the rotating shaft 100. In this way, the rotation shaft 100 can be prevented from moving in the radial direction or the axial direction with respect to the bearing, and the accuracy and the life of the bearing can be improved.

therefore, in order to solve the above problem, based on other embodiments of the present invention, a rotor system according to an embodiment of the present invention is coated with an anti-wear coating 101 at a portion of the rotating shaft 100 where a bearing is installed, as shown in fig. 7.

The anti-abrasion coating 101 is coated on the part of the rotating shaft 100 where the bearing is installed, so that the abrasion of the rotating shaft 100 and the bearing can be effectively prevented. The wear-resistant coating 101 is preferably a chemically stable, corrosion resistant, highly lubricious non-stick and good resistance to aging, such as polytetrafluoroethylene.

At present, the non-contact bearing generally includes an electromagnetic bearing and an air bearing. However, the electromagnetic bearing has the problems of too large energy consumption, heat generation and the like when being started for a long time; when the surface linear velocity of the air bearing is close to or exceeds the sonic velocity, shock waves can be generated, so that the bearing is unstable, and even disastrous results such as shaft collision and the like are generated.

therefore, in consideration of the development requirement of high rotation speed of the gas turbine or the gas turbine generator set, in order to improve the working performance of the thrust bearing and the radial bearing, in the embodiment of the invention, the thrust bearing may adopt a gas-magnetic hybrid thrust bearing, and the first radial bearing and the second radial bearing may adopt a gas-magnetic hybrid radial bearing.

Any of the rotor systems of the embodiments of the present invention may be adapted for use in a gas turbine generator set. As shown in FIG. 8, an embodiment of the present invention provides a gas turbine power plant including a housing 310, an inlet 320, and a combustion chamber 330, and any one of the above rotor systems. The rotor system includes a rotating shaft 100, a motor 400, a compressor 300, a turbine 200, a thrust bearing 700, a first radial bearing 500, a second radial bearing 600 and an auxiliary thrust bearing 800, which are disposed on the rotating shaft 100, wherein the auxiliary thrust bearing 800 is formed by an auxiliary thrust disc 810 disposed between the compressor 300 and the turbine 200. The air inlet passage 320 is communicated with an air inlet of the compressor 300, an air outlet of the compressor 300 is communicated with an air inlet of the combustion chamber 330, and an air outlet of the combustion chamber 330 is communicated with an air inlet of the turbine 200.

Wherein, the compressor 300 can be a centrifugal compressor, and the turbine 200 can be a centrifugal turbine; the bearing of the motor 400 may be a hydrodynamic bearing, and a portion of the rotating shaft 100 corresponding to the bearing of the motor 400 may be provided with a fourth dynamic pressure generating groove; the combustion chamber 330 may be an annular combustion chamber.

Optionally, the air inlet 320 is formed by the housing of the electric machine 400 and the housing 310 of the gas turbine generator set. Thus, when air enters the compressor through the air inlet 320, the air flows through the housing of the motor 400, and can cool the motor 400.

Optionally, the motor 400 is a starter-integral motor.

The operation of the gas turbine power plant will be described in detail below.

As indicated above, the thrust bearing in the rotor system may be a hybrid gas-magnetic thrust bearing, and the radial bearing may be a hybrid gas-magnetic radial bearing. For convenience of description, a bearing which can perform a lubricating function without rotating the rotating shaft is defined as a hydrostatic bearing, and a bearing which can operate only when the rotating shaft rotates to a certain speed is defined as a hydrodynamic bearing. According to the logic, a static pressure bearing can be formed by arranging a magnetic bearing or a static pressure air inlet throttling hole on the air-magnetic hybrid thrust bearing (or the air-magnetic hybrid radial bearing); the dynamic pressure bearing can be formed by arranging a dynamic pressure generating groove on the gas-magnetic hybrid thrust bearing (or the gas-magnetic hybrid radial bearing).

As shown in fig. 9, an embodiment of the present invention provides a control method for a gas turbine generator set, including:

And S11, opening a hydrostatic bearing in the radial bearing and the thrust bearing to move the rotating shaft to a preset radial position and move the thrust disc of the thrust bearing to a preset axial position.

Wherein, opening the hydrostatic bearing includes: opening magnetic bearings in the bearings and/or delivering gas to static pressure inlet orifices in the bearings.

S12, starting a gas turbine generator set, compressing air by the air compressor, and then enabling the air to enter the combustion chamber and mix and burn fuel in the combustion chamber; the high-temperature high-pressure gas discharged from the combustion chamber impacts a turbine of the turbine to rotate the turbine, and the turbine drives the motor to rotate through the rotating shaft to generate power.

The starting process of the gas turbine generator set is specifically described below by taking the motor as an example for starting the integrated motor.

After receiving the start signal, a gas turbine controller (Electronic Control Unit, abbreviated as ECU) sends a motor driving mode command to a motor power controller (Data Processing Center, abbreviated as DPC); and switching the DPC to a motor driving mode, carrying out frequency conversion on the direct current of the built-in battery of the gas turbine by the DPC, driving the motor to work, and driving the gas turbine to increase the rotating speed by the motor.

And opening the fuel valve after the rotating speed of the gas turbine is increased to the ignition rotating speed, and entering an ignition program. Air enters the air compressor from the air inlet channel to be compressed and then enters the heat regenerator and is preheated by high-temperature gas exhausted from the turbine, the preheated compressed air enters the combustion chamber to be mixed with fuel and combusted, the high-temperature high-pressure gas after the combustion chamber is fully combusted enters the turbine to impact the turbine, so that the turbine of the turbine rotates, the cold compressed air before entering the combustion chamber is preheated by the exhaust pipe after the turbine exhausts, and the turbine drives the air compressor to rotate together to the self-sustaining speed due to the fact that the turbine is connected with the air compressor and the motor through the rotating shaft.

after the gas turbine reaches the self-sustaining rotating speed, the DPC is hung up, the motor idles and continues to increase the accelerator, and the turbine continues to increase the power, so that the rotating speed is increased to the working rotating speed. The ECU sends a generator mode command to the DPC; the DPC is switched to a generator mode, and alternating current output by the motor is rectified and transformed to output voltage and current required by a user.

The compressor is a centrifugal compressor which comprises movable blades and static blades arranged along the circumferential direction, and the static blades are diffusers. Thus, the specific process of the air entering the compressor from the air inlet channel for compression can be as follows: after air enters a movable blade of the centrifugal compressor and is compressed, the air enters a diffuser (namely a static blade) arranged along the circumferential direction and is continuously compressed.

Wherein the turbine is a centrifugal turbine provided with moving blades. The combustion chamber outlet is circumferentially arranged with stationary vanes, which are nozzles. Therefore, the high-temperature and high-pressure gas after the combustion chamber is fully combusted enters the turbine to do work, and the specific process of rotating the turbine can be as follows: the high-temperature and high-pressure gas that has been sufficiently combusted in the combustion chamber is expanded and accelerated by a nozzle (i.e., a stationary blade) arranged in the circumferential direction at the combustion chamber outlet, and then impacts the movable blade of the turbine to rotate the turbine.

And S13, after the rotating speed of the rotating shaft is accelerated to the working rotating speed, closing the static pressure bearing in the radial bearing and the thrust bearing.

Wherein closing the hydrostatic bearing comprises: closing the magnetic bearings in the bearings and/or stopping the delivery of gas to the static pressure intake orifices in the bearings.

And S14, when the gas turbine generator set stops, starting a hydrostatic bearing in the radial bearing and a hydrostatic bearing in the thrust bearing.

And S15, closing the static pressure bearing in the radial bearing and the thrust bearing after the rotating speed of the rotating shaft is reduced to zero.

In the above process, the bearings in the rotor system are controlled so that the hydrostatic bearings in the radial bearing and the thrust bearing are opened until the rotation speed of the rotating shaft reaches the working rotation speed.

When the gas turbine generator set stops, the bearings in the rotor system are controlled, and the hydrostatic bearings in the radial bearing and the thrust bearing are enabled to be opened until the rotating speed of the rotating shaft is zero.

as shown in fig. 10, another control method for a gas turbine generator set according to an embodiment of the present invention includes:

And S21, opening a hydrostatic bearing in the radial bearing and the thrust bearing to move the rotating shaft to a preset radial position and move the thrust disc of the thrust bearing to a preset axial position.

s22, starting a gas turbine generator set, compressing air by the air compressor, and then enabling the air to enter the combustion chamber and mix and burn fuel in the combustion chamber; the high-temperature high-pressure gas discharged from the combustion chamber impacts a turbine of the turbine to rotate the turbine, and the turbine drives the motor to rotate through the rotating shaft to generate power.

and S23, after the rotating speed of the rotating shaft is accelerated to a first preset value, closing the hydrostatic bearings in the radial bearing and the thrust bearing.

Wherein the first preset value may be 5% to 30% of the rated rotation speed.

And S24, when the rotor system accelerates to a first-order critical speed or a second-order critical speed, the hydrostatic bearings in the radial bearing and the thrust bearing are started.

and S25, closing the static pressure bearings in the radial bearing and the thrust bearing after the rotor system smoothly passes the first-order critical speed or the second-order critical speed.

And S26, in the shutdown process of the gas turbine generator set, when the rotor system decelerates to a first-order critical speed or a second-order critical speed, starting the hydrostatic bearings in the radial bearing and the thrust bearing.

And S27, closing the static pressure bearings in the radial bearing and the thrust bearing after the rotor system smoothly passes the first-order critical speed or the second-order critical speed.

And S28, when the rotating speed of the rotating shaft is reduced to a second preset value, opening a hydrostatic bearing in the radial bearing and a hydrostatic bearing in the thrust bearing.

The second preset value may be equal to the first preset value or not, and the second preset value may be 5% to 30% of the rated rotation speed.

And S29, closing the static pressure bearing in the radial bearing and the thrust bearing after the rotating speed of the rotating shaft is reduced to zero.

In the process, before the gas turbine generator set is started, the bearings in the rotor system are controlled, and the hydrostatic bearings of the radial bearing and the thrust bearing are opened. Thus, the rotating shaft is supported to a preset radial position under the action of a hydrostatic bearing of the radial bearing; the thrust disc is pushed to a preset axial position under the action of a hydrostatic bearing of the thrust bearing.

After the gas turbine generator set is started, the rotating speed of the rotating shaft is gradually increased, and when the rotating speed of the rotating shaft reaches a first preset value, for example, 5% to 30% of the rated rotating speed, the bearings in the rotor system are controlled, so that the static pressure bearings in the radial bearing and the thrust bearing stop working. When the rotating speed of the rotating shaft reaches a first-order critical speed or a second-order critical speed, the bearings in the rotor system are controlled, and the hydrostatic bearings of the radial bearing and the thrust bearing are restarted. And after the rotating speed of the rotating shaft stably passes the first-order critical speed or the second-order critical speed, controlling the bearings in the rotor system to enable the hydrostatic bearings in the radial bearing and the thrust bearing to stop working again.

And when the rotating speed of the rotating shaft reaches a second-order critical speed or a first-order critical speed, controlling a bearing in the rotor system to enable the hydrostatic bearings of the radial bearing and the thrust bearing to be started again. And after the rotating speed of the rotating shaft smoothly passes through the second-order critical speed or the first-order critical speed, controlling the bearings in the rotor system to stop the static pressure bearings in the radial bearing and the thrust bearing again. When the rotating speed of the rotating shaft is reduced to a preset value, for example, 5% to 30% of the rated rotating speed, the bearings in the rotor system are controlled, the hydrostatic bearings of the radial bearing and the thrust bearing are opened again until the rotating speed is reduced to zero, and then the bearings in the rotor system are controlled, and the hydrostatic bearings of the radial bearing and the thrust bearing are stopped again.

In the method for controlling the gas turbine generator set, the control of the hydrostatic bearing does not include the control of the auxiliary power bearing.

The following describes a control method of the rotor system based on the control method of the gas turbine power generator set.

as shown in fig. 11, an embodiment of the present invention provides a control method of a rotor system, including:

S101, starting a hydrostatic bearing in the radial bearing and the thrust bearing to enable the rotating shaft to move to a preset radial position and enable a thrust disc of the thrust bearing to move to a preset axial position.

and S102, closing the hydrostatic bearings in the radial bearing and the thrust bearing after the rotating speed of the rotating shaft is accelerated to the working rotating speed.

And S103, when the rotor system is stopped, starting a hydrostatic bearing in the radial bearing and a hydrostatic bearing in the thrust bearing.

And S104, closing the hydrostatic bearings in the radial bearing and the thrust bearing after the rotating speed of the rotating shaft is reduced to zero.

in the process, before the rotor system is started, the bearings in the rotor system are controlled, and the hydrostatic bearings of the radial bearing and the thrust bearing are opened. Thus, the rotating shaft is supported to a preset radial position under the action of a hydrostatic bearing of the radial bearing; the thrust disc is pushed to a preset axial position under the action of a hydrostatic bearing of the thrust bearing. And the hydrostatic bearings in the radial bearing and the thrust bearing are opened until the rotating speed of the rotating shaft reaches the working rotating speed.

When the rotor system stops, the bearings in the rotor system are controlled, and the hydrostatic bearings in the radial bearing and the thrust bearing are enabled to be started until the rotating speed of the rotating shaft is zero.

As shown in fig. 12, an embodiment of the present invention provides another control method for a rotor system, including:

S201, starting a hydrostatic bearing in the radial bearing and the thrust bearing to enable the rotating shaft to move to a preset radial position and enable a thrust disc of the thrust bearing to move to a preset axial position.

Wherein, open hydrostatic bearing includes: opening magnetic bearings in the bearings and/or delivering gas to static pressure inlet orifices in the bearings.

S202, after the rotating speed of the rotating shaft is accelerated to a first preset value, closing a hydrostatic bearing in the radial bearing and the thrust bearing.

wherein the first preset value may be 5% to 30% of the rated rotation speed.

and S203, when the rotor system is accelerated to a first-order critical speed or a second-order critical speed, starting hydrostatic bearings in the radial bearing and the thrust bearing.

And S204, after the rotor system passes through the first-order critical speed or the second-order critical speed in a smooth mode, closing the static pressure bearings in the radial bearing and the thrust bearing.

And S205, when the rotor system decelerates to a first-order critical speed or a second-order critical speed, starting hydrostatic bearings in the radial bearing and the thrust bearing.

And S206, after the rotor system passes through the first-order critical speed or the second-order critical speed in a smooth mode, closing the static pressure bearings in the radial bearing and the thrust bearing.

And S207, when the rotating speed of the rotating shaft is reduced to a second preset value, starting a hydrostatic bearing in the radial bearing and a hydrostatic bearing in the thrust bearing.

and S208, closing the hydrostatic bearings in the radial bearing and the thrust bearing after the rotating speed of the rotating shaft is reduced to zero.

in the process, before the rotor system is started, the bearings in the rotor system are controlled, and the hydrostatic bearings of the radial bearing and the thrust bearing are opened. Thus, the rotating shaft is supported to a preset radial position under the action of a hydrostatic bearing of the radial bearing; the thrust disc is pushed to a preset axial position under the action of a hydrostatic bearing of the thrust bearing.

After the rotor system is started, the rotating speed of the rotating shaft is gradually increased, and when the rotating speed of the rotating shaft reaches a first preset value, for example, 5% to 30% of the rated rotating speed, the bearings in the rotor system are controlled, so that the static pressure bearings in the radial bearing and the thrust bearing stop working. When the rotating speed of the rotating shaft reaches a first-order critical speed or a second-order critical speed, the bearings in the rotor system are controlled, and the hydrostatic bearings of the radial bearing and the thrust bearing are restarted. And after the rotating speed of the rotating shaft stably passes the first-order critical speed or the second-order critical speed, controlling the bearings in the rotor system to enable the hydrostatic bearings in the radial bearing and the thrust bearing to stop working again.

And in the stopping process of the rotor system, the rotating speed of the rotating shaft is gradually reduced, and when the rotating speed of the rotating shaft reaches the second-order critical speed or the first-order critical speed, the bearings in the rotor system are controlled to enable the hydrostatic bearings of the radial bearing and the thrust bearing to be started again. And after the rotating speed of the rotating shaft smoothly passes through the second-order critical speed or the first-order critical speed, controlling the bearings in the rotor system to stop the static pressure bearings in the radial bearing and the thrust bearing again. When the rotating speed of the rotating shaft is reduced to a preset value, for example, 5% to 30% of the rated rotating speed, the bearings in the rotor system are controlled, the hydrostatic bearings of the radial bearing and the thrust bearing are opened again until the rotating speed is reduced to zero, and then the bearings in the rotor system are controlled, and the hydrostatic bearings of the radial bearing and the thrust bearing are stopped again.

in the above-described method for controlling the rotor system, the control of the hydrostatic bearing does not include the control of the auxiliary power bearing.

the gas-magnetic hybrid thrust bearing in the rotor system may include a foil-type gas-magnetic hybrid thrust bearing, a groove-type gas-magnetic hybrid thrust bearing, or a gas-magnetic hybrid thrust bearing in which a magnetic bearing is disposed on one side of a thrust disk and a gas bearing is disposed on the other side of the thrust disk. For the aero-magnetic hybrid radial bearing in the rotor system described above, a foil aero-magnetic hybrid radial bearing or a groove aero-magnetic hybrid radial bearing may be included.

In some embodiments, the aero-magnetic hybrid thrust bearing may be a foil aero-magnetic hybrid thrust bearing.

as shown in fig. 13 to 16, the foil-type air-magnetic hybrid thrust bearing 5100 includes:

the first thrust disc 5101, the first thrust disc 5101 is fixedly connected to the rotating shaft 100;

The first stator 5102 and the second stator 5103 penetrate through the rotating shaft 100, and the first stator 5102 and the second stator 5103 are respectively arranged on two opposite sides of the first thrust disc 5101;

Each of the first stator 5102 and the second stator 5103 includes a first magnetic bearing 5104 and a first foil bearing 5105, the first magnetic bearing 5104 is provided with a plurality of first magnetic components along a circumferential direction, and the first foil bearing 5105 is provided with a second magnetic component capable of generating a magnetic force with the plurality of first magnetic components;

The first foil bearing 5105 is disposed between the first magnetic bearing 5104 and the first thrust disk 5101, and has a fourth gap 5106 with the first thrust disk 5101, and the first foil bearing 5105 is capable of moving in the axial direction of the rotating shaft 100 under the action of magnetic force between the first magnetic member and the second magnetic member.

In the embodiment of the present invention, the fourth gap 5106 and the first magnetic bearing 5104 are provided in the thrust bearing 5100, so that the thrust bearing 5100 forms a hybrid gas-magnetic thrust bearing.

during operation, the gas bearing in the thrust bearing 5100 and the first magnetic bearing 5104 can work in cooperation, and when the thrust bearing 5100 is in a stable working state, the gas bearing is used for supporting; when the thrust bearing 5100 is in an unstable working state, the thrust bearing 5100 is controlled and responded in time by means of the first magnetic bearing 5104.

Therefore, the embodiment of the invention can improve the dynamic performance and stability of the thrust bearing, particularly in a high-speed running state, has strong disturbance resistance, and further improves the bearing capacity of the thrust bearing. The thrust bearing of the embodiment of the invention can meet the requirements of a rotor system with high rotating speed, such as a gas turbine or a gas turbine power generation combined unit.

in the embodiment of the present invention, the outer diameters of the first thrust plate 5101, the first stator 5102 and the second stator 5103 may be equal, and the structures of the first stator 5102 and the second stator 5103 may be identical.

When the rotor system of the embodiment of the present invention is applied to a gas turbine or a gas turbine power generation combined unit, the first stator 5102 and the second stator 5103 may be connected to a housing of the gas turbine through a connection member.

Optionally, the plurality of first magnetic components comprise a plurality of first permanent magnets circumferentially disposed on the first magnetic bearing 5104;

Alternatively, the plurality of first magnetic members include a plurality of first electromagnets circumferentially disposed on the first magnetic bearing 5104, and each of the plurality of first electromagnets includes a first magnetic core 51041 disposed on the first magnetic bearing 5104 and a first coil 51042 wound around the first magnetic core.

In the embodiment of the present invention, when the foil gas-magnetic hybrid thrust bearing 5100 only requires the magnetic member to provide magnetic force and does not require magnetic control, the first magnetic member is preferably a first permanent magnet; when the foil gas-magnetic hybrid thrust bearing 5100 requires both magnetic force and magnetic control, the first magnetic member is preferably a first electromagnet.

When the first magnetic member is a first electromagnet, a current is applied to the first coil 51042, so that the first magnetic core 51041 generates a magnetic force. The magnitude of the current flowing into the first coil 51042 is different, and the magnitude of the magnetic force generated by the first magnetic core 51041 is also different; the direction of the current flowing to the first coil 51042 is different, and the magnetic pole of the first magnetic core 51041 is also different.

In the preferred embodiment of the present invention, the first magnetic core 51041 is formed by laminating a plurality of silicon steel sheets or silicon steel sheets, because the silicon steel sheets or silicon steel sheets have physical properties such as high magnetic permeability and low eddy current loss.

Optionally, the first magnetic bearing 5104 includes:

The first magnetic bearing base 51043 is arranged opposite to the first thrust disc 5101, a plurality of first accommodating grooves 51044 are circumferentially arranged on the first magnetic bearing base 51043, a plurality of first magnetic components are arranged in the first accommodating grooves 51044, and magnetic poles of the plurality of first magnetic components face one side where the first foil bearing 5105 is located;

The first end cap 51045 is disposed on a side of the first magnetic bearing holder 51043 away from the first foil bearing 5105, and is engaged with the first foil bearing 5105 to fix the first magnetic member to the first magnetic bearing holder 51043.

in the preferred embodiment of the present invention, the first magnetic bearing base 51043 is formed by laminating a plurality of silicon steel sheets or silicon steel sheets, because the silicon steel sheets or silicon steel sheets have physical properties such as high magnetic permeability and low eddy current loss. The number of the first receiving grooves 51044 may be, but is not limited to, six or eight, and is uniformly arranged along the circumferential direction of the first magnetic bearing holder 51043. In this way, the magnetic force between the first magnetic bearing holder 51043 and the first foil bearing 5105 can be made more uniform and stable. The plurality of first magnetic members may be provided on the first magnetic bearing holder 51043 in other manners, which is not limited. The material of the first end cap 51045 may be a non-magnetic material, preferably a duralumin material.

Optionally, the first foil bearing 5105 includes:

a first foil bearing mount 51051 fixedly connected to the first magnetic bearing mount 51043;

The first foil 51052 and the second foil 51053 are arranged on the first foil bearing seat 51051, the first foil 51052 is arranged on the first foil bearing seat 51051, and the second foil 51053 is overlapped on one side, close to the first thrust plate 5101, of the first foil 51052;

The second foil 51053 is a flat foil, and the second magnetic component is disposed on the second foil 51053, so that the second foil 51053 can move in the axial direction of the rotating shaft 100 under the magnetic force action of the first magnetic component and the second magnetic component; the first foil 51052 is an elastically deformable foil that is capable of elastically deforming when the second foil 51053 is moved.

wherein the material of the first foil bearing mount 51051 is a non-magnetic material, preferably a duralumin material. The first foil 51052 is an elastically deformable foil, and the first foil 51052 is preferably a stainless steel band that is not magnetically permeable, considering that the material of the magnetically permeable material is hard and brittle and is not suitable for the elastically deformable foil.

In the embodiment of the present invention, the second foil 51053 is provided as a flat foil, so that the distance between the second foil 51053 and the first thrust plate 5101 is conveniently controlled, or the size of the fourth gap 5106 is conveniently controlled. The first foil 51052 is made of an elastically deformable foil, which serves to connect the second foil 51053 and the first foil bearing seat 51051, and on the other hand, the second foil 51053 is movable relative to the first foil bearing seat 51051 in the axial direction of the rotating shaft 100.

Optionally, the first foil 51052 is a wavy elastically deformable foil, and the first foil 51052 is an unclosed ring shape, and is provided with an opening, one end of the opening is a fixed end, the fixed end is fixed on the first foil bearing seat 51051, and the other end of the opening is a movable end;

in this case, when the second foil 51053 moves in the axial direction of the rotating shaft 100, the wave pattern on the first foil 51052 expands or contracts, and the movable end moves in the circumferential direction of the ring shape.

In the embodiment of the present invention, the first foil 51052 is provided as an elastically deformable foil having a wavy shape, so that the second foil 51053 is pushed to move in the axial direction of the rotating shaft 100 by the stretching or shrinking characteristics of the wavy veins.

It should be noted that the shape of the first foil 51052 in the embodiment of the present invention is not limited to the wave shape, and other shapes capable of generating elastic deformation may be applied to the first foil 51052 in the embodiment of the present invention.

Alternatively, the second magnetic member includes a first magnetic material disposed on a side surface of the second foil 51053 adjacent to the first magnetic bearing 5104;

wherein, the first magnetic material is distributed in a strip shape on the second foil 51053 to form a plurality of strip-shaped magnetic portions, and the plurality of strip-shaped magnetic portions are radial or annular;

Alternatively, the first magnetic elements are distributed in dots on the second foils 51053.

The second foil 51053 is preferably made of a non-magnetic material, and after the first magnetic material is sprayed on the surface of the second foil 51053, the first magnetic material may be covered with a ceramic coating. The second foil 51053 may be made by sintering ceramic nanopowders using 40% zirconia, 30% alpha alumina and 30% magnesium aluminate spinel.

If the surface of the second foil 51053 is completely covered with the first magnetic material, the magnetic force generated between the first magnetic material and the first magnetic member is greatly increased, which easily causes the second foil 51053 to be deformed. In view of this, in the embodiment of the present invention, the first magnetic material is sprayed on the surface of the second foil 51053, so that the first magnetic material is distributed in a stripe shape or a dot shape on the second foil 51053, and the magnetic force generated between the first magnetic material and the first magnetic component can be controlled within a reasonable range, thereby preventing the second foil 51053 from being deformed due to an excessive magnetic force.

Optionally, the foil air-magnetic hybrid thrust bearing 5100 further includes a first sensor 5107, and a sensor probe of the first sensor 5107 is disposed in the fourth gap 5106.

In the embodiment of the present invention, by providing the first sensor 5107, parameters, such as the air film pressure at the fourth gap 5106, can be detected in real time. In this way, the first magnetic bearing 5104 can actively control the thrust bearing 5100 based on the detection result of the first sensor 5107, and can achieve high accuracy in control.

Optionally, the first sensor 5107 includes a first sensor cover 51071 and a first sensor probe 51072, a first end of the first sensor probe 51072 is connected to the first sensor cover 51071, the first sensor cover 51071 is fixed on a first magnetic bearing 5104, and through holes for the first sensor probe 51072 to pass through are formed in the first magnetic bearing 5104 and the first foil bearing 5105; the second end of the first sensor probe 51072 passes through the through holes of the first magnetic bearing 5104 and the first foil bearing 5105 and extends to the fourth gap 5106, and the second end of the first sensor probe 51072 is flush with the side of the first foil bearing 5105 close to the first thrust plate 5101.

In the embodiment of the present invention, the first sensor 5107 can be more stably mounted to the first magnetic bearing 5104 by the structural form and mounting manner of the first sensor 5107. The second end of the first sensor probe 51072 is flush with the side of the first foil bearing 5105 close to the first thrust plate 5101, so that on one hand, the first sensor probe 51072 can be prevented from being touched by the first thrust plate 5101, and therefore the first sensor probe 51072 can be protected; on the other hand, the air film in the fourth gap 5106 is not affected, and the air film in the fourth gap 5106 is prevented from being disturbed.

Optionally, the first sensor 5107 is disposed between two adjacent first magnetic components.

in the embodiment of the present invention, at least one first sensor 5107, preferably one first sensor 5107, is disposed on each stator, and the first sensor 5107 is preferably disposed between two adjacent first magnetic components.

optionally, the first sensor 5107 is any one or combination of:

A displacement sensor for detecting the position of the first thrust plate 5101;

A pressure sensor for detecting the air film pressure at the fourth gap 5106;

A speed sensor for detecting the rotation speed of the first thrust plate 5101;

An acceleration sensor for detecting the rotational acceleration of the first thrust plate 5101.

A specific control method of the embodiment of the present invention when the foil gas-magnetic hybrid thrust bearing (in which the first magnetic component in the first magnetic bearing is an electromagnet) participates in the control process of the rotor system will be described in detail below.

the embodiment of the invention provides a control method of a foil type gas-magnetic hybrid thrust bearing, which comprises the following steps:

And S511, starting a first magnetic bearing in the first stator and the second stator, and controlling the first thrust disc to move in the axial direction of the rotating shaft under the action of the magnetic force of the plurality of first magnetic components, so that the difference between a fourth gap between the first thrust disc and a first foil bearing in the first stator and a fourth gap between the first thrust disc and a first foil bearing in the second stator is smaller than or equal to a preset value.

And S512, after the rotating speed of the rotating shaft is accelerated to the working rotating speed, closing the first magnetic bearings in the first stator and the second stator.

And S513, when the rotor system is stopped, starting the first magnetic bearings in the first stator and the second stator.

And S514, after the rotating speed of the rotating shaft is reduced to zero, closing the first magnetic bearing in the first stator and the second stator.

in the process, after the first magnetic bearing is started, the first thrust disc reaches a preset position between the first stator and the second stator under the action of the first magnetic bearing, and fourth gaps are formed among the first thrust disc, the first stator and the end face of the second stator.

as the rotating shaft rotates, the first thrust disc starts to rotate relative to the first stator and the second stator while being lubricated by the air flow in the fourth gap, so as to prevent wear. The specific process of starting the first magnetic bearing is as follows: a current signal with a preset value is input into the first coil, and the first thrust disc reaches a preset position between the first stator and the second stator under the action of the first magnetic bearing.

With the increasing of the rotating speed of the rotating shaft, the rotating speed of the first thrust disc is synchronously increased, when the rotating speed of the rotating shaft reaches the working rotating speed, the first thrust disc can be stabilized by the air film pressure generated by the aerodynamic pressure bearing of the thrust bearing (the fourth gap is arranged between the first thrust disc and the first stator and between the first thrust disc and the second stator, namely the aerodynamic pressure bearing of the thrust bearing is formed), and then the first magnetic bearing can be closed.

When the rotor system stops, the first thrust disc decelerates along with the deceleration of the rotating shaft, and in order to keep the rotating shaft stable in the whole rotor system stopping process, the first magnetic bearing is started when the rotor system stops, and the first magnetic bearing is closed until the first thrust disc completely stops.

The embodiment of the invention also provides another control method of the foil type gas-magnetic hybrid thrust bearing, which comprises the following steps:

And S521, starting a first magnetic bearing in the first stator and the second stator, and controlling the first thrust disc to move in the axial direction of the rotating shaft under the action of the magnetic force of the plurality of first magnetic components, so that the difference between a fourth gap between the first thrust disc and a first foil bearing in the first stator and a fourth gap between the first thrust disc and a first foil bearing in the second stator is smaller than or equal to a preset value.

And S522, after the rotating speed of the rotating shaft is accelerated to the first preset value, closing the first magnetic bearing in the first stator and the second stator.

And S523, when the rotating speed of the rotating shaft is reduced to a second preset value, starting a first magnetic bearing in the first stator and the second stator.

And S524, after the rotating speed of the rotating shaft is reduced to zero, closing the first magnetic bearing in the first stator and the second stator.

As the rotating speed of the rotating shaft is increased, the rotating speed of the first thrust disc is also increased synchronously, and when the rotating speed of the rotating shaft reaches a first preset value, for example, 5% to 30% of the rated rotating speed, the first thrust disc can be stabilized by the air film pressure generated by the aerodynamic bearing of the thrust bearing (the aerodynamic bearing which forms the foil type aerodynamic hybrid thrust bearing is provided with a fourth gap between the first thrust disc and the first stator and the second stator), and at the moment, the first magnetic bearing can be closed.

during the shutdown process of the rotor system, the first thrust disc decelerates along with the deceleration of the rotating shaft, and when the rotating speed of the rotating shaft is lower than a second preset value, for example, 5% to 30% of the rated rotating speed, at this time, the air film pressure generated by the aerodynamic bearing of the thrust bearing also decreases along with the deceleration of the first thrust disc, so that the first magnetic bearing needs to be opened to keep the first thrust disc stable, and the first magnetic bearing can be closed until the first thrust disc completely stops.

Optionally, the method further includes:

When a load is loaded on the first thrust disc, the first thrust disc moves in the axial direction of the rotating shaft under the action of the load, and the difference value between a fourth gap between the first thrust disc and the first foil bearing in the first stator and a fourth gap between the first thrust disc and the first foil bearing in the second stator is larger than a preset value, starting a first magnetic bearing in the first stator and the second stator;

The first magnetic bearing in the first and second stators is turned off when a difference between a fourth gap between the first thrust disc and the first foil bearing in the first stator and a fourth gap between the first thrust disc and the first foil bearing in the second stator is less than or equal to a predetermined value.

When a load is loaded on the first thrust disc, such that the fourth gap between the first thrust disc and the first foil bearing of the first stator or the second stator becomes smaller and approaches the first foil bearing on that side, the first sensor (here, the first sensor is preferably a pressure sensor) obtains a signal of an increase in air pressure, at which time the first magnetic bearing needs to be interworked. The first magnetic bearing does not completely and directly apply magnetic force to the first thrust disc to enable the first thrust disc to move towards the first foil bearing on the other side, but uses the magnetic force to enable the first foil bearing on the other side to move towards the direction far away from the first thrust disc, so that the fourth gap between the first thrust disc and the first foil bearing on the other side is increased, the pressure on the side where the fourth gap is reduced is increased, the first magnetic bearing is adaptive to the weight of a load on the first thrust disc, and the airflow pressure on the two fourth gaps is automatically redistributed. When the first thrust disc reaches the new equilibrium position, the first magnetic bearing stops working.

Specifically, if a fourth gap between the first thrust disc and the first foil bearing in the first stator is smaller than a fourth gap between the first thrust disc and the first foil bearing in the second stator, the first foil bearing in the second stator is controlled to move in the axial direction of the rotating shaft in the direction away from the first thrust disc under the action of magnetic force between the plurality of first magnetic components and the second magnetic component.

and if the fourth gap between the first thrust disc and the first foil bearing in the second stator is smaller than the fourth gap between the first thrust disc and the first foil bearing in the first stator, controlling the first foil bearing in the first stator to move in the axial direction of the rotating shaft in the direction away from the first thrust disc under the action of the magnetic force between the plurality of first magnetic components and the second magnetic component.

Optionally, when a load is applied to the first thrust disc, the first thrust disc moves in the axial direction of the rotating shaft under the action of the load, and a difference between a fourth gap between the first thrust disc and the first foil bearing in the first stator and a fourth gap between the first thrust disc and the first foil bearing in the second stator is greater than a predetermined value, the first magnetic bearing in the first stator and the second stator is turned on, including:

when a load is loaded on the first thrust disc, the first thrust disc moves in the axial direction of the rotating shaft under the action of the load, and the difference value between a fourth gap between the first thrust disc and the first foil bearing in the first stator and a fourth gap between the first thrust disc and the first foil bearing in the second stator is larger than a preset value, controlling the first magnetic bearings in the first stator and the second stator to be started at the maximum power; or,

And when the load is loaded on the first thrust disc, the first thrust disc moves in the axial direction of the rotating shaft under the action of the load, and the difference value between a fourth gap between the first thrust disc and the first foil bearing in the first stator and a fourth gap between the first thrust disc and the first foil bearing in the second stator is larger than a preset value, controlling the first magnetic bearings in the first stator and the second stator to be started in a stroboscopic mode according to a preset frequency.

When external impact disturbance occurs, the first thrust disc may rapidly approach the first foil bearing on one side, which may cause the fourth gap on the side to be instantaneously too small, so that the local gas flow velocity at the fourth gap on the side approaches or even reaches the sonic velocity, thereby causing the shock wave to generate the air hammer self-excitation phenomenon. The generation of the shock wave causes turbulence and chaos in the local gas flow, with the pressure dropping dramatically in steps as the fluid velocity changes from sonic to subsonic. In this case, it is desirable that the side first foil bearing actively "dodge" the first thrust disk, thereby increasing the side fourth gap to maintain the gas flow velocity in the subsonic region as much as possible to maintain its normal fluid pressure. Specifically, the first magnetic bearings on the first stator and the second stator need to be controlled simultaneously, so that the magnetic poles of the first magnetic bearings are excited with the same polarity, that is, the side with the reduced fourth gap generates suction for sucking back the first foil bearing on the side, and the side with the increased fourth gap generates suction for pulling back the first thrust disc. In this way, the difference of the acting distances of the magnetic forces on the two sides is utilized to generate a magnetic force difference, so that the first thrust disc is pulled to enable the fourth gap between the first thrust disc and the first foil bearings on the two sides to be normal, and the first thrust disc is enabled to return to the balance state again.

In the process, the first magnetic bearing is utilized to facilitate real-time control, and the first thrust disc is fixed in a certain minimum range in the axial direction of the rotating shaft by actively balancing the unbalanced mass of the first thrust disc or the factors causing excessive deviation of the first thrust disc, such as the whirling motion of the first thrust disc. In addition, in the acceleration process of the first thrust disc, the position where the shock wave is generated (namely the linear velocity supersonic speed part) can be accurately positioned, and the first magnetic bearing generates opposite force to balance the shock wave action by controlling the current magnitude, the current direction and the like of the first magnetic bearing. And after the shock wave is stable, adjusting the control strategy of the first magnetic bearing again, and fixing the first thrust disc in a certain minimum range in a most energy-saving mode.

In summary, the embodiment of the invention has the following beneficial effects:

Firstly, the electromagnetic bearing and the gas bearing work cooperatively, so that the dynamic performance and stability of the bearing in a high-speed running state are improved, the disturbance resistance is high, and the bearing capacity of the bearing is improved. Meanwhile, the electromagnetic bearing and the gas bearing are in a parallel connection structure, so that the structure is simplified, the integration level is high, the processing, the manufacturing and the operation are easy, and the comprehensive performance of the bearing is improved. When the rotor system is started or stopped, the electromagnetic bearings can be used for enabling the thrust disc and the stator of the bearing to rotate in the bearing gap, the low-speed performance of the bearing is improved, the service life of the bearing is prolonged, and the safety and the reliability of the bearing and the whole system can be improved.

Compared with the traditional gas dynamic and static pressure hybrid thrust bearing adopting the combination of a gas static pressure bearing and a gas dynamic pressure bearing, the foil type gas-magnetic hybrid thrust bearing provided by the embodiment of the invention has the advantage of high response speed.

thirdly, the magnetic material is arranged on the foil, the foil can be properly deformed through the attraction of the magnetic pole of the electromagnetic bearing, the highest pressure of one side of a lubricating air film in the bearing is improved, the lubricating air flow is prevented from leaking, the capability of the thrust disc for resisting the disturbance eccentric wall collision is improved, and the bearing capacity of the bearing is improved.

Fourthly, a pressure sensor with lower cost is adopted to collect the pressure change of the air film, the deformation of the foil is controlled by a simple control method, and higher rotor damping can be provided, so that the stability of the rotor is improved. In addition, the control method is simple, and the requirement on the machining precision of the bearing is not high.

in some embodiments, the aero-magnetic hybrid thrust bearing may be a groove aero-magnetic hybrid thrust bearing.

As shown in fig. 17 to 23, the groove type air-magnetic hybrid thrust bearing 5200 includes:

A second thrust disk 5201, the second thrust disk 5201 is fixedly connected to the rotating shaft 100, and a third magnetic component is arranged on the second thrust disk 5201;

A third stator 5202 and a fourth stator 5203 which are arranged on the rotating shaft 100 in a penetrating way, wherein the third stator 5202 and the fourth stator 5203 are respectively arranged on two opposite sides of the second thrust plate 5201;

of the third stator 5202 and the fourth stator 5203, each of the stators includes a second magnetic bearing 5204, the second magnetic bearing 5204 is provided with a plurality of fourth magnetic members capable of generating a magnetic force with the third magnetic member in the circumferential direction, the second magnetic bearing 5204 has a fifth gap 5206 with the second thrust plate 5201, and the second thrust plate 5201 is movable in the axial direction of the rotary shaft 100 by the magnetic force between the third magnetic member and the plurality of fourth magnetic members;

In this case, the end surfaces of the second thrust plate 5201 facing the third stator 5202 and the fourth stator 5203, or the end surfaces of the third stator 5202 and the fourth stator 5203 facing the second thrust plate 5201 are provided with fifth dynamic pressure generating grooves 5205.

In the embodiment of the present invention, the thrust bearing 5200 is formed into an air-magnetic hybrid thrust bearing by providing the fifth gap 5206 and the second magnetic bearing 5204 in the thrust bearing 5200.

During operation, the gas bearing in the thrust bearing 5200 and the second magnetic bearing 5204 can work together, and when the thrust bearing 5200 is in a stable operating state, the gas bearing is used for supporting; when the thrust bearing 5200 is in an unstable working state, the second magnetic bearing 5204 is used for controlling and responding to the thrust bearing 5200 in time.

In the embodiment of the present invention, the outer diameters of the second thrust plate 5201, the third stator 5202 and the fourth stator 5203 may be equal, and the structures of the third stator 5202 and the fourth stator 5203 may be identical.

when the rotor system of the embodiment of the present invention is applied to a gas turbine, the third stator 5202 and the fourth stator 5203 may be connected to a casing of the gas turbine by a connection member.

In the embodiment of the invention, when the second thrust plate 5201 is rotated, the flowing gas existing in the fifth gap 5206 is pressed into the fifth dynamic pressure generating groove 5205, thereby generating a pressure to realize that the second thrust plate 5201 is held in the axial direction without contact. The pressure generated by the fifth dynamic pressure generating groove 5205 varies with the angle, groove width, groove length, groove depth, number of grooves, and flatness of the fifth dynamic pressure generating groove 5205. The magnitude of the pressure generated by the fifth dynamic pressure generating groove 5205 is also related to the rotation speed of the second thrust plate 5201 and the fifth gap 5206. The parameters of the fifth dynamic pressure generating groove 5205 may be designed according to actual conditions. The fifth dynamic pressure generating groove 5205 may be formed on the third stator 5202 and the fourth stator 5203 by forging, rolling, etching, or punching, or the like, or the fifth dynamic pressure generating groove 5205 may be formed on the second thrust plate 5201 by forging, rolling, etching, or punching, or the like.

Optionally, the plurality of fourth magnetic components include a plurality of second permanent magnets, which are circumferentially disposed on the second magnetic bearing 5204;

Alternatively, the plurality of fourth magnetic members include a plurality of second electromagnets that are circumferentially disposed on the second magnetic bearing 5204, and each of the plurality of second electromagnets includes a second magnetic core 52041 disposed on the second magnetic bearing 5204 and a second coil 52042 wound around the second magnetic core 52041.

In the embodiment of the present invention, when the slot air-magnetic hybrid thrust bearing 5200 only requires the magnetic component to provide magnetic force and does not require magnetic control, the fourth magnetic component is preferably a second permanent magnet; when the slot air-magnetic hybrid thrust bearing 5200 requires both magnetic force and magnetic control, the fourth magnetic member is preferably a second electromagnet.

When the fourth magnetic member is the second electromagnet, the second magnetic core 52041 can generate a magnetic force by applying a current to the second coil 52042. The magnitude of the current applied to the second coil 52042 is different, and the magnitude of the magnetic force generated by the second magnetic core 52041 is also different; the direction of the current flowing to the second coil 52042 is different and the magnetic pole of the second magnetic core 52041 is also different.

In the preferred embodiment of the present invention, the second magnetic core 52041 may be formed by laminating a plurality of silicon steel sheets or silicon steel sheets, because the silicon steel sheets or silicon steel sheets have physical properties such as high magnetic permeability and low eddy current loss.

optionally, the second magnetic bearing 5204 includes:

A second magnetic bearing seat 52043, the second magnetic bearing seat 52043 is disposed opposite to the second thrust plate 5201, the second magnetic bearing seat 52043 is circumferentially provided with a plurality of second accommodation grooves 52044, the plurality of fourth magnetic members are disposed in the plurality of second accommodation grooves 52044, and magnetic poles of the plurality of fourth magnetic members face a side where the second thrust plate 5201 is located;

a second end cover 52045 and a first press ring 52046, wherein the second end cover 52045 is disposed on a side of the second magnetic bearing holder 52043 away from the second thrust plate 5201, the first press ring 52046 is disposed on a side of the second magnetic bearing holder 52043 close to the second thrust plate 5201, and the second end cover 52045 is fitted with the first press ring 52046 to fix the plurality of fourth magnetic members to the second magnetic bearing holder 52043.

In the preferred embodiment of the present invention, the second magnetic bearing seat 52043 may be formed by laminating a plurality of silicon steel sheets or silicon steel sheets, because the silicon steel sheets or silicon steel sheets have physical properties such as high magnetic permeability and low eddy current loss. The number of the second accommodation grooves 52044 may be, but not limited to, six or eight, and are uniformly arranged along the circumferential direction of the second magnetic bearing holder 52043. In this way, the magnetic force between the second magnetic bearing 5204 and the second thrust plate 5201 can be made more uniform and stable. The plurality of fourth magnetic members may be provided on the second magnetic bearing base 52043 in another manner, but is not limited thereto. The material of the second end cover 52045 may be a non-magnetic material, preferably a duralumin material. The material of the first compression ring 52046 may be a non-magnetic material, preferably a duralumin material.

in the embodiment of the present invention, a fifth dynamic pressure generating groove 5205 may be provided on the first pressing ring 52046, and the first pressing ring 52046 may be made of a stainless material in order to facilitate the processing of the fifth dynamic pressure generating groove 5205.

Alternatively, the third magnetic member includes a second magnetic material (not shown in the drawings) provided on an end surface of the second thrust plate 5201 facing the third stator 5202 and the fourth stator 5203;

Wherein, the second magnetic material is distributed in a strip shape on the second thrust disk 5201 to form a plurality of strip-shaped magnetic portions, and the plurality of strip-shaped magnetic portions are radial or annular;

Alternatively, the second magnetic members are disposed in a dot shape on the second thrust plate 5201.

In the embodiment of the present invention, the second magnetic material is distributed in a stripe shape or a dot shape on the second thrust plate 5201, so that the magnetic force generated between the second magnetic material and the fourth magnetic member can be controlled within a reasonable range.

Alternatively, the fifth dynamic pressure generating grooves 5205 may be arranged in a radial or concentric manner, which is advantageous for the gas film to be more uniformly distributed in the fifth gap 5206.

Alternatively, the fifth dynamic pressure generating groove 5205 includes a first spiral groove 52051 and a second spiral groove 52052, the first spiral groove 52051 surrounds the second spiral groove 52052, the spiral directions of the first spiral groove 52051 and the second spiral groove 52052 are opposite, and an end of the first spiral groove 52051 near the second spiral groove 52052 is connected to or disconnected from an end of the second spiral groove 52052 near the first spiral groove 52051.

wherein, the distance from the end of the first spiral groove 52051 close to the second spiral groove 52052 to the axle center of the rotating shaft 100 is equal to the distance from the end of the first spiral groove 52051 close to the second spiral groove 52052 to the outer peripheral edge of the third stator 5202 or the fourth stator 5203 or the second thrust plate 5201. Alternatively, the distance from the end of the second spiral groove 52052 close to the first spiral groove 52051 to the axial center of the rotating shaft 100 is equal to the distance from the end of the second spiral groove 52052 close to the first spiral groove 52051 to the outer peripheral edge of the third stator 5202 or the fourth stator 5203 or the second thrust plate 5201.

In the embodiment of the present invention, by adopting the arrangement of the fifth dynamic pressure generating groove 5205, the second thrust plate 5201 can be held in a non-contact manner in a desired manner when the rotating shaft 100 rotates in the forward direction or in the reverse direction, so that the rotating shaft 100 has advantages of high load capacity and good stability.

Optionally, in the third stator 5202 and the fourth stator 5203, each stator is further provided with a first static pressure intake orifice 5208, one end of the first static pressure intake orifice 5208 is communicated with the fifth gap 5206, and the other end is connected with an external air source for conveying the external air source into the fifth gap 5206.

In the embodiment of the present invention, the first static pressure intake orifice 5208 is provided to form a gas static pressure bearing, and the thrust bearing 5200 can constitute a gas hybrid thrust bearing. The flow diameter of the first static pressure intake orifice 5208 can be adjusted according to actual conditions such as air quantity demand.

Alternatively, in the third stator 5202 and the fourth stator 5203, a plurality of first static pressure intake orifices 5208 are provided on each stator, and the plurality of first static pressure intake orifices 5208 are provided at intervals in the circumferential direction of the stator.

In the embodiment of the invention, the plurality of first static pressure intake orifices 5208 are provided at intervals in the circumferential direction of the stator, and preferably, at even intervals in the circumferential direction of the stator. This is advantageous in making the gas film pressure within the fifth gap 5206 more uniform.

Alternatively, in the third stator 5202 and the fourth stator 5203, the distance from the first static pressure intake orifice 5208 to the axial center of the rotating shaft 100 is greater than or equal to the distance from the first static pressure intake orifice 5208 to the outer peripheral edge of the stator.

In the embodiment of the present invention, the first static pressure intake orifice 5208 is provided in such a manner that the gas static pressure bearing is more stable, and if the static pressure intake orifice is too close to the axis of the rotating shaft 100, the gas film cannot be effectively spread over the entire end surface of the second thrust plate 5201 in time, and the rotation of the second thrust plate 5201 is not stable enough. Preferably, the distance from the first static pressure intake orifice 5208 to the axial center of the rotating shaft 100 is equal to the distance from the first static pressure intake orifice 5208 to the outer peripheral edge of the stator.

Optionally, the slot air-magnetic hybrid thrust bearing 5200 further includes a second sensor 5207, and a sensor probe of the second sensor 5207 is disposed in the fifth gap 5206.

in the embodiment of the present invention, by providing the second sensor 5207, a parameter at the fifth gap 5206, such as an air film pressure at the fifth gap 5206, can be detected in real time. In this way, the second magnetic bearing 5204 can actively control the thrust bearing 5200 based on the detection result of the second sensor 5207, and can achieve high control accuracy.

Optionally, the second sensor 5207 includes a second sensor cover 52071 and a second sensor probe 52072, a first end of the second sensor probe 52072 is connected to the second sensor cover 52071, the second sensor cover 52071 is fixed to the second magnetic bearing 5204, and the second magnetic bearing 5204 is provided with a through hole for the second sensor probe 52072 to pass through; the second end of the second sensor probe 52072 passes through a through hole in the second magnetic bearing 5204 and extends to the fifth gap 5206, and the second end of the second sensor probe 52072 is flush with the side of the second magnetic bearing 5204 close to the second thrust plate 5201.

In the embodiment of the present invention, the second sensor 5207 can be more stably mounted to the second magnetic bearing 5204 by the above-described configuration and mounting manner of the second sensor 5207. Moreover, the second end of the second sensor probe 52072 is flush with the side of the second magnetic bearing 5204 close to the second thrust plate 5201, so that on one hand, the second sensor probe 52072 can be prevented from being touched by the second thrust plate 5201, thereby being beneficial to protecting the second sensor probe 52072; on the other hand, the air film in the fifth gap 5206 is not affected, and the air film in the fifth gap 5206 is prevented from being disturbed.

Alternatively, the second sensor 5207 is disposed between the adjacent two fourth magnetic members.

in the embodiment of the present invention, at least one second sensor 5207 should be disposed on each stator, preferably one second sensor 5207 is disposed, and the second sensor 5207 is preferably disposed between two adjacent fourth magnetic members.

Optionally, the second sensor 5207 is any one or combination of:

A displacement sensor for detecting the position of the second thrust plate 5201;

a pressure sensor for detecting the air film pressure at the fifth gap 5206;

A speed sensor for detecting the rotational speed of the second thrust plate 5201;

an acceleration sensor for detecting the rotational acceleration of the second thrust plate 5201.

The following describes a specific control method of the embodiment of the present invention when the slot air-magnetic hybrid thrust bearing (in which the fourth magnetic component in the second magnetic bearing is an electromagnet) participates in the control process of the rotor system.

the embodiment of the invention provides a control method of a groove type gas-magnetic hybrid thrust bearing, which comprises the following steps:

And S531, starting a second magnetic bearing in the third stator and the fourth stator, and controlling the second thrust disc to move in the axial direction of the rotating shaft under the action of magnetic force between the third magnetic component and the plurality of fourth magnetic components, so that the difference value between a fifth gap between the second thrust disc and the second magnetic bearing in the third stator and a fifth gap between the second thrust disc and the second magnetic bearing in the fourth stator is smaller than or equal to a preset value.

s532, after the rotating speed of the rotating shaft is accelerated to the working rotating speed, the second magnetic bearings in the third stator and the fourth stator are closed.

And S533, when the rotor system is stopped, starting a second magnetic bearing in the third stator and the fourth stator.

And S534, after the rotating speed of the rotating shaft is reduced to zero, closing the second magnetic bearing in the third stator and the fourth stator.

in the above process, after the second magnetic bearing is started, the second thrust disc reaches a predetermined position between the third stator and the fourth stator under the action of the second magnetic bearing, and fifth gaps are formed between the second thrust disc and the end faces of the third stator and the fourth stator.

As the rotating shaft rotates, the second thrust disc starts to rotate relative to the third stator and the fourth stator while being lubricated by the air flow in the fifth gap, to prevent wear. The specific process of opening the second magnetic bearing is as follows: and a current signal with a preset value is input into the second coil, and the second thrust disc reaches a preset position between the third stator and the fourth stator under the action of the second magnetic bearing.

with the increasing of the rotating speed of the rotating shaft, the rotating speed of the second thrust disc is synchronously increased, when the rotating speed of the rotating shaft reaches the working rotating speed, the second thrust disc can be stabilized by the air film pressure generated by the aerodynamic pressure bearing of the thrust bearing (the fifth gap is arranged between the second thrust disc and the third stator and the fourth stator, namely the aerodynamic pressure bearing of the thrust bearing is formed), and then the second magnetic bearing can be closed.

When the rotor system stops, the second thrust disc decelerates along with the deceleration of the rotating shaft, and in order to keep the rotating shaft stable in the whole rotor system stopping process, the second magnetic bearing is started when the rotor system stops, and the second magnetic bearing is closed until the second thrust disc completely stops.

The embodiment of the invention also provides another control method of the groove type gas-magnetic hybrid thrust bearing, which comprises the following steps:

And S541, starting a second magnetic bearing in the third stator and the fourth stator, and controlling the second thrust disc to move in the axial direction of the rotating shaft under the action of magnetic force between the third magnetic component and the plurality of fourth magnetic components, so that the difference value between a fifth gap between the second thrust disc and the second magnetic bearing in the third stator and a fifth gap between the second thrust disc and the second magnetic bearing in the fourth stator is smaller than or equal to a preset value.

And S542, after the rotating speed of the rotating shaft is accelerated to the first preset value, closing the second magnetic bearing in the third stator and the fourth stator.

And S543, when the rotating speed of the rotating shaft is reduced to a second preset value, starting a second magnetic bearing in the third stator and the fourth stator.

And S544, after the rotating speed of the rotating shaft is reduced to zero, closing the second magnetic bearing in the third stator and the fourth stator.

In the above process, after the second magnetic bearing is started, the second thrust disc reaches a predetermined position between the third stator and the fourth stator under the action of the second magnetic bearing, and fifth gaps are formed between the second thrust disc and the end faces of the third stator and the fourth stator. As the rotating shaft rotates, the second thrust disc starts to rotate relative to the third stator and the fourth stator while being lubricated by the air flow in the fifth gap, to prevent wear. The specific process of opening the second magnetic bearing is as follows: and a current signal with a preset value is input into the second coil, and the second thrust disc reaches a preset position between the third stator and the fourth stator under the action of the second magnetic bearing.

as the rotating speed of the rotating shaft is increased, the rotating speed of the second thrust disc is also increased synchronously, and when the rotating speed of the rotating shaft reaches a second preset value, for example, 5% to 30% of the rated rotating speed, the second thrust disc can be stabilized by the air film pressure generated by the aerodynamic bearing of the thrust bearing (the aerodynamic bearing which forms the groove-type air-magnetic hybrid thrust bearing is provided with a fifth gap between the second thrust disc and the third stator and the fourth stator), and at that time, the second magnetic bearing can be closed.

During the shutdown process of the rotor system, the second thrust disc decelerates along with the deceleration of the rotating shaft, and when the rotating speed of the rotating shaft is lower than a second preset value, for example, 5% to 30% of the rated rotating speed, at this time, the air film pressure generated by the aerodynamic bearing of the thrust bearing also decreases along with the deceleration of the second thrust disc, so that the second magnetic bearing needs to be opened to keep the second thrust disc stable, and the second magnetic bearing can be closed until the second thrust disc completely stops.

Optionally, the method further includes:

When a load is loaded on a second thrust disc, the second thrust disc moves in the axial direction of the rotating shaft under the action of the load, and the difference value between a fifth gap between the second thrust disc and a second magnetic bearing in the third stator and a fifth gap between the second thrust disc and a second magnetic bearing in the fourth stator is larger than a preset value, the second magnetic bearing in the third stator or the fourth stator is started;

and when the difference value between the fifth gap between the second thrust disc and the second magnetic bearing in the third stator and the fifth gap between the second thrust disc and the second magnetic bearing in the fourth stator is less than or equal to a preset value, closing the second magnetic bearing in the third stator or the fourth stator.

When a load is loaded on the second thrust disk, and a fifth gap between the second thrust disk and the second magnetic bearing of the third stator or the fourth stator is reduced and approaches the second magnetic bearing on the side, the second sensor (here, the second sensor is preferably a pressure sensor) obtains a signal of an increase in air pressure, and at this time, the second magnetic bearing needs to be involved in work. The second magnetic bearing acts magnetic force on the second thrust disc to move the second thrust disc to the second magnetic bearing on the other side, and when the second thrust disc reaches a new balance position, the second magnetic bearing stops working.

Specifically, if a fifth gap between the second thrust disk and the second magnetic bearing of the third stator is smaller than a fifth gap between the second thrust disk and the second magnetic bearing of the fourth stator, and a difference between the fifth gap between the second thrust disk and the second magnetic bearing of the third stator and the fifth gap between the second thrust disk and the second magnetic bearing of the fourth stator is greater than a predetermined value, the second magnetic bearing of the fourth stator is controlled to move the second thrust disk in the axial direction of the rotating shaft in the direction away from the fourth stator under the magnetic force action between the third magnetic member and the plurality of fourth magnetic members.

And if the fifth gap between the second thrust disc and the second magnetic bearing in the fourth stator is smaller than the fifth gap between the second thrust disc and the second magnetic bearing in the third stator, and the difference value between the fifth gap between the second thrust disc and the second magnetic bearing in the third stator and the fifth gap between the second thrust disc and the second magnetic bearing in the fourth stator is larger than a preset value, controlling the second magnetic bearing in the third stator to enable the second thrust disc to move in the axial direction of the rotating shaft in the direction away from the third stator under the action of the magnetic force between the third magnetic component and the plurality of fourth magnetic components.

Optionally, when a load is applied to the second thrust disc, the second thrust disc moves in the axial direction of the rotating shaft under the action of the load, and a difference between a fifth gap between the second thrust disc and the second magnetic bearing in the third stator and a fifth gap between the second thrust disc and the second magnetic bearing in the fourth stator is greater than a predetermined value, the second magnetic bearing in the third stator or the fourth stator is turned on, including:

when the load is loaded on the second thrust disc, the second thrust disc moves in the axial direction of the rotating shaft under the action of the load, and the difference value between a fifth gap between the second thrust disc and the second magnetic bearing in the third stator and a fifth gap between the second thrust disc and the second magnetic bearing in the fourth stator is larger than a preset value, controlling the second magnetic bearing in the third stator or the fourth stator to be started at the maximum power; or,

And when the load is loaded on the second thrust disc, the second thrust disc moves in the axial direction of the rotating shaft under the action of the load, and the difference value between a fifth gap between the second thrust disc and the second magnetic bearing in the third stator and a fifth gap between the second thrust disc and the second magnetic bearing in the fourth stator is greater than a preset value, controlling the second magnetic bearing in the third stator or the fourth stator to be started in a stroboscopic mode according to preset frequency.

When external impact disturbance occurs, the second thrust disc may rapidly approach the second magnetic bearing on one side, which may cause the fifth gap on the side to be instantaneously too small, so that the local gas flow velocity at the fifth gap on the side approaches to even reaches the sonic velocity, thereby causing shock wave to generate air hammer self-excitation. The generation of the shock wave causes turbulence and chaos in the local gas flow, with the pressure dropping dramatically in steps as the fluid velocity changes from sonic to subsonic. In this case, it is necessary to control the second magnetic bearings in the third stator or the fourth stator to be turned on at the maximum power, or to control the second magnetic bearings in the third stator or the fourth stator to be turned on in a stroboscopic manner according to a preset frequency, so as to provide a damping effect on the disturbance, thereby effectively suppressing the external disturbance. And when the second thrust disc returns to the balance state again, the second magnetic bearing stops working.

In the embodiment of the present invention, in the case where the electromagnetic bearing (the fourth magnetic member in the second magnetic bearing is an electromagnet, that is, the electromagnetic bearing is formed) and the aerostatic bearing (the aerostatic bearing is formed by the first static pressure intake orifice provided in the third stator and the fourth stator) are provided at the same time, the electromagnetic bearing and the aerostatic bearing can be mutually backed up, and in the case where one of them fails, or fails to satisfy the opening condition, the other can serve as the backup bearing to perform the same function. For example, in the case of detecting the failure of the electromagnetic bearing, an external air source is controlled to be opened to perform corresponding actions instead of the electromagnetic bearing, so that the safety and the reliability of the bearing are improved.

in the embodiment of the present invention, in the case where the electromagnetic bearing and the aerostatic bearing are provided at the same time, the step of "turning on the hydrostatic bearing in the thrust bearing to move the thrust disk of the thrust bearing to the preset axial position" may include the following embodiments:

Turning on a second magnetic bearing of the third stator and the fourth stator; and/or starting an external gas source, and conveying gas to the fifth gap through the first static pressure gas inlet throttling hole;

Controlling the second thrust disc to move in an axial direction of the rotating shaft under a magnetic force between the third magnetic member and the fourth magnetic member, and/or a pushing action of the gas, so that a difference between the fifth gap between the second thrust disc and a second magnetic bearing of the third stator and the fifth gap between the second thrust disc and a second magnetic bearing of the fourth stator is less than or equal to the predetermined value.

In the process, the second thrust disc is fixed in a certain minimum range in the axial direction of the rotating shaft by utilizing the advantage that the second magnetic bearing is convenient to control in real time and actively balancing the unbalanced mass of the second thrust disc or the factors causing the excessive deviation of the second thrust disc, such as the whirling motion of the second thrust disc. In addition, in the acceleration process of the second thrust disc, the position (namely the linear velocity supersonic speed part) generating the shock wave can be accurately positioned, and the second magnetic bearing generates opposite force to balance the shock wave action by controlling the current magnitude, the current direction and the like of the second magnetic bearing. And after the shock wave is stable, adjusting the control strategy of the second magnetic bearing again, and fixing the second thrust disc in a certain minimum range in a most energy-saving mode.

firstly, the electromagnetic bearing and the gas bearing work cooperatively, so that the dynamic performance and stability of the bearing in a high-speed running state are improved, the disturbance resistance is high, and the bearing capacity of the bearing is improved. Meanwhile, the electromagnetic bearing and the gas bearing are in a parallel connection structure, so that the structure is simplified, the integration level is high, the processing, the manufacturing and the operation are easy, and the comprehensive performance of the bearing is improved. When the rotor system is started or stopped, the electromagnetic bearing can be used for enabling the thrust disc and the stator of the bearing to rotate in the fifth gap, the low-speed performance of the bearing is improved, the service life of the bearing is prolonged, and the safety and the reliability of the bearing and the whole system can be improved.

secondly, compared with the traditional gas dynamic and static pressure hybrid thrust bearing adopting the combination of a gas static pressure bearing and a gas dynamic pressure bearing, the groove type gas-magnetic hybrid thrust bearing provided by the embodiment of the invention has the advantage of high response speed.

And thirdly, the gas hydrostatic bearing is added to form a groove type hybrid dynamic-static pressure-magnetic thrust bearing, under the condition that the electromagnetic bearing and the gas hydrostatic bearing are arranged at the same time, the bearing capacity of the bearing is further increased, the electromagnetic bearing and the gas hydrostatic bearing can be mutually standby, and under the condition that one of the two bearings is failed, fails or cannot meet the starting condition, the other bearing can be used as a standby bearing to play the same role. For example, in the case of detecting the failure of the electromagnetic bearing, the control system controls the aerostatic bearing to be opened to replace the electromagnetic bearing to perform corresponding actions, so that the safety and the reliability of the bearing are improved.

In some embodiments, as shown in fig. 24-32, the air-magnetic hybrid thrust bearing comprises:

The third thrust disc 701, the third thrust disc 701 is fixedly connected to the rotating shaft 100;

the fifth stator 702 and the sixth stator 703 penetrate through the rotating shaft 100, the fifth stator 702 and the sixth stator 703 are respectively arranged on two opposite sides of the third thrust disc 701, a sixth gap is formed between the fifth stator 702 and the third thrust disc 701, and a seventh gap is formed between the sixth stator 703 and the third thrust disc 701;

The fifth stator 702 includes a third magnetic bearing 704, a plurality of fifth magnetic components are circumferentially disposed on the third magnetic bearing 704, and the third magnetic bearing 704 can control the third thrust disc 701 to move in the axial direction of the rotating shaft 100; a gas bearing is formed between the sixth stator 703 and the third thrust disk 701.

In the embodiment of the present invention, by providing a sixth gap between the fifth stator 702 and the third thrust disk 701, and providing the third magnetic bearing 704 on the fifth stator 702, the side forms a magnetic bearing; by providing a seventh gap between sixth stator 703 and third thrust disk 701, the side forms a gas bearing, so that the thrust bearing forms a gas-magnetic hybrid thrust bearing.

When the thrust bearing works, the third magnetic bearing 704 in the thrust bearing and the gas bearing can work cooperatively, and when the thrust bearing is in a stable working state, the support is realized by the gas bearing; and when the thrust bearing is in an unstable working state, the third magnetic bearing 704 is relied on to control and respond to the thrust bearing in time.

Therefore, through the arrangement, the dynamic performance and stability of the thrust bearing in a high-speed running state can be improved, the disturbance resistance is high, and the bearing capacity of the thrust bearing is improved. When the rotating shaft 100 is started or stopped, the dynamic pressure air film is not established or disappears, the third thrust disc 701 and the stator rotate at a preset gap by using the third magnetic bearing 704, the low-speed performance of the air bearing is improved, the negative effects of vibration and impact of the third thrust disc 701 are reduced, the service life of the thrust bearing is prolonged, and the reliability of the whole system is improved. Due to the characteristics of the thrust bearing, the thrust bearing provided by the embodiment of the invention can meet the requirements of a gas turbine or a gas turbine power generation combined unit with high rotation speed and the like.

In the embodiment of the present invention, the third magnetic bearing 704 and the gas bearing are respectively disposed on two sides of the third thrust disk 701, and compared to the case where both sides of the third thrust disk 701 are the gas-magnetic hybrid bearings, the embodiment of the present invention not only can achieve the same technical effect, but also has other advantages. On one hand, the strict requirement of the gas bearing on the gap is not taken into consideration when the third magnetic bearing 704 is designed and processed, and the structural requirement of the third magnetic bearing 704 is not taken into consideration when the gas bearing is designed and processed, so that the third magnetic bearing 704 and the gas bearing are separately arranged, the structure is simpler, and the processing and the manufacturing are easier. On the other hand, the third magnetic bearing 704 is provided only on one side, which is low in energy consumption. In addition, the gas bearing and the third magnetic bearing 704 are independently controlled without influencing each other, and the reliability of bearing control is improved.

In the embodiment of the present invention, the outer diameters of the third thrust disk 701, the fifth stator 702, and the sixth stator 703 may be equal, and when the thrust bearing of the embodiment of the present invention is applied to a gas turbine or a gas turbine power generation combined unit, the fifth stator 702 and the sixth stator 703 may be connected to a casing of the gas turbine through a connecting member.

Optionally, a second magnetic component is disposed on the third thrust disk 701, and the third thrust disk 701 can move in the axial direction of the rotating shaft 100 under the action of a magnetic force between the plurality of fifth magnetic components and the second magnetic component. The second magnetic member includes a magnetic material provided on an end surface of the third thrust disk 701 facing the fifth stator 702; the magnetic material is distributed on the third thrust disc 701 in a strip shape to form a plurality of strip-shaped magnetic parts, and the strip-shaped magnetic parts are radial or annular; alternatively, the magnetic material is distributed in a dotted manner on the third thrust disk 701.

in the embodiment of the present invention, the magnetic materials are distributed in a stripe shape or in a dot shape on the third thrust disk 701, so that the magnetic force generated between the fifth magnetic component and the second magnetic component can be controlled in a reasonable range.

optionally, the third magnetic bearing 704 includes:

the magnetic bearing seat 7043 is arranged opposite to the third thrust disc 701, a plurality of accommodating grooves are formed in the magnetic bearing seat 7043 along the circumferential direction, a plurality of fifth magnetic components are arranged in the accommodating grooves, and magnetic poles of the fifth magnetic components face the side where the third thrust disc 701 is located;

the end cover 707 is disposed on a side of the magnetic bearing housing 7043 away from the third thrust disk 701, the pressing ring 709 is disposed on a side of the magnetic bearing housing 7043 close to the third thrust disk 701, and the end cover 707 is engaged with the pressing ring 709 to fix the fifth magnetic members to the magnetic bearing housing 7043.

In the preferred embodiment of the present invention, the magnetic bearing base 7043 is formed by laminating a plurality of silicon steel sheets or silicon steel sheets, because the silicon steel sheets or silicon steel sheets have physical properties such as high magnetic permeability and low eddy current loss. The number of the accommodation grooves may be, but is not limited to, six or eight, and is uniformly arranged along the circumferential direction of the magnetic bearing housing 7043. In this way, the magnetic force between the third magnetic bearing 704 and the third thrust disk 701 can be made more uniform and stable. The plurality of fifth magnetic members may be provided on the magnetic bearing base 7043 in other manners, which is not limited to this. The material of the end cap 707 may be a non-magnetic material, preferably a duralumin material. The material of the pressure ring 709 may be a non-magnetic material, preferably a duralumin material.

Optionally, the plurality of fifth magnetic components comprise a plurality of permanent magnets circumferentially arranged on the third magnetic bearing 704; alternatively, the plurality of fifth magnetic members include a plurality of electromagnets that are disposed circumferentially on the third magnetic bearing 704, each of the plurality of electromagnets including a magnetic core 7041 disposed on the third magnetic bearing 704 and a coil 7042 wound around the magnetic core 7041.

In the embodiment of the invention, when the thrust bearing only needs the second magnetic part to provide magnetic force and does not need magnetic control, the second magnetic part is preferably a permanent magnet; when the thrust bearing requires the second magnetic component to provide both magnetic force and magnetic control, the second magnetic component is preferably an electromagnet.

when the second magnetic member is an electromagnet, current is applied to the coil 7042, so that the magnetic core 7041 generates magnetic force. The magnitude of the current supplied to the coil 7042 is different, and the magnitude of the magnetic force generated by the magnetic core 7041 is also different; the direction of current flow to the coil 7042 is different, as is the magnetic polarity of the magnetic core 7041.

in the preferred embodiment of the present invention, the magnetic core 7041 is formed by laminating a plurality of silicon steel sheets or silicon steel sheets, because the silicon steel sheets or silicon steel sheets have physical properties such as high magnetic permeability and low eddy current loss.

Optionally, the fifth stator 702 is provided with a sensor 7081, the sensor 7081 includes a sensor cover and a sensor probe, a first end of the sensor probe is connected to the sensor cover, the sensor cover is fixed to the third magnetic bearing 704, and a second end of the sensor probe passes through the third magnetic bearing 704 and extends to the sixth gap; and/or the presence of a gas in the gas,

The sixth stator 703 is provided with a sensor 7081, the sensor 7081 includes a sensor cover and a sensor probe, a first end of the sensor probe is connected to the sensor cover, the sensor cover is fixed to the sixth stator 703, and a second end of the sensor probe passes through the sixth stator 703 and extends to the seventh gap.

in the embodiment of the invention, the sensor is arranged, so that the parameters, such as the air film pressure and the like, at the sixth gap or the seventh gap can be detected in real time. In this way, the third magnetic bearing 704 can actively control the thrust bearing based on the detection result of the sensor, and can achieve high accuracy of control.

Optionally, in a case that the gas-magnetic hybrid bearing of the thrust bearing is a groove-type gas-magnetic hybrid bearing, a through hole 7082 for the sensor probe to pass through is formed in the third magnetic bearing 704; the second end of the sensor probe passes through the through hole 7082 on the third magnetic bearing 704 and the second end of the sensor probe is flush with the side of the third magnetic bearing 704 near the third thrust disk 701.

In this way, the sensor 7081 can be more stably mounted on the third magnetic bearing 704 by the structural form and the mounting manner of the sensor 7081. In addition, the second end of the sensor probe is flush with the side, close to the third thrust disc 701, of the third magnetic bearing 704, so that on one hand, the sensor probe can be prevented from being touched by the third thrust disc 701, and the sensor probe can be protected; on the other hand, the air film in the sixth gap is not affected, and the air film in the sixth gap is prevented from being disturbed.

Optionally, the sensor 7081 is disposed between two adjacent second magnetic members.

Optionally, in a case that the gas-magnetic hybrid bearing of the thrust bearing is a foil-type gas-magnetic hybrid bearing, through holes 7082 for the sensor probes to pass through are provided on the third magnetic bearing 704 and the second foil bearing 705; the second end of the sensor probe passes through a through hole 7082 in the third magnetic bearing 704 and the second foil bearing 705, and the second end of the sensor probe is flush with the side of the second foil bearing 705 near the third thrust disk 701.

In this way, the sensor 7081 can be more stably mounted on the third magnetic bearing 704 by the structural form and the mounting manner of the sensor 7081. In addition, the second end of the sensor probe is flush with the side, close to the third thrust disc 701, of the second foil bearing 705, so that on one hand, the sensor probe can be prevented from being touched by the third thrust disc 701, and therefore the sensor probe is protected; on the other hand, the air film in the sixth gap is not affected, and the air film in the sixth gap is prevented from being disturbed.

Optionally, a through hole for the sensor probe to pass through is formed in the sixth stator 703; the second end of the sensor probe passes through the through hole of the sixth stator 703, and the end of the second end of the sensor probe is flush with the side of the sixth stator 703 close to the third thrust disk 701.

In this way, the sensor 7081 can be more stably provided on the sixth stator 703 due to the structural form and the mounting manner of the sensor 7081. In addition, the second end of the sensor probe is flush with the side of the sixth stator 703 close to the third thrust disc 701, so that the sensor probe can be prevented from being touched by the third thrust disc 701, and the sensor probe can be protected; on the other hand, the air film in the seventh gap is not affected, and the air film in the seventh gap is prevented from being disturbed.

Optionally, the sensor 7081 of the fifth stator 702 is any one or more of the following:

A displacement sensor for detecting the position of the third thrust disk 701;

A pressure sensor for detecting a pressure of the air film at the sixth gap;

A speed sensor for detecting the rotational speed of the third thrust disk 701;

And an acceleration sensor for detecting the rotational acceleration of the third thrust disk 701.

Optionally, the sensor 7081 of the sixth stator 703 is any one or more of the following in combination:

A displacement sensor for detecting the position of the third thrust disk 701;

a pressure sensor for detecting a pressure of the air film at the seventh gap;

A speed sensor for detecting the rotational speed of the third thrust disk 701;

In the embodiment of the invention, one side of the magnetic bearing of the thrust bearing can be a pure magnetic bearing in the structural form or a gas-magnetic mixed bearing. The gas-magnetic hybrid bearing may be a groove-type gas-magnetic hybrid bearing including the magnetic bearing, or may be a foil-type gas-magnetic hybrid bearing including the magnetic bearing, and various embodiments of the gas-magnetic hybrid bearing are described below.

On the other hand, taking as an example a hybrid gas-magnetic bearing as a thrust bearing a groove-type hybrid gas-magnetic bearing including the above-described magnetic bearing, as shown in fig. 1, a sixth dynamic pressure generating groove is provided on an end surface of the third thrust disk 701 facing the fifth stator 702, or on an end surface of the fifth stator 702 facing the third thrust disk 701.

In this embodiment, when the third thrust disk 701 rotates, the flowing gas existing in the sixth gap is pressed into the sixth dynamic pressure generating groove, thereby generating a pressure to realize non-contact holding of the third thrust disk 701 in the axial direction. The pressure generated by the sixth dynamic pressure generating groove varies with the angle, width, length, depth, number and flatness of the dynamic pressure generating grooves. The magnitude of the pressure generated by the sixth dynamic pressure generating groove is also related to the rotational speed of the third thrust disk 701 and the sixth clearance. The parameters of the sixth dynamic pressure generating groove can be designed according to actual working conditions. The sixth dynamic pressure generating grooves may be formed on the fifth stator 702 by forging, rolling, etching, or punching, or the like, or the sixth dynamic pressure generating grooves may be formed on the third thrust plate 701 by forging, rolling, etching, or punching, or the like.

in an embodiment of the present invention, a sixth dynamic pressure generating groove may be formed in the pressure ring 709, and the pressure ring 709 may be made of a stainless steel material to facilitate machining of the sixth dynamic pressure generating groove.

Alternatively, as shown in fig. 6 to 9, the sixth dynamic pressure generating grooves may be arranged in a radial or concentric manner, which is advantageous to more uniformly distribute the gas film in the sixth gap.

Optionally, the sixth dynamic pressure generating groove includes a first spiral groove and a second spiral groove, the first spiral groove surrounds the second spiral groove, the spiral directions of the first spiral groove and the second spiral groove are opposite, and one end of the first spiral groove close to the second spiral groove is connected or disconnected with one end of the second spiral groove close to the first spiral groove.

The distance from one end of the first spiral groove close to the second spiral groove to the axis of the rotating shaft 100 is equal to the distance from one end of the first spiral groove close to the second spiral groove to the outer peripheral edge of the fifth stator 702 or the third thrust disc 701. Alternatively, the distance from the end of the second spiral groove close to the first spiral groove to the shaft center of the rotating shaft 100 is equal to the distance from the end of the second spiral groove close to the first spiral groove to the outer peripheral edge of the fifth stator 702 or the third thrust disc 701.

In the embodiment of the present invention, by adopting the above-described arrangement of the sixth dynamic pressure generating groove, the third thrust disk 701 can be held in a non-contact manner in a desired manner when the rotating shaft 100 rotates in the forward direction or in the reverse direction, so that the rotating shaft 100 has advantages of high load capacity and good stability.

optionally, the fifth stator 702 is provided with a static pressure intake orifice 710, one end of the static pressure intake orifice 710 is communicated with the sixth gap, and the other end of the static pressure intake orifice 710 is connected with an external pressure air source for conveying the external pressure air source into the sixth gap.

in the embodiment of the present invention, in addition to the groove type air-magnetic hybrid bearing on the fifth stator 702 side of the thrust bearing, the static pressure air intake orifice 710 is provided to form an air static pressure bearing on the side, thereby forming a groove type air hybrid-magnetic hybrid bearing on the side. The flow diameter of the static pressure intake orifice 710 can be adjusted according to actual working conditions such as air quantity requirements.

With the above arrangement, since the third magnetic bearing 704 and the aerostatic bearing are provided at the same time, the bearing capacity of the thrust bearing is further increased. Moreover, the third magnetic bearing 704 and the aerostatic bearing may be mutually redundant, and in case one of them fails, fails or fails to satisfy the opening condition, the other may play the same role as a redundant bearing; for example, in the event that a failure of the third magnetic bearing 704 is detected, the control system controls the aerostatic bearing to open to perform a corresponding action in place of the third magnetic bearing 704, thereby improving the safety and reliability of the thrust bearing.

alternatively, the fifth stator 702 is provided with a plurality of static pressure intake orifices 710, and the plurality of static pressure intake orifices 710 are provided at intervals in the circumferential direction of the fifth stator 702. This is advantageous in that the gas film pressure in the sixth gap is made more uniform. Preferably, a plurality of static pressure intake orifices 710 are provided at regular intervals in the circumferential direction of the fifth stator 702.

Alternatively, the distance from the static pressure intake orifice 710 to the shaft center of the rotating shaft 100 is greater than or equal to the distance from the static pressure intake orifice 710 to the outer peripheral edge of the fifth stator 702.

with the above arrangement, the aerostatic bearing on the fifth stator 702 side of the thrust bearing can be stabilized, and if the static pressure intake orifice 710 is too close to the axis of the rotating shaft 100, the gas film cannot be effectively spread over the entire end surface of the third thrust disk 701 facing the fifth stator 702 in time, and the rotation of the third thrust disk 701 is not stabilized enough. Preferably, the distance from the static pressure intake orifice 710 to the axial center of the rotating shaft 100 is equal to the distance from the static pressure intake orifice 710 to the outer peripheral edge of the fifth stator 702.

On the other hand, taking the gas-magnetic hybrid bearing as a thrust bearing as an example of a foil-type gas-magnetic hybrid bearing including the above-described magnetic bearings, as shown in fig. 2, the fifth stator 702 further includes a second foil bearing 705, the second foil bearing 705 is disposed between the third magnetic bearing 704 and the third thrust disk 701 with a sixth gap therebetween, the second foil bearing 705 is provided with a third magnetic member, and the second foil bearing 705 is movable in the axial direction of the rotating shaft 100 by a magnetic force between the plurality of fifth magnetic members and the third magnetic member so that the third thrust disk 701 is moved in the axial direction of the rotating shaft 100.

Optionally, the second foil bearing 705 comprises:

a second foil bearing mount fixedly connected to the third magnetic bearing 704;

The first foil 7052 and the second foil 7051 are arranged on the second foil bearing seat, the first foil 7052 is arranged on the second foil bearing seat, and the second foil 7051 is overlapped on one side, close to the third thrust disc 701, of the first foil 7052;

wherein the second foil 7051 is a flat foil, and the third magnetic component is disposed on the second foil 7051, so that the second foil 7051 can move in the axial direction of the rotating shaft 100 under the magnetic force of the fifth and third magnetic components; the first foil 7052 is an elastically deformable foil that can be elastically deformed when the second foil 7051 is moved.

Wherein the material of the second foil bearing seat is a non-magnetic material, preferably a duralumin material. The compression ring 709 in fig. 2 may act as a second foil bearing mount. The first foil 7052 is an elastically deformable foil, and the first foil 7052 is preferably a stainless steel band which is not magnetically conductive, considering that the material of the magnetically conductive material is hard and brittle and is not suitable for the elastically deformable foil.

Thus, by providing the second foil 7051 as a flat foil, it is convenient to control the distance between the second foil 7051 and the third thrust disk 701, or in other words, to control the size of the sixth gap; the first foil 7052 is made of an elastically deformable foil, and on the one hand, functions to connect the second foil 7051 to the second foil bearing seat, and on the other hand, can achieve the purpose that the second foil 7051 is movable relative to the second foil bearing seat in the axial direction of the rotating shaft 100.

Optionally, the first foil 7052 is a wavy elastically deformable foil, and the first foil 7052 is an unclosed ring, and has an opening, one end of the opening is a fixed end, the fixed end is fixed to the second foil bearing block, and the other end of the opening is a movable end;

Wherein, when the second foil 7051 moves in the axial direction of the rotating shaft 100, the wave pattern on the first foil 7052 expands or contracts, and the movable end moves in the circumferential direction of the ring shape.

In this way, by providing the first foil 7052 as an elastically deformable foil having a wavy shape, it is facilitated to push the second foil 7051 to move in the axial direction of the rotary shaft 100 by utilizing the expansion or contraction characteristic of the wavy veins.

it should be noted that the shape of the first foil 7052 in this embodiment is not limited to the wavy shape, and other shapes capable of generating elastic deformation may be applied to the first foil 7052 in this embodiment.

optionally, the third magnetic component comprises a magnetic material disposed on a surface of the second foil 7051 on a side thereof proximate to the third magnetic bearing 704;

Wherein, the magnetic material is distributed on the second foil 7051 in a strip shape to form a plurality of strip-shaped magnetic portions, and the plurality of strip-shaped magnetic portions are radial or annular;

Alternatively, the magnetic material is distributed in dots on the second foil 7051.

The material of the second foil 7051 is preferably a non-magnetic material, and after the magnetic material is sprayed on the surface of the second foil 7051, the magnetic material may be covered with a ceramic coating. The second foil 7051 may be made by sintering ceramic nanopowders using 40% zirconia, 30% alpha alumina and 30% magnesium aluminate spinel.

If the surface of the second foil 7051 is completely covered with the magnetic material, the magnetic force generated between the magnetic material and the fifth magnetic member is greatly increased, which may easily cause the second foil 7051 to deform. In view of this, in this embodiment, the magnetic material is sprayed on the surface of the second foil 7051, so that the magnetic material is distributed in a stripe shape or a dot shape on the second foil 7051, and the magnetic force generated between the magnetic material and the fifth magnetic member can be controlled within a reasonable range, thereby preventing the second foil 7051 from being deformed due to an excessive magnetic force.

In the embodiment of the present invention, the sixth stator 703 side of the thrust bearing is a gas bearing, which may be a gas dynamic pressure bearing, a gas static pressure bearing, or a gas dynamic and static pressure bearing.

On the other hand, taking the gas bearing as the thrust bearing as an example of a gas dynamic pressure bearing, as shown in fig. 6 to 9, the end surface of the third thrust disk 701 facing the sixth stator 703 or the end surface of the sixth stator 703 facing the third thrust disk 701 is provided with seventh dynamic pressure generating grooves.

In this embodiment, when the third thrust disk 701 rotates, the flowing gas existing in the seventh gap is pressed into the seventh dynamic pressure generating groove, thereby generating pressure to achieve non-contact holding of the third thrust disk 701 in the axial direction. The magnitude of the pressure generated by the seventh dynamic pressure generating groove varies with the angle, width, length, depth, number and flatness of the dynamic pressure generating grooves. The magnitude of the pressure generated by the seventh dynamic pressure generating groove is also related to the rotational speed of the third thrust disk 701 and the seventh clearance. The parameters of the seventh dynamic pressure generating groove can be designed according to actual working conditions. The seventh dynamic pressure generating groove may be formed on the sixth stator 703 by forging, rolling, etching, or punching.

in the embodiment of the present invention, other structures and arrangement manners of the sixth dynamic pressure generating groove are also applicable to the seventh dynamic pressure generating groove, and have the same technical effects, and are not described herein again to avoid repetition.

on the other hand, taking the gas bearing of the thrust bearing as an example of a gas hydrostatic bearing, the sixth stator 703 is provided with a hydrostatic inlet orifice 710, one end of the hydrostatic inlet orifice 710 is communicated with the seventh gap, and the other end is connected to an external pressure gas source for delivering the external pressure gas source into the seventh gap.

the flow diameter of the static pressure intake orifice 710 can be adjusted according to actual working conditions such as air quantity requirements.

alternatively, the sixth stator 703 is provided with a plurality of static pressure intake orifices 710, and the plurality of static pressure intake orifices 710 are provided at intervals in the circumferential direction of the sixth stator 703. This is advantageous in that the gas film pressure in the seventh gap is made more uniform. Preferably, the plurality of static pressure intake orifices 710 are provided at regular intervals in the circumferential direction of the sixth stator 703.

alternatively, the distance from the static pressure intake orifice 710 to the shaft center of the rotating shaft 100 is greater than or equal to the distance from the static pressure intake orifice 710 to the outer peripheral edge of the sixth stator 703.

With the above arrangement, the aerostatic bearing on the sixth stator 703 side of the thrust bearing can be further stabilized, and if the static pressure intake orifice 710 is too close to the axis of the rotating shaft 100, the gas film cannot be timely and effectively spread over the entire end surface of the third thrust disk 701 facing the sixth stator 703, and the rotation of the third thrust disk 701 is not stabilized enough. Preferably, the distance from the static pressure intake orifice 710 to the axial center of the rotating shaft 100 is equal to the distance from the static pressure intake orifice 710 to the outer peripheral edge of the sixth stator 703.

On the other hand, taking the gas bearing of the thrust bearing as an example of a gas hybrid bearing, an end surface of the third thrust disk 701 facing the sixth stator 703 or an end surface of the sixth stator 703 facing the third thrust disk 701 is provided with a seventh dynamic pressure generating groove, the sixth stator 703 is provided with a static pressure intake orifice 710, one end of the static pressure intake orifice 710 communicates with the seventh gap, and the other end is connected with an external pressure gas source for delivering the external pressure gas source into the seventh gap.

optionally, an inner circumferential surface of the fifth stator 702 facing the rotating shaft 100, or an outer circumferential surface of the rotating shaft 100 facing the fifth stator 702 is provided with an eighth dynamic pressure generating groove; and/or the presence of a gas in the gas,

The inner circumferential surface of the sixth stator 703 facing the rotation shaft 100 or the outer circumferential surface of the rotation shaft 100 facing the sixth stator 703 is provided with a ninth dynamic pressure generating groove.

in this way, when the rotating shaft 100 rotates, dynamic pressure gas will be formed in the gap between the fifth stator 702 and the rotating shaft 100, and/or dynamic pressure gas will be formed in the gap between the sixth stator 703 and the rotating shaft 100, so as to realize the bearing capacity of the thrust bearing in the radial direction, thereby enabling the thrust bearing in the embodiment of the present invention to simultaneously have the function of a radial bearing, and further improving the dynamic performance and stability of the thrust bearing, especially in a high-speed operating state.

The following describes in detail a control method of the thrust bearing (in which the fifth magnetic component of the third magnetic bearing is an electromagnet) in the rotor system according to the embodiment of the present invention.

the embodiment of the invention provides a control method of a thrust bearing, which comprises the following steps:

s301: and starting the third magnetic bearing, and controlling the thrust disc to move in the axial direction of the rotating shaft under the action of the magnetic force of the fifth magnetic components so that the difference value between the sixth gap and the seventh gap is smaller than or equal to a preset value.

the specific process of starting the third magnetic bearing is as follows: and a current signal with a preset value is input into the coil, and the thrust disc reaches a preset position between the fifth stator and the sixth stator under the action of the third magnetic bearing.

S302: and after the rotating speed of the rotating shaft is accelerated to the working rotating speed, the third magnetic bearing is closed.

S303: and when the rotor system is stopped, the third magnetic bearing is started.

s304: and after the rotating speed of the rotating shaft is reduced to zero, the third magnetic bearing is closed.

in the process, after the third magnetic bearing is started, the thrust disc reaches a preset position between the fifth stator and the sixth stator under the action of the third magnetic bearing, and bearing gaps are formed among the thrust disc and the end faces of the fifth stator and the sixth stator.

With the rotation of the rotating shaft, the thrust disk starts to rotate relative to the fifth stator and the sixth stator under the condition of being lubricated by the air flow in the bearing gap, so that the abrasion is prevented.

With the increasing of the rotating speed of the rotating shaft, the rotating speed of the thrust disc also increases synchronously, and when the rotating speed of the rotating shaft reaches the working rotating speed, the thrust disc can be stabilized by the air film pressure generated by the aerodynamic pressure bearing of the thrust bearing (the thrust disc, the aerodynamic pressure bearing which forms the thrust bearing is formed by the bearing gap arranged between the fifth stator and the sixth stator), and then the third magnetic bearing can be closed.

When the rotor system stops, the thrust disc decelerates along with the deceleration of the rotating shaft, and in order to keep the rotating shaft stable in the whole rotor system stopping process, the third magnetic bearing is started when the rotor system stops, and the third magnetic bearing is closed until the thrust disc completely stops.

The embodiment of the invention also provides another control method of the thrust bearing, which comprises the following steps:

S401: starting the third magnetic bearing, and controlling the thrust disc to move in the axial direction of the rotating shaft under the action of the magnetic force of the fifth magnetic components, so that the difference value between the sixth gap and the seventh gap is smaller than or equal to a preset value;

S402: and after the rotating speed of the rotating shaft is accelerated to a first preset value, the third magnetic bearing is closed.

S403: and when the rotating speed of the rotating shaft is reduced to a second preset value, the third magnetic bearing is started.

s404: and after the rotating speed of the rotating shaft is reduced to zero, the third magnetic bearing is closed.

As the rotating speed of the rotating shaft is increased, the rotating speed of the thrust disc is also increased synchronously, and when the rotating speed of the rotating shaft reaches a first preset value, for example, 5% to 30% of the rated rotating speed, the thrust disc can be stabilized by the gas film pressure generated by the gas dynamic pressure bearing of the thrust bearing (the gas dynamic pressure bearing forming the thrust bearing is provided with the bearing gap between the thrust disc and the fifth stator and the sixth stator), and then the third magnetic bearing can be closed.

During the shutdown process of the rotor system, the thrust disc decelerates along with the deceleration of the rotating shaft, and when the rotating speed of the rotating shaft is lower than a second preset value, for example, 5% to 30% of the rated rotating speed, the air film pressure generated by the aerodynamic bearing of the thrust bearing also decreases along with the deceleration of the thrust disc, so that the third magnetic bearing needs to be started to keep the thrust disc stable, and the third magnetic bearing can be closed until the thrust disc completely stops.

optionally, the method further includes:

when a load is loaded on the thrust disc, the thrust disc moves in the axial direction of the rotating shaft under the action of the load, and the difference value between the sixth gap and the seventh gap is larger than the preset value, the third magnetic bearing is started;

Turning off the third magnetic bearing when the difference between the sixth gap and the seventh gap is less than or equal to the predetermined value.

When a load is loaded on the thrust disc, so that the bearing gap between the thrust disc and the fifth stator or the sixth stator becomes smaller and approaches the stator on the side, a sensor (preferably a pressure sensor) obtains a signal of air pressure increase, at this time, the third magnetic bearing needs to be involved in work, and when the thrust disc reaches a new equilibrium position, the third magnetic bearing can stop working.

Optionally, when a load is applied to the thrust disk, the thrust disk moves in the axial direction of the rotating shaft under the action of the load, and the difference between the sixth gap and the seventh gap is greater than the predetermined value, the third magnetic bearing is turned on, and the method includes:

when a load is loaded on the thrust disc, the thrust disc moves in the axial direction of the rotating shaft under the action of the load, and the difference value between the sixth gap and the seventh gap is larger than the preset value, controlling the third magnetic bearing to be started at the maximum power; or,

And when a load is loaded on the thrust disc, the thrust disc moves in the axial direction of the rotating shaft under the action of the load, and the difference value between the sixth gap and the seventh gap is greater than the preset value, controlling the third magnetic bearing to be opened in a stroboscopic mode according to a preset frequency.

When external impact disturbance occurs, the thrust disc can be quickly close to a stator on one side, so that the bearing gap on the side is possibly over-small instantaneously, the local gas flow velocity at the bearing gap on the side is close to or even reaches the sonic velocity, and the shock wave is caused to generate the self-excitation phenomenon of the air hammer. The generation of the shock wave causes turbulence and chaos in the local gas flow, with the pressure dropping dramatically in steps as the fluid velocity changes from sonic to subsonic. In this case, it is necessary to control the third magnetic bearing to be turned on at the maximum power, or to control the third magnetic bearing to be turned on at a predetermined frequency in turn, so as to provide a damping effect on the disturbance, thereby effectively suppressing the external disturbance. When the thrust disc returns to the equilibrium state, the third magnetic bearing stops working.

in the embodiment of the present invention, when the third magnetic bearing and the aerostatic bearing are provided at the same time, the third magnetic bearing and the aerostatic bearing may be in mutual backup, and when one of them fails, fails or fails to satisfy the start condition, the other one may serve as a backup bearing to perform the same function. For example, in case of detecting the failure of the third magnetic bearing, the external pressure air source is controlled to be opened to perform corresponding actions instead of the third magnetic bearing, thereby improving the safety and reliability of the bearing.

In the embodiment of the present invention, when the third magnetic bearing and the aerostatic bearing are provided at the same time, the following embodiments may be included:

Turning on the third magnetic bearing; and/or starting an external pressure air source, and conveying air to the bearing gap through the static pressure air inlet throttling hole;

controlling the thrust disc to move in the axial direction of the rotating shaft under the magnetic force of the third magnetic bearing and/or the pushing action of the gas so that the difference between the sixth gap and the seventh gap is less than or equal to the predetermined value.

In the embodiment in which the third magnetic bearing and the aerostatic bearing are simultaneously turned on, the bearing capacity of the thrust bearing according to the embodiment of the present invention can be further improved.

in the process, the thrust disc is fixed in a certain minimum range in the axial direction of the rotating shaft by utilizing the advantages of the magnetic bearing that the real-time control is convenient, and actively balancing the unbalanced mass of the thrust disc or the factors of excessive deviation of the thrust disc caused by the vortex motion of the thrust disc and the like. In addition, in the acceleration process of the thrust disc, the position (namely the linear velocity supersonic speed position) generating the shock wave can be accurately positioned, and the shock wave action is balanced by controlling the current magnitude, the direction and the like of the magnetic bearing to enable the magnetic bearing to generate opposite force. After the shock wave is stable, the control strategy of the magnetic bearing is adjusted again, and the thrust disc is fixed in a certain minimum range in the most energy-saving mode.

in summary, the preferred embodiment of the present invention has the following beneficial effects:

firstly, the magnetic bearing and the gas bearing work cooperatively, so that the dynamic performance and stability of the bearing in a high-speed running state are improved, the disturbance resistance is high, and the bearing capacity of the bearing is improved. Meanwhile, the magnetic bearing and the gas bearing adopt a parallel connection structure, so that the structure is simplified, the integration level is high, the processing, the manufacturing and the operation are easy, and the comprehensive performance of the bearing is improved. When the rotor system is started or stopped, the thrust disc and the stator of the bearing can rotate in the bearing gap by using the magnetic bearing, so that the low-speed performance of the bearing is improved, the service life of the bearing is prolonged, and the safety and the reliability of the bearing and the whole system can be improved.

Compared with the traditional gas dynamic and static pressure mixed thrust bearing adopting the combination of the gas static pressure bearing and the gas dynamic pressure bearing, the thrust bearing provided by the embodiment of the invention has the advantage of high response speed.

Thirdly, a pressure sensor with lower cost is adopted to collect the pressure change of the air film, the deformation of the foil is controlled by a simple control method, and higher rotor damping can be provided, so that the stability of the rotor is improved. In addition, the control method is simple, and the requirement on the machining precision of the bearing is not high.

In some embodiments, the aero-magnetic hybrid radial bearing is a foil aero-magnetic hybrid radial bearing, the foil aero-magnetic hybrid radial bearing comprising:

a fourth magnetic bearing sleeved on the rotating shaft, wherein a plurality of sixth magnetic components are arranged on the fourth magnetic bearing along the circumferential direction;

The second foil bearing is sleeved on the rotating shaft and positioned between the fourth magnetic bearing and the rotating shaft, and the third foil bearing is provided with a seventh magnetic component capable of generating magnetic force with the sixth magnetic components;

Wherein an eighth gap is provided between the third foil bearing and the rotating shaft, and the second foil bearing is movable in a radial direction of the rotating shaft by a magnetic force of the plurality of sixth magnetic members and the seventh magnetic member.

for a specific scheme of the above-mentioned foil type gas-magnetic hybrid radial bearing, reference may be made to the relevant descriptions in patent application documents with application numbers CN201810030888.1, CN201810030299.3, or CN201810031822.4, and the same beneficial effects can be achieved.

In some embodiments, the aero-magnetic hybrid radial bearing may be a groove aero-magnetic hybrid radial bearing.

as shown in fig. 33 to 40, the groove-type air-magnetic hybrid radial bearing 6200 includes:

a fourth magnetic bearing 6201 sleeved on the rotating shaft 100, wherein a plurality of eighth magnetic components are arranged on the fourth magnetic bearing 6201 along the circumferential direction;

A tenth dynamic pressure generating groove 6202 is provided on a side wall of the fourth magnetic bearing 6201 facing the rotating shaft 100, or on a circumferential surface of the rotating shaft 100 facing the fourth magnetic bearing 6201;

Wherein, a ninth gap 6203 is provided between the fourth magnetic bearing 6201 and the rotating shaft 100, and the rotating shaft 100 can move in the radial direction of the rotating shaft 100 under the magnetic force of the plurality of eighth magnetic members.

in the embodiment of the present invention, the radial bearing 6200 is formed into a gas-magnetic hybrid radial bearing by providing the ninth gap 6203 and the fourth magnetic bearing 6201 in the radial bearing 6200.

When the radial bearing 6200 works, the gas bearing in the radial bearing 6200 and the fourth magnetic bearing 6201 can work cooperatively, and when the radial bearing 6200 is in a stable working state, the gas bearing is used for realizing support; and when the radial bearing 6200 is in an unstable working state, the radial bearing 6200 is controlled and responded by the fourth magnetic bearing 6201 in time.

Therefore, the embodiment of the invention can improve the dynamic performance and stability of the radial bearing, particularly in a high-speed running state, has strong disturbance resistance, and further improves the bearing capacity of the radial bearing. The radial bearing of the embodiment of the invention can meet the requirements of a rotor system with high rotating speed, such as a gas turbine or a gas turbine power generation combined unit.

In the embodiment of the present invention, since the silicon steel sheet or the silicon steel sheet has physical properties such as high magnetic permeability and low eddy current loss, the rotating shaft 100 may be formed by laminating a plurality of silicon steel sheets or silicon steel sheets.

In the embodiment of the present invention, when the rotation shaft 100 rotates, the flowing gas existing in the ninth gap 6203 is pressed into the tenth dynamic pressure generating groove 6202, thereby generating a pressure to float the rotation shaft 100, so that the rotation shaft 100 is non-contact held in the radial direction. The pressure generated by the tenth pressure-generating groove 6202 varies with the angle, groove width, groove length, groove depth, number of grooves, and flatness of the tenth pressure-generating groove 6202. In addition, the magnitude of the pressure generated by the tenth dynamic pressure generating groove 6202 is also related to the rotation speed of the rotation shaft 100 and the ninth gap 6203. The parameter of the tenth dynamic pressure generating groove 6202 may be designed according to an actual working condition. The tenth dynamic pressure generating groove 6202 may be formed on the fourth magnetic bearing 6201 or the rotating shaft by forging, rolling, etching, or punching.

Optionally, the plurality of eighth magnetic members include a plurality of fourth permanent magnets, and the plurality of fourth permanent magnets are circumferentially disposed on the fourth magnetic bearing 6201;

Alternatively, the plurality of eighth magnetic members include a plurality of fourth electromagnets disposed circumferentially on the fourth magnetic bearing 6201, and each of the plurality of fourth electromagnets includes a fourth magnetic core 62011 disposed on the fourth magnetic bearing 6201 and a fourth coil 62012 wound on the fourth magnetic core 62011.

In the embodiment of the invention, when the groove type air-magnetic hybrid radial bearing 6200 only needs the magnetic part to provide magnetic force and does not need magnetic control, the eighth magnetic part is preferably a fourth permanent magnet; when the foil gas-magnetic hybrid thrust bearing requires both magnetic force and magnetic control, the eighth magnetic component is preferably a fourth electromagnet.

When the eighth magnetic element is a fourth electromagnet, a current is applied to the fourth coil 62012, so that the fourth magnetic core 62011 generates a magnetic force. The magnitude of the current flowing into the fourth coil 62012 is different, and the magnitude of the magnetic force generated by the fourth magnetic core 62011 is also different; the direction of current flow to the fourth coil 62012 is different, and the magnetic pole of the fourth magnetic core 62011 is also different.

In a preferred embodiment of the present invention, the fourth magnetic core 62011 may be formed by laminating a plurality of silicon steel sheets or silicon steel sheets, because the silicon steel sheets or silicon steel sheets have physical properties of high magnetic permeability and low eddy current loss.

optionally, the fourth magnetic bearing 6201 includes:

A fourth magnetic bearing holder 62013, in which the fourth magnetic bearing holder 62013 is sleeved on the rotating shaft 100, a plurality of fourth accommodating grooves 62014 are circumferentially disposed on the fourth magnetic bearing holder 62013, a plurality of eighth magnetic members are disposed in the plurality of fourth accommodating grooves 62014, and magnetic poles of the plurality of eighth magnetic members face the rotating shaft 100;

A second bearing housing 62015 sleeved outside the fourth magnetic bearing seat 62013;

A second bearing cover 62016 sleeved between the fourth magnetic bearing pedestal 62013 and the rotating shaft 100;

And a fifth end cap 62017 and a sixth end cap 62018 disposed at both ends of the second bearing shell 62015, respectively;

The second bearing cover 62016, the fifth end cap 62017, and the sixth end cap 62018 cooperate to fix the eighth magnetic members to the fourth magnetic bearing seat 62013.

In the embodiment of the present invention, by providing the second bearing cover 62016, the gap between the fourth magnetic core 62011 and the fourth coil 62012 can be closed, so that a stable and uniform air film pressure is formed between the second bearing cover 62016 and the rotating shaft 100. In addition, the size of the ninth gap 6203 can be easily adjusted and controlled by providing second bearing sleeves 62016 of different radial thicknesses.

Wherein, the width of the ninth gap 6203 between the second bearing cover 62016 and the rotation axis 100 may be 5 μm to 12 μm, preferably 8 μm to 10 μm.

in the preferred embodiment of the present invention, the fourth magnetic bearing seat 62013 may be formed by laminating a plurality of silicon steel sheets or silicon steel sheets, because the silicon steel sheets or silicon steel sheets have physical properties such as high magnetic permeability and low eddy current loss. The number of the fourth receiving grooves 62014 may be, but is not limited to, six or eight, which are uniformly arranged in the circumferential direction of the fourth magnetic bearing base 62013. In this way, the magnetic force between the fourth magnetic bearing 6201 and the rotating shaft 100 can be made more uniform and stable. The plurality of eighth magnetic members may be provided on the fourth magnetic bearing holder 62013 in another manner, which is not limited. The material of fifth end cap 62017 and sixth end cap 62018 may each be a non-magnetic material, preferably a duralumin material. The material of the second bearing cover 62016 may be a non-magnetic material, preferably a duralumin material. The material of the second bearing shell 62015 may be a non-magnetic material, preferably a duralumin material.

Preferably, the fifth end cap 62017 and the sixth end cap 62018 are provided with bosses having the same outer diameter as the inner diameter of the second bearing housing 62015, and the bosses of the fifth end cap 62017 and the sixth end cap 62018 are used for fixing and pressing silicon steel sheets or silicon steel sheets constituting the fourth magnetic bearing base 62013 from both ends.

In the embodiment of the present invention, the tenth dynamic pressure generating groove 6202 may be provided on the second bearing sleeve 62016, and in order to facilitate the machining of the tenth dynamic pressure generating groove 6202, the second bearing sleeve 62016 may be made of a stainless steel material. Specifically, the tenth dynamic pressure generating groove 6202 may be provided at a middle portion of the rotating shaft 100 corresponding to the circumferential surface of the second bearing sleeve 62016, or may be provided as two independent tenth dynamic pressure generating grooves 6202 symmetrically distributed at both sides of the middle portion; the tenth dynamic pressure generating groove 6202 may be provided in a middle portion of an inner side wall of the second bearing sleeve 62016, or may be provided as two independent tenth dynamic pressure generating grooves 6202 symmetrically distributed at both ends of the inner side wall of the second bearing sleeve 62016.

Optionally, the tenth dynamic pressure generating grooves 6202 are arranged in a matrix, which is beneficial to more uniformly distributing the gas film in the ninth gap 6203.

alternatively, the tenth dynamic pressure generating groove 6202 is a V-shaped groove provided continuously or at intervals.

In the embodiment of the present invention, by adopting the above arrangement manner of the tenth dynamic pressure generating groove 6202, the rotating shaft can be held in a non-contact manner in a desired manner under the condition that the rotating shaft 100 rotates in the forward direction or in the reverse direction, so that the rotating shaft 100 has the advantages of high load capacity and good stability. The tenth pressure-generating groove 6202 may be provided as a chevron-shaped groove or a groove of another shape in addition to the V-shaped groove.

optionally, a second static pressure intake orifice 6205 is also provided in the fourth magnetic bearing 6201, one end of the second static pressure intake orifice 6205 communicates with the ninth gap 6203, and the other end is connected to an external air source for delivering the external air source into the ninth gap 6203.

In the embodiment of the present invention, by providing the second static pressure intake orifice 6205, a gas static pressure bearing may be formed, so that the groove type gas-magnetic hybrid radial bearing 6200 may constitute a groove type gas static pressure-magnetic hybrid radial bearing. The flow diameter of the second static pressure air inlet throttle 6205 can be adjusted according to actual working conditions such as air quantity requirements and the like.

Optionally, the second static inlet orifice 6205 branches into at least two branches within the fourth magnetic bearing 6201 communicating into the ninth gap 6203.

In embodiments of the present invention, the second static inlet orifice 6205 may, in turn, pass through the fifth end cover 62017 or the sixth end cover 62018, the fourth magnetic bearing 6201, and the second bearing housing 62016 to communicate an external gas source to the ninth gap 6203. Further, the second static pressure intake orifice 6205 may branch into two or more branches to the ninth gap 6203, so that the film pressure in the ninth gap 6203 is more uniform. Further, an annular groove may be provided in the fifth end cover 62017 or the sixth end cover 62018, and a plurality of second static pressure intake orifices 6205 may be provided in an annular region of the fourth magnetic bearing 6201 corresponding to the annular groove, for example, one second static pressure intake orifice 6205 may be provided in each fourth magnetic core 62011 or in each two adjacent fourth magnetic cores 62011. The flow diameters of the second static pressure intake orifice 6205 and the branch can be adjusted according to actual working conditions such as air quantity requirements.

optionally, the slot gas-magnetic hybrid radial bearing 6200 further comprises a plurality of fourth sensors 6204 disposed circumferentially spaced apart along the fourth magnetic bearing 6201, wherein the sensor probe of each fourth sensor 6204 is disposed within the ninth gap 6203.

in the embodiment of the present invention, by providing the fourth sensor 6204, a parameter at the ninth gap 6203, for example, a pressure of an air film at the ninth gap 6203, can be detected in real time. In this way, the fourth magnetic bearing 6201 can actively control the radial bearing 6200 based on the detection result of the fourth sensor 6204, and can achieve high accuracy in control.

Optionally, each of the fourth sensors 6204 includes a fourth sensor cover 62041 and a fourth sensor probe 62042, the first end of the fourth sensor probe 62042 is connected to the fourth sensor cover 62041, the fourth sensor cover 62041 is fixed to the fourth magnetic bearing 6201, and a through hole for the fourth sensor probe 62042 to pass through is formed in the fourth magnetic bearing 6201; the second end of the fourth sensor probe 62042 passes through the through hole of the fourth magnetic bearing 6201 and extends to the ninth gap 6203, and the second end of the fourth sensor probe 62042 is flush with the side of the fourth magnetic bearing 6201 close to the rotating shaft 100.

In the embodiment of the present invention, the fourth sensor 6204 can be more stably mounted on the fourth magnetic bearing 6201 by the structural form and the mounting manner of the fourth sensor 6204. In addition, the second end of the fourth sensor probe 62042 is flush with the side of the fourth magnetic bearing 6201 close to the rotating shaft 100, so that the fourth sensor probe 62042 can be prevented from being touched by the rotating shaft 100, and the fourth sensor probe 62042 can be protected; on the other hand, the air film in the ninth gap 6203 is not affected, and the air film in the ninth gap 6203 is prevented from being disturbed.

In an embodiment of the present invention, the number of the fourth sensors 6204 may be the same as the number of the eighth magnetic members. The fourth sensor 6204 may be disposed between two adjacent eighth magnetic members, or may be disposed through the eighth magnetic members, which is not limited in the embodiment of the present invention. Each fourth sensor 6204 is preferably disposed in a middle portion of the fourth magnetic bearing 6201.

Optionally, the plurality of fourth sensors 6204 is any one or more of the following in combination:

A displacement sensor for detecting the position of the rotating shaft 100;

A pressure sensor for detecting the air film pressure at the ninth gap 6203;

A speed sensor for detecting a rotation speed of the rotary shaft 100;

An acceleration sensor for detecting the rotational acceleration of the rotary shaft 100.

In some embodiments, the rotor system may be configured such that the thrust bearing and the radial bearing adjacent to the thrust bearing are integrated to form an integrated bearing.

As shown in fig. 41 to 50, the integrated bearing 1000 includes:

A third bearing housing 1001, the third bearing housing 1001 being a hollow solid of revolution, the third bearing housing 1001 being provided with a first accommodation chamber and a second accommodation chamber;

The radial sub-bearing 1002 is arranged in the first accommodating cavity, the radial sub-bearing 1002 is arranged on the rotating shaft 100 in a penetrating manner, and a tenth gap 1004 is formed between the radial sub-bearing 1002 and the rotating shaft 100;

The thrust sub-bearing 1003 is disposed in the second accommodating cavity, the thrust sub-bearing 1003 includes a fourth thrust disc 10031, and a seventh stator 10032 and an eighth stator 10033 which are disposed on two sides of the fourth thrust disc 10031, respectively, the fourth thrust disc 10031 is fixedly connected to the rotating shaft 100, and the seventh stator 10032 and the eighth stator 10033 are both disposed on the rotating shaft 100 in a penetrating manner; an eleventh gap 1005 is provided between each of the seventh stator 10032 and the eighth stator 10033 and the fourth thrust disc 10031.

In the embodiment of the invention, the radial sub-bearing 1002 and the thrust sub-bearing 1003 are integrated in one bearing shell, so that the bearing shell is easy to process and install, has the characteristics of simplified structure and high integration level, and can effectively meet the requirement of consistent coaxiality of the radial sub-bearing 1002 and the thrust sub-bearing 1003 during processing and installation. In addition, since the tenth gap 1004 is arranged in the radial sub-bearing 1002 and the eleventh gap 1005 is arranged in the thrust sub-bearing 1003, the bearing of the invention is a non-contact bearing, and can meet the requirement of high-speed rotation of the rotor.

Among them, the material of the third bearing housing 1001 may be a non-magnetic material, preferably a duralumin material.

In this case, the seventh stator 10032 and the third bearing housing 1001 may be integrally formed, and the eighth stator 10033 and the third bearing housing 1001 may be detachably connected.

When the rotor system of the embodiment of the present invention is applied to a gas turbine or a gas turbine power generation combined unit, the third bearing housing 1001 may be connected to a casing of the gas turbine through a connection member.

In an embodiment of the present invention, each of the radial sub-bearing 1002 and the thrust sub-bearing 1003 may include a magnetic bearing, wherein the magnetic bearing disposed in the radial sub-bearing 1002 is configured as follows:

the radial sub-bearing 1002 includes a fifth magnetic bearing 10021 sleeved on the rotating shaft 100, the fifth magnetic bearing 10021 is detachably mounted in the first accommodating cavity, and a plurality of ninth magnetic members are circumferentially disposed on the fifth magnetic bearing 10021;

wherein the rotation shaft 100 is movable in a radial direction of the rotation shaft 100 by a magnetic force of the plurality of ninth magnetic members.

further, the fifth magnetic bearing 10021 comprises:

the fifth magnetic bearing seat is sleeved on the rotating shaft 100, a plurality of fifth accommodating grooves are formed in the fifth magnetic bearing seat along the circumferential direction, a plurality of ninth magnetic parts are arranged in the plurality of fifth accommodating grooves, and magnetic poles of the plurality of ninth magnetic parts face the rotating shaft 100;

And a third bearing housing 10022 sleeved between the fifth magnetic bearing seat and the rotating shaft 100, wherein the third bearing housing 10022 is matched with the fifth magnetic bearing seat to fix the plurality of ninth magnetic members on the fifth magnetic bearing seat.

For other specific embodiments of the magnetic bearing disposed in the radial sub-bearing 1002, reference may be made to the relevant description in the tenth embodiment, and the same beneficial effects can be achieved, so as to avoid repetition, and further description is omitted here.

in an embodiment of the present invention, the integrated bearing 1000 may further include a seventh end cover 1006, where the seventh end cover 1006 is disposed at an end of the third bearing housing 1001 close to the first accommodating cavity, and the seventh end cover 1006 abuts against the fifth magnetic bearing seat, so as to fix the radial sub-bearing 1002 in the first accommodating cavity.

In an embodiment of the present invention, each of the radial sub-bearing 1002 and the thrust sub-bearing 1003 may include a magnetic bearing, wherein the form of the magnetic bearing disposed in the thrust sub-bearing 1003 is as follows:

Each of the seventh stator 10032 and the eighth stator 10033 includes a sixth magnetic bearing 10034, on which a plurality of tenth magnetic members are circumferentially disposed;

A tenth magnetic member is provided on the fourth thrust disc 10031, and the fourth thrust disc 10031 is movable in the axial direction of the rotary shaft 100 by a magnetic force between the plurality of tenth magnetic members and the tenth magnetic member.

Further, the sixth magnetic bearing 10034 includes:

A sixth magnetic bearing seat, which is disposed opposite to the fourth thrust disc 10031, and is circumferentially provided with a plurality of sixth receiving grooves, a plurality of tenth magnetic components are disposed in the plurality of sixth receiving grooves, and magnetic poles of the plurality of tenth magnetic components face to a side where the fourth thrust disc 10031 is located;

And the second pressure ring is arranged on one side, close to the fourth thrust disc 10031, of the sixth magnetic bearing seat, and the second pressure ring is matched with the sixth magnetic bearing seat to fix the tenth magnetic components on the sixth magnetic bearing seat.

For other specific embodiments of the magnetic bearing disposed in the thrust sub-bearing 1003, reference may be made to the relevant description in the tenth embodiment, and the same beneficial effects can be achieved, so that repeated descriptions are omitted for avoiding repetition.

In the embodiment of the present invention, by providing a magnetic bearing, especially an electromagnetic bearing (the ninth magnetic component in the fifth magnetic bearing 10021 is an electromagnet, and the tenth magnetic component in the sixth magnetic bearing 10034 is an electromagnet) in the integrated bearing 1000, when the rotor system is started or stopped, the electromagnetic bearing can be used to enable the thrust disk and the stator as well as the rotating shaft and the bearing sleeve in the integrated bearing 1000 to rotate in the gap, so as to improve the low-speed performance of the integrated bearing 1000, prolong the service life of the integrated bearing 1000, and improve the safety and reliability of the integrated bearing 1000 and the entire rotor system.

in the embodiment of the present invention, the seventh stator 10032 may be integrally formed with the third bearing housing 1001, and the eighth stator 10033 may be detachably connected to the third bearing housing 1001.

in the embodiment of the present invention, the radial sub-bearing 1002 and the thrust sub-bearing 1003 may be provided with dynamic pressure generating grooves, wherein the dynamic pressure generating grooves provided in the radial sub-bearing 1002 have the following structural form:

The radial sub-bearing 1002 has an eleventh dynamic pressure generating groove 10023 formed on a side wall facing the rotation shaft 100 or a circumferential surface of the rotation shaft 100 facing the radial sub-bearing 1002.

Further, the eleventh pressure generating grooves 10023 are arranged in a matrix.

Further, the eleventh dynamic pressure generating grooves 10023 are V-shaped grooves provided continuously or at intervals.

for other specific embodiments of the radial sub-bearing 1002 with dynamic pressure generating grooves, reference may be made to the relevant descriptions in the twelfth embodiment, and the same beneficial effects can be achieved.

in the embodiment of the present invention, the radial sub-bearing 1002 and the thrust sub-bearing 1003 may be provided with dynamic pressure generating grooves, wherein the dynamic pressure generating grooves provided in the thrust sub-bearing 1003 have the following structural form:

An end surface of the fourth thrust disk 10031 facing the seventh stator 10032 and the eighth stator 10033, or an end surface of the seventh stator 10032 and the eighth stator 10033 facing the fourth thrust disk 10031 is provided with a twelfth dynamic pressure generating groove 10035.

Further, the twelfth dynamic pressure generating grooves 10035 are arranged in a radial or concentric manner.

Further, the twelfth dynamic pressure generating groove 10035 includes a first spiral groove and a second spiral groove, the first spiral groove surrounds the second spiral groove, the spiral directions of the first spiral groove and the second spiral groove are opposite, and one end of the first spiral groove close to the second spiral groove is connected or disconnected with one end of the second spiral groove close to the first spiral groove.

for other specific embodiments of the thrust sub-bearing 1003 provided with the dynamic pressure generating groove, reference may be made to the relevant description in the tenth embodiment, and the same beneficial effects can be achieved, and for avoiding repetition, the description is omitted here.

In the embodiment of the present invention, the integrated bearing 1000 includes a dynamic pressure gas bearing by providing a dynamic pressure generating groove in the integrated bearing 1000. Under the condition that the electromagnetic bearing and the dynamic pressure gas bearing are arranged at the same time, the dynamic performance and the stability of the integrated bearing 1000 in a high-speed running state are improved, the disturbance resistance is high, and the bearing capacity of the bearing is further improved. Meanwhile, the electromagnetic bearing and the dynamic pressure gas bearing adopt a nested parallel structure, so that the structure is simplified, the integration level is high, the processing, the manufacturing and the operation are easy, and the comprehensive performance of the integrated bearing 1000 is improved.

In the embodiment of the present invention, the integrated bearing 1000 may further include a static pressure intake orifice, and the structural form thereof is as follows:

The third bearing housing 1001 is also provided with a third static pressure intake orifice 1007;

Wherein one end of the third static pressure intake orifice 1007 is connected to an external air supply, and the other end is communicated with the tenth gap 1004 via the radial sub-bearing 1002, and/or communicated with the eleventh gap 1005 via the seventh stator 10032 and the eighth stator 10033, for delivering the external air supply to the tenth gap 1004 and/or the eleventh gap 1005.

In the embodiment of the present invention, a static pressure intake orifice may be further provided through the integrated bearing 1000, so that the integrated bearing 1000 includes a gas static pressure bearing. In the case where the electromagnetic bearing and the aerostatic bearing are provided at the same time, the bearing capacity of the integrated bearing 1000 can be further increased. In addition, the electromagnetic bearing and the gas hydrostatic bearing can be mutually standby, and under the condition that one of the two parts is failed or fails or the starting condition cannot be met, the other part can be used as a standby bearing to play the same role. For example, in the case where a failure of the electromagnetic bearing is detected, the aerostatic bearing is controlled to be turned on to perform corresponding actions instead of the electromagnetic bearing, thereby improving the safety and reliability of the integrated bearing 1000.

for other specific embodiments of the integrated bearing 1000 with static pressure intake orifices, reference may be made to the relevant descriptions in the tenth embodiment and the twelfth embodiment, and the same beneficial effects can be achieved, so that no further description is provided for avoiding repetition.

In the embodiment of the present invention, sensors may be disposed in both the radial sub-bearing 1002 and the thrust sub-bearing 1003, and the structural forms thereof are as follows:

The radial sub-bearing 1002 is provided with a fifth sensor (not shown), and a sensor probe of the fifth sensor is arranged in the tenth gap 1004.

In this way, parameters at the ninth gap 1004, such as the air film pressure at the tenth gap 1004, etc., can be detected in real time. In this way, the fifth magnetic bearing 10021 can actively control the radial sub-bearing 102 based on the detection result of the fifth sensor, and can achieve high accuracy in control.

Optionally, each fifth sensor in the plurality of fifth sensors includes a first sensor cover and a fifth sensor probe, a first end of the fifth sensor probe is connected to the fifth sensor cover, the fifth sensor cover is fixed to the fifth magnetic bearing 10021, and the fifth magnetic bearing 10021 is provided with a through hole for the fifth sensor probe to pass through; the second end of the fifth sensor probe passes through the through hole of the fifth magnetic bearing 10021 and extends to the tenth gap 1004, and the second end of the fifth sensor probe is flush with the side of the fifth magnetic bearing 10021 close to the rotating shaft 100.

In this way, the fifth sensor can be more stably provided on the fifth magnetic bearing 10021. In addition, the second end of the sensor probe is flush with the side of the fifth magnetic bearing 10021 close to the rotating shaft 100, so that on one hand, the sensor probe can be prevented from being touched by the rotating shaft 100, thereby being beneficial to protecting the sensor probe; on the other hand, the air film in the tenth gap 1004 is not affected, and the air film in the ninth gap 1004 is prevented from being disturbed.

The pusher bearing 1003 is provided with a sixth sensor (not shown), and a sensor probe of the sixth sensor is disposed in the eleventh gap 1005.

In this way, a parameter at the eleventh gap 1005, such as the air film pressure at the eleventh gap 1005, etc., can be detected in real time. In this way, the sixth magnetic bearing 10034 can actively control the thrust sub-bearing 103 based on the detection result of the sixth sensor, and can achieve high accuracy in control.

Optionally, the sixth sensor includes a sixth sensor cover and a sixth sensor probe, a first end of the sixth sensor probe is connected to the sixth sensor cover, the sixth sensor cover is fixed on the sixth magnetic bearing 10034, and a through hole for the sixth sensor probe to pass through is formed in the sixth magnetic bearing 10034; the second end of the sixth sensor probe passes through the through hole of the sixth magnetic bearing 10034 and extends to the eleventh gap 1005, and the second end of the sixth sensor probe is flush with the side of the sixth magnetic bearing 10034 close to the fourth thrust disc 10031.

In this way, the sixth sensor can be more stably provided on the sixth magnetic bearing 10034. In addition, the second end of the sixth sensor probe is flush with the side of the sixth magnetic bearing 10034 close to the fourth thrust disc 10031, so that on one hand, the sixth sensor probe can be prevented from being touched by the fourth thrust disc 10031, thereby being beneficial to protecting the sixth sensor probe; on the other hand, the air film in the eleventh gap 1005 is not affected, and the air film in the eleventh gap 1005 is prevented from being disturbed.

The above description is only for the specific embodiments of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present invention, and the changes or substitutions should be covered within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.

Claims

1. a rotor system, comprising:

The shaft body of the rotating shaft is of an integrated structure;

2. the rotor system of claim 1,

The auxiliary thrust disc is connected with the shell of the rotor system, a through hole is formed in the center of the auxiliary thrust disc, the auxiliary thrust disc penetrates through the rotating shaft, and a third gap is formed between the auxiliary thrust disc and the rotating shaft.

3. The rotor system of claim 1 or 2,

The end face of the auxiliary thrust disc, which faces the air compressor, or the end face of an impeller of the air compressor, which faces the auxiliary thrust disc, is provided with a first dynamic pressure generating groove; and/or the presence of a gas in the gas,

and the end surface of the auxiliary thrust disc, which faces the turbine, or the end surface of an impeller of the turbine, which faces the auxiliary thrust disc, is provided with a second dynamic pressure generating groove.

4. The rotor system of claim 1 or 2,

The rotor system is provided with a static pressure air inlet throttling pipeline which is communicated with the first gap and the second gap, and the static pressure air inlet throttling pipeline is used for conveying a pressure air source into the first gap and the second gap.

5. The rotor system of claim 4,

The static pressure air inlet throttling pipeline is communicated with an air outlet of the air compressor and is used for conveying compressed air output by the air compressor into the first gap and the second gap.

6. The rotor system of claim 2,

And the inner circumferential surface of the auxiliary thrust disc facing the rotating shaft, or the outer circumferential surface of the rotating shaft facing the auxiliary thrust disc is provided with a third dynamic pressure generating groove.

7. The rotor system of claim 1,

the thrust bearing is arranged between the first radial bearing and the motor;

Or, the thrust bearing is disposed between the motor and the second radial bearing;

Or the thrust bearing is arranged on one side of the first radial bearing, which is far away from the motor;

or, the thrust bearing is arranged between the second radial bearing and the compressor.

8. The rotor system according to claim 1, wherein the motor is a dynamic pressure bearing motor, and a fourth dynamic pressure generating groove is provided in a portion of the rotating shaft corresponding to a bearing of the motor.

9. the rotor system of claim 1, wherein the electric machine is a starter-integral electric machine.

10. The rotor system of claim 1,

The rotor system further comprises a locking device for locking the rotating shaft when the rotating shaft is static.

11. The rotor system of claim 1,

The thrust bearing is a gas-magnetic hybrid thrust bearing;

The first radial bearing and the second radial bearing are both air-magnetic hybrid radial bearings.

12. A gas turbine power plant comprising an inlet duct, a combustion chamber and a rotor system according to any one of claims 1 to 11, the inlet duct communicating with an inlet port of the compressor, an outlet port of the compressor communicating with an inlet port of the combustion chamber, an outlet port of the combustion chamber communicating with an inlet port of the turbine.