CN108868891B

CN108868891B - Rotor system and control method thereof, gas turbine generator set and control method thereof

Info

Publication number: CN108868891B
Application number: CN201810030299.3A
Authority: CN
Inventors: 靳普
Original assignee: Liu Muhua
Current assignee: Liu Muhua
Priority date: 2018-01-12
Filing date: 2018-01-12
Publication date: 2024-04-02
Anticipated expiration: 2038-01-12
Also published as: WO2019137023A1; CN108868891A

Abstract

The invention provides a rotor system and a control method thereof, and a gas turbine generator set and a control method thereof, wherein the rotor system comprises: the rotating shaft is vertically arranged; the motor, the air compressor and the turbine are sequentially arranged on the rotating shaft; the thrust bearing and the at least two radial bearings are non-contact bearings; the thrust bearing is arranged at a preset position on one side of the turbine, which is close to the compressor, wherein the preset position is a position which enables the center of gravity of the rotor system to be located between the two radial bearings farthest from each other in the at least two radial bearings. The invention enables the rotor system to be arranged vertically by adopting the non-contact bearing. Therefore, the gravity center of the rotor system is positioned at the axle center, static deflection is not generated, and the moment generated by gravity on the axle line is zero, so that the influence of gravity on the rotation of the rotor system can be eliminated, and the stability of the rotor system can be improved.

Description

Rotor system and control method thereof, gas turbine generator set and control method thereof

Technical Field

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

Background

The gas turbine mainly comprises a compressor, a combustion chamber and a turbine. The air enters the compressor and is compressed into high-temperature high-pressure air, and then the air is supplied to the combustion chamber for mixed combustion with fuel, and the generated high-temperature high-pressure gas expands in the turbine to do work. When the rotor rotates at high speed, the rotor receives a force in a radial direction and a force in an axial direction. In order to limit the radial and axial movement of the shaft, radial and thrust bearings are required to be installed in the rotor system. Conventional radial bearings and thrust bearings commonly employ contact bearings such as oil film lubricated bearings or rolling bearings.

On the one hand, with increasing rotor speeds, especially when rotor speeds exceed 40000 revolutions per minute, the demands for operating speeds have not been met due to the large mechanical wear of the contact bearings described above.

On the other hand, the lubrication and sealing manner of the oil film lubrication bearing determines that the rotor system of the existing gas turbine needs to be horizontally installed, namely, the rotating shaft needs to be horizontally arranged. Because the gravity born by the rotating shaft is different everywhere, the rotating shaft is easy to generate static deflection. During the rotation of the rotor system, gravity will generate an alternating moment on the shaft, so that the rotor system has angular acceleration. This affects the dynamics of the rotor system, resulting in a reduced stability of the rotor system.

It can be seen that there is a need to provide a new rotor system that solves the above-mentioned problems with existing gas turbine generator sets.

Disclosure of Invention

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

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

the rotating shaft is of an integral structure, and is vertically arranged;

the motor, the air compressor and the turbine are sequentially arranged on the rotating shaft;

the thrust bearing and the at least two radial bearings are non-contact bearings;

the thrust bearing is arranged at a preset position on one side of the turbine, which is close to the compressor, wherein the preset position is a position which can enable the center of gravity of the rotor system to be located between the two radial bearings farthest from each other in the at least two radial bearings.

Optionally, the at least two radial bearings include a first radial bearing and a second radial bearing, the first radial bearing is disposed on a side of the motor away from the compressor, and the second radial bearing is disposed between the compressor and the turbine; wherein,

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

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 disposed between the motor and the compressor.

Optionally, the at least two radial bearings further comprise a third radial bearing, the third radial bearing being disposed between the motor and the compressor.

Optionally, the at least two radial bearings further comprise a fourth radial bearing, the fourth radial bearing being disposed on a side of the turbine remote from the compressor; wherein,

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

or the thrust bearing is arranged between the motor and the compressor;

alternatively, the thrust bearing is disposed between the compressor and the second radial bearing.

Optionally, the fourth radial bearing is a gas dynamic-static pressure mixed radial bearing.

Optionally, a thermal insulation layer is arranged on one side of the turbine, which is close to the second radial bearing.

Optionally, the motor is a dynamic pressure bearing motor, and a first dynamic pressure generating groove is arranged at a position of the rotating shaft corresponding to a bearing of the motor.

Optionally, the motor is a heuristic integrated motor.

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

Optionally, the bearing-mounting part of the rotating shaft is coated with an anti-wear coating.

Optionally, the thrust bearing is a gas-magnetic hybrid thrust bearing;

at least one radial bearing in the at least two radial bearings is a gas-magnetic hybrid radial bearing or a gas dynamic-static pressure hybrid radial bearing.

Optionally, when the second radial bearing is a gas-magnetic hybrid radial bearing, the magnetic component of the second radial bearing is disposed on a region of the second radial bearing remote from the turbine.

Optionally, the air-magnetic hybrid thrust bearing is a foil type air-magnetic hybrid thrust bearing, and the foil type air-magnetic hybrid thrust bearing includes:

the first thrust disc is fixedly connected to the rotating shaft;

the first stator and the second stator are arranged on the opposite sides of the first thrust disc in a penetrating manner;

Each of the first stator and the second stator comprises a first magnetic bearing and a first foil bearing, a plurality of first magnetic components are arranged on the first magnetic bearing along the circumferential direction, and a second magnetic component capable of generating magnetic force with the plurality of first magnetic components is arranged on the first foil bearing;

the first foil bearing is arranged between the first magnetic bearing and the first thrust disc, a first gap is reserved between the first foil bearing and the first thrust disc, and the first foil bearing can move in the axial direction of the rotating shaft under the action of magnetic force between the first magnetic component and the second magnetic component.

Optionally, the air-magnetic hybrid thrust bearing is a groove type air-magnetic hybrid thrust bearing, and the groove type air-magnetic hybrid thrust bearing includes:

the second thrust disc is fixedly connected to the rotating shaft and is provided with a third magnetic component;

the third stator and the fourth stator are arranged on the opposite sides of the second thrust disc in a penetrating manner;

each of the third stator and the fourth stator includes a second magnetic bearing on which a plurality of fourth magnetic members capable of generating magnetic force with the third magnetic member are circumferentially provided, a second gap is provided between the second magnetic bearing and the second thrust disk, and the second thrust disk is movable in an axial direction of the rotating shaft under a magnetic force between the third magnetic member and the plurality of fourth magnetic members;

And the end surfaces of the second thrust disc facing the third stator and the fourth stator, or the end surfaces of the third stator and the fourth stator facing the second thrust disc are provided with second dynamic pressure generating grooves.

Optionally, in the third stator and the fourth stator, a first static pressure air inlet orifice is further arranged on each stator, one end of the first static pressure air inlet orifice is communicated with the second gap, and the other end of the first static pressure air inlet orifice is connected with an external air source and used for conveying the external air source into the second gap.

Optionally, the air-magnetic hybrid radial bearing is a foil-type air-magnetic hybrid radial bearing, and the foil-type air-magnetic hybrid radial bearing includes:

the third magnetic bearing is sleeved on the rotating shaft, and a plurality of fifth magnetic components are arranged on the third magnetic bearing along the circumferential direction;

the second foil bearing is sleeved on the rotating shaft and positioned between the third magnetic bearing and the rotating shaft, and a sixth magnetic component capable of generating magnetic force with the plurality of fifth magnetic components is arranged on the second foil bearing;

and a third gap is arranged between the second foil bearing and the rotating shaft, and the second foil bearing can move in the radial direction of the rotating shaft under the action of the magnetic force of the fifth magnetic components and the sixth magnetic components.

Optionally, the air-magnetic hybrid radial bearing is a groove-type air-magnetic hybrid radial bearing, and the groove-type air-magnetic hybrid radial bearing includes:

the fourth magnetic bearing is sleeved on the rotating shaft, and a plurality of seventh magnetic components are arranged on the fourth magnetic bearing along the circumferential direction;

a third dynamic pressure generating groove is formed in the circumferential surface of the fourth magnetic bearing facing to the side wall of the rotating shaft or the rotating shaft facing to the fourth magnetic bearing;

and a fourth gap is formed between the fourth magnetic bearing and the rotating shaft, and the rotating shaft can move in the radial direction of the rotating shaft under the action of the magnetic force of the seventh magnetic components.

Optionally, a second static pressure air inlet orifice is further arranged on the fourth magnetic bearing, one end of the second static pressure air inlet orifice is communicated with the fourth gap, and the other end of the second static pressure air inlet orifice is connected with an external air source and used for conveying the external air source into the fourth gap.

Optionally, in the rotor system, the thrust bearing and a radial bearing adjacent to the thrust bearing are integrated into one body to form an integrated bearing, and the integrated bearing includes:

the third bearing shell is a hollow revolving body and is provided with a first accommodating cavity and a second accommodating cavity;

The radial sub-bearing is arranged in the first accommodating cavity, penetrates through the rotating shaft, and has a fifth gap with the rotating shaft;

the thrust sub-bearing comprises a third thrust disc, a fifth stator and a sixth stator which are respectively arranged at two sides of the thrust disc, the thrust disc is fixedly connected to the rotating shaft, and the fifth stator and the sixth stator are respectively arranged on the rotating shaft in a penetrating way; and a sixth gap is arranged between each of the fifth stator and the sixth stator and the third thrust disk.

Optionally, the radial sub-bearing includes a fifth magnetic bearing sleeved on the rotating shaft, the fifth magnetic bearing and the rotating shaft have the fifth gap therebetween, and a plurality of eighth magnetic components are circumferentially arranged on the fifth magnetic bearing; the rotating shaft can move in the radial direction of the rotating shaft under the action of the magnetic force of the eighth magnetic components;

each of the fifth stator and the sixth stator includes a sixth magnetic bearing on which a plurality of ninth magnetic members are circumferentially arranged; the third thrust disc is provided with a tenth magnetic part, and the third thrust disc can move in the axial direction of the rotating shaft under the action of magnetic force between the ninth magnetic parts and the tenth magnetic part.

Optionally, the third bearing housing is further provided with a third static pressure air inlet orifice;

and one end of the third static pressure air inlet throttle hole is connected with an external air source, and the other end of the third static pressure air inlet throttle hole is communicated with the fifth gap through the radial bearing, and/or is communicated with the sixth gap through the fifth stator and the sixth stator, and is used for conveying the external air source to the fifth gap and/or the sixth gap.

In another aspect, the present invention provides a control method of a rotor system, for the above rotor system, the method including:

opening hydrostatic bearings in the radial bearing and the thrust bearing to enable the rotating shaft to move to a preset radial position, and enabling a thrust disc of the thrust bearing to move to a preset axial position;

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

when the rotor system is stopped, the hydrostatic bearings in the radial bearings and the hydrostatic bearings in the thrust bearings are started;

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

wherein opening the hydrostatic bearing comprises: opening a magnetic bearing in the bearing and/or delivering gas to a static pressure inlet orifice in the bearing;

Closing the hydrostatic bearing includes: closing the magnetic bearings in the bearings and/or stopping the delivery of gas to the static pressure inlet orifice in the bearings.

In another aspect, the present invention provides another control method of a rotor system, for the above rotor system, the method including:

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;

when the rotor system accelerates to a first-order critical speed or a second-order critical speed, opening hydrostatic bearings in the radial bearing and the thrust bearing;

closing hydrostatic bearings in the radial bearing and the thrust bearing after the rotor system has smoothly passed the first-order critical speed or the second-order critical speed;

when the rotor system is decelerated to the first-order critical speed or the second-order critical speed, a hydrostatic bearing in the radial bearing and the thrust bearing is started;

When the rotating speed of the rotating shaft is reduced to a second preset value, a hydrostatic bearing in the radial bearing and a hydrostatic bearing in the thrust bearing are started;

closing the hydrostatic bearing, comprising: closing the magnetic bearings in the bearings and/or stopping the delivery of gas to the static pressure inlet orifice in the bearings.

Optionally, opening a hydrostatic bearing in the thrust bearing to move a thrust disc of the thrust bearing to a preset axial position, including:

opening first magnetic bearings in the first stator and the second stator, and controlling the first thrust disk to move in the axial direction of the rotating shaft under the action of magnetic forces of the plurality of first magnetic components so that the first gap between the first thrust disk and the first foil bearing in the first stator is equal to the first gap between the first thrust disk and the first foil bearing in the second stator;

The method further comprises the steps of:

opening a first magnetic bearing in the first stator and the second stator when a load is applied to the first thrust disc, the first thrust disc moving in the axial direction of the rotating shaft under the load, the first gap between the first thrust disc and a first foil bearing in the first stator not being equal to the first gap between the first thrust disc and a first foil bearing in the second stator;

the first magnetic bearings in the first stator and the second stator are closed when the first gap between the first thrust disc and the first foil bearing in the first stator is equal to the first gap between the first thrust disc and the first foil bearing in the second stator.

opening second magnetic bearings in the third stator and the fourth stator, and controlling the second thrust disk 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 a difference between the second gap between the second thrust disk and the second magnetic bearings in the third stator and the second gap between the second thrust disk and the second magnetic bearings in the fourth stator is smaller than or equal to a predetermined value;

The method further comprises the steps of:

opening a second magnetic bearing in the third stator or the fourth stator 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 the second gap between the second thrust disc and the second magnetic bearing in the third stator and the second gap between the second thrust disc and the second magnetic bearing in the fourth stator is greater than the predetermined value;

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

opening a second magnetic bearing of the third stator and the fourth stator; and/or starting an external gas source, and conveying gas to the second gap through the first static pressure inlet orifice;

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 fourth magnetic component and/or the pushing action of the gas so that the difference value between the second gap between the second thrust disc and the second magnetic bearing in the third stator and the second gap between the second thrust disc and the second magnetic bearing in the fourth stator is smaller than or equal to the preset value.

Optionally, opening a hydrostatic bearing in the radial bearings to move the rotating shaft to a preset radial position includes:

starting the third magnetic bearing, and controlling the rotating shaft to move in the radial direction of the rotating shaft under the action of the magnetic force of the plurality of fifth magnetic components so as to enable the rotating shaft to move to a preset radial position;

the method further comprises the steps of:

when a third gap between the rotating shaft and the second foil bearing is changed, the third magnetic bearing is started, so that the second foil bearing corresponding to the gap reducing side moves towards the direction approaching to the rotating shaft under the action of magnetic force between the plurality of fifth magnetic components and the sixth magnetic component;

And after the rotating shaft is positioned at the balanced radial position, the third magnetic bearing is closed.

opening the fourth magnetic bearing, and controlling the rotating shaft to move in the radial direction of the rotating shaft under the action of the magnetic force of the seventh magnetic components so as to enable the rotating shaft to move to a preset radial position;

the method further comprises the steps of:

when a fourth gap between the rotating shaft and the fourth magnetic bearing is changed, the fourth magnetic bearing is started, so that the rotating shaft moves away from the gap reducing side under the action of magnetic force of the seventh magnetic components;

and after the rotating shaft is at the balanced radial position, the fourth magnetic bearing is closed.

opening the fourth magnetic bearing; and/or starting an external air source, and conveying air to the fourth gap through the second static pressure air inlet throttle hole;

and controlling the rotating shaft to move in the radial direction of the rotating shaft under the action of magnetic force of the seventh magnetic components and/or the pushing action of the gas so as to enable the rotating shaft to move to a preset radial position.

In another aspect, the invention provides a gas turbine generator set, comprising an air inlet channel, a combustion chamber and the rotor system, wherein the air inlet channel is communicated with an air inlet of a gas compressor, an air outlet of the gas compressor is communicated with the air inlet of the combustion chamber, and an air outlet of the combustion chamber is communicated with the air inlet of a turbine.

In another aspect, the present invention provides a control method of a gas turbine generator set, for the gas turbine generator set, including:

starting the gas turbine generator set, compressing air by the compressor, and then entering the combustion chamber and fuel in the combustion chamber for mixed combustion; the high-temperature high-pressure gas discharged by the combustion chamber impacts the turbine of the turbine, so that the turbine rotates, and the turbine drives the motor to rotate through the rotating shaft to generate electricity;

When the gas turbine generator set is stopped, the hydrostatic bearings in the radial bearings and the hydrostatic bearings in the thrust bearings are started;

In the invention, the rotor system can be arranged vertically by adopting the non-contact bearing. Therefore, the gravity center of the rotor system is positioned at the axle center, static deflection is not generated, and the moment generated by gravity on the axle line is zero, so that the influence of gravity on the rotation of the rotor system can be eliminated, and the stability of the rotor system can be improved. Meanwhile, as the rotor system is arranged vertically, the gravity centers of all the components are downward, and the problems caused by a cantilever shaft type structure due to the horizontal arrangement of the rotor system can be avoided. The invention also enables the gravity center of the whole rotor system to be positioned between the two radial bearings which are farthest from each other through adjusting the setting positions of the thrust bearings, further enables the whole rotor system to keep stable structure when rotating at high speed, and meets the requirement of high rotating speed of the gas turbine.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are needed in the description of the embodiments of the present invention will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic view of a rotor system according to a first embodiment;

FIG. 2 is a schematic view of another rotor system according to the first embodiment;

FIG. 3 is a schematic view of another rotor system according to the first embodiment;

FIG. 4 is a schematic view of a structure corresponding to FIG. 1 in which a magnetic bearing is disposed on a second radial bearing;

FIG. 5 is a schematic view of a structure corresponding to FIG. 2 in which a magnetic bearing is disposed on a second radial bearing;

FIG. 6 is a schematic view of a structure corresponding to FIG. 3 in which a magnetic bearing is disposed on a second radial bearing;

FIG. 7 is a schematic view of a rotor system according to a second embodiment;

FIG. 8 is a schematic view of another rotor system according to the second embodiment;

FIG. 9 is a schematic view of another rotor system according to the second embodiment;

FIG. 10 is a schematic view of another rotor system according to the second embodiment;

FIG. 11 is a schematic view of a structure corresponding to FIG. 7 in which a magnetic bearing is disposed on a second radial bearing;

FIG. 12 is a schematic view of a structure corresponding to FIG. 8 in which a magnetic bearing is disposed on a second radial bearing;

FIG. 13 is a schematic view of a structure corresponding to FIG. 9 in which a magnetic bearing is disposed on a second radial bearing;

FIG. 14 is a schematic view of a structure corresponding to FIG. 10 in which a magnetic bearing is disposed on a second radial bearing;

FIG. 15 is a schematic view of another rotor system provided in accordance with the third embodiment;

FIG. 16 is a schematic view of a structure corresponding to FIG. 15 in which a magnetic bearing is disposed on a second radial bearing;

FIG. 17 is a schematic view of another rotor system according to the fourth embodiment;

FIG. 18 is a schematic view of a structure corresponding to FIG. 17 in which a magnetic bearing is disposed on a second radial bearing;

fig. 19 is a schematic view of a structure in which a locking device is provided in a rotor system according to a fifth embodiment;

FIG. 20 is a schematic view of another embodiment of a locking device in a rotor system;

FIG. 21 is a schematic view of the structure in the direction C-C in FIG. 20;

FIG. 22 is a schematic view of a structure for coating a wear-resistant coating on a rotating shaft according to a sixth embodiment;

FIG. 23 is a schematic illustration of a gas turbine generator set provided in accordance with a seventh embodiment;

FIG. 24 is a flow chart of a method of controlling a gas turbine generator set provided in embodiment seven;

FIG. 25 is a flow chart of another method of controlling a gas turbine generator set provided in embodiment seven;

fig. 26 is a flowchart of a control method of a rotor system according to the eighth embodiment;

FIG. 27 is a flow chart of another method of controlling a rotor system according to the eighth embodiment;

FIG. 28 is a cross-sectional view of a foil type hybrid gas-magnetic thrust bearing provided in accordance with a ninth embodiment;

FIG. 29 is a schematic view showing the structure of a first magnetic bearing in a foil type air-magnetic hybrid thrust bearing according to a ninth embodiment;

FIG. 30 is a schematic view showing the structure of a first magnetic bearing seat in a foil type air-magnetic hybrid thrust bearing according to a ninth embodiment;

FIG. 31 is a schematic view showing the structure of a first foil in a foil type air-magnetic hybrid thrust bearing according to a ninth embodiment;

FIG. 32 is a cross-sectional view of a slotted air-magnetic hybrid thrust bearing provided in accordance with a tenth embodiment;

FIG. 33 is a schematic view of a second magnetic bearing in a groove-type aero-magnetic hybrid thrust bearing according to a tenth embodiment;

FIG. 34 is a schematic view showing the structure of a second magnetic bearing seat in a groove type air-magnetic hybrid thrust bearing according to the tenth embodiment;

Fig. 35 is one of schematic structural views of a groove-type air-magnetic hybrid thrust bearing in which a second dynamic pressure generating groove is provided on a second thrust disk according to the tenth embodiment;

fig. 36 is a second schematic view of a structure in which a second dynamic pressure generating groove is provided on a second thrust disk in a groove type air-magnetic hybrid thrust bearing according to the tenth embodiment;

fig. 37 is one of schematic structural views of a groove-type air-magnetic hybrid thrust bearing provided in the tenth embodiment in which a second dynamic pressure generating groove is provided on a first pressure ring;

fig. 38 is a second schematic view of a structure in which a second dynamic pressure generating groove is provided in a first pressure ring in a groove type air-magnetic hybrid thrust bearing according to the tenth embodiment;

FIG. 39 is a cross-sectional view of a foil type hybrid gas-magnetic radial bearing provided in accordance with an eleventh embodiment;

FIG. 40 is an external view of a foil type hybrid gas-magnetic radial bearing provided in accordance with an eleventh embodiment;

FIG. 41 is a schematic view showing the structure of a third magnetic bearing seat in a foil type air-magnetic hybrid radial bearing according to an eleventh embodiment;

FIG. 42 is a schematic structural diagram of a fourth foil with strip-shaped magnetic material distributed thereon in a foil-type hybrid gas-magnetic radial bearing according to an eleventh embodiment;

FIG. 43 is a schematic structural diagram of a fourth foil with dot magnetic material distributed thereon in a foil-type hybrid gas-magnetic radial bearing according to an eleventh embodiment;

FIG. 44 is an enlarged schematic view of portion A of FIG. 39;

FIG. 45 is a half cross-sectional view of a groove type air-magnetic hybrid radial bearing provided in accordance with a twelfth embodiment;

FIG. 46 is a half cross-sectional view of another groove type air-magnetic hybrid radial bearing provided in accordance with the twelfth embodiment;

FIG. 47 is an external view of a groove-type air-magnetic hybrid radial bearing provided in accordance with a twelfth embodiment;

FIG. 48 is a schematic structural view of a fourth magnetic bearing in a groove-type air-magnetic hybrid radial bearing according to the twelfth embodiment;

FIG. 49 is a schematic view showing the structure of a fourth magnetic bearing seat in a groove-type air-magnetic hybrid radial bearing according to the twelfth embodiment;

FIG. 50 is a schematic diagram of a third dynamic pressure generating groove formed in a second bearing sleeve in a groove type air-magnetic hybrid radial bearing according to a twelfth embodiment;

FIG. 51 is a second schematic view of a third dynamic pressure generating groove provided on a second bearing sleeve in a groove type air-magnetic hybrid radial bearing according to the twelfth embodiment;

fig. 52 is a schematic structural view of a third dynamic pressure generating groove provided on a rotating shaft in a groove type air-magnetic hybrid radial bearing according to the twelfth embodiment;

fig. 53 to 68 are schematic structural views of a rotor system using an integrated bearing corresponding to fig. 1 to 18;

FIG. 69 is a cross-sectional view of an integrated bearing according to thirteenth embodiment;

FIG. 70 is a cross-sectional view taken along the direction A-A in FIG. 69;

FIG. 71 is a cross-sectional view taken in the direction B-B of FIG. 69;

fig. 72 is one of schematic structural views of an integrated bearing provided in the thirteenth embodiment in which a fifth dynamic pressure generating groove is provided on a third bearing sleeve;

fig. 73 is a second schematic view showing a structure in which a fifth dynamic pressure generating groove is provided in a third bearing sleeve in the integrated bearing according to the thirteenth embodiment;

fig. 74 is a schematic view showing a structure in which a fifth dynamic pressure generating groove is provided on a rotating shaft in an integrated bearing according to thirteenth embodiment;

fig. 75 is one of schematic structural views of an integrated bearing provided in the thirteenth embodiment in which sixth dynamic pressure generating grooves are provided on a third thrust plate;

fig. 76 is a second schematic view showing a structure in which sixth dynamic pressure generating grooves are provided on a third thrust plate in the integrated bearing according to the thirteenth embodiment;

fig. 77 is one of schematic structural views of an integrated bearing provided in an eleventh embodiment in which sixth dynamic pressure generating grooves are provided on a fifth stator;

fig. 78 is a second schematic view showing a structure in which a sixth dynamic pressure generating groove is provided in a fifth stator in the integrated bearing provided in the eleventh embodiment.

Detailed Description

The following description of the embodiments of the present invention will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are some, but not all embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.

An embodiment of the present invention provides a rotor system including:

the rotating shaft is of an integral structure, and is vertically arranged;

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

With the increase of the rotation speed of the rotor, the contact bearing cannot meet the requirement of the rotor with high rotation speed due to larger mechanical abrasion. Therefore, in the embodiment of the invention, in order to adapt to the development requirement of high-speed rotation of the rotor, the thrust bearing and the radial bearing can adopt non-contact bearings.

In the embodiment of the invention, the shaft body of the rotating shaft is of an integrated structure, which is understood to be a whole shaft, or the shaft body of the rotating shaft is formed by rigidly connecting a plurality of shaft sections. Because the shaft body of the rotating shaft is of an integrated structure, the strength of the shaft body at all positions on the rotating shaft is consistent, and the setting position of the thrust bearing on the rotating shaft is not limited.

In the embodiment of the invention, the shaft body of the rotating shaft is of an integrated structure, so that the gas turbine rotor and the motor rotor are connected by adopting the coupler in the prior art. Compared with the prior art, the strength of the shaft body at all positions on the rotating shaft is consistent, so that the setting position of the thrust bearing on the rotating shaft is not limited.

Further, the thrust bearing is disposed at a predetermined position on a side of the turbine adjacent to the compressor, the predetermined position being a position at which a center of gravity of the rotor system can be located between two radial bearings farthest from each other among the at least two radial bearings.

In the embodiment of the invention, the setting positions of the thrust bearings can be flexibly adjusted according to the setting number of the radial bearings of the at least two radial bearings, the setting position of each radial bearing, the mass of each component in the whole rotor system (including the mass of the thrust bearing itself) and other parameters, so that the gravity center of the whole rotor system is positioned between the two radial bearings farthest from each other, and preferably, the gravity center of the whole rotor system is positioned on the compressor.

In the embodiment of the present invention, the rotation shaft is 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 can be applied to a vertical unit that needs to use a vertical rotor system, for example, a vertical gas turbine generator set that will be specifically described below.

The thrust bearing and the radial bearing are non-contact bearings, so that the rotor system can be arranged vertically. Therefore, the gravity center of the rotor system is positioned at the axle center, static deflection is not generated, and the moment generated by gravity on the axle line is zero, so that the influence of gravity on the rotation of the rotor system can be eliminated, and the stability of the rotor system can be improved. Meanwhile, as the rotor system is arranged vertically, the gravity centers of all the components are downward, and the problems caused by a cantilever shaft type structure due to the horizontal arrangement of the rotor system can be avoided.

In order to better understand the overall technical scheme of the rotor system according to the embodiment of the present invention, a specific description of each embodiment of the rotor system provided by the embodiment of the present invention is provided below with reference to each drawing.

Example 1

As shown in fig. 1 to 3, the rotor system includes:

the rotating shaft 100, the shaft body of the rotating shaft 100 is of an integrated structure, and the rotating shaft 100 is vertically arranged;

The motor 200, the compressor 300 and the turbine 400 are sequentially arranged on the rotating shaft 100;

and a thrust bearing 500, a first radial bearing 600 and a second radial bearing 700 provided on the rotating shaft 100, the first radial bearing 600 being provided on a side of the motor 200 remote from the compressor 300, the second radial bearing 700 being provided between the compressor 300 and the turbine 400.

The thrust bearing 500 is disposed between the first radial bearing 600 and the motor 200, as shown in fig. 1; alternatively, thrust bearing 500 is disposed on a side of first radial bearing 600 remote from motor 200, as shown in fig. 2; alternatively, thrust bearing 500 is disposed between motor 200 and compressor 300, as shown in FIG. 3.

Where the mass of the turbine 400 is relatively large, for example, the turbine 400 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 600 and the second radial bearing 700.

When the mass of the turbine 400 is small, for example, the turbine 400 is made of ceramic material or ceramic fiber composite material, the embodiment shown in fig. 3 may be used to locate the center of gravity of the entire rotor system between the first radial bearing 600 and the second radial bearing 700.

It should be noted that, in the embodiment shown in fig. 3, since the thrust bearing 500 is disposed between the motor 200 and the compressor 300, in order to avoid the thrust disc of the thrust bearing 500 from blocking the air inlet of the compressor 300, the embodiment shown in fig. 3 is applicable to the thrust bearing 500 having a smaller thrust disc diameter.

Currently, non-contact bearings generally include electromagnetic bearings and air bearings. However, the electromagnetic bearing has the problems of too high energy consumption, heat generation and the like when being opened for a long time; and when the surface linear speed of the air bearing approaches or exceeds the sonic speed, shock waves can be generated, so that the bearing is unstable, and even catastrophic results such as shaft collision and the like are generated.

Therefore, in order to improve the working performance of the thrust bearing and the radial bearing, in the embodiment of the present invention, the thrust bearing 500 may be a gas-magnetic hybrid thrust bearing, and the first radial bearing 600 may be a gas-magnetic hybrid radial bearing, in consideration of the development requirement of the high rotation speed of the gas turbine or the gas turbine generator set.

In addition, the second radial bearing 700 is close to the turbine 400, and considering that the magnetic components in the magnetic bearing cannot withstand the high temperature transmitted from the turbine 400, the second radial bearing 700 may be a gas dynamic-static pressure hybrid radial bearing.

As another embodiment, the second radial bearing 700 may be a gas-magnetic hybrid radial bearing, in which the magnetic component of the second radial bearing 700 is disposed on the second radial bearing 700 in a region away from the turbine 400. That is, the area of the second radial bearing 700 near the turbine 400 is not provided with magnetic components.

To protect the magnetic components on the second radial bearing 700, this may be accomplished by reducing the heat energy radiated by the turbine 400 onto the second radial bearing 700. Specifically, a thermal barrier (not shown) is disposed on the turbine 400 on a side thereof adjacent to the second radial bearing 700. Here, the material of the insulating layer may be aerogel or other materials having good insulating properties.

Fig. 4 to 6 each show a schematic view of the second radial bearing 700 of fig. 1 to 3 in which the magnetic component is arranged in a region remote from the turbine 400.

In the embodiment of the present invention, the compressor 300 may be a centrifugal compressor 300, and the turbine 400 may be a centrifugal turbine; the bearing of the motor 200 may be a hydrodynamic bearing, and the portion of the rotating shaft 100 corresponding to the bearing of the motor 200 may be provided with a first dynamic pressure generating groove 201.

Further, the motor 200 may also be a heuristic-integrated motor.

Thus, at the initial start-up time of the rotor system, the motor 200 may be turned on in a start-up mode to rotate the rotor system, and after the rotational speed of the rotor system is increased to a preset rotational speed, the operation mode of the motor 200 may be switched to a power generation mode.

Example two

As shown in fig. 7 to 10, the rotor system includes:

and a thrust bearing 500, a first radial bearing 600, a second radial bearing 700 and a third radial bearing 800 which are disposed on the rotating shaft 100, wherein the first radial bearing 600 is disposed on one side of the motor 200 away from the compressor 300, the second radial bearing 700 is disposed between the compressor 300 and the turbine 400, and the third radial bearing 800 is disposed between the motor 200 and the compressor 300.

The thrust bearing 500 is disposed between the first radial bearing 600 and the motor 200, as shown in fig. 7; alternatively, the thrust bearing 500 is disposed on a side of the first radial bearing 600 remote from the motor 200, as shown in fig. 8; alternatively, the thrust bearing 500 is disposed between the motor 200 and the compressor 300 as shown in fig. 9 or 10.

Because the third radial bearing 800 is added, in the embodiment of the present invention, when the thrust bearing 500 is disposed between the motor 200 and the compressor 300, the thrust bearing 500 may be disposed between the motor 200 and the third radial bearing 800, as shown in fig. 9; the thrust bearing 500 may in turn be disposed between the third radial bearing 800 and the compressor 300, as shown in fig. 10.

Compared with the first embodiment, the third radial bearing 800 is added between the motor 200 and the compressor 300, so that the stability of the whole rotor system can be further improved.

In the embodiment of the present invention, the thrust bearing 500 may be a gas-magnetic hybrid thrust bearing, and the first radial bearing 600 may be a gas-magnetic hybrid radial bearing; the second radial bearing 700 is close to the turbine 400, and the second radial bearing 700 may be a gas dynamic-static pressure hybrid radial bearing in consideration of the fact that the magnetic components contained in the magnetic bearing cannot withstand the high temperature transmitted from the turbine 400.

To protect the magnetic components on the second radial bearing 700, this may be accomplished by reducing the heat energy radiated by the turbine 400 onto the second radial bearing 700. Specifically, a thermal barrier (not shown) is disposed on the turbine 400 on a side thereof adjacent to the second radial bearing 700. Here, the insulation layer may be aerogel or other material.

Fig. 11 to 14 show schematic views of the second radial bearing 700 of fig. 7 to 10, respectively, in which the magnetic components are arranged in the region remote from the turbine 400.

The rest can refer to the related description in the first embodiment and achieve the same technical effects, and in order to avoid repetition, the description of the embodiment of the present invention is omitted.

Example III

As shown in fig. 15, the rotor system includes:

and a thrust bearing 500, a first radial bearing 600, a second radial bearing 700 and a fourth radial bearing 900 which are disposed on the rotating shaft 100, wherein the first radial bearing 600 is disposed on one side of the motor 200 away from the compressor 300, the second radial bearing 700 is disposed between the compressor 300 and the turbine 400, the fourth radial bearing 900 is disposed on one side of the turbine 400 away from the compressor 300, and the thrust bearing 500 is disposed between the compressor 300 and the second radial bearing 700.

The embodiment of the present invention can be applied to the case that the mass of the motor 200 is excessively large, and when the mass of the motor 200 is excessively large, radial bearings (i.e., the first radial bearing 600 and the fourth radial bearing 900) are required to be provided at both ends of the rotor system in order to maintain the stability of the rotor system, and the thrust bearing 500 is required to move toward one side of the turbine 400.

In view of the high temperature of the turbine 400, when the thrust bearing 500 is a gas-magnetic hybrid thrust bearing, the thrust bearing 500 may be disposed between the compressor 300 and the second radial bearing 700 because the magnetic components in the magnetic bearing cannot withstand the high temperature transmitted from the turbine 400. Accordingly, the second radial bearing 700 may be a hybrid gas-dynamic-pressure radial bearing.

Generally, the temperature of the turbine 400 on the side near the fourth radial bearing 900 is higher than the temperature of the turbine 400 on the side near the second radial bearing 700, and therefore, the fourth radial bearing 900 is preferably a hybrid aerostatic radial bearing.

FIG. 16 shows a schematic view of the second radial bearing 700 of FIG. 15 with magnetic components disposed in a region remote from the turbine 400.

It should be noted that, when the mass of the motor 200 is not too large, the thrust bearing 500 may be disposed between the first radial bearing 600 and the motor 200; alternatively, the thrust bearing 500 may be disposed at a side of the first radial bearing 600 remote from the motor 200; alternatively, the thrust bearing 500 may be disposed between the motor 200 and the compressor 300. This will not be described in detail, as it will be readily appreciated.

Example IV

As shown in fig. 17, the rotor system includes:

and a thrust bearing 500, a first radial bearing 600, a second radial bearing 700, a third radial bearing 800 and a fourth radial bearing 900 which are disposed on the rotating shaft 100, wherein the first radial bearing 600 is disposed on one side of the motor 200 far from the compressor 300, the second radial bearing 700 is disposed between the compressor 300 and the turbine 400, the third radial bearing 800 is disposed between the motor 200 and the compressor 300, the fourth radial bearing 900 is disposed on one side of the turbine 400 far from the compressor 300, and the thrust bearing 500 is disposed between the compressor 300 and the second radial bearing 700.

In the third embodiment of the present invention, a third radial bearing 800 is added between the motor 200 and the compressor 300 to further improve the stability of the whole rotor system.

In the embodiment of the present invention, the thrust bearing 500 may be a gas-magnetic hybrid thrust bearing, and the second radial bearing 700 and the fourth radial bearing 900 may be gas dynamic-static hybrid radial bearings.

FIG. 18 shows a schematic view of the second radial bearing 700 of FIG. 17 with magnetic components disposed in a region remote from the turbine 400.

The rest can refer to the related description in the third embodiment and achieve the same technical effects, and in order to avoid repetition, the embodiment of the present invention will not be described in detail.

Example five

When the rotor system is used on mobile equipment, such as an extended range electric automobile, the rotating shaft is in direct contact with the bearing under the condition that the rotor system does not work. During running of the automobile, the rotating shaft moves radially or axially relative to the bearing due to jolt or vibration, so that abrasion is generated between the rotating shaft and the bearing, and the precision and the service life of the bearing are further affected.

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

In the embodiment of the present invention, the structure and the arrangement manner of the locking device are not unique, and for convenience of understanding, two embodiments are specifically described below with reference to the accompanying drawings.

In one embodiment, as shown in fig. 19, the locking device 110 includes a telescopic propping unit 111, a connecting rod 112 and a fixing member 113, one end of the connecting rod 112 is connected with the fixing member 113, the other end is connected with the telescopic propping unit 111, the telescopic propping unit 111 faces an end face of one end, far away from the turbine 400, of the rotating shaft 100, and the other end of the fixing member 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 110 acts and pushes the rotating shaft 100 in the axial direction of the rotating shaft 100, so that the stator of the thrust bearing 500 contacts with the thrust disc, thereby axially fixing the rotating shaft 100, and simultaneously radially fixing the rotating shaft 100 by using the friction force between the stator of the thrust bearing 500 and the thrust disc.

Further, the telescopic jacking unit 111 is provided with a jacking portion (not shown in the figure), and an end surface of the rotating shaft 100 at an end far from the turbine 400 is provided with a jacking hole (not shown in the figure). In the locked state, the tip portion is pushed into the tip hole of the rotating shaft 100, so that the rotating shaft 100 can be better fixed, and abrasion and damage to the rotating shaft 100 and the bearing in the running process of the vehicle are prevented.

In another embodiment, as shown in fig. 20 to 21, the locking device 120 may be configured as a locking device of a ferrule structure. Specifically, locking device 120 includes a telescoping unit 121 and a ferrule 122, ferrule 122 being connected to the telescoping end of telescoping unit 122. Ferrule 122 may be a semi-circular ferrule having a radius equal to or slightly greater than the radius of shaft 100, with the axis of ferrule 122 disposed parallel to the axis of shaft 100, and telescoping unit 121 mounted to a generally axially intermediate position of shaft 100 and fixedly connected to the housing in which the rotor system of the present application is mounted.

When the rotor system is stopped, the telescopic unit 121 is extended, so that the clamping sleeve 122 clamps the rotating shaft 100 and pushes the rotating shaft 100 into contact with the radial bearing, thereby radially fixing the rotating shaft 100, and simultaneously 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 select a piston cylinder or a hydraulic cylinder, etc. capable of realizing telescopic control.

In this embodiment, the location of the locking device 120 on the rotating shaft 100 may not be limited, and preferably, the locking device 120 is disposed between the farthest two radial bearings in the rotor system.

It should be noted that the locking devices in fig. 19 and 20 are both based on the rotor system shown in fig. 1, and the locking devices are not described in detail herein for the rotor system according to other embodiments of the present invention.

In the embodiment of the invention, the locking device is arranged, so that the locking device can lock the rotating shaft when the rotor system does not work. In this way, the movement of the rotating shaft in the radial direction or the axial direction relative to the bearing can be prevented, and the accuracy and the service life of the bearing can be improved.

Example six

Therefore, in order to solve the above-mentioned problems, on the basis of other embodiments of the present invention, the rotor system of the embodiment of the present invention is coated with an anti-wear coating 101 at the bearing-mounting portion of the rotating shaft 100, as shown in fig. 22.

The abrasion-proof coating 101 is coated on the bearing-mounting part of the rotating shaft 100, so that the abrasion of the rotating shaft 100 and the bearing can be effectively prevented. The wear-resistant coating 101 is preferably made of a material having chemical stability, corrosion resistance, high lubrication non-tackiness, and good aging resistance, such as polytetrafluoroethylene.

Any of the above-described rotor systems according to the first to sixth embodiments may be applied to a horizontal gas turbine generator set, and in particular, to a horizontal micro gas turbine generator set, and a specific description will be given below with reference to an example in which the rotor system is applied to the horizontal gas turbine generator set.

Example seven

As shown in fig. 23, an embodiment of the present invention provides a gas turbine generator set, which includes a housing 310, an air inlet 320, and a combustion chamber 330, and any of the rotor systems of the first to sixth embodiments, wherein the rotor system includes a rotating shaft 100, a motor 200, a compressor 300, a turbine 400, and thrust bearings and radial bearings (not shown) disposed on the rotating shaft 100. The air inlet 320 is communicated with an air inlet of the air compressor 300, an air outlet of the air 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 400.

Wherein the compressor 300 may be a centrifugal compressor 300 and the turbine 400 may be a centrifugal turbine; the bearing of the motor 200 may be a hydrodynamic bearing, and the portion of the rotating shaft 100 corresponding to the bearing of the motor 200 may be provided with a first dynamic pressure generating groove 201; the combustion chamber 330 may be an annular combustion chamber.

Alternatively, air scoop 320 is formed by a housing of electric machine 200 and housing 310 of a gas turbine generator set. Thus, when air enters the compressor 300 through the air inlet 320, the air flows through the casing of the motor 200, and can cool the motor 200.

Optionally, motor 200 is a heuristic motor.

The operation of the gas turbine generator set is described in detail below.

As previously indicated, 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 thrust bearing or a hybrid gas-dynamic-static pressure radial bearing. For convenience of description, a bearing that can perform lubrication without rotation of the rotating shaft 100 is defined as a hydrostatic bearing, and a bearing that can be operated when the rotating shaft 100 rotates to a certain speed is defined as a hydrodynamic bearing. According to the logic, the magnetic bearing and the aerostatic bearing in the aeromagnetic hybrid thrust bearing and the aerostatic bearing in the aerostatic hybrid radial bearing can be called as hydrostatic bearings; the aerodynamic bearing in the aerodynamic-magnetic hybrid thrust bearing and the aerodynamic bearing in the aerodynamic-static hybrid radial bearing can be called dynamic pressure bearings.

As shown in fig. 24, an embodiment of the present invention provides a control method of a gas turbine generator set, including:

s11, opening the hydrostatic bearings in the radial bearing and the thrust bearing, so that the rotating shaft moves to a preset radial position, and the thrust disc of the thrust bearing moves to a preset axial position.

Wherein, open hydrostatic bearing includes: the magnetic bearings in the bearings are turned on and/or gas is delivered to the static pressure intake orifice in the bearings.

S12, starting a gas turbine generator set, and enabling air to enter a combustion chamber and fuel in the combustion chamber for mixed combustion after being compressed by a gas compressor; the high-temperature and high-pressure gas exhausted from the combustion chamber impacts the turbine of the turbine, so that the turbine rotates, 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 a motor as an example of a heuristic integrated motor.

After receiving the start signal, the gas turbine controller (Electronic Control Unit, ECU for short) sends a motor driving mode command to the motor power controller (Data Processing Center, DPC for short); DPC is switched to a motor driving mode, the DPC carries out frequency conversion on direct current of a built-in battery of the gas turbine, the motor is driven to work, and the motor drives the gas turbine to increase the rotating speed.

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

After the gas turbine reaches the self-sustaining speed, DPC is hung, the motor idles to continue to increase the accelerator, and the turbine continues to increase the power, so that the speed is increased to the working speed. The ECU sends a generator mode instruction to the DPC; 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 centrifugal compressor comprises movable blades and stationary blades which are circumferentially arranged, and the stationary blades are diffusers. Thus, the specific process of air entering the compressor from the air inlet channel for compression can be as follows: after entering the blades of the centrifugal compressor, the air enters the diffuser (i.e. the stator blades) arranged along the circumferential direction to be compressed continuously.

The turbine is a centrifugal turbine, and the centrifugal turbine is provided with movable blades. The combustor outlet is circumferentially arranged with vanes, which are nozzles. In this way, the high-temperature and high-pressure gas after the combustion chamber is fully combusted enters the turbine to apply work, so that the specific process of rotating the turbine of the turbine can be as follows: the high-temperature and high-pressure gas after being fully combusted in the combustion chamber is expanded and accelerated through nozzles (i.e., stationary blades) arranged along the circumferential direction at the outlet of the combustion chamber, and then impacts the movable blades of the turbine, so that the turbine rotates.

S13, after the rotating speed of the rotating shaft is accelerated to the working rotating speed, closing the hydrostatic bearings 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 inlet orifice in the bearings.

And S14, when the gas turbine generator set is stopped, starting the hydrostatic bearings in the radial bearings and the hydrostatic bearings in the thrust bearings.

S15, after the rotating speed of the rotating shaft is reduced to zero, closing the hydrostatic bearings in the radial bearing and the thrust bearing.

In the process, the bearings in the rotor system are controlled to enable the hydrostatic bearings in the radial bearings and the thrust bearings to be opened until the rotating speed of the rotating shaft reaches the working rotating speed.

When the gas turbine generator set is stopped, the bearings in the rotor system are controlled, so that the hydrostatic bearings in the radial bearings and the thrust bearings are always started until the rotating speed of the rotating shaft is zero.

As shown in fig. 25, an embodiment of the present invention provides another control method of a gas turbine generator set, including:

s21, opening the hydrostatic bearings in the radial bearing and the thrust bearing so that the rotating shaft moves to a preset radial position, and enabling the thrust disc of the thrust bearing to move to a preset axial position.

S22, starting the gas turbine generator set, and enabling air to enter a combustion chamber and fuel in the combustion chamber for mixed combustion after being compressed by a gas compressor; the high-temperature and high-pressure gas exhausted from the combustion chamber impacts the turbine of the turbine, so that the turbine rotates, and the turbine drives the motor to rotate through the rotating shaft to generate power.

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.

The first preset value may be 5% to 30% of the rated rotational speed.

Wherein, close hydrostatic bearing, include: closing the magnetic bearings in the bearings and/or stopping the delivery of gas to the static pressure inlet orifice in the bearings.

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

S25, after the rotor system steadily passes the first-order critical speed or the second-order critical speed, closing the hydrostatic bearings in the radial bearings and the thrust bearings.

And S26, in the process of the gas turbine generator set, when the rotor system is decelerated to a first-order critical speed or a second-order critical speed, the hydrostatic bearings in the radial bearings and the thrust bearings are started.

And S27, closing the hydrostatic bearings in the radial bearing and the thrust bearing after the rotor system steadily 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, starting the hydrostatic bearings in the radial bearings and the hydrostatic bearings in the thrust bearings.

The second preset value may be equal to or different from the first preset value, and the second preset value may be 5% to 30% of the rated rotation speed.

S29, after the rotating speed of the rotating shaft is reduced to zero, closing the hydrostatic bearings in the radial bearing and the thrust bearing.

In the process, before the gas turbine generator set is started, the bearings in the rotor system are controlled to enable the hydrostatic bearings of the radial bearings and the thrust bearings to be started. In this way, the rotating shaft is supported to a preset radial position under the action of the 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, 5-30% of the rated rotating speed, the bearings in the rotor system are controlled, so that the hydrostatic bearings in the radial bearings and the thrust bearings 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 to restart the hydrostatic bearings of the radial bearings and the thrust bearings. After the rotating speed of the rotating shaft steadily passes the first-order critical speed or the second-order critical speed, the bearings in the rotor system are controlled, so that the hydrostatic bearings in the radial bearings and the thrust bearings stop working again.

In the shutdown process of the gas turbine generator set, the rotating speed of the rotating shaft gradually decreases, and when the rotating speed of the rotating shaft reaches a second-order critical speed or a first-order critical speed, the bearings in the rotor system are controlled, so that the hydrostatic bearings of the radial bearings and the thrust bearings are opened again. After the rotating speed of the rotating shaft steadily passes the second-order critical speed or the first-order critical speed, the bearings in the rotor system are controlled, so that the hydrostatic bearings in the radial bearings and the thrust bearings stop working again. When the rotation speed of the rotating shaft is reduced to a preset value, for example, 5-30% of the rated rotation speed, the bearings in the rotor system are controlled, so that the hydrostatic bearings of the radial bearings and the thrust bearings are opened again until the rotation speed is reduced to zero, and the bearings in the rotor system are controlled, so that the hydrostatic bearings in the radial bearings and the thrust bearings stop working again.

The control method of the rotor system will be specifically described based on the control method of the gas turbine generator set.

Example eight

As shown in fig. 26, an embodiment of the present invention provides a control method of a rotor system, including:

s101, opening the hydrostatic bearings in the radial bearing and the thrust bearing so as to enable the rotating shaft to move to a preset radial position and enable the thrust disc of the thrust bearing to move to a preset axial position.

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

And S103, when the rotor system is stopped, opening the hydrostatic bearings in the radial bearings and the hydrostatic bearings in the thrust bearings.

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

In the process, before the rotor system is started, the bearings in the rotor system are controlled to enable the hydrostatic bearings of the radial bearings and the thrust bearings to be started. In this way, the rotating shaft is supported to a preset radial position under the action of the 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. The hydrostatic bearings in the radial bearing and the thrust bearing are always opened until the rotating speed of the rotating shaft reaches the working rotating speed.

When the rotor system is stopped, the bearings in the rotor system are controlled, so that the hydrostatic bearings in the radial bearings and the thrust bearings are always started until the rotating speed of the rotating shaft is zero.

As shown in fig. 27, an embodiment of the present invention provides another control method of a rotor system, including:

s201, opening the hydrostatic bearings in the radial bearing and the thrust bearing, so that the rotating shaft moves to a preset radial position, and the thrust disc of the thrust bearing moves to a preset axial position.

Wherein, open hydrostatic bearing, include: the magnetic bearings in the bearings are turned on and/or gas is delivered to the static pressure intake orifice in the bearings.

S202, 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.

The first preset value may be 5% to 30% of the rated rotational speed.

S203, when the rotor system accelerates to the first-order critical speed or the second-order critical speed, the hydrostatic bearings in the radial bearings and the thrust bearings are started.

S204, after the rotor system steadily passes the first-order critical speed or the second-order critical speed, closing the hydrostatic bearings in the radial bearings and the thrust bearings.

S205, when the rotor system is decelerated to a first-order critical speed or a second-order critical speed, the hydrostatic bearings in the radial bearings and the thrust bearings are started.

S206, after the rotor system steadily passes the first-order critical speed or the second-order critical speed, closing the hydrostatic bearings in the radial bearings and the thrust bearings.

S207, when the rotating speed of the rotating shaft is reduced to a second preset value, the hydrostatic bearings in the radial bearings and the hydrostatic bearings in the thrust bearings are started.

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

In the process, before the rotor system is started, the bearings in the rotor system are controlled to enable the hydrostatic bearings of the radial bearings and the thrust bearings to be started. In this way, the rotating shaft is supported to a preset radial position under the action of the 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, 5-30% of the rated rotating speed, the bearings in the rotor system are controlled to stop the static pressure bearings in the radial bearings and the thrust bearings. 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 to restart the hydrostatic bearings of the radial bearings and the thrust bearings. After the rotating speed of the rotating shaft steadily passes the first-order critical speed or the second-order critical speed, the bearings in the rotor system are controlled, so that the hydrostatic bearings in the radial bearings and the thrust bearings stop working again.

In the shutdown process of the rotor system, the rotating speed of the rotating shaft gradually decreases, and when the rotating speed of the rotating shaft reaches a second-order critical speed or a first-order critical speed, the bearings in the rotor system are controlled to enable the hydrostatic bearings of the radial bearings and the thrust bearings to be opened again. After the rotating speed of the rotating shaft steadily passes the second-order critical speed or the first-order critical speed, the bearings in the rotor system are controlled, so that the hydrostatic bearings in the radial bearings and the thrust bearings stop working again. When the rotation speed of the rotating shaft is reduced to a preset value, for example, 5-30% of the rated rotation speed, the bearings in the rotor system are controlled, so that the hydrostatic bearings of the radial bearings and the thrust bearings are opened again until the rotation speed is reduced to zero, and the bearings in the rotor system are controlled, so that the hydrostatic bearings in the radial bearings and the thrust bearings stop working again.

In view of the foregoing, it is apparent that the overall structure of the rotor system, the overall structure of the gas turbine generator set using the rotor system, the control method of the gas turbine generator set, and the control method of the rotor system provided in the embodiments of the present invention are described.

It should be noted that the thrust bearing and the radial bearing in the rotor system may take various configurations. For the aero-magnetic hybrid thrust bearing, a foil type aero-magnetic hybrid thrust bearing or a slot type aero-magnetic hybrid thrust bearing can be included; for the aero-magnetic hybrid radial bearing, a foil aero-magnetic hybrid radial bearing or a groove aero-magnetic hybrid radial bearing may be included.

Various specific configurations of thrust bearings and radial bearings in the rotor system, and specific control procedures for each thrust bearing and each radial bearing in the overall rotor system control, are described in detail below with reference to the accompanying drawings.

Example nine

Fig. 28 to 31 are schematic structural views of a foil type air-magnetic hybrid thrust bearing according to an embodiment of the present invention.

As shown in fig. 28 to 31, the foil type air-magnetic hybrid thrust bearing 5100 includes:

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

and, a first stator 5102 and a second stator 5103 penetrating through the rotating shaft 100, wherein the first stator 5102 and the second stator 5103 are respectively arranged at two opposite sides of the first thrust plate 5101;

each of the first stator 5102 and the second stator 5103 includes a first magnetic bearing 5104 and a first foil bearing 5105, a plurality of first magnetic members are provided on the first magnetic bearing 5104 in a circumferential direction, and the first foil bearing 5105 is provided with a second magnetic member capable of generating magnetic force with the plurality of first magnetic members;

the first foil bearing 5105 is disposed between the first magnetic bearing 5104 and the first thrust plate 5101, and has a first gap 5106 with the first thrust plate 5101, and the first foil bearing 5105 can move in the axial direction of the rotating shaft 100 under the action of magnetic force between the first magnetic component and the second magnetic component.

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

When in operation, the gas bearing in the thrust bearing 5100 can work cooperatively with the first magnetic bearing 5104, and when the thrust bearing 5100 is in a stable working state, the support is realized by the gas bearing; while the thrust bearing 5100 is in an unstable operating state, the thrust bearing 5100 is controlled and responded to 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 high-rotation-speed rotor system, such as a gas turbine or a gas turbine power generation combined set.

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 unit, the first stator 5102 and the second stator 5103 may be connected with a housing of the gas turbine through a connection member.

Optionally, the plurality of first magnetic components includes a plurality of first permanent magnets disposed circumferentially 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, each of the plurality of first electromagnets including 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 type air-magnetic hybrid thrust bearing 5100 only needs the magnetic component to provide magnetic force without magnetic control, the first magnetic component preferably selects the first permanent magnet; when the foil type air-magnetic hybrid thrust bearing 5100 requires both magnetic force and magnetic control, the first magnetic component 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 supplied to 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 current flowing through the first coil 51042 is different, and the magnetic poles of the first core 51041 are 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 characteristics of high magnetic permeability, low eddy current loss, etc.

Optionally, the first magnetic bearing 5104 includes:

the first magnetic bearing seat 51043, the first magnetic bearing seat 51043 is opposite to the first thrust disc 5101, a plurality of first accommodating grooves 51044 are formed in the first magnetic bearing seat 51043 along the circumferential direction, a plurality of first magnetic components are arranged in the plurality of first accommodating grooves 51044, and magnetic poles of the plurality of first magnetic components face to one side where the first foil bearing 5105 is located;

the first end cap 51045, the first end cap 51045 is disposed on a side of the first magnetic bearing block 51043 remote from the first foil bearing 5105, and cooperates with the first foil bearing 5105 to secure the first magnetic component to the first magnetic bearing block 51043.

In the preferred embodiment of the present invention, the first magnetic bearing seat 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 characteristics of high magnetic permeability, low eddy current loss, etc. The number of the first receiving grooves 51044 may be, but is not limited to, six or eight, and are uniformly disposed along the circumferential direction of the first magnetic bearing mount 51043. In this way, the magnetic force between the first magnetic bearing block 51043 and the first foil bearing 5105 can be more uniform and stable. The plurality of first magnetic members may be provided on the first magnetic bearing seat 51043 in other manners, which is not limited thereto. 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;

and a first foil 51052 and a second foil 51053 disposed on the first foil bearing support 51051, the first foil 51052 being mounted on the first foil bearing support 51051, the second foil 51053 being stacked on a side of the first foil 51052 adjacent to the first thrust plate 5101;

wherein 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 of the first magnetic component and the second magnetic component; the first foil 51052 is an elastically deformable foil capable of being elastically deformed when the second foil 51053 is moved.

The material of the first foil bearing seat 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 strip that is not magnetically permeable, because the magnetically permeable material is hard and brittle and is not suitable as an elastically deformable foil.

In the embodiment of the present invention, by setting the second foil 51053 as a flat foil, it is convenient to control the distance between the second foil 51053 and the first thrust plate 5101, or, in other words, to control the size of the first gap 5106. The first foil 51052 adopts a foil capable of elastically deforming, so that on one hand, the function of connecting the second foil 51053 and the first foil bearing seat 51051 is achieved, and on the other hand, the purpose that the second foil 51053 can move relative to the first foil bearing seat 51051 along the axial direction of the rotating shaft 100 can be achieved.

Optionally, the first foil 51052 is an elastically deformable foil in a wavy shape, and the first foil 51052 is in an unsealed 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;

wherein, when the second foil 51053 moves in the axial direction of the rotating shaft 100, the corrugations on the first foil 51052 expand or contract, and the movable end moves along the circumferential direction of the ring shape.

In the embodiment of the present invention, by providing the first foil 51052 as a waved elastically deformable foil, the second foil 51053 is pushed to move in the axial direction of the rotating shaft 100 by utilizing the stretching or shrinking characteristics of the waved patterns.

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 suitable for the first foil 51052 in the embodiment of the present invention.

Optionally, the second magnetic component comprises a first magnetic material disposed on a side surface of the second foil 51053 proximate 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 parts, and the plurality of strip-shaped magnetic parts are radial or annular;

Alternatively, the first magnetic means are distributed in a spot on the second foil 51053.

The material of the second foil 51053 is preferably a non-magnetic material, and after the surface of the second foil 51053 is covered with the first magnetic material, 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 completely covers the first magnetic material, magnetic force generated between the first magnetic material and the first magnetic component is greatly increased, which easily causes deformation of the second foil 51053. In view of this, in the embodiment of the present invention, by spraying the first magnetic material on the surface of the second foil 51053, the first magnetic material is distributed in a stripe shape or a dot shape on the second foil 51053, so that the magnetic force generated between the first magnetic material and the first magnetic component can be controlled within a reasonable range, thereby avoiding the deformation of the second foil 51053 due to the excessive magnetic force.

Optionally, the foil-type 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 first gap 5106.

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

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 the first magnetic bearing 5104, and through holes for the first sensor probe 51072 to pass through are provided on 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 in the first magnetic bearing 5104 and the first foil bearing 5105 and extends to the first gap 5106, and the second end of the first sensor probe 51072 is flush with the side of the first foil bearing 5105 adjacent to the first thrust plate 5101.

In the embodiment of the present invention, the first sensor 5107 can be more stably disposed on the first magnetic bearing 5104 by the structural form and the mounting manner of the first sensor 5107. The second end part of the first sensor probe 51072 is flush with one side of the first foil bearing 5105, which is 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 the first sensor probe 51072 can be protected; on the other hand, the air film in the first gap 5106 is not affected, and disturbance of the air film in the first gap 5106 is avoided.

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

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

Optionally, the first sensor 5107 is a combination of any one or more of:

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

a pressure sensor for detecting the gas film pressure at the first gap 5106;

a speed sensor for detecting the rotational speed of the first thrust disc 5101;

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

The following describes in detail a specific control method when the foil type air-magnetic hybrid thrust bearing (wherein the first magnetic component in the first magnetic bearing is an electromagnet) participates in the control process of the rotor system according to the embodiment of the present invention.

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

s511, opening the first magnetic bearings 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 first magnetic components so that a first gap between the first thrust disc and the first foil bearing in the first stator is equal to a first gap between the first thrust disc and the first foil bearing in the second stator.

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

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

S514, after the rotating speed of the rotating shaft is reduced to zero, the first magnetic bearings in the first stator and the second stator are closed.

In the above process, after the first magnetic bearing is opened, the first thrust disc reaches a predetermined position between the first stator and the second stator under the action of the first magnetic bearing, and the first thrust disc and the end surfaces of the first stator and the second stator have first gaps.

With the rotation of the rotating shaft, the first thrust disc starts to rotate relative to the first stator and the second stator under the condition of being lubricated by the air flow in the first gap so as to prevent abrasion. The specific process for opening the first magnetic bearing is as follows: a current signal of a predetermined value is input to the first coil, and the first thrust disk reaches a predetermined position between the first stator and the second stator by the first magnetic bearing.

Along with the increasing of the rotating speed of the rotating shaft, the rotating speed of the first thrust disc is synchronously increased, and when the rotating speed of the rotating shaft reaches the working rotating speed, the air film pressure generated by the air dynamic bearing of the thrust bearing (the air dynamic bearing forming the thrust bearing by arranging a first gap between the first thrust disc and the first stator and between the first stator and the second stator) can stabilize the first thrust disc, and then the first magnetic bearing can be closed.

When the rotor system is stopped, 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 is stopped, and the first magnetic bearing can be closed until the first thrust disc is completely stopped.

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

s521, opening the first magnetic bearings in the first stator and the second stator, and controlling the first thrust disk to move in the axial direction of the rotating shaft under the action of the magnetic force of the first magnetic components so that a first gap between the first thrust disk and the first foil bearing in the first stator is equal to a first gap between the first thrust disk and the first foil bearing in the second stator.

S522, after the rotating speed of the rotating shaft is accelerated to a first preset value, the first magnetic bearings in the first stator and the second stator are closed.

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

S524, after the rotating speed of the rotating shaft is reduced to zero, the first magnetic bearings in the first stator and the second stator are closed.

With the increasing rotation speed of the rotating shaft, the rotation speed of the first thrust disc is synchronously increased, and when the rotation speed of the rotating shaft reaches a first preset value, for example, 5-30% of the rated rotation speed, the air film pressure generated by the air dynamic bearing of the thrust bearing (the air dynamic bearing forming the foil type air magnetic hybrid thrust bearing is formed by arranging a first gap between the first thrust disc and the first stator and between the first stator and the second stator) can stabilize the first thrust disc, and then the first magnetic bearing can be closed.

During the shutdown of the rotor system, the first thrust disk is decelerated 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 air dynamic pressure bearing of the thrust bearing is also reduced along with the deceleration of the first thrust disk, so that the first magnetic bearing needs to be started to keep the first thrust disk stable, and the first magnetic bearing can be closed until the first thrust disk is completely stopped.

Optionally, the method further comprises:

when the 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 first gap between the first thrust disc and a first foil bearing in the first stator is not equal to a first gap between the first thrust disc and a first foil bearing in the second stator, the first magnetic bearings in the first stator and the second stator are opened;

When a load is placed on the first thrust disc, such that the first 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 of the 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 involved. The first magnetic bearing does not completely and directly act on the first thrust disk to enable the first magnetic bearing to move towards the first foil bearing on the other side, but uses magnetic force to move the first foil bearing on the other side towards a direction away from the first thrust disk to enable a first gap between the first thrust disk and the first foil bearing on the other side to be improved, so that the pressure on the side where the first gap is reduced is improved, the load weight on the first thrust disk is adapted, and the air flow pressure on the two first gaps is automatically redistributed. When the first thrust disc reaches a new equilibrium position, the first magnetic bearing stops working.

Specifically, if the first gap between the first thrust disc and the first foil bearing in the first stator is smaller than the first 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 forces between the plurality of first magnetic components and the second magnetic component.

And if the first gap between the first thrust disc and the first foil bearing in the second stator is smaller than the first 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 magnetic force between the plurality of first magnetic components and the second magnetic component.

Optionally, when the load is applied to the first thrust disc, the first thrust disc moves in the axial direction of the rotating shaft under the load, and the first gap between the first thrust disc and the first foil bearing in the first stator is not equal to the first gap between the first thrust disc and the first foil bearing in the second stator, the first magnetic bearing in the first stator and the second stator is turned on, including:

When the 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 first gap between the first thrust disc and a first foil bearing in the first stator is not equal to a first gap between the first thrust disc and a first foil bearing in the second stator, the first magnetic bearings in the first stator and the second stator are controlled to be opened at maximum power; or,

when the 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 the first gap between the first thrust disc and the first foil bearing in the first stator is not equal to the first gap between the first thrust disc and the first foil bearing in the second stator, the first magnetic bearings in the first stator and the second stator are controlled to be opened in a stroboscopic manner according to a preset frequency.

When external impact disturbance occurs, the first thrust disc may quickly approach a first foil bearing on a certain side, which may cause the first gap on the certain side to be excessively small instantaneously, so that the local gas flow velocity at the first gap on the certain side approaches or even reaches the sonic velocity, and the shock wave is triggered to generate the air hammer self-excitation phenomenon. The generation of shock waves causes local gas flow disturbances and upsets, with a significant step drop in pressure as the fluid velocity changes between sonic to subsonic. In this case, the side first foil bearing is required to actively "dodge" the first thrust disc, thereby increasing the side first gap to maintain the air flow velocity as far as possible in the subsonic region to maintain its normal fluid pressure. Specifically, it is necessary to control the first magnetic bearings on the first stator and the second stator simultaneously, so that the magnetic poles of the first magnetic bearings are excited with the same polarity, that is, the side with the reduced first gap generates a suction force for sucking back the side first foil bearing, and the side with the increased first gap generates a suction force for pulling back the first thrust disk. In this way, the difference of the magnetic force acting distances of the two sides is utilized to generate magnetic force difference, and the first thrust disc is pulled to enable the first gap between the first thrust disc and the first foil bearings of the two sides to be restored to be normal, so that the first thrust disc is returned to the balanced state again.

In the process, the advantages of the first magnetic bearing that the real-time control is convenient are utilized, and the factors of the unbalanced mass of the first thrust disk or the excessive deflection of the first thrust disk caused by the vortex of the first thrust disk and the like are actively balanced, so that the first thrust disk is fixed in a certain minimum range in the axial direction of the rotating shaft. In addition, in the acceleration process of the first thrust disk, the position (namely the linear velocity supersonic speed part) where the shock wave is generated can be accurately positioned, and the first magnetic bearing generates opposite force to balance the shock wave action by controlling the current magnitude, the direction and the like of the first magnetic bearing. And after the shock wave is stable, the control strategy of the first magnetic bearing is regulated again, and the first thrust disc is fixed in a certain minimum range in the 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 further improved. Meanwhile, the electromagnetic bearing and the gas bearing adopt a 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 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 clearance by using the electromagnetic bearing, so that the low-speed performance of the bearing is improved, the service life of the bearing is prolonged, and the safety and reliability of the bearing and the whole system can be improved.

Secondly, compared with the traditional aerostatic and static pressure mixed thrust bearing adopting the combination of the aerostatic pressure bearing and the aerodynamic pressure bearing, the foil type aeromagnetic mixed thrust bearing provided by the embodiment of the invention has the advantage of high response speed.

Thirdly, through setting up magnetic material on the foil, can make the foil moderate deformation through the attraction of electromagnetic bearing's magnetic pole, improve the highest pressure of lubricated air film one side in the bearing and prevent lubricated air current leakage, improve thrust disk and receive the ability that the disturbance eccentric hits the wall to bearing capacity has also been improved.

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

Examples ten

Fig. 32 to 38 are schematic structural views of a groove-type air-magnetic hybrid thrust bearing according to an embodiment of the present invention.

As shown in fig. 32 to 38, the groove type air-magnetic hybrid thrust bearing 5200 includes:

the second thrust plate 5201, the second thrust plate 5201 is fixedly connected to the rotating shaft 100, and the second thrust plate 5201 is provided with a third magnetic component;

And a third stator 5202 and a fourth stator 5203 penetrating the rotating shaft 100, wherein the third stator 5202 and the fourth stator 5203 are respectively disposed on two opposite sides of the second thrust disc 5201;

in the third stator 5202 and the fourth stator 5203, each stator includes a second magnetic bearing 5204, a plurality of fourth magnetic members capable of generating magnetic force with the third magnetic members are circumferentially provided on the second magnetic bearing 5204, a second gap 5206 is provided between the second magnetic bearing 5204 and the second thrust plate 5201, and the second thrust plate 5201 is capable of moving in the axial direction of the rotary shaft 100 by the magnetic force between the third magnetic members and the plurality of fourth magnetic members;

wherein, the end faces of the second thrust plate 5201 facing the third stator 5202 and the fourth stator 5203, or the end faces of the third stator 5202 and the fourth stator 5203 facing the second thrust plate 5201 are provided with second dynamic pressure generating grooves 5205.

In the embodiment of the invention, the second gap 5206 and the second magnetic bearing 5204 are arranged in the thrust bearing 5200, so that the thrust bearing 5200 forms a gas-magnetic hybrid thrust bearing.

When the thrust bearing 5200 works, the gas bearing in the thrust bearing 5200 and the second magnetic bearing 5204 can work cooperatively, and when the thrust bearing 5200 is in a stable working state, the support is realized by the gas bearing; while the thrust bearing 5200 is in an unstable working state, the thrust bearing 5200 is controlled and responded by the second magnetic bearing 5204 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 the casing of the gas turbine through a connection.

In the embodiment of the present invention, when the second thrust plate 5201 rotates, the flowing gas present in the second gap 5206 is pressed into the second dynamic pressure generating groove 5205, thereby generating pressure to achieve that the second thrust plate 5201 is held in a noncontact manner in the axial direction. The magnitude of the pressure generated by the second dynamic pressure generating grooves 5205 varies depending on the angle, groove width, groove length, groove depth, groove number, and flatness of the second dynamic pressure generating grooves 5205. The magnitude of the pressure generated by the second dynamic pressure generating grooves 5205 is also related to the rotational speed of the second thrust disk 5201 and the second gap 5206. The parameters of the second dynamic pressure generating grooves 5205 can be designed according to the actual conditions. The second dynamic pressure generating grooves 5205 may be formed on the third stator 5202 and the fourth stator 5203 by forging, rolling, etching, or pressing, or the second dynamic pressure generating grooves 5205 may be formed on the second thrust plate 5201 by forging, rolling, etching, or pressing, or the like.

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

alternatively, the plurality of fourth magnetic members include a plurality of second electromagnets circumferentially disposed on the second magnetic bearing 5204, each of the plurality of second electromagnets including a second magnetic core 52041 disposed on the second magnetic bearing 5204 and a second coil 52042 wound on the second magnetic core 52041.

In the embodiment of the invention, when the groove type air-magnetic hybrid thrust bearing 5200 only needs the magnetic component to provide magnetic force without magnetic control, the fourth magnetic component is preferably a second permanent magnet; when the slot type air-magnetic hybrid thrust bearing 5200 requires both magnetic force and magnetic control, the fourth magnetic component is preferably a second electromagnet.

When the fourth magnetic member is a second electromagnet, a current is supplied to the second coil 52042, so that the second magnetic core 52041 generates a magnetic force. The magnitude of the current flowing through 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 current flowing through the second coil 52042 is different, and the magnetic poles of the second core 52041 are 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 characteristics of high magnetic permeability, low eddy current loss, etc.

Optionally, the second magnetic bearing 5204 includes:

the second magnetic bearing seat 52043, the second magnetic bearing seat 52043 is opposite to the second thrust disk 5201, a plurality of second accommodating grooves 52044 are circumferentially arranged on the second magnetic bearing seat 52043, a plurality of fourth magnetic components are arranged in the plurality of second accommodating grooves 52044, and the magnetic poles of the plurality of fourth magnetic components face to one side where the second thrust disk 5201 is located;

second end cover 52045 and first clamping ring 52046, second end cover 52045 set up in the one side of second magnetic bearing frame 52043 that keeps away from second thrust disk 5201, and first clamping ring 52046 sets up in the one side of second magnetic bearing frame 52043 that is close to second thrust disk 5201, and second end cover 52045 cooperates with first clamping ring 52046, fixes a plurality of fourth magnetic component on second magnetic bearing frame 52043.

In the preferred embodiment of the present invention, the second magnetic bearing seat 52043 may be formed by stacking a plurality of silicon steel sheets or silicon steel sheets, because the silicon steel sheets or silicon steel sheets have physical characteristics of high magnetic permeability, low eddy current loss, etc. The number of the second receiving grooves 52044 may be, but is not limited to, six or eight, and is uniformly disposed along the circumferential direction of the second magnetic bearing seat 52043. In this way, the magnetic force between the second magnetic bearing 5204 and the second thrust disk 5201 can be made more uniform and stable. The plurality of fourth magnetic members may be provided on the second magnetic bearing block 52043 in other manners, which is not limited thereto. The material of the second end cap 52045 can be a non-magnetic material, preferably a duralumin material. The material of the first pressure ring 52046 can be a non-magnetic material, preferably a duralumin material.

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

Optionally, the third magnetic component includes a second magnetic material (not shown in the figure) disposed 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 plate 5201 to form a plurality of strip-shaped magnetic parts, and the plurality of strip-shaped magnetic parts are radial or annular;

alternatively, the second magnetic members are distributed 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 disk 5201, so that the magnetic force generated between the second magnetic material and the fourth magnetic component can be controlled within a reasonable range.

Optionally, the second dynamic pressure generating grooves 5205 are arranged radially or concentrically, which is advantageous for more uniformly distributing the air film in the second gap 5206.

Optionally, the second 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 one end of the first spiral groove 52051 near the second spiral groove 52052 is connected or disconnected with one 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 near 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 near 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 shaft center of the rotary 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 above-mentioned arrangement manner of the second dynamic pressure generating grooves 5205, the second thrust disc 5201 can be held in a non-contact manner in a desired manner in the case 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.

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

In the embodiment of the present invention, by providing the first static pressure air inlet orifice 5208, a aerostatic bearing may be formed, so that the thrust bearing 5200 may form a hybrid aerostatic-magnetic thrust bearing. The flow diameter of the first static pressure air inlet orifice 5208 can be adjusted according to actual working conditions such as air flow requirements.

Optionally, in the third stator 5202 and the fourth stator 5203, a plurality of first static pressure air inlet orifices 5208 are disposed on each stator, and the plurality of first static pressure air inlet orifices 5208 are disposed at intervals along the circumferential direction of the stator.

In the embodiment of the present invention, the plurality of first static pressure air intake orifices 5208 are arranged at intervals along the circumferential direction of the stator, preferably at uniform intervals along the circumferential direction of the stator. In this way, it is advantageous to make the gas film pressure in the second gap 5206 more uniform.

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

In the embodiment of the present invention, the above-mentioned first static pressure air inlet orifice 5208 is arranged in a manner that the aerostatic bearing is more stable, and if the static pressure air inlet orifice is too close to the axis of the rotating shaft 100, the air film cannot be effectively distributed over the end face of the whole second thrust disc 5201 in time, so that the rotation of the second thrust disc 5201 is not stable enough. Preferably, the distance from the first static pressure intake orifice 5208 to the axial center of the rotary 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 groove type 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 second gap 5206.

In the embodiment of the invention, by arranging the second sensor 5207, parameters at the second gap 5206, such as the air film pressure at the second gap 5206, and the like, can be detected in real time. In this way, the second magnetic bearing 5204 can actively control the thrust bearing 5200 according to the detection result of the second sensor 5207, and can achieve higher accuracy of control.

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 on the second magnetic bearing 5204, and a through hole for the second sensor probe 52072 to pass through is provided on the second magnetic bearing 5204; the second end of the second sensor probe 52072 passes through the through hole in the second magnetic bearing 5204 and extends to the second gap 5206, and the second end of the second sensor probe 52072 is flush with the side of the second magnetic bearing 5204 that is adjacent to the second thrust disk 5201.

In the embodiment of the present invention, the second sensor 5207 can be more stably disposed on the second magnetic bearing 5204 by the structural form and the mounting manner of the second sensor 5207. In addition, the second end of the second sensor probe 52072 is flush with the side of the second magnetic bearing 5204, which is 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, and the second sensor probe 52072 can be protected; on the other hand, the air film in the second gap 5206 is not affected, and the air film in the second gap 5206 is prevented from being disturbed.

Optionally, the second sensor 5207 is disposed between two adjacent fourth magnetic components.

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

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

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

a pressure sensor for detecting the gas film pressure at the second gap 5206;

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

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

The following describes in detail a specific control method when the groove type air-magnetic hybrid thrust bearing (wherein 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 air-magnetic hybrid thrust bearing, which comprises the following steps:

s531, opening second magnetic bearings in the third stator and the fourth stator, and controlling the second thrust disk 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 second gap between the second thrust disk and the second magnetic bearings in the third stator and a second gap between the second thrust disk and the second magnetic bearings 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.

S533, when the rotor system is stopped, the second magnetic bearings in the third stator and the fourth stator are started.

S534, after the rotating speed of the rotating shaft is reduced to zero, the second magnetic bearings in the third stator and the fourth stator are closed.

In the above process, after the second magnetic bearing is opened, 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 the second thrust disc and the end surfaces of the third stator and the fourth stator have second gaps.

With the rotation of the rotating shaft, the second thrust disc starts to rotate relative to the third stator and the fourth stator under the condition of being lubricated by the air flow in the second gap so as to prevent abrasion. The specific process of opening the second magnetic bearing is as follows: a current signal of a preset value is input to the second coil, and the second thrust disk reaches a preset position between the third stator and the fourth stator under the action of the second magnetic bearing.

Along with the increasing of the rotating speed of the rotating shaft, the rotating speed of the second thrust disc is synchronously increased, and when the rotating speed of the rotating shaft reaches the working rotating speed, the air film pressure generated by the air dynamic bearing of the thrust bearing (the air dynamic bearing forming the thrust bearing by arranging a second gap between the second thrust disc and the third stator and the fourth stator) can stabilize the second thrust disc, and then the second magnetic bearing can be closed.

When the rotor system is stopped, 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 is stopped, and the second magnetic bearing is closed until the second thrust disc is completely stopped.

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

s541, opening second magnetic bearings in the third stator and the fourth stator, and controlling the second thrust disk 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 a difference between a second gap between the second thrust disk and the second magnetic bearings in the third stator and a second gap between the second thrust disk and the second magnetic bearings in the fourth stator is smaller than or equal to a preset value.

S542, after the rotating speed of the rotating shaft is accelerated to a first preset value, the second magnetic bearings in the third stator and the fourth stator are closed.

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

S544, after the rotating speed of the rotating shaft is reduced to zero, the second magnetic bearings in the third stator and the fourth stator are closed.

In the above process, after the second magnetic bearing is opened, 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 the second thrust disc and the end surfaces of the third stator and the fourth stator have second gaps. With the rotation of the rotating shaft, the second thrust disc starts to rotate relative to the third stator and the fourth stator under the condition of being lubricated by the air flow in the second gap so as to prevent abrasion. The specific process of opening the second magnetic bearing is as follows: a current signal of a preset value is input to the second coil, and the second thrust disk reaches a preset position between the third stator and the fourth stator under the action of the second magnetic bearing.

Along with the increasing rotation speed of the rotating shaft, the rotation speed of the second thrust disc is synchronously increased, and when the rotation speed of the rotating shaft reaches a second preset value, for example, 5-30% of the rated rotation speed, the air film pressure generated by the air dynamic bearing of the thrust bearing (the air dynamic bearing forming the groove type air-magnetic hybrid thrust bearing is formed by arranging a second gap between the second thrust disc and the third stator and the fourth stator) can stabilize the second thrust disc, and then the second magnetic bearing can be closed.

During the shutdown of the rotor system, the second thrust disk is decelerated 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 air dynamic pressure bearing of the thrust bearing is also reduced along with the deceleration of the second thrust disk, so that the second magnetic bearing needs to be started to keep the second thrust disk stable, and the second magnetic bearing can be closed until the second thrust disk is completely stopped.

Optionally, the method further comprises:

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

When a load is placed on the second thrust disk, so that the second gap between the second thrust disk and the second magnetic bearing of the third stator or the fourth stator becomes smaller to approach the second magnetic bearing on the side, the second sensor (the second sensor here is preferably a pressure sensor) obtains a signal of an increase in air pressure, at which time the second magnetic bearing needs to be involved in operation. The second magnetic bearing acts on the second thrust disk by magnetic force to move the second thrust disk to the second magnetic bearing at the other side, and the second magnetic bearing stops working after the second thrust disk reaches a new balance position.

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

And if the second gap between the second thrust disc and the second magnetic bearing in the fourth stator is smaller than the second gap between the second thrust disc and the second magnetic bearing in the third stator, and the difference between the second gap between the second thrust disc and the second magnetic bearing in the third stator and the second 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 far away from the third stator under the action of magnetic force between the third magnetic component and the plurality of fourth magnetic components.

Optionally, when the 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 second gap between the second thrust disc and the second magnetic bearing in the third stator and a second 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 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 the difference between the second gap between the second thrust disc and the second magnetic bearing in the third stator and the second gap between the second thrust disc and the 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 controlled to be opened at the maximum power; or,

when the 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 the difference between the second gap between the second thrust disc and the second magnetic bearing in the third stator and the second gap between the second thrust disc and the 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 controlled to be opened in a stroboscopic mode according to preset frequency.

When external impact disturbance occurs, the second thrust disc may quickly approach to the second magnetic bearing on a certain side, and the second gap on the certain side may be excessively small instantaneously, so that the local gas flow velocity at the second gap on the certain side approaches to or even reaches to the sonic velocity, and the shock wave is triggered to generate the air hammer self-excitation phenomenon. The generation of shock waves causes local gas flow disturbances and upsets, with a significant step drop in pressure as the fluid velocity changes between 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 turn in a stroboscopic manner at a preset frequency to provide a damping effect on the disturbance, thereby effectively suppressing the external disturbance. After the second thrust disk returns to the equilibrium state, the second magnetic bearing stops operating.

In the embodiment of the present invention, when the electromagnetic bearing (the electromagnetic bearing is formed as the fourth magnetic component in the second magnetic bearing) and the hydrostatic gas bearing (the hydrostatic gas bearing is formed as the first hydrostatic gas inlet orifice provided in the third stator and the fourth stator) are simultaneously provided, the electromagnetic bearing and the hydrostatic gas bearing may be mutually spare, and when one of them fails, or the opening condition cannot be satisfied, the other may serve as a spare bearing. For example, in the case of detecting a failure of the electromagnetic bearing, the external air source is controlled to be turned on to perform a corresponding action instead of the electromagnetic bearing, thereby improving the safety and reliability of the bearing.

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 "opening the aerostatic bearing in the thrust bearing to move the thrust disc of the thrust bearing to the preset axial position" may include the following implementation modes:

In the process, the advantages of the second magnetic bearing that the real-time control is convenient are utilized, and the factors of the unbalanced mass of the second thrust disk or excessive deflection of the second thrust disk caused by the vortex of the second thrust disk and the like are actively balanced, so that the second thrust disk is fixed in a certain minimum range in the axial direction of the rotating shaft. In addition, in the acceleration process of the second thrust disk, the position (namely the linear velocity supersonic speed part) where the shock wave is generated can be accurately positioned, and the second magnetic bearing generates opposite force to balance the shock wave action by controlling the current magnitude, the direction and the like of the second magnetic bearing. And after the shock wave is stable, the control strategy of the second magnetic bearing is regulated again, and the second thrust disc is fixed in a certain minimum range in the 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 further improved. Meanwhile, the electromagnetic bearing and the gas bearing adopt a 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 bearing is improved. When the rotor system is started or stopped, the thrust disc of the bearing and the stator can rotate in the second gap by using the electromagnetic bearing, so that the low-speed performance of the bearing is improved, the service life of the bearing is prolonged, and the safety and reliability of the bearing and the whole system can be improved.

Secondly, compared with the traditional aerostatic and static hybrid thrust bearing adopting the combination of the aerostatic bearing and the aerodynamic bearing, the groove type aeromagnetic hybrid thrust bearing provided by the embodiment of the invention has the advantage of high response speed.

Thirdly, the aerostatic bearing is added to form a groove type dynamic static pressure-magnetic mixed thrust bearing, under the condition that the electromagnetic bearing and the aerostatic bearing are simultaneously arranged, the bearing capacity of the bearing is further increased, the electromagnetic bearing and the aerostatic bearing can be mutually standby, and under the condition that one of the electromagnetic bearing and the aerostatic bearing fails or cannot meet the opening condition, the other can serve as a standby bearing to play the same role. For example, when a fault of the electromagnetic bearing is detected, the control system controls the aerostatic bearing to be opened to replace the electromagnetic bearing to execute corresponding actions, so that the safety and the reliability of the bearing are improved.

Example eleven

Fig. 39 to 44 are schematic structural views of a foil type air-magnetic hybrid radial bearing according to an embodiment of the present invention.

As shown in fig. 39 to 44, the foil type air-magnetic hybrid radial bearing 6100 includes:

the third magnetic bearing 6101 is sleeved on the rotating shaft 100, and a plurality of fifth magnetic components are arranged on the third magnetic bearing 6101 along the circumferential direction;

the second foil bearing 6102 is sleeved on the rotating shaft 100 and is positioned between the third magnetic bearing 6101 and the rotating shaft 100, and a sixth magnetic component capable of generating magnetic force with the plurality of fifth magnetic components is arranged on the second foil bearing 6102;

wherein, a third gap 6103 is provided between the second foil bearing 6102 and the rotating shaft 100, and the second foil bearing 6102 can move in the radial direction of the rotating shaft 100 under the magnetic force of a plurality of fifth magnetic members and sixth magnetic members.

In the embodiment of the present invention, the radial bearing 6100 is formed into a gas-magnetic hybrid radial bearing by providing the third gap 6103 and the third magnetic bearing 6101 in the radial bearing 6100.

When the radial bearing 6100 works, the gas bearing in the radial bearing 6100 and the third magnetic bearing 6101 can work cooperatively, and when the radial bearing 6100 is in a stable working state, the support is realized by means of the gas bearing; while when the radial bearing 6100 is in an unstable operation state, the radial bearing 6100 is controlled and responded by the third magnetic bearing 6101 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 high-rotation-speed rotor system, such as a gas turbine or a gas turbine power generation combined set.

In the embodiment of the invention, the rotating shaft 100 may be formed by laminating a plurality of silicon steel sheets or silicon steel sheets due to the physical characteristics of high magnetic permeability, low eddy current loss and the like of the silicon steel sheets or the silicon steel sheets.

Optionally, the plurality of fifth magnetic components includes a plurality of third permanent magnets, the plurality of third permanent magnets being circumferentially disposed on the third magnetic bearing 6101;

alternatively, the plurality of fifth magnetic components include a plurality of third electromagnets circumferentially disposed on the third magnetic bearing 6101, each of the plurality of third electromagnets including a third magnetic core 61011 disposed on the third magnetic bearing 6101 and a third coil 61012 wound around the third magnetic core 61011.

In the embodiment of the present invention, when the foil type air-magnetic hybrid radial bearing 6100 only needs the magnetic component to provide magnetic force without magnetic control, the fifth magnetic component preferably uses the third permanent magnet; when the foil type air-magnetic hybrid thrust bearing requires both magnetic force and magnetic control, the fifth magnetic component is preferably a third electromagnet.

When the fifth magnetic component is the third electromagnet, current is applied to the third coil 61012, so that the third magnetic core 61011 can generate magnetic force. The magnitude of the current flowing through the third magnetic core 61012 is different, and the magnitude of the magnetic force generated by the third magnetic core 61011 is also different; the direction of current flowing through the third coil 61012 is different, and the magnetic poles of the third core 61011 are also different.

In the preferred embodiment of the present invention, the third magnetic core 61011 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 characteristics of high magnetic permeability, low eddy current loss, and the like.

Optionally, the third magnetic bearing 6101 includes:

the third magnetic bearing seat 61013, the third magnetic bearing seat 61013 is sleeved on the rotating shaft 100, a plurality of third containing grooves 61014 are circumferentially arranged on the third magnetic bearing seat 61013, a plurality of fifth magnetic members are arranged in the third containing grooves 61014, and the magnetic poles of the fifth magnetic members face to the side where the second foil bearing 6102 is located;

a first bearing shell 61015 sleeved outside the third magnetic bearing base 61013;

a first bearing sleeve 61016 sleeved between the third magnetic bearing support 61013 and the second foil bearing 6102;

and a third end cover 61017 and a fourth end cover 61018 provided at both ends of the first bearing housing 61015, respectively;

The first bearing housing 61016, the third end cap 61017, and the fourth end cap 61018 cooperate to fix the plurality of fifth magnetic members to the third magnetic bearing housing 61013.

In the preferred embodiment of the present invention, the third magnetic bearing 61013 may be formed by stacking a plurality of silicon steel sheets or silicon steel sheets, because the silicon steel sheets or silicon steel sheets have physical characteristics of high magnetic permeability, low eddy current loss, etc. The number of the third receiving grooves 61014 may be, but not limited to, six or eight, and are uniformly arranged along the circumferential direction of the third magnetic bearing support 61013. In this way, the magnetic force between the third magnetic bearing 6101 and the second foil bearing 6102 can be made more uniform and stable. The plurality of fifth magnetic members may be provided on the third magnetic bearing base 61013 in other manners, which is not limited thereto. The material of the third end cap 61017 and the fourth end cap 61018 may both be a non-magnetic material, preferably a duralumin material. The material of the first bearing housing 61016 may be a non-magnetic material, preferably a duralumin material. The material of the first bearing shell 61015 may be a non-magnetic material, preferably a duralumin material.

It should be noted that, when the rotating shaft 100 is not started, the rotating shaft 100 and the first bearing sleeve 61016 are coaxially disposed, and after the rotating shaft 100 is started, the axis of the rotating shaft 100 deviates from any side of the axis of the first bearing sleeve 61016, and the eccentricity epsilon is 0.3 to 0.5, so as to ensure that a wedge-shaped third gap 6103 can be formed between the second foil bearing 6102 and the rotating shaft 100. As the shaft 100 rotates, gas is forced into the third gap 6103, thereby creating pressure to support the load. Wherein, eccentricity epsilon=e/(R-R), wherein e is the distance between the axis of the rotating shaft and the axis of the first bearing sleeve, R is the inner diameter of the first bearing sleeve, R is the inner diameter of the rotating shaft, and (R-R) is the width of the third gap.

Optionally, the second foil bearing 6102 includes a third foil 61021 and a fourth foil 61022, where the third foil 61021 is mounted on the first bearing sleeve 61016 and the fourth foil 61022 is stacked on a side of the third foil 61021 near the rotating shaft 100;

the fourth foil 61022 is a flat foil, and the sixth magnetic member is disposed on the fourth foil 61022, so that the fourth foil 61022 can move in the radial direction of the rotating shaft 100 under the magnetic force of the plurality of fifth magnetic members and the sixth magnetic member; the third foil 61021 is an elastically deformable foil that can be elastically deformed when the fourth foil 61022 is moved.

Among these, the third foil 61021 is preferably a stainless steel strip that is not magnetically conductive, since the material of the magnetically conductive material is hard and brittle and is not suitable as an elastically deformable foil.

In the embodiment of the present invention, by setting the fourth foil 61022 as a flat foil, it is convenient to control the distance between the fourth foil 61022 and the rotation shaft 100, or, it is convenient to control the size of the third gap 6103.

Optionally, the third foil 61021 is an elastically deformable foil that is wavy, and the third foil 61021 is an unsealed ring, and is provided with an opening, one end of the opening is a fixed end, the fixed end is fixed on the first bearing sleeve 61016, and the other end of the opening is a movable end;

When the fourth foil 61022 moves in the radial direction of the rotation shaft 100, the corrugations on the third foil 61021 extend or contract, and the movable end moves along the circumferential direction of the ring.

In the embodiment of the present invention, by arranging the third foil 61021 as an elastically deformable foil in a wave shape, the fourth foil 61022 is pushed to move in the radial direction of the rotation shaft 100 by utilizing the expansion or contraction characteristics of the wave pattern.

It should be noted that the shape of the third foil 61021 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 third foil 61021 in the embodiment of the present invention.

Optionally, the sixth magnetic component comprises a third magnetic material 61023 provided on a side surface of the fourth foil 61022 adjacent the first bearing sleeve 61016;

the third magnetic material 61023 is distributed on the fourth foil 61022 in a stripe shape to form a plurality of stripe-shaped magnetic portions, and the length direction of the plurality of stripe-shaped magnetic portions is parallel to the axis direction of the rotating shaft 100;

alternatively, the third magnetic means are distributed in a spot on the fourth foil 61022.

The material of the fourth foil 61022 is preferably a non-magnetic material, and after the surface of the fourth foil 61022 is coated with the third magnetic material 61023, the third magnetic material 61023 may be covered with a ceramic coating. The fourth foil 61022 may be made by sintering ceramic nano-powders using 40% zirconia, 30% alpha alumina and 30% magnesium aluminate spinel.

If the surface of the fourth foil 61022 completely covers the third magnetic material 61023, the magnetic force generated between the third magnetic material 61023 and the first magnetic member is greatly increased, which easily causes deformation of the fourth foil 61022. In view of this, in the embodiment of the present invention, by spraying the third magnetic material 61023 on the surface of the fourth foil 61022, the third magnetic material 61023 is distributed in a stripe shape or a dot shape on the fourth foil 61022, so that the magnetic force generated between the third magnetic material 61023 and the first magnetic member can be controlled within a reasonable range, thereby avoiding the fourth foil 61022 from being deformed due to excessive magnetic force.

Optionally, the foil-type air-magnetic hybrid radial bearing 6100 further includes a plurality of third sensors 6104 disposed at intervals along the circumferential direction of the third magnetic bearing 6101, where each third sensor 6104 includes a third sensor cover 61041 and a third sensor probe 61042, a first end of the third sensor probe 61042 is connected to the third sensor cover 61041, the third sensor cover 61041 is fixed to the third magnetic bearing 6101, and through holes for the third sensor probe 61042 to pass through are provided in the first bearing shell 61015, the third magnetic bearing support 61013, and the first bearing sleeve 61016; the second end of the third sensor probe 61042 passes through the through holes in the first bearing shell 61015, the third magnetic bearing support 61013, and the first bearing sleeve 61016, and extends into the gap between the first bearing sleeve 61016 and the third foil 61021, and the second end of the third sensor probe 61042 is flush with the side of the first bearing sleeve 61016 near the third foil 61021.

In the embodiment of the present invention, by providing the third sensor 6104, the gas pressure parameter at the third foil 61021 can be detected in real time. In this way, the third magnetic bearing 6101 can actively control the radial bearing 6100 according to the detection result of the third sensor 6104, and can achieve high accuracy of control.

In the embodiment of the present invention, the third sensor 6104 can be more stably disposed on the third magnetic bearing 6101 by the structural form and the mounting manner of the third sensor 6104 described above. In addition, the second end of the third sensor probe 61042 is flush with the side of the first bearing sleeve 61016 near the third foil 61021, so that on one hand, the third sensor probe 61042 can be prevented from being touched by the third foil 61021, thereby being beneficial for protecting the third sensor probe 61042; on the other hand, the air film in the third gap 6103 is not affected, and the air film in the third gap 6103 is prevented from being disturbed.

Optionally, among the plurality of third sensors 6104, each third sensor 6104 is disposed between two adjacent fifth magnetic members, respectively.

In the embodiment of the present invention, the number of the third sensors 6104 may be the same as the number of the fifth magnetic members, each third sensor 6104 is disposed between two adjacent fifth magnetic members, and each third sensor 6104 is preferably disposed in the middle of the third magnetic bearing 6101. Further, in the embodiment of the present invention, in addition to the third sensor 6104 for detecting the gas pressure parameter at the third foil 61021, a displacement sensor for detecting the position of the rotation shaft, or a speed sensor for detecting the rotation speed of the rotation shaft, or an acceleration sensor for detecting the rotation acceleration of the rotation shaft, or the like may be provided.

The following describes in detail a specific control method when the foil type air-magnetic hybrid radial bearing (wherein the fifth magnetic component in the third magnetic bearing is an electromagnet) participates in the control process of the rotor system according to the embodiment of the present invention.

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

s611, starting the third magnetic bearing, and controlling the rotating shaft to move in the radial direction of the rotating shaft under the action of the magnetic force of the plurality of fifth magnetic components so as to enable the rotating shaft to move to a preset radial position.

S612, after the rotating speed of the rotating shaft is accelerated to the working rotating speed, the third magnetic bearing is closed.

S613, when the rotor system is stopped, the third magnetic bearing is started.

S614, after the rotating speed of the rotating shaft is reduced to zero, the third magnetic bearing is closed.

In the above process, after the third magnetic bearing is opened, the rotating shaft is supported and reaches a preset position under the action of the third magnetic bearing, and a third gap is formed between the second foil bearing and the rotating shaft.

As the shaft rotates, the shaft starts to rotate while being lubricated by the air flow in the third gap to prevent wear. The specific process for opening the third magnetic bearing is as follows: and inputting a current signal with a preset value into the third coil, and supporting the rotating shaft under the action of the third magnetic bearing and reaching a preset position.

With the rotating speed of the rotating shaft becoming larger and larger, when the rotating speed of the rotating shaft reaches the working rotating speed, the air film pressure generated by the air dynamic bearing of the radial bearing (the third gap arranged between the second foil bearing and the rotating shaft, namely the air dynamic bearing forming the radial bearing) can stabilize the rotating shaft, and then the third magnetic bearing can be closed.

When the rotor system is stopped, the rotating shaft is decelerated, 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 is stopped, and the third magnetic bearing is closed until the rotating shaft is completely stopped.

The embodiment of the invention also provides a control method of the foil type air-magnetic hybrid radial bearing, which comprises the following steps:

s621, starting the third magnetic bearing, and controlling the rotating shaft to move in the radial direction of the rotating shaft under the action of the magnetic force of the plurality of fifth magnetic components so as to enable the rotating shaft to move to a preset radial position.

S622, after the rotating speed of the rotating shaft is accelerated to a first preset value, the third magnetic bearing is closed.

S623, when the rotating speed of the rotating shaft is accelerated to the first-order critical speed or the second-order critical speed, starting the third magnetic bearing.

Specifically, when the gas flow rate at the third gap between the rotating shaft and the second foil bearing (further, the fourth foil) reaches the first-order critical speed or the second-order critical speed, the third magnetic bearing is started until the rotating shaft is restored to the balanced radial position.

Optionally, when the rotation speed of the rotating shaft accelerates to the first-order critical speed or the second-order critical speed, the third magnetic bearing is started, including:

when the rotating speed of the rotating shaft is accelerated to a first-order critical speed or the second-order critical speed, the third magnetic bearing is controlled to be started at the maximum power; or,

when the rotating speed of the rotating shaft is accelerated to the first-order critical speed or the second-order critical speed, the third magnetic bearing is controlled to be opened in a stroboscopic mode according to the preset frequency.

S624, after the rotor system steadily passes the first-order critical speed or the second-order critical speed, the third magnetic bearing is closed.

S625, in the shutdown process of the rotor system, when the rotor system is decelerated to the first-order critical speed or the second-order critical speed, the third magnetic bearing is started.

Specifically, when the gas flow rate at the third gap between the rotating shaft and the second foil bearing (further, the fourth foil) is reduced to the first-order critical speed or the second-order critical speed, the third magnetic bearing is started until the rotating shaft is restored to the balanced radial position.

Optionally, when the rotation speed of the rotating shaft is reduced to a first-order critical speed or the second-order critical speed, starting the third magnetic bearing, including:

when the rotating speed of the rotating shaft is reduced to a first-order critical speed or the second-order critical speed, the third magnetic bearing is controlled to be started at the maximum power; or,

When the rotating speed of the rotating shaft is reduced to the first-order critical speed or the second-order critical speed, the third magnetic bearing is controlled to be opened in a stroboscopic mode according to the preset frequency.

S626, after the rotor system steadily passes through the first-order critical speed or the second-order critical speed, the third magnetic bearing is closed.

And S627, when the rotating speed of the rotating shaft is reduced to a second preset value, starting the third magnetic bearing.

S628, after the rotating speed of the rotating shaft is reduced to zero, the third magnetic bearing is closed.

As the rotational speed of the rotational shaft increases, when the rotational speed of the rotational shaft reaches a first preset value, for example, 5% to 30% of the rated rotational speed, the gas film pressure generated by the gas dynamic bearing of the radial bearing (the gas dynamic bearing forming the radial bearing, which is a third gap between the second foil bearing and the rotational shaft) can stabilize the rotational shaft, and then the third magnetic bearing can be closed.

And in the stopping process of the rotor system, the rotating shaft is decelerated, and when the rotating speed of the rotating shaft is reduced to a second preset value, for example, 5-30% of the rated rotating speed, the third magnetic bearing is started, and the third magnetic bearing can be closed until the rotating shaft is completely stopped.

Optionally, the method further comprises:

when a third gap between the rotating shaft and the second foil bearing (further, a fourth foil) is changed, the third magnetic bearing is started, so that the second foil bearing corresponding to the smaller gap side moves towards the direction approaching to the rotating shaft under the action of magnetic force between the plurality of fifth magnetic components and the sixth magnetic component;

When a load is placed on the spindle, causing the spindle to gradually descend and approach the fourth foil underneath, the third sensor (here the third sensor is preferably a pressure sensor) obtains a signal of an increase in air pressure, at which time the third magnetic bearing needs to be operated in an intervening manner. The third magnetic bearing does not directly act on the rotating shaft to enable the magnetic force to suspend upwards, but pushes the fourth foil below upwards (namely, towards the direction close to the rotating shaft) by using the magnetic force, so that the lower gap is reduced, the pressure at the lower gap is improved, the weight of the load on the rotating shaft is adapted, and the air flow pressure in all directions of the third gap is automatically redistributed. When the rotating shaft reaches a new balanced radial position, the third magnetic bearing stops working.

When external impact disturbance occurs, the rotating shaft may quickly approach the second foil bearing, and the gap between the rotating shaft and the second foil bearing may be excessively small instantaneously, so that the local gas flow velocity at the gap reduction position approaches or even reaches the sonic velocity, and the shock wave is triggered to generate the air hammer self-excitation phenomenon. The generation of shock waves causes local gas flow disturbances and upsets, with a significant step drop in pressure as the fluid velocity changes between sonic to subsonic. In this case, it is necessary to have the second foil bearing actively "dodge" the spindle, thereby increasing the gap between the spindle and the second foil bearing to maintain the air flow velocity as far as possible in the subsonic region to maintain its normal fluid pressure. Specifically, the magnetic poles of the fifth magnetic members on the opposite sides where the gap is changed need to be excited with the same polarity, that is, the direction where the gap is reduced generates a suction force for sucking back the second foil bearing, and the direction where the gap is increased generates a suction force for pulling back the rotating shaft. Thus, the difference of the magnetic force acting distances of the two sides is utilized to generate magnetic force difference, so that the rotating shaft is pulled to restore the normal gap between the rotating shaft and the second foil bearing, and the rotating shaft is returned to a new balanced radial position.

In the process, the advantages of the third magnetic bearing that the real-time control is convenient are utilized, and the factors of the unbalanced mass of the rotating shaft or the excessive deflection of the rotating shaft caused by the whirling of the rotating shaft and the like are actively balanced, so that the rotating shaft is fixed in a certain minimum range in the radial direction. In addition, in the acceleration process of the rotating shaft, the position (namely the linear velocity supersonic speed part) where the shock wave is generated can be accurately positioned, and the third magnetic bearing generates opposite force to balance the shock wave action by controlling the current magnitude, the direction and the like of the third magnetic bearing. And after the shock wave is stable, the control strategy of the third magnetic bearing is adjusted again, and the rotating shaft is fixed in a certain minimum range in the 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 further improved. Meanwhile, the electromagnetic bearing and the gas bearing adopt a nested 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 clearance by using the electromagnetic bearing, so that the low-speed performance of the bearing is improved, the service life of the bearing is prolonged, and the safety and reliability of the bearing and the whole system can be improved.

Secondly, compared with the traditional aerostatic pressure mixed thrust bearing adopting the combination of the aerostatic pressure bearing and the aerodynamic pressure bearing, the foil type aeromagnetic mixed radial bearing provided by the embodiment of the invention has the advantage of high response speed.

Example twelve

Fig. 45 to 52 are schematic structural views of a groove-type air-magnetic hybrid radial bearing according to an embodiment of the present invention.

As shown in fig. 45 to 52, 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 seventh magnetic components are circumferentially arranged on the fourth magnetic bearing 6201;

A third 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, there is a fourth gap 6203 between the fourth magnetic bearing 6201 and the rotating shaft 100, and the rotating shaft 100 is capable of moving in a radial direction of the rotating shaft 100 under the magnetic force of the seventh magnetic members.

In the embodiment of the present invention, the fourth gap 6203 and the fourth magnetic bearing 6201 are disposed in the radial bearing 6200, so that the radial bearing 6200 forms a gas-magnetic hybrid radial bearing.

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 support is realized by the gas bearing; while the radial bearing 6200 is in an unstable operating state, the radial bearing 6200 is controlled and responded to by means of the fourth magnetic bearing 6201 in time.

In the embodiment of the present invention, when the rotation shaft 100 rotates, the flowing gas existing in the fourth gap 6203 is pressed into the third dynamic pressure generating groove 6202, thereby generating pressure to float the rotation shaft 100, so that the rotation shaft 100 is held contactlessly in the radial direction. The pressure generated by the third dynamic pressure generating groove 6202 varies with the angle, the groove width, the groove length, the groove depth, the groove number, and the flatness of the third dynamic pressure generating groove 6202. In addition, the amount of pressure generated by the third dynamic pressure generating groove 6202 is also related to the rotational speed of the shaft 100 and the fourth gap 6203. Parameters of the third dynamic pressure generating tank 6202 may be designed according to actual conditions. The third dynamic pressure generating groove 6202 may be formed on the fourth magnetic bearing 6201 or the rotating shaft by forging, rolling, etching, or punching, etc.

Optionally, the plurality of seventh magnetic components includes a plurality of fourth permanent magnets disposed circumferentially on the fourth magnetic bearing 6201;

alternatively, the plurality of seventh magnetic elements includes a plurality of fourth electromagnets circumferentially disposed on the fourth magnetic bearing 6201, each of the plurality of fourth electromagnets including a fourth magnetic core 62011 disposed on the fourth magnetic bearing 6201 and a fourth coil 62012 wound around the fourth magnetic core 62011.

In the embodiment of the present invention, when the groove type air-magnetic hybrid radial bearing 6200 only needs the magnetic component to provide magnetic force without magnetic control, the seventh magnetic component is preferably a fourth permanent magnet; when the foil type air-magnetic hybrid thrust bearing requires both magnetic force and magnetic control, the seventh magnetic component is preferably a fourth electromagnet.

When the seventh 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 in which current is supplied to the fourth magnetic core 62012 is different, and the magnetic pole of the fourth magnetic core 62011 is also different.

In the 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 characteristics of high magnetic permeability, low eddy current loss, etc.

Optionally, the fourth magnetic bearing 6201 includes:

a fourth magnetic bearing seat 62013, wherein the fourth magnetic bearing seat 62013 is sleeved on the rotating shaft 100, a plurality of fourth accommodating grooves 6204 are circumferentially arranged on the fourth magnetic bearing seat 62013, a plurality of seventh magnetic components are arranged in the fourth accommodating grooves 62014, and magnetic poles of the seventh magnetic components face the rotating shaft 100;

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

a second bearing housing 62016 sleeved between the fourth magnetic bearing housing 62013 and the rotating shaft 100;

and a fifth end cap 62017 and a sixth end cap 62018 provided at both ends of the second bearing housing 62015, respectively;

wherein the second bearing housing 62016, the fifth end cap 62017 and the sixth end cap 62018 cooperate to secure the seventh plurality of magnetic elements to the fourth magnetic bearing housing 62013.

In the embodiment of the present invention, by providing the second bearing cover 62016, a 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 fourth gap 6203 can be conveniently adjusted and controlled by providing the second bearing sleeves 62016 with different radial thicknesses.

The fourth gap 6203 between the second bearing housing 62016 and the rotating shaft 100 may have a width of 5 μm to 12 μm, preferably 8 μm to 10 μm.

It should be noted that, when the rotating shaft 100 is not started, the rotating shaft 100 and the second bearing sleeve 62016 are coaxially disposed, after the rotating shaft 100 is started, the axis of the rotating shaft 100 deviates from any side of the axis of the second bearing sleeve 62016, and the eccentricity epsilon is 0.3 to 0.5, so as to ensure that a wedge-shaped fourth gap 6203 can be formed between the second bearing sleeve 62016 and the rotating shaft 100. As the shaft 100 rotates, gas is forced into the fourth gap 6203, creating pressure to support the load. Wherein, the eccentricity epsilon=e/(R-R), wherein e is the distance between the axis of the rotating shaft and the axis of the second bearing sleeve, R is the inner diameter of the second bearing sleeve, R is the inner diameter of the rotating shaft, and (R-R) is the width of the fourth gap.

In the preferred embodiment of the present invention, the fourth magnetic bearing seat 62013 may be formed by stacking a plurality of silicon steel sheets or silicon steel sheets, because the silicon steel sheets or silicon steel sheets have physical characteristics of high magnetic permeability, low eddy current loss, etc. The number of the fourth receiving grooves 62014 may be, but is not limited to, six or eight, uniformly arranged along the circumferential direction of the fourth magnetic bearing seat 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 seventh magnetic members may be provided on the fourth magnetic bearing block 62013 in other manners, which is not limited thereto. The materials of the fifth end cap 62017 and the sixth end cap 62018 can both be non-magnetic materials, preferably duralumin materials. The material of the second bearing housing 62016 may be a non-magnetic material, preferably a duralumin material. The material of the second bearing housing 62015 may be a non-magnetic material, preferably a duralumin material.

Preferably, the fifth end cap 62017 and the sixth end cap 62018 are each provided with a boss 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 to fix and compress silicon steel sheets or sheets constituting the fourth magnetic bearing housing 62013 from both ends.

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

Optionally, the third dynamic pressure generating grooves 6202 are arranged in a matrix, which is advantageous for more uniformly distributing the air film in the fourth gap 6203.

Optionally, the third dynamic pressure generating grooves 6202 are V-shaped grooves arranged continuously or at intervals.

In the embodiment of the present invention, by adopting the above-mentioned arrangement mode of the third dynamic pressure generating groove 6202, the rotating shaft 100 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 rotates in the reverse direction, so that the rotating shaft 100 has the advantages of high load capacity and good stability. The third dynamic pressure generating groove 6202 may be provided as a herringbone groove or other shaped groove in addition to the V-shaped groove.

Optionally, a second static pressure air inlet orifice 6205 is further disposed on the fourth magnetic bearing 6201, one end of the second static pressure air inlet orifice 6205 is communicated with the fourth gap 6203, and the other end is connected to an external air source for conveying the external air source into the fourth gap 6203.

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

Optionally, the second static pressure intake orifice 6205 is split within the fourth magnetic bearing 6201 into at least two branches that communicate into the fourth gap 6203.

In an embodiment of the present invention, the second static pressure air inlet orifice 6205 may sequentially pass through the fifth end cap 62017 or the sixth end cap 62018, the fourth magnetic bearing 6201, and the second bearing 62016 to communicate the external air source with the fourth gap 6203. Further, the second static pressure intake orifice 6205 may be split into two or more branches that communicate to the fourth gap 6203, such that the gas film pressure within the fourth gap 6203 is more uniform. Further, an annular groove may be provided on the fifth end cap 62017 or the sixth end cap 62018, and a plurality of second static pressure air 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 air intake orifice 6205 may be provided in each fourth magnetic core 62011 or in each two adjacent fourth magnetic cores 62011. The flow diameter of the second static pressure air inlet orifice 6205 and the branch can be adjusted according to actual working conditions such as air flow requirements.

Optionally, the groove-type aero-magnetic hybrid radial bearing 6200 further includes a plurality of fourth sensors 6204 disposed at intervals along the circumferential direction of the fourth magnetic bearing 6201, wherein a sensor probe of each fourth sensor 6204 is disposed within the fourth gap 6203.

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

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

In the embodiment of the present invention, the fourth sensor 6204 can be more stably disposed 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, close to the rotating shaft 100, of the fourth magnetic bearing 6201, so that on one hand, 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 fourth gap 6203 is not affected, and the air film in the fourth gap 6203 is prevented from being disturbed.

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

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

a displacement sensor for detecting the position of the rotation shaft 100;

a pressure sensor for detecting the gas film pressure at the fourth gap 6203;

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

an acceleration sensor for detecting rotational acceleration of the rotation shaft 100.

The following describes in detail a specific control method when the groove type air-magnetic hybrid radial bearing (wherein, the seventh magnetic component in the fourth 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 air-magnetic hybrid radial bearing, which comprises the following steps:

s631, opening the fourth magnetic bearing, controlling the rotating shaft to move in the radial direction of the rotating shaft under the action of the magnetic force of the seventh magnetic components, and pushing the rotating shaft to a preset radial position.

S632, after the rotating speed of the rotating shaft is accelerated to the working rotating speed, the fourth magnetic bearing is closed.

S633, when the rotor system is stopped, the fourth magnetic bearing is started.

S634, after the rotating speed of the rotating shaft is reduced to zero, the fourth magnetic bearing is closed.

In the above process, after the fourth magnetic bearing is opened, the rotating shaft is supported under the action of the fourth magnetic bearing and reaches the preset radial position, and a fourth gap is formed between the fourth magnetic bearing and the rotating shaft.

With the rotation of the rotating shaft, the rotating shaft starts to rotate under the condition of being lubricated by the air flow in the fourth gap so as to prevent abrasion. The specific process of opening the fourth magnetic bearing is as follows: and inputting a current signal with a preset value into the fourth coil, and supporting the rotating shaft under the action of the fourth magnetic bearing and reaching a preset radial position.

With the rotating speed of the rotating shaft becoming larger and larger, when the rotating speed of the rotating shaft reaches the working rotating speed, the air film pressure generated by the air dynamic bearing of the radial bearing (the air dynamic bearing forming the radial bearing is formed by arranging a fourth gap between the fourth magnetic bearing and the rotating shaft) can stabilize the rotating shaft, and then the fourth magnetic bearing can be closed.

When the rotor system is stopped, the rotating shaft is decelerated, in order to keep the rotating shaft stable in the whole rotor system stopping process, the fourth magnetic bearing is started when the rotor system is stopped, and the fourth magnetic bearing is closed until the rotating shaft is completely stopped.

The embodiment of the invention also provides a control method of the groove type air-magnetic hybrid radial bearing, which comprises the following steps:

s641, opening the fourth magnetic bearing, controlling the rotating shaft to move in the radial direction of the rotating shaft under the action of the magnetic force of the seventh magnetic components, and pushing the rotating shaft to a preset radial position.

S642, after the rotating speed of the rotating shaft is accelerated to a first preset value, the fourth magnetic bearing is closed.

S643, when the rotating speed of the rotating shaft is accelerated to the first-order critical speed or the second-order critical speed, the fourth magnetic bearing is started.

Specifically, when the gas flow rate at the fourth gap between the rotating shaft and the fourth magnetic bearing reaches the first-order critical speed or the second-order critical speed, the fourth magnetic bearing is started until the rotating shaft is restored to the balanced radial position.

Optionally, when the rotation speed of the rotating shaft accelerates to the first-order critical speed or the second-order critical speed, the fourth magnetic bearing is started, including:

when the rotating speed of the rotating shaft is accelerated to a first-order critical speed or a second-order critical speed, the fourth magnetic bearing is controlled to be started at the maximum power; or,

when the rotating speed of the rotating shaft is accelerated to the first-order critical speed or the second-order critical speed, the fourth magnetic bearing is controlled to be opened in a stroboscopic mode according to the preset frequency.

S644, after the rotor system steadily passes the first-order critical speed or the second-order critical speed, the fourth magnetic bearing is closed.

S645, in the shutdown process of the rotor system, when the rotor system is decelerated to a first-order critical speed or a second-order critical speed, the fourth magnetic bearing is started.

Specifically, when the gas flow rate at the fourth gap between the rotating shaft and the fourth magnetic bearing is reduced to the first-order critical speed or the second-order critical speed, the fourth magnetic bearing is started until the rotating shaft is restored to the balanced radial position.

Optionally, when the rotation speed of the rotating shaft is reduced to a first-order critical speed or a second-order critical speed, the fourth magnetic bearing is started, including:

when the rotating speed of the rotating shaft is reduced to a first-order critical speed or a second-order critical speed, the fourth magnetic bearing is controlled to be started at the maximum power; or,

When the rotating speed of the rotating shaft is reduced to the first-order critical speed or the second-order critical speed, the fourth magnetic bearing is controlled to be opened in a stroboscopic mode according to the preset frequency.

S646, after the rotor system steadily passes the first-order critical speed or the second-order critical speed, the fourth magnetic bearing is closed.

S647, when the rotating speed of the rotating shaft is reduced to a second preset value, starting the fourth magnetic bearing.

S648, after the rotating speed of the rotating shaft is reduced to zero, the fourth magnetic bearing is closed.

With the increasing rotation speed of the rotating shaft, when the rotation speed of the rotating shaft reaches a first preset value, for example, 5% to 30% of the rated rotation speed, the gas film pressure generated by the gas dynamic bearing of the radial bearing (the gas dynamic bearing forming the radial bearing by arranging a fourth gap between the fourth magnetic bearing and the rotating shaft) can stabilize the rotating shaft, and then the fourth magnetic bearing can be closed.

In the stopping process of the rotor system, the rotating shaft is decelerated, and when the rotating speed of the rotating shaft is reduced to a second preset value, for example, 5-30% of the rated rotating speed, the fourth magnetic bearing is started, and the fourth magnetic bearing can be closed until the rotating shaft is completely stopped.

Optionally, the method further comprises:

When a load is applied to the rotating shaft, causing the rotating shaft to gradually descend and approach the fourth magnetic bearing below, the fourth sensor (here, the fourth sensor is preferably a pressure sensor) obtains a signal of an increase in air pressure, and the fourth magnetic bearing needs to be involved in the operation. The fourth magnetic bearing acts on the rotating shaft to enable the rotating shaft to suspend upwards, and when the rotating shaft reaches a new balance position, the fourth magnetic bearing stops working.

When external impact disturbance occurs, the rotating shaft may quickly approach the fourth magnetic bearing, and the gap between the rotating shaft and the fourth magnetic bearing may be excessively small instantaneously, so that the local gas flow velocity at the gap reduction position approaches or even reaches the sonic velocity, and the shock wave is triggered to generate the air hammer self-excitation phenomenon. The generation of shock waves causes local gas flow disturbances and upsets, with a significant step drop in pressure as the fluid velocity changes between sonic to subsonic. In this case, it is necessary to control the seventh magnetic members of the fourth magnetic bearing to be alternately turned on at a preset frequency to provide a damping effect on the disturbance, thereby effectively suppressing the external disturbance. After the shaft returns to the new equilibrium radial position, the fourth magnetic bearing stops.

In the embodiment of the present invention, when the electromagnetic bearing (the seventh magnetic component in the fourth magnetic bearing is an electromagnet, that is, the electromagnetic bearing) and the hydrostatic gas bearing (the hydrostatic gas bearing is formed by the second hydrostatic gas inlet orifice provided in the fourth magnetic bearing) are simultaneously provided, the electromagnetic bearing and the hydrostatic gas bearing may be mutually spare, and when one of them fails or fails to satisfy the opening condition, the other may serve as a spare bearing. For example, in the case of detecting a failure of the electromagnetic bearing, the external air source is controlled to be turned on to perform a corresponding action instead of the electromagnetic bearing, thereby improving the safety and reliability of the bearing.

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 "opening the aerostatic bearing in the radial bearing to move the rotating shaft to the preset radial position" may include the following implementation manner:

opening the fourth magnetic bearing; or, starting an external air source, and conveying air to the fourth gap through the second static pressure air inlet throttle hole;

and controlling the rotating shaft to move in the radial direction of the rotating shaft under the action of magnetic force of the seventh magnetic components or the pushing action of the gas so as to enable the rotating shaft to move to a preset radial position.

In the process, the advantages of the fourth magnetic bearing that the real-time control is convenient are utilized, and the factors of the unbalanced mass of the rotating shaft or the excessive deflection of the rotating shaft caused by the whirling of the rotating shaft and the like are actively balanced, so that the rotating shaft is fixed in a certain minimum range in the radial direction. In addition, in the acceleration process of the rotating shaft, the position (namely the linear velocity supersonic speed part) where the shock wave is generated can be accurately positioned, and the shock wave effect is balanced by controlling the current magnitude, the direction and the like of the fourth magnetic bearing, so that the fourth magnetic bearing generates opposite force. And after the shock wave is stable, the control strategy of the fourth magnetic bearing is adjusted again, and the rotating shaft is fixed in a certain minimum range in the 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 further improved. Meanwhile, the electromagnetic bearing and the gas bearing adopt a nested 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 of the bearing and the stator can rotate in the first gap by using the electromagnetic bearing, so that the low-speed performance of the bearing is improved, the service life of the bearing is prolonged, and the safety and reliability of the bearing and the whole system can be improved.

Secondly, compared with the traditional aerostatic pressure mixed thrust bearing adopting the combination of the aerostatic pressure bearing and the aerodynamic pressure bearing, the groove type aeromagnetic mixed radial bearing provided by the embodiment of the invention has the advantage of high response speed.

Example thirteen

In the rotor system, the thrust bearing and the radial bearing adjacent to the thrust bearing may be integrated to form an integrated bearing. Fig. 53 to 68 show schematic structural views of an integrated bearing 1000 formed by integrating a thrust bearing and a radial bearing adjacent to the thrust bearing, corresponding to the rotor systems shown in fig. 1 to 18, respectively.

Fig. 69 to 78 are schematic structural diagrams of an integrated bearing according to an embodiment of the present invention.

As shown in fig. 69 to 78, the integrated bearing 1000 includes:

the third bearing housing 1001, the third bearing housing 1001 is a hollow revolution body, and the third bearing housing 1001 is provided with a first accommodating chamber and a second accommodating chamber;

the radial sub-bearing 1002 is arranged in the first accommodating cavity, the radial sub-bearing 1002 penetrates through the rotating shaft 100, and a fifth 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 third thrust disc 10031, and a fifth stator 10032 and a sixth stator 10033 respectively disposed on two sides of the third thrust disc 10031, the third thrust disc 10031 is fixedly connected to the rotating shaft 100, and the fifth stator 10032 and the sixth stator 10033 are all disposed on the rotating shaft 100 in a penetrating manner; in the fifth stator 10032 and the sixth stator 10033, there is a sixth gap 1005 between each stator and the third 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 radial sub-bearing is easy to process and install, has the characteristics of simple structure and high integration level, and can effectively ensure the requirement of consistent coaxiality of the radial sub-bearing 1002 and the thrust sub-bearing 1003 during processing and installation. In addition, as the fifth gap 1004 is arranged in the radial sub-bearing 1002, and the sixth 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.

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

The fifth stator 10032 and the third bearing housing 1001 may be integrally formed, and the sixth 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 complex, the third bearing housing 1001 may be connected to the housing of the gas turbine through a connection member.

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

the radial sub-bearing 1002 comprises 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 eighth magnetic components are circumferentially arranged on the fifth magnetic bearing 10021;

wherein the rotating shaft 100 is movable in a radial direction of the rotating shaft 100 by magnetic forces of a plurality of eighth magnetic members.

Further, the fifth magnetic bearing 10021 includes:

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 eighth magnetic components are arranged in the fifth accommodating grooves, and magnetic poles of the eighth magnetic components face the rotating shaft 100;

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

Other embodiments of the magnetic bearing provided in the radial sub-bearing 1002 can be referred to in the description of the tenth embodiment, and the same advantages can be achieved, which will not be repeated.

In an embodiment of the present invention, the integrated bearing 1000 may further include a seventh end cap 1006, where the seventh end cap 1006 is disposed at an end of the third bearing housing 1001 near the first accommodating cavity, and the seventh end cap 1006 abuts against the fifth magnetic bearing seat for fixing the radial sub-bearing 1002 in the first accommodating cavity.

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

the fifth stator 10032 and the sixth stator 10033 each include a sixth magnetic bearing 10034, and a plurality of ninth magnetic members are circumferentially disposed on the sixth magnetic bearing 10034;

the tenth magnetic member is provided on the third thrust disk 10031, and the third thrust disk 10031 is movable in the axial direction of the rotating shaft 100 by magnetic force between the plurality of ninth 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 third thrust disk 10031, and is provided with a plurality of sixth receiving grooves along the circumferential direction, a plurality of ninth magnetic components are disposed in the plurality of sixth receiving grooves, and the magnetic poles of the plurality of ninth magnetic components face to the side where the third thrust disk 10031 is located;

and the second pressing ring is arranged on one side of the sixth magnetic bearing seat, which is close to the third thrust disc 10031, and is matched with the sixth magnetic bearing seat to fix the plurality of ninth magnetic components on the sixth magnetic bearing seat.

Other embodiments of the magnetic bearing in the thrust sub-bearing 1003 described above may be referred to in the description of the tenth embodiment, and the same advantageous effects may be achieved, and for avoiding repetition, a description thereof will be omitted.

In the embodiment of the invention, by arranging the magnetic bearing, particularly the electromagnetic bearing (the eighth magnetic component in the fifth magnetic bearing 10021 is an electromagnet, and the ninth magnetic component in the sixth magnetic bearing 10034 is an electromagnet) in the integrated bearing 1000, when the rotor system starts or stops, the thrust disc and the stator in the integrated bearing 1000 and the rotating shaft and the bearing sleeve can rotate in the gap by using the electromagnetic bearing, thereby improving the low-speed performance of the integrated bearing 1000, prolonging the service life of the integrated bearing 1000 and improving the safety and reliability of the integrated bearing 1000 and the whole rotor system.

In an embodiment of the present invention, the fifth stator 10032 may be integrally formed with the third bearing housing 1001, and the sixth stator 10033 may be detachably connected with the third bearing housing 1001.

In the embodiment of the present invention, dynamic pressure generating grooves may be disposed in both the radial sub-bearing 1002 and the thrust sub-bearing 1003, wherein the dynamic pressure generating grooves are disposed in the radial sub-bearing 1002 in the following structural form:

the radial sub-bearing 1002 is provided with fourth dynamic pressure generating grooves 10023 toward a side wall of the rotating shaft 100, or a circumferential surface of the rotating shaft 100 toward the radial sub-bearing 1002.

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

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

Other embodiments of providing dynamic pressure generating grooves in the radial sub-bearing 1002 can be referred to in the twelfth embodiment, and the same advantageous effects can be achieved, and the description thereof will not be repeated.

In the embodiment of the present invention, dynamic pressure generating grooves may be disposed in both the radial sub-bearing 1002 and the thrust sub-bearing 1003, wherein the dynamic pressure generating grooves are disposed in the thrust sub-bearing 1003 in the following structural form:

the end surfaces of the third thrust disk 10031 facing the fifth stator 10032 and the sixth stator 10033 or the end surfaces of the fifth stator 10032 and the sixth stator 10033 facing the third thrust disk 10031 are provided with fifth dynamic pressure generating grooves 10035.

Further, the fifth dynamic pressure generating grooves 10035 are arranged radially or concentrically.

Further, the fifth 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, which is close to the second spiral groove, is connected with or disconnected from one end of the second spiral groove, which is close to the first spiral groove.

Other embodiments of the dynamic pressure generating grooves in the thrust sub-bearing 1003 described above may be referred to in the description of the tenth embodiment, and the same advantageous effects may be achieved, and for avoiding repetition, description thereof will be omitted.

In the embodiment of the present invention, the dynamic pressure generating grooves are provided in the integrated bearing 1000, so that the integrated bearing 1000 includes a dynamic pressure gas bearing. Under the condition that the electromagnetic bearing and the dynamic pressure gas bearing are simultaneously arranged, 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 be provided with a static pressure air inlet orifice, and its structural form is as follows:

the third bearing housing 1001 is also provided with a third static pressure inlet orifice 1007;

wherein, one end of the third static pressure air inlet orifice 1007 is connected with an external air source, and the other end is communicated with the fifth gap 1004 via the radial sub-bearing 1002, and/or is communicated with the sixth gap 1005 via the fifth stator 10032 and the sixth stator 10033, for delivering the external air source to the fifth gap 1004 and/or the sixth gap 1005.

In the embodiment of the present invention, a hydrostatic air inlet orifice may also be disposed through the integrated bearing 1000, so that the integrated bearing 1000 includes a hydrostatic bearing. In the case where both the electromagnetic bearing and the aerostatic bearing are provided, the bearing capacity of the integrated bearing 1000 can be further increased. In addition, the electromagnetic bearing and the gas hydrostatic bearing can mutually reserve, and when one of the electromagnetic bearing and the gas hydrostatic bearing fails or cannot meet the opening condition, the other can serve as a reserve bearing to play the same role. For example, in the case of detecting a failure of the electromagnetic bearing, the safety and reliability of the integrated bearing 1000 are improved by controlling the aerostatic bearing to be turned on to perform a corresponding action instead of the electromagnetic bearing.

Other embodiments of the above integrated bearing 1000 with static pressure air inlet orifices can be referred to in the tenth embodiment and the twelfth embodiment, and can achieve the same beneficial effects, and for avoiding repetition, description thereof will be omitted.

In the embodiment of the present invention, the radial sub-bearing 1002 and the thrust sub-bearing 1003 may be provided with sensors, and their structural forms are as follows:

a fifth sensor (not shown) is provided on the radial sub-bearing 1002, and a sensor probe of the fifth sensor is disposed in the fifth gap 1004.

In this way, parameters at the fifth gap 1004, such as the gas film pressure at the fifth 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 according to the detection result of the fifth sensor, and can achieve high control accuracy.

Optionally, each of 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 on the fifth magnetic bearing 10021, and a through hole for the fifth sensor probe to pass through is formed on the fifth magnetic bearing 10021; the second end of the fifth sensor probe passes through the through hole on the fifth magnetic bearing 10021 and extends to the fifth gap 1004, and the second end of the fifth sensor probe is flush with one side of the fifth magnetic bearing 10021 near 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 one side, close to the rotating shaft 100, of the fifth magnetic bearing 10021, so that on one hand, the sensor probe can be prevented from being touched by the rotating shaft 100, and the sensor probe can be protected; on the other hand, the air film in the fifth gap 1004 is not affected, and disturbance of the air film in the fifth gap 1004 is avoided.

A sixth sensor (not shown) is provided to the thrust sub-bearing 1003, and a sensor probe of the sixth sensor is provided in the sixth gap 1005.

In this way, parameters at the sixth gap 1005, such as the gas film pressure at the sixth 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 according to the detection result of the sixth sensor, and can achieve high accuracy of control.

Optionally, the sixth sensor includes a sixth sensor cover and a sixth sensor probe, the 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 arranged on the sixth magnetic bearing 10034; the second end of the sixth sensor probe passes through the through hole in the sixth magnetic bearing 10034 and extends to the sixth gap 1005, and the second end of the sixth sensor probe is flush with the side of the sixth magnetic bearing 10034 that is adjacent to the third 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, close to the third thrust disc 10031, of the sixth magnetic bearing 10034, so that on one hand, the sixth sensor probe can be prevented from being touched by the third thrust disc 10031, and the sixth sensor probe can be protected; on the other hand, the air film in the sixth gap 1005 is not affected, and disturbance of the air film in the sixth gap 1005 is avoided.

Other specific implementations of the radial bearing and the thrust bearing provided with the sensors can be referred to the related descriptions in the twelfth embodiment and the tenth embodiment respectively, and can achieve the same beneficial effects, and for avoiding repetition, the description is omitted.

It should be noted that, in the ninth embodiment to the twelfth embodiment, the related technical solutions are also applicable to the embodiments of the present invention, and the same beneficial effects can be achieved, so that the repetition is avoided and the description is omitted.

In the embodiment of the present invention, the specific control method when the integrated bearing (in which the eighth magnetic component in the fifth magnetic bearing is an electromagnet and the ninth magnetic component in the sixth magnetic bearing is an electromagnet) participates in the control process of the rotor system may be referred to the related description in the twelfth embodiment and the tenth embodiment, and the same beneficial effects may be achieved, so that repetition is avoided and no repetition is made.

The foregoing is merely illustrative 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 think about variations or substitutions within the technical scope of the present invention, and the invention should be covered. Therefore, the protection scope of the invention is subject to the protection scope of the claims.

Claims

1. A rotor system, comprising:

the rotating shaft is of an integral structure, and is vertically arranged;

the thrust bearing is arranged at a preset position on one side of the turbine, which is close to the compressor, wherein the preset position is a position capable of enabling the center of gravity of the rotor system to be located between the two radial bearings farthest from each other in the at least two radial bearings;

the at least two radial bearings comprise a first radial bearing and a second radial bearing, the first radial bearing is arranged on one side of the motor, which is far away from the compressor, and the second radial bearing is arranged between the compressor and the turbine; wherein the thrust bearing is disposed between the first radial bearing and the motor;

or the thrust bearing is arranged between the motor and the compressor;

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

at least one radial bearing in the at least two radial bearings is a gas-magnetic hybrid radial bearing or a gas dynamic-static pressure hybrid radial bearing;

when the second radial bearing is a gas-magnetic hybrid radial bearing, the magnetic component of the second radial bearing is arranged in a region, far away from the turbine, on the second radial bearing;

the air-magnetic hybrid thrust bearing is a foil type air-magnetic hybrid thrust bearing, and the foil type air-magnetic hybrid thrust bearing comprises: the first thrust disc is fixedly connected to the rotating shaft;

The first foil bearing is arranged between the first magnetic bearing and the first thrust disc, a first gap is formed between the first foil bearing and the first thrust disc, and the first foil bearing can move in the axial direction of the rotating shaft under the action of magnetic force between the first magnetic component and the second magnetic component;

the air-magnetic hybrid radial bearing is a foil type air-magnetic hybrid radial bearing or a slot type air-magnetic hybrid radial bearing, and the foil type air-magnetic hybrid radial bearing comprises: the third magnetic bearing is sleeved on the rotating shaft, and a plurality of fifth magnetic components are arranged on the third magnetic bearing along the circumferential direction;

wherein a third gap is formed between the second foil bearing and the rotating shaft, and the second foil bearing can move in the radial direction of the rotating shaft under the action of magnetic forces of the fifth magnetic components and the sixth magnetic components;

the groove type air-magnetic hybrid radial bearing comprises: the fourth magnetic bearing is sleeved on the rotating shaft, and a plurality of seventh magnetic components are arranged on the fourth magnetic bearing along the circumferential direction;

a fourth gap is formed between the fourth magnetic bearing and the rotating shaft, and the rotating shaft can move in the radial direction of the rotating shaft under the action of the magnetic force of the seventh magnetic components;

the fourth magnetic bearing is also provided with a second static pressure air inlet orifice, one end of the second static pressure air inlet orifice is communicated with the fourth gap, and the other end of the second static pressure air inlet orifice is connected with an external air source and used for conveying the external air source into the fourth gap;

in the rotor system, the thrust bearing and a radial bearing adjacent to the thrust bearing are integrated into a whole to form an integrated bearing, the integrated bearing comprising: the third bearing shell is a hollow revolving body and is provided with a first accommodating cavity and a second accommodating cavity;

the thrust sub-bearing comprises a third thrust disc, and a fifth stator and a sixth stator which are respectively arranged at two sides of the third thrust disc, the third thrust disc is fixedly connected to the rotating shaft, and the fifth stator and the sixth stator are respectively arranged on the rotating shaft in a penetrating way; a sixth gap is formed between each of the fifth stator and the sixth stator and the third thrust disk;

The radial sub-bearing comprises a fifth magnetic bearing sleeved on the rotating shaft, a fifth gap is formed between the fifth magnetic bearing and the rotating shaft, and a plurality of eighth magnetic components are arranged on the fifth magnetic bearing along the circumferential direction; the rotating shaft can move in the radial direction of the rotating shaft under the action of the magnetic force of the eighth magnetic components;

each of the fifth stator and the sixth stator includes a sixth magnetic bearing on which a plurality of ninth magnetic members are circumferentially arranged; a tenth magnetic part is arranged on the third thrust disc, and the third thrust disc can move in the axial direction of the rotating shaft under the action of magnetic force between the ninth magnetic parts and the tenth magnetic part;

the third bearing shell is also provided with a third static pressure air inlet orifice;

2. The rotor system of claim 1, wherein the rotor system comprises a plurality of rotor blades,

the at least two radial bearings further comprise a third radial bearing, the third radial bearing being arranged between the motor and the compressor.

3. The rotor system of claim 2, wherein the rotor system comprises a plurality of rotor blades,

the at least two radial bearings further comprise a fourth radial bearing, and the fourth radial bearing is arranged on one side of the turbine far away from the compressor; wherein the thrust bearing is disposed between the first radial bearing and the motor;

or the thrust bearing is arranged between the motor and the compressor;

4. A rotor system according to claim 3, wherein,

the fourth radial bearing is a gas dynamic-static pressure mixed radial bearing.

5. The rotor system of claim 1, wherein the rotor system comprises a plurality of rotor blades,

and a heat insulation layer is arranged on one side of the turbine, which is close to the second radial bearing.

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

7. The rotor system of claim 1, wherein the motor is a heuristic-integrated motor.

8. The rotor system of claim 1, wherein the rotor system comprises a plurality of rotor blades,

the rotor system further comprises a locking device for locking the shaft when the shaft is stationary.

9. The rotor system of claim 1, wherein the rotor system comprises a plurality of rotor blades,

the part of the rotating shaft, on which the bearing is arranged, is coated with an anti-wear coating.

10. A control method of a rotor system for a rotor system according to any one of claims 1 to 9, characterized in that the method comprises: opening hydrostatic bearings in the radial bearing and the thrust bearing to enable the rotating shaft to move to a preset radial position, and enabling a thrust disc of the thrust bearing to move to a preset axial position;

11. A control method of a rotor system for a rotor system according to any one of claims 1 to 9, characterized in that the method comprises: opening hydrostatic bearings in the radial bearing and the thrust bearing to enable the rotating shaft to move to a preset radial position, and enabling a thrust disc of the thrust bearing to move to a preset axial position;

during the shutdown of the rotor system, when the rotor system is decelerated to the first-order critical speed or the second-order critical speed, a hydrostatic bearing in the radial bearing and the thrust bearing is started;

12. The method of claim 11 for the rotor system of claim 1, wherein opening a hydrostatic bearing of the thrust bearings to move a thrust disc of the thrust bearings to a preset axial position comprises: opening first magnetic bearings in the first stator and the second stator, and controlling the first thrust disk to move in the axial direction of the rotating shaft under the action of magnetic forces of the plurality of first magnetic components so that the first gap between the first thrust disk and the first foil bearing in the first stator is equal to the first gap between the first thrust disk and the first foil bearing in the second stator;

The method further comprises the steps of:

13. The method of claim 11 for use in a rotor system as recited in claim 1, wherein opening a hydrostatic bearing of the radial bearings to move the shaft to a preset radial position comprises: starting the third magnetic bearing, and controlling the rotating shaft to move in the radial direction of the rotating shaft under the action of the magnetic force of the plurality of fifth magnetic components so as to enable the rotating shaft to move to a preset radial position;

The method further comprises the steps of:

14. The method of claim 11 for use in a rotor system as recited in claim 1, wherein opening a hydrostatic bearing of the radial bearings to move the shaft to a preset radial position comprises: opening the fourth magnetic bearing, and controlling the rotating shaft to move in the radial direction of the rotating shaft under the action of the magnetic force of the seventh magnetic components so as to enable the rotating shaft to move to a preset radial position;

the method further comprises the steps of:

15. The method of claim 11 for use in a rotor system as recited in claim 1, wherein opening a hydrostatic bearing of the radial bearings to move the shaft to a preset radial position comprises: opening the fourth magnetic bearing; and/or starting an external air source, and conveying air to the fourth gap through the second static pressure air inlet throttle hole;

16. A gas turbine generator set comprising an inlet duct, a combustion chamber and a rotor system according to any one of claims 1 to 9, the inlet duct being in communication with the air inlet of the compressor, the air outlet of the compressor being in communication with the air inlet of the combustion chamber, the air outlet of the combustion chamber being in communication with the air inlet of the turbine.

17. A control method for a gas turbine generator set as set forth in claim 16, wherein the method includes: opening hydrostatic bearings in the radial bearing and the thrust bearing to enable the rotating shaft to move to a preset radial position, and enabling a thrust disc of the thrust bearing to move to a preset axial position;