CN117052491A - Magnetic suspension supporting system of thin-wall drum blade disc rotor and gas turbine thereof - Google Patents

Abstract

The invention relates to the technical field of gas turbines, in particular to a magnetic suspension supporting system of a thin-wall drum blade disc rotor and a gas turbine thereof, wherein the magnetic suspension supporting system comprises a low-temperature end magnetic bearing system, a casing, a gas turbine rotor, a sealing structure, a high-temperature end magnetic bearing system, a temperature detection and control system and a high-temperature-resistant busbar; the gas turbine rotor is arranged in the casing, the low-temperature end of the gas turbine rotor is supported by the low-temperature end magnetic bearing system, and the high-temperature end of the gas turbine rotor is supported by the high-temperature end magnetic bearing system; the sealing structure is used for connecting the magnetic bearing system and the gas turbine rotor; the low-temperature-end high-temperature-resistant bus is led out from the high-temperature-end magnetic bearing system and is connected to a control terminal box in the temperature detection and control system. Compared with the prior art, the magnetic suspension supporting system designed by the invention can realize the supporting of the thin-wall drum rotor system by the design of the discrete internal and external actuators, weaken the influence of high-temperature environment on the thin-wall drum rotor and improve the running stability of the thin-wall drum rotor.

Description

Magnetic suspension supporting system of thin-wall drum blade disc rotor and gas turbine thereof

Technical Field

The invention relates to the technical field of gas turbines, in particular to a magnetic suspension supporting system of a thin-wall drum blade disc rotor and a gas turbine thereof.

Background

The gas turbine is a rotary power machine which uses continuously flowing gas as working medium and converts heat energy into mechanical work, and the design of the hollow shaft is an important structural form for realizing high rigidity, low weight and excellent running performance. The thin-walled drum rotor of blades operating in a high temperature environment is a core component of a gas turbine, and during operation of the gas turbine, the ambient temperature around the rotor can reach above 1000 ℃, which can lead to significant thermal deformation of the thin-walled rotor. The magnetic bearing has the advantages of no contact, no abrasion, high rotating speed, high safety and the like, the rotating speed and the service life of the magnetic bearing can be effectively improved when the magnetic bearing is applied to a thin-wall rotor structure of a gas turbine, but the rotor system of the gas turbine is subjected to the action of high-temperature alternating load, the generated thermoelastic coupling vibration often makes the vibration of the existing magnetic bearing system difficult to control, and the design of a complex disc-sheet-shaft structure of the gas turbine, the design of a sensor wiring arrangement structure, the singleness of a rotor mode of the magnetic bearing control and the imperfection of a temperature compensation design can make the conventional magnetic bearing difficult to be applied to the rotor of the gas turbine, so the design of a magnetic suspension supporting system under the action of high-temperature heat load is particularly important.

Because of the trend of continuously improving the speed and efficiency of the rotary machine, the gaps between the blades and the casing and between the blades and the seal of the gas turbine are gradually reduced, and unbalance of a rotor system, bending of a rotating shaft and the like are extremely easy to cause friction faults of the rotor, so that the system is unstable and a series of adverse effects are caused. Therefore, the design of the arrangement mode of the magnetic suspension bearing, the design of the control system and other parts are very important to the improvement of the bearing capacity, the stability and the like of the magnetic bearing. The utility model patent 202121991379.9 designs a magnetic suspension gas turbine rotor, which adopts a magnetic bearing to support the rotor, and adopts an integrated disc drum structure for the compressor rotor, so that the stability of the whole machine is improved. The utility model patent 202121081931.0 discloses a gas turbine hollow rotor structure supported by magnetic bearings, which adopts the magnetic bearings and adopts a two-stage turbine structure for cooling air of blades through flow. The 202121876726.3 gas turbine adopts an air bearing, the traditional fixed support is omitted, and the service life and the performance of the whole miniature gas turbine are improved by adopting the air bearing. The utility model patent 202210422896.7 proposes a magnetic bearing nonlinear control system with variable working points, in which only one set of outside actuators controls the rotor with lower control accuracy than the outside and inside synchronous setting actuators. The 202220052437.X designs an integrated structure of a magnetic suspension bearing and a displacement sensor, wherein the integrated structure is circumferentially provided with 4 radial displacement sensors and 2 axial displacement sensors in the radial direction, and the design is not suitable for the condition that the displacement of the whole circle is changed in the rotation process of a flexible rotor.

In the prior art, the gas turbine rotor supported by the magnetic bearing, the magnetic bearing structure, the magnetic bearing fixed supporting structure and the internal sensor wiring structure are not disclosed enough; the common unidirectional actuator controls the suction force to be generated only in one direction, which is likely to lead the actuator which needs to provide the suction side to be obviously deformed by heat, and the deformation of the thin-wall rotor is more obvious under the action of the suction force and the thermal deformation, so that friction is generated; also if there is no temperature compensation link, the control of a single magnetic bearing may also have an influence of control imbalance under the influence of high temperature alternation of the gas turbine, and once such a situation occurs, the rub-impact fault of the blade and the casing will be caused.

In view of the above, there is a lack of a magnetic levitation support system for thin-walled drum bladed disk rotors in high temperature environments and gas turbines therefor.

The principle analysis is carried out on three common magnetic bearing models in the prior art, and the working principle and advantages of the magnetic bearing model selected by the invention are given through the analysis. The three magnetic bearing principles are analyzed as follows:

the design schematic diagram of the magnetic bearing model A is shown in fig. 1, the magnetic bearing model A consists of a displacement sensor and an actuator, and the actuator and the displacement sensor in the thin-wall rotor are uniformly distributed along the circumference; when the rotor is concavely deformed, the actuator is close to the rotor, and the electromagnetic attraction force is increased; the rotor system requires a reduction in electromagnetic attraction force, which can only be achieved by reducing the control current of the actuator, but it is difficult to obtain an appropriate electromagnetic force. The thin-wall rotor magnetic bearing model is suitable for rigid rotors which are not easy to deform and is not suitable for thermoelastic coupling flexible rotor systems.

Magnetic bearing model B schematic design As shown in FIG. 2, two actuators of the magnetic bearing are differential to generate electromagnetic force, one of the actuators is driven by current I _X And control current I _O Driven by the sum of the currents, the other actuator having a phase angle of 180 DEG, driven by the current I _X And control current I _O The actuator can only generate attractive force in one direction driven by the difference. As the deformation of the rotor top approaches the top actuator, the bottom actuator is required to generate an attractive force. However, if the deformation of the bottom side is also close to the bottom actuator at this time, the attractive force applied to the bottom of the rotor easily causes a friction phenomenon. Neglecting external loads, the vibration shape of the unconstrained thin-walled rotor under thermal loading is irregular (see the discussion of results below), and the friction phenomenon described above can occur between the rotor and the actuator. This differential control model is applicable to non-deformable rigid rotors, and is not applicable to thermoelastically coupled flexible rotors.

The design schematic diagram of the magnetic bearing model C is shown in fig. 3, and the control unit of the magnetic bearing consists of a pair of actuators and a sensor, and a plurality of control units are uniformly distributed along the circumferential direction of the thin-wall drum. At each position acted by electromagnetic force, a pair of actuators are operated by differential control described in model B to regulate the effect of thermal deformation. The magnetic bearing model is more suitable for flexible thin-wall rotors with thermal deformation.

FIG. 4 is a graph showing the vibration response of three magnetic bearing rotor models, FIG. 4 (a) is a graph showing the displacement-current time response of the magnetic bearing actuators at the left and right ends of the magnetic bearing model A, FIG. 4 (a) is a graph showing the displacement-current time response of one of the actuators at the left end of the magnetic bearing, and FIG. 4 (a) is a graph showing the displacement-current time response of one of the actuators at the right end of the magnetic bearing; it was found that within 0.03s the displacement at the actuator had exceeded the air gap (0.5 mm), which caused the blade to rub against the magnetic bearing. FIG. 4 (B) shows the thermo-elastic coupling vibration mode of the thin-walled rotor without constraint, wherein the thermo-elastic coupling vibration mode of the two ends of the rotor along the circumferential direction is irregular, and the friction phenomenon between the rotor and the actuator can occur due to the selection of the magnetic bearing model B; fig. 4 (C) shows the displacement-current time response of the magnetic bearing model C at the left and right magnetic bearing actuators, fig. 4 (C) shows the lower displacement-current time response of the magnetic bearing at the left end, and the lower panel shows the lower displacement-current time response of the magnetic bearing at the right end, and it can be found that the current curve and the deformation curve at the actuators are both antisymmetric, which can help the rotor to be stabilized at the equilibrium position, and the thermoelastic coupling vibration response is stable and controllable, which indicates that the magnetic bearing model C is suitable for a thin-walled drum flexible rotor system with thermoelastic coupling vibration.

Disclosure of Invention

The invention aims to provide a magnetic suspension supporting system of a thin-wall drum blade disc rotor, which is based on the principle of a magnetic bearing model C in the background technology to realize the supporting of the thin-wall drum rotor system of thermoelastic coupling vibration.

The technical solution for realizing the purpose of the invention is as follows: a magnetic suspension supporting system of a thin-wall drum blade disc rotor comprises a low-temperature end magnetic bearing system, a casing, a gas turbine rotor, a sealing structure, a high-temperature end magnetic bearing system, a temperature detection and control system and a high-temperature resistant bus; the gas turbine rotor is arranged in the casing, and is supported by the low-temperature end magnetic bearing system and the high-temperature end magnetic bearing system; the sealing structure is used for sealing the high-temperature end magnetic bearing system and the low-temperature end magnetic bearing system with the rotor of the gas turbine; the high-temperature-resistant bus at the high-low temperature end is led out from the magnetic bearing system and is connected to a control terminal box in the temperature detection and control system; an execution control unit is arranged in the high-temperature end magnetic bearing system and the low-temperature end magnetic bearing system and used for generating magnetic force to support the rotor of the gas turbine; the temperature detection and control system is used for detecting, controlling and regulating the stable operation of the gas turbine; the control execution unit comprises an outer ring actuator, an inner ring actuator and a displacement sensor. A gas turbine comprising a magnetically levitated support system of a thin-walled drum blisk rotor as claimed in any of claims 1-11.

A gas turbine comprising a magnetically levitated support system of a thin-walled drum blisk rotor according to any of claims 1-11.

Compared with the prior art, the invention has the remarkable advantages that:

1. the scheme designs a magnetic suspension bearing actuator with two discrete ends for application to a thin-wall rotor aiming at thermoelastic coupling vibration caused by a high-temperature environment. A control actuator unit of the magnetic bearing is composed of a pair of inner and outer actuators and a displacement sensor, and at each position acted by electromagnetic force, the pair of actuators are differentially controlled to generate electromagnetic force to weaken the influence of thermal deformation; the control execution units are uniformly distributed at the two ends of the thin-wall rotor along the circumferential direction, so that the deformation of any one point position at the two ends of the rotor can be detected through the control execution units, the effective control under thermoelastic coupling vibration is realized, and the running stability of the rotor is improved.

2. The scheme designs a temperature compensation scheme (changing with time) aiming at the characteristic that the high temperature alternation of the thin-wall rotor of the gas turbine is severe and the axial temperature gradient distribution is overlarge under the action of high temperature load. The magnitude of the axial thermal gradient of the thin-wall rotor can be changed due to different constant exhaust temperatures, and when the load of the gas turbine suddenly increases or decreases, the thin-wall rotor can be bent and deformed to cause friction between the blades and the casing. The thermocouple sensors in the casing designed by the scheme are axially arranged at the air inlet and the air outlet for detecting the axial temperature gradient of the thin-wall rotor, when the change of the ambient temperature of the rotor is detected, the controller parameters are corrected in time through signals collected by the thermocouple sensors, and the discrete distributed control actuator receives the signals and adjusts the electromagnetic force to inhibit the thermal vibration of the thin-wall rotor system, so that the temperature compensation of the system is realized. And secondly, the unique information of the thin-wall rotor can be detected through a displacement sensor in the internal actuator bracket, if the position of the rotor is deviated in the running process, the fault early warning system can react, and at the moment, the PD parameter is regulated again to stably control the rotor system.

3. The design is designed for the complex disk-sheet-shaft structure of the gas turbine combined with the internal airflow, and the discrete distributed multi-actuator magnetic bearing structure is realized by arranging the design of the controller circuit, the design of the sealing ring, the design of the multi-actuator mounting and fixing structure, the design of the flow guiding impeller and the like, so that the complex thin-wall rotor magnetic bearing system is simple in structure and convenient to install.

4. Two inner actuator fixing support mounting modes are provided, and different thin-wall rotor requirements are met. First kind: the thin-wall rotor structure is short and small, and the turbine stage number is small. Second kind: the long-span thin-wall rotor has more turbine stages, and the inner and outer ring actuator supports cannot be designed into an integrated structure due to the complex internal structure of the gas turbine, so that an inner ring actuator connecting support is designed and installed inside the multistage bladed disk rotor of the gas turbine; the low temperature end of the gas turbine rotor is provided with an integrated inner ring and outer ring actuator bracket, the high temperature end is provided with another inner ring actuator bracket, and the two are connected through an inner ring actuator connecting bracket.

Drawings

FIG. 1 is a schematic diagram of a magnetic bearing model A; wherein, (a) is a schematic diagram of an installation structure of the magnetic bearing model A, and (b) is a cross-sectional view of an internal structure of the thin-wall rotor of the magnetic bearing model A;

FIG. 2 is a schematic diagram of a magnetic bearing model B design;

FIG. 3 is a schematic diagram of a magnetic bearing model C;

FIG. 4 is a graph of the comparative effects of three magnetic bearing models; wherein, (a) is the displacement-current time response of the magnetic bearing 90 DEG actuator at the left end and the right end of the magnetic bearing model A; (b) The shape of thermoelastic coupling vibration of the unconstrained thin-wall rotor of the magnetic bearing model B is adopted; (c) The displacement-current time response of the 90-degree actuator of the magnetic bearing at the left end and the right end of the magnetic bearing model C is obtained; wherein, (b 1) is a perspective view of the shape of the thermoelastic coupling vibration, (b 2) is a plane projection view of the shape of the thermoelastic coupling vibration,

FIG. 5 is a schematic diagram of the overall structure of a magnetic levitation support system;

FIG. 6 is a cross-sectional view of the general structure of the magnetic levitation support system;

FIG. 7 is an exploded view of a magnetic levitation support system;

FIG. 8 is an exploded view of a low temperature end magnetic bearing system;

FIG. 9 is an overall block diagram of a low temperature end magnetic bearing system;

FIG. 10 is a cross-sectional view of the general structure of the low temperature end magnetic bearing system;

FIG. 11 is a partial cross-sectional view of the inner and outer actuators of the low temperature end magnetic bearing system;

FIG. 12 is a cross-sectional view of a stationary diaphragm at the low temperature end of a gas turbine;

FIG. 13 is a schematic view of the structure of the low temperature end internal and external actuator support;

FIG. 13 (a) is a schematic view of the structure of the inner and outer actuator support at the low temperature end, wherein (a) is a schematic view of the end face of the inner and outer actuator support at the low temperature end, and (b) is a sectional view of the inner and outer actuator support at the low temperature end;

FIG. 14 is a schematic view of a stationary diaphragm at the low temperature end of a gas turbine;

FIG. 15 is an assembly view of the low temperature end inner and outer actuator mount and the actuator;

FIG. 16 is a schematic view of a low temperature end inner and outer actuator support;

FIG. 17 is a schematic diagram of an inner and outer magnetic bearing system actuator;

FIG. 18 is an exploded view of a high temperature end magnetic bearing system;

FIG. 19 is an overall block diagram of a high temperature end magnetic bearing system;

FIG. 20 is a cross-sectional view of the general structure of the high temperature end magnetic bearing system;

FIG. 21 is a partial cross-sectional view of the high temperature end magnetic bearing system at the inner and outer actuators;

FIG. 22 is a schematic view of a high temperature end stationary guide vane disk of a gas turbine;

FIG. 23 is an assembly view of the high temperature end internal and external actuator mount and the actuator;

FIG. 24 is a schematic view of a high temperature end internal and external actuator support;

FIG. 25 is a schematic diagram of a magnetic levitation support system seal configuration;

FIG. 26 is a cross-sectional view of the overall structure of a gas turbine multi-stage disk rotor magnetic bearing support system with magnetic bearings supported;

FIG. 27 is an exploded view of the overall structure of a gas turbine multi-stage blisk rotor magnetic bearing support system;

FIG. 28 is an exploded view of the overall structure of a gas turbine multi-stage blisk rotor high temperature end magnetic bearing system;

FIG. 29 is a general block diagram of a gas turbine multi-stage blisk rotor high temperature end magnetic bearing system;

FIG. 30 is a cross-sectional view of the overall structure of a gas turbine multi-stage blisk rotor high temperature end magnetic bearing system;

FIG. 31 is a partial cross-sectional view of the gas turbine multi-stage blisk rotor high temperature end magnetic bearing system at the inner and outer actuators;

FIG. 32 is a schematic view of a stationary diaphragm at the high temperature end of a gas turbine multi-stage diaphragm rotor;

FIG. 33 is an assembly view of the high temperature end inner and outer actuator supports and actuators of the multi-stage blisk of the gas turbine;

FIG. 34 is a schematic view of a gas turbine multi-stage disk height Wen Waijuan actuator support;

FIG. 35 is a schematic view of a gas turbine multi-stage disk height Wen Najuan actuator support;

FIG. 36 is an assembly view of a gas turbine multi-stage blisk inner ring actuator bracket connection;

FIG. 37 is a schematic view of a gas turbine multi-stage blisk rotor inner race actuator attachment bracket;

FIG. 38 is a block diagram of a case internal temperature sensor compensation control;

1-a low temperature end magnetic bearing system; 2-a case; 3-controlling a terminal box; 4-a gas turbine rotor; 5-sealing structure; 6-high temperature end magnetic bearing system; 7-thermocouple sensors; 8-a high-temperature-resistant bus; 9-a low-temperature end static flow guide impeller; 10-a low-temperature end internal and external actuator support; 11-a magnetic core; 12-an outer ring actuator; 13-an inner ring actuator; 14-a displacement sensor; 15—first thickened stator blades; 16-connecting plates of the diversion disc of the low-temperature end casing; 17-a low-temperature diversion leaf disc arc-shaped diversion plate; 18-a high-temperature-resistant bus threading hole at the low temperature end; 19-connecting the low-temperature guide vane disc with the casing to form a mounting hole; 20-a control execution unit lead integration box; 21-a displacement sensor mount; 22-a low-temperature end internal and external actuator support control execution unit line collecting groove; 23-an outer actuator fixing plate of an inner actuator bracket and an outer actuator bracket at the low temperature end; 24-fixing the mounting hole of the external actuator of the low-temperature end; 25-fixing the mounting hole of the actuator in the low-temperature end; 26-an inner actuator fixing plate of an inner actuator bracket and an outer actuator bracket at the low temperature end; 27-a low-temperature end reinforcing rib; 28-an actuator core; 29-actuator core rivet holes; 30-an actuator coil; 31-a high temperature end internal and external actuator support; 32-a high-temperature end static flow guide impeller; 33-high-temperature guide vane arc guide plates; 34-high-temperature-end high-temperature-resistant bus threading holes; 35-a high-temperature end casing guide plate connecting plate; 36-connecting the high-temperature guide vane disc with the casing to form a mounting hole; 37-a displacement sensor mount; 38-an inner actuator fixing plate of an inner actuator bracket and an outer actuator bracket at the high temperature end; 39-inner actuator fixed mounting holes; 40-outer actuator fixed mounting holes; 41-an outer actuator fixing plate of an inner actuator bracket and an outer actuator bracket at the high temperature end; 42-high temperature end reinforcing ribs; 43-sealing structure and baffle connection plate; 43-1-a seal structure and disk attachment slot; 44-a multi-stage disk rotor low temperature end magnetic bearing system; 45-gas turbine multi-stage blisk rotor; 46-a second sealing structure; 47-high temperature resistant bus of multi-stage impeller rotor; 48-a second terminal control box; 49-a second casing; 50-a high-temperature end magnetic bearing system of a multistage leaf disc rotor; 51-a connecting bracket of an inner ring actuator of the multistage leaf disc rotor; 52-a multi-stage blisk rotor thermocouple sensor; 53-multi-stage blade height Wen Najuan actuator mount; 54-multistage blade height Wen Waijuan actuator support; 55-multistage leaf disc height Wen Daoliu leaf discs; 56-high temperature guide vane hollow sheet structure; 57-multistage leaf disc rotor case guide disc connecting plate; 58-connecting the high-temperature guide vane disk of the multistage vane disk rotor with the casing through a mounting hole; 59-a multistage leaf disc rotor high-temperature guide leaf disc arc-shaped guide plate; 60-a high-temperature outer ring actuator support actuator fixing plate; 61-mounting holes of the high-temperature outer ring fixing support actuator; 62-multistage leaf disc rotor reinforcing ribs; 63-inner ring actuator mounting bracket mounting holes; 64-high temperature inner ring actuator support actuator fixing plate; 65-high temperature inner ring actuator support actuator mounting holes; 66-a multi-stage blisk rotor control execution unit lead integration box; 67-high-temperature inner ring fixed support control execution unit line collecting groove; 68-high-temperature inner ring fixed support displacement sensor mounting seats; 69-fixing a bracket connecting rod on the low-temperature inner ring; and 70-fixing a bracket connecting rod on the high-temperature inner ring.

Detailed Description

The invention is further described with reference to the drawings and specific embodiments.

Example 1

As shown in fig. 5-7, the magnetic suspension supporting system of the thin-wall drum blade disc rotor disclosed by the invention comprises a low-temperature end magnetic bearing system 1, a casing 2, a gas turbine rotor 4, a sealing structure 5, a high-temperature end magnetic bearing system 6, a temperature detection and control system and a high-temperature-resistant bus 8. As shown in fig. 6, a gas turbine rotor 4 (thin-walled drum rotor) is provided inside the casing 2, both ends of the gas turbine rotor 4 being supported by two magnetic bearing systems, the low temperature end thereof being supported by the low temperature end magnetic bearing system 1, and the high temperature end thereof being supported by the high temperature end magnetic bearing system 6; the low-temperature end magnetic bearing system 1 and the gas turbine rotor 4 are connected through a sealing structure 5, and the sealing structure of the high-temperature end magnetic bearing system 6 is designed to be integrated with the high-temperature end static guide vane disk and connected with the gas turbine rotor 4. One end of the low-temperature-end high-temperature-resistant bus 8 is led out from the low-temperature-end magnetic bearing system 1, the other end of the low-temperature-end high-temperature-resistant bus is connected with the control terminal box 3 in the temperature detection and control system, one end of the high-temperature-end high-temperature-resistant bus 8 is led out from the high-temperature-end magnetic bearing system 6, and the other end of the high-temperature-end high-temperature-resistant bus is connected with the control terminal box 3 in the temperature detection and control system. The temperature detection and control system is arranged on the casing and is used for detecting the temperature inside the gas turbine and controlling the magnetic suspension bearing to realize the stable operation of the rotor of the gas turbine.

As shown in fig. 8, the low temperature end magnetic bearing system 1 comprises a low temperature end static guide vane 9, a low temperature end inner and outer actuator bracket 10, a magnetic core 11, an outer ring actuator 12, an inner ring actuator 13 and a displacement sensor 14. Referring to fig. 5, an outer ring of the low-temperature-end static guide vane disk 9 is riveted on the inner wall of the casing 2, and as shown in fig. 9 and 10, an inner ring of the low-temperature-end static guide vane disk 9 is fixedly connected with an outer ring of the low-temperature-end inner and outer actuator bracket 10; as shown in fig. 11, the magnetic core 11 is made of soft magnetic ferrite material, has good magnetoelectric performance, and the outer ring of the magnetic core 11 is concentrically and rotatably arranged with the inner ring of the low-temperature end inner and outer actuator bracket 10; the inner ring of the magnetic core 11 is in interference fit with the low temperature end of the gas turbine rotor 4. The internal and external actuators thus generate magnetic field forces to support the magnetic core 11 and thus the gas turbine rotor 4.

As shown in fig. 8 and 10, a set of control execution units includes an outer ring actuator 12, an inner ring actuator 13, and a displacement sensor 14; as shown in fig. 15, the plurality of groups of control execution units are uniformly arranged and fixedly installed in the inner and outer actuator brackets 10 at the low temperature end along the circumferential direction. The magnetic field force generated by the internal and external actuators due to the differential control is used to support the rotation of the gas turbine rotor 4, and the displacement sensor 14 is used to detect the displacement of the gas turbine rotor 4. The low temperature end of the embodiment adopts 15 groups of control execution units, the number of the inner and outer ring actuators is the same, and the differential control of the inner and outer ring bidirectional actuators is adopted, so that the number of the control execution units can be increased singly according to the control precision and the actual structure, such as 16 groups, 17 groups or 18 groups.

As shown in fig. 12 and 14, the low-temperature-end static guide vane 9 of the gas turbine comprises a first thickened vane 15, a low-temperature-end casing guide vane connecting plate 16, a low-temperature guide vane arc guide plate 17, a low-temperature-end high-temperature-resistant bus threading hole 18 and a low-temperature guide vane and casing connecting mounting hole 19. As shown in fig. 14, 8 low-temperature guide vane plates and a casing connection mounting hole 19 uniformly distributed along the circumferential direction are distributed on the casing guide vane connecting plate 16 and are used for fixedly connecting the casing 2 through rivets. As shown in fig. 12, the low temperature end casing guide plate connecting plate 16 is internally and uniformly provided with a common blade, a first thickened blade 15 and a second thickened blade, the first thickened blade 15 and the second thickened blade are axially symmetrically installed, and the thicknesses of the blades are the same for keeping the balance of the guide blade plate structure. The inner rings of the blades are fixedly provided with the low-temperature guide vane disk arc-shaped guide plates 17, and the surfaces of the low-temperature guide vane disk arc-shaped guide plates 17 are of arc-shaped structures, so that the flow resistance of air flow can be reduced, and the air flow in the casing 2 is uniformly dispersed. The structural design of the stationary guide vane disk 9 at the low temperature end does not cause the problem of blocking the circulation of air flow in the gas turbine due to the installation of the inner and outer actuator brackets. As shown in fig. 12, a through hole of the low-temperature-end high-temperature-resistant bus threading hole 18 is formed from the low-temperature-end casing guide plate connecting plate 16 to the first thickened blade 15.

As shown in fig. 16, with reference to fig. 13, the low-temperature-end inside and outside actuator support 10 includes a control execution unit lead integration box 20, a low-temperature-end displacement sensor mount 21, a low-temperature-end inside and outside actuator support control execution unit line collection groove 22, a low-temperature-end inside and outside actuator support outside actuator fixing plate 23, a low-temperature-end outside actuator fixing mounting hole 24, a low-temperature-end inside actuator fixing mounting hole 25, a low-temperature-end inside and outside actuator support inside actuator fixing plate 26, and a low-temperature-end reinforcing rib 27. The low-temperature end inner and outer actuator support outer actuator fixing plates 23 and the low-temperature end inner actuator fixing plates 26 are uniformly distributed in 15 groups along the circumferential direction of the low-temperature end inner and outer actuator support 10; two low-temperature end outer actuator fixing mounting holes 24 are formed in each group of low-temperature end outer actuator fixing plates 23 and are used for fixedly connecting the outer ring actuators 12 through rivets, and two inner actuator fixing mounting holes 25 are formed in each group of low-temperature end inner actuator fixing plates 26 and are used for fixedly connecting the inner ring actuators 13 through rivets; 15 low-temperature end displacement sensor mounting seats 21 are uniformly distributed on the inner ring of the low-temperature end inner and outer actuator bracket 10 along the circumferential direction and are used for mounting the displacement sensors 14; the outer ring of the inner and outer actuator bracket 10 of the low temperature end is uniformly distributed with 15 low temperature end reinforcing ribs 27 along the circumferential direction for enhancing the strength and rigidity of the guide vane disk, so as to save the material consumption, reduce the weight and reduce the cost.

As shown in fig. 13, the control execution unit lead wire integration box 20 of the inner and outer low-temperature end actuator support is located at a radial position of the outer side surface of the inner and outer low-temperature end actuator support, the control execution unit wire collection groove 22 is located at the outer side surface of the inner and outer low-temperature end actuator support and takes the shape of a circular ring, and the circle center of the circular ring is concentric with the outer side surface.

As shown in fig. 11-13, the control execution unit lead of the low-temperature end magnetic bearing system is led out from the control execution unit, passes through the displacement sensor mounting seat 21 or the inner and outer actuator fixing plate, extends into the low-temperature end inner and outer actuator support control execution unit wire collecting groove 22, is collected in the control execution unit lead integrated box 20, and is integrated into a high-temperature resistant bus 8, passes through the low-temperature end high-temperature resistant bus threading hole 18, and is led out from the casing 2 wall, and is connected with the terminal control box 3.

As shown in fig. 17, the inner and outer ring actuators of the magnetic bearing system have the same structure, each actuator comprises an actuator core 28 and an actuator coil 30, the actuator core 28 is made of silicon steel material such as aluminum-iron-boron, and the like, and the actuator core 28 is wound with the actuator coil 30 in an i shape; the actuator coil 30 is longitudinally arranged for 12 turns along the i-shaped actuator core 28 for energizing to thereby generate electromagnetic force; the actuator core 28 is provided with an actuator core rivet hole 29.

As shown in fig. 18, the high temperature end magnetic bearing system 6 includes a high temperature end stationary diaphragm 32, a high temperature end inner and outer actuator support 31, a magnetic core 11, an outer ring actuator 12, an inner ring actuator 13, and a displacement sensor 14. The outer ring of the high-temperature-end static guide vane 32 is riveted on the inner wall of the casing 2, as shown in fig. 19 and 20, and the inner ring of the high-temperature-end static guide vane 32 is fixedly connected with the outer ring of the high-temperature-end inner and outer actuator bracket 31; the outer ring of the magnetic core 11 is rotatably mounted concentrically with the inner ring of the high temperature end inner and outer actuator support 31, the inner ring of the magnetic core 11 is in interference fit with the high temperature end of the gas turbine rotor 4, and the mounting mode and the function are the same as those of the magnetic core 11 in the low temperature end magnetic bearing system 1.

As shown in fig. 18-20, the design principle and the structure of the control execution unit at the high temperature end are the same as those of the control execution unit at the low temperature end, the outer ring actuator 12, the inner ring actuator 13 and the displacement sensor 14 are fixedly installed in the inner and outer actuator bracket 31 at the high temperature end, one control execution unit comprises an outer ring actuator 12, an inner ring actuator 13 and a displacement sensor 14, a plurality of groups of control execution units are uniformly distributed in the circumferential direction of the inner and outer actuator bracket 31 at the high temperature end, and then the magnetic field force generated by the inner and outer actuators supports the thin-wall drum rotor, and the displacement sensor 14 is used for detecting the displacement of the gas turbine rotor 4. The high temperature end of the embodiment adopts 15 groups of control execution units, the number of the inner and outer ring actuators is the same, and the differential control of the inner and outer ring bidirectional actuators is adopted, so that the number of the control execution units can be singly increased according to the control precision and the actual structure, such as 16 groups, 17 groups or 18 groups.

As shown in fig. 22, the high temperature end stationary guide vane 32 includes a first thickened vane 15, a high Wen Daoliu vane arc guide plate 33, a high temperature end high temperature bus threading hole 34, a high temperature end casing guide vane connecting plate 35, and a high Wen Daoliu vane and casing connecting mounting hole 36. Referring to fig. 12, 21 and 22, the high Wen Daoliu disk arc baffle 33 is structurally different from the low temperature disk arc baffle 17 in that: as shown in fig. 21, the high Wen Daoliu leaf disc arc-shaped guide plate 33 is a hollow cavity with an inner and outer double-layer structure, the inner ring sheet of the high Wen Daoliu leaf disc arc-shaped guide plate 33 is fixedly connected to the inner and outer actuator bracket 31 at the high temperature end, and the outer ring sheet of the high leaf disc arc-shaped guide plate is added with a heat-insulating coating for preventing high temperature airflow heat conduction in the casing. As shown in fig. 22, 8 high Wen Daoliu blades evenly distributed along the circumferential direction are arranged on the outer ring of the high-temperature-end casing guide plate connecting plate 35, and the high-temperature-end static guide blade plates 32 are fixed on the casing 2 through rivets and fixedly connected through casing connecting mounting holes 36. The rest of the structures (such as the first thickened blade 15, the high-temperature-end high-temperature-resistant bus threading hole 34, the control execution unit lead integrated box 20 and the like) in the high-temperature-end static guide blade disk 32 are the same as the internal structure of the low-temperature-end static guide blade disk 9.

As shown in fig. 23, the high temperature end inside and outside actuator bracket 31 includes a high temperature end control execution unit lead integration box, a high temperature end displacement sensor mount 37, a high temperature end inside and outside actuator bracket displacement sensor wire collecting groove, a high temperature end inside actuator fixing plate 38, a high temperature end inside actuator fixing mounting hole 39, a high temperature end outside actuator fixing mounting hole 40, a high temperature end outside actuator fixing plate 41, and a high temperature end reinforcing rib 42. As shown in fig. 24, the high temperature end outer actuator fixing plates 41 and the high temperature end inner actuator fixing plates 38 are uniformly distributed in 15 groups along the circumferential direction, two high temperature end outer actuator fixing mounting holes 40 are formed in one group of the high temperature end outer actuator fixing plates 41, the outer ring actuator 12 is fixedly connected by rivets, two high temperature end inner actuator fixing mounting holes 39 are formed in the same group of the high temperature end inner actuator fixing plates 38, and the inner ring actuator 13 is fixedly connected by rivets. 15 high-temperature end displacement sensor mounting seats 37 are uniformly distributed on the inner ring of the high-temperature end inner and outer actuator bracket along the circumferential direction; the outer ring of the high-temperature end inner and outer actuator support is uniformly provided with 15 high-temperature end reinforcing ribs 42 along the circumferential direction, which are used for enhancing the strength and rigidity of the flow guide blade disc, so that the material consumption is saved, the weight is reduced, and the cost is reduced. The positions and the functions of the high-temperature end control execution unit lead integration box and the high-temperature end inner and outer executor support displacement sensor line collection groove are the same as those of the low-temperature end.

The control execution unit lead wire of the high-temperature end magnetic bearing system is led out from the control execution unit, passes through the high-temperature end displacement sensor mounting seat 37 or the high-temperature end inner and outer actuator fixing plate, extends into the high-temperature end inner and outer actuator support control execution unit wire collecting groove, is collected in the high-temperature end control execution unit lead wire integrated box, and is integrated into a high-temperature resistant bus 8 which passes through the high-temperature resistant bus threading hole 34 at the high-temperature end, and then is led out of the wall surface of the casing 2 to be connected with the terminal control box 3.

The gas turbine sealing structure 5 adopts a graphite sealing structure, and is high-temperature resistant and corrosion resistant. As shown in fig. 25, the sealing structure 5 comprises a sealing structure and a baffle connection plate 43 and a sealing structure and a vane connection groove 43-1, wherein the sealing structure and the baffle connection plate 43 are connected with the low-temperature end static baffle vane 9 into a whole, and the sealing structure and the vane connection groove 43-1 are connected with the rotor vane 4 of the gas turbine into a whole, so that gas is prevented from flowing into the rotor.

The temperature detection and control system comprises a control terminal box 3, a thermocouple sensor 7 and a fault early warning system. A PD controller is arranged in the control terminal box 3 and is used for carrying out data processing and controlling a distributed actuator on the whole magnetic suspension supporting system; the fault early warning system is connected with the displacement sensor and the PD controller and is used for warning and reacting when the rotor position is deviated; the thermocouple sensors are axially arranged at the air inlet and the air outlet of the casing wall, are connected into the control terminal box 3 through thermocouple sensor connecting wires and are used for detecting the axial temperature gradient of the thin-wall rotor, when the change of the ambient temperature of the rotor is detected, temperature signals acquired through the thermocouple sensors are transmitted to the controller, further parameters of the controller are corrected in time, and the discrete distributed actuator receives the signals of the controller and adjusts the electromagnetic force to inhibit the thermal vibration of the thin-wall rotor system, so that the temperature compensation control of the system is realized.

The invention discloses a control system of a magnetic suspension supporting system of a thin-wall drum blade disc rotor, which is shown in a figure 38, and the control system has the working principle that: the thermocouple sensor 7 detects the temperature of the rotor in the combustion chamber, transmits the acquired information to the PD controller, adaptively adjusts PD parameters according to the acquired signals, converts the adjustment of the PD parameters into the change of current input to adjust the distributed internal and external actuators, and realizes the stable control of the thin-wall gas turbine rotor system by changing the magnitude of electromagnetic force. Meanwhile, the displacement sensor 14 monitors the displacement information of the gas turbine rotor (thin-wall drum rotor) in real time, compares the displacement information with a reference position in real time and feeds back the reference position to the PD controller; if the rotor position deviates during the operation, the fault early warning system reacts, and the PD parameter is regulated again to perform stable control on the rotor system.

The working process between the magnetic suspension support and the temperature detection and control system of the thin-wall drum blade disc rotor comprises the following steps: when the gas turbine rotor 4 rotates at a high speed, the high and low Wen Cizhou bearing systems arranged on the two sides of the gas turbine rotor 4 play a role in protecting and supporting. In the running process, when the rubbing clearance tends to disappear, the two-end magnetic bearing system detects the displacement of the two ends of the rotor through the displacement sensor 14 in the rotor system, and when the displacement is bigger or smaller, the PD parameter of the magnetic bearing system is regulated to stabilize the suspension to control the operation of the rotor; when the temperature fluctuation occurs in the gas turbine, the PD parameter of the magnetic bearing system is regulated to realize stable control of the gas turbine rotor 4 system when the temperature is higher or lower through the temperature signal detected by the thermocouple sensor 7.

The low temperature side magnetic bearing system 1 and the high temperature side magnetic bearing system 6 in the present embodiment are provided at both ends of the gas turbine rotor 4, and the impeller of the gas turbine rotor 4 is provided at an intermediate position.

Example 2

In embodiment 2, a gas turbine multi-stage blisk rotor magnetic bearing support system is described, wherein a multi-stage blisk rotor 45 of a gas turbine is supported at one end by a multi-stage blisk rotor low temperature end magnetic bearing system 44 and at the other end by a multi-stage blisk rotor high temperature end magnetic bearing system 50 disposed intermediate the multi-stage blisks, such rotors typically having a plurality of stages of blisks. The following magnetic levitation supporting system is designed for the drum leaf disc rotor, and the specific structure is as follows:

as shown in fig. 26 and 27, the gas turbine multi-stage blisk rotor magnetic suspension bearing support system includes a multi-stage blisk rotor low temperature end magnetic bearing system 44, a second casing 49, a gas turbine multi-stage blisk rotor 45, a second seal structure 46, a multi-stage blisk rotor high temperature end magnetic bearing system 50, a temperature detection and control system, a multi-stage blisk rotor high temperature bus 47, and a multi-stage blisk rotor inner ring actuator connection bracket 51. The multistage leaf disc rotor magnetic bearing support system is different from that in embodiment 1 in that: the low-temperature end of the multistage impeller rotor 45 of the gas turbine is fixedly provided with a multistage impeller rotor low-temperature end magnetic bearing system 44, and a multistage impeller rotor high-temperature end magnetic bearing system 50 is arranged at the middle position of the turbine impeller; as shown in fig. 26, the multi-stage impeller rotor 45 of the gas turbine is of a hollow thin-wall drum structure, the low-temperature end magnetic bearing system 44 of the multi-stage impeller rotor is fixedly installed at the low-temperature end of the second casing 49, the multi-stage impeller rotor 45 of the gas turbine is installed inside the second casing 49, and the high-temperature end magnetic bearing system 50 of the multi-stage impeller rotor is fixedly installed at the high-temperature end of the second casing 49. The multistage blisk rotor inner ring actuator connecting bracket 51 is installed inside the multistage blisk rotor 45 of the gas turbine, the low temperature end of the multistage blisk rotor inner ring actuator connecting bracket is fixedly connected with the multistage blisk rotor low temperature end magnetic bearing system 44, and the high temperature end of the multistage blisk rotor inner ring actuator connecting bracket is fixedly connected with the multistage blisk rotor high temperature end magnetic bearing system 50. 26-27, the second casing 49, the temperature detecting and controlling system and the high temperature resistant bus 47 of the multistage leaf disc rotor in the multistage leaf disc rotor magnetic bearing supporting system are the same as those in the embodiment 1; the low-temperature end magnetic bearing system 44 of the multistage impeller rotor and the gas turbine rotor 45 of the multistage impeller rotor are sealed through a second sealing structure 46; the second seal structure 46 is identical in structure to the seal structure 5.

The technical scheme of the multi-stage impeller rotor low-temperature end magnetic bearing system 44 is the same as that of the low-temperature end magnetic bearing system 1 in embodiment 1.

28-30, the gas turbine multi-stage disk high temperature end magnetic bearing system 50 includes a multi-stage disk high Wen Daoliu disk 55, a multi-stage disk high Wen Waijuan actuator support 54, a multi-stage disk high Wen Najuan actuator support 53, a magnetic core 11, an outer ring actuator 12, an inner ring actuator 13, and a displacement sensor 14. As shown in fig. 29 and 30, the inner ring of the multi-stage high-temperature-end guide vane 55 is fixedly connected with the outer ring of the multi-stage high-vane Wen Waijuan actuator support 54, and the multi-stage high-vane Wen Najuan actuator support 53 is concentrically (rotatably) connected with the multi-stage high-vane Wen Waijuan actuator support 54; referring to fig. 31, the outer ring actuator 12 is mounted in a multi-stage disk height Wen Waijuan actuator holder 54, and the inner ring actuator 13 and the displacement sensor 14 are fixedly mounted in a multi-stage disk height Wen Najuan actuator holder 53. The outer ring of the magnetic core 11 and the inner ring of the actuator support 53 in the actuator support with the multi-stage blade height Wen Najuan are concentrically and rotatably arranged; the inner ring of the magnetic core is fixedly connected with a multistage blisk rotor 45 of the gas turbine.

As shown in fig. 33 and 34, a control execution unit includes an outer ring actuator 12, an inner ring actuator 13, and a displacement sensor 14, and a plurality of groups of control execution units are uniformly distributed in the circumferential direction on the inner and outer actuator support 53 at the high temperature end of the multi-stage blade disc, so that the magnetic force generated by the inner and outer actuators supports the thin-wall drum rotor, and the displacement sensor 14 is used for detecting the displacement of the rotor. The invention adopts the differential control of the inner and outer ring bidirectional actuators, the number of the inner and outer ring actuators is the same, the embodiment adopts 15 groups of control execution units, and the number of the actuator units can be singly increased according to the control precision and the actual structure, such as 16 groups, 17 groups or 18 groups.

As shown in fig. 31 and 32, the structure of the high-temperature-end diaphragm 55 of the multistage vane rotor of the gas turbine differs from that of the high-temperature-end stationary diaphragm 32 of embodiment 1 in that it is affected by a high-temperature environment as follows: the high-temperature guide vane hollow thin plate structure 56 is of an inner-outer double-layer structure, an inner ring thin plate is fixedly connected with the multistage vane high-temperature end outer actuator support 54, a heat insulation coating is added on an outer ring thin plate to prevent heat conduction inside the second casing 49, and multistage vane rotor high-temperature guide vane arc-shaped guide plates 59 are arranged on two sides of a multistage vane casing guide plate connecting plate 57 and are respectively connected with vane rotors on the two sides. The remaining structure of the multi-stage blisk rotor high temperature end diaphragm 55 is the same as the high temperature end stationary diaphragm 32 of embodiment 1.

As shown in fig. 34, the multi-stage blisk height Wen Waijuan actuator support 54 includes a high Wen Waijuan actuator support actuator mounting plate 60, high Wen Waijuan fixed support actuator mounting holes 61, and multi-stage blisk rotor stiffener 62. The outer actuator fixing plates 60 are uniformly distributed in 15 groups along the circumferential direction, two high Wen Waijuan fixing support actuator mounting holes 61 are formed in one group of high Wen Waijuan actuator support actuator fixing plates 60, the outer ring actuators 12 are fixedly connected through rivets, and the multi-stage impeller rotor reinforcing ribs 62 are used for enhancing the strength and rigidity of the guide impeller, so that the material consumption is reduced, the weight is reduced, and the cost is reduced.

As shown in fig. 35, the multi-stage blisk height Wen Waijuan actuator support 53 includes an inner ring actuator support mounting hole 63, a high Wen Najuan actuator support actuator mounting plate 64, a high Wen Najuan actuator support actuator mounting hole 65, a multi-stage blisk rotor control execution unit lead integration box 66, a high Wen Najuan fixed support control execution unit sump 67, a high Wen Najuan fixed support displacement sensor mount 68. The inner ring actuator fixing support mounting holes 63 are evenly distributed 4 along the inner ring of the actuator support, the high Wen Najuan actuator support actuator fixing plates 64 are evenly distributed 15 groups along the circumferential direction, two high Wen Najuan actuator support actuator mounting holes 65 are formed in one group of high Wen Najuan actuator support actuator fixing plates 64, the inner ring actuator 13 is fixedly connected through rivets, and 15 high Wen Najuan fixing support displacement sensor mounting seats 68 are evenly distributed along the circumferential direction in the inner ring of the high-temperature end actuator support and are used for mounting the displacement sensor 14. The outer end surface of the multi-stage blade disc height Wen Najuan actuator support 53 of the gas turbine is also designed with a control execution unit wire collecting groove 67 and a control execution unit wire lead integrated box 66, the wires of the control execution units are collected and concentrated in the control execution unit wire lead integrated box 66 through the control execution unit wire collecting groove 67, and then pass through the high-temperature-resistant bus hole of the multi-stage blade disc rotor, and the specific wire routing is the same as that of the control execution unit in embodiment 1.

The connection and assembly diagram of the multi-stage blade disc inner ring actuator bracket at the high and low temperature end of the gas turbine is shown in fig. 36, and two ends of the multi-stage blade disc rotor inner ring actuator connection bracket 51 are respectively and fixedly connected with the multi-stage blade disc rotor low temperature end magnetic bearing system 44 and the multi-stage blade disc height Wen Najuan actuator bracket 53; as shown in fig. 37, the connecting bracket 51 for the multi-stage blade disc rotor inner ring actuator of the gas turbine comprises a middle connecting rod, a low-temperature inner ring fixing bracket connecting rod 69 and a high-temperature inner ring fixing bracket connecting rod 70, wherein four low-temperature inner ring fixing bracket connecting rods 69 are arranged at the low-temperature end of the middle connecting rod in a 90-degree uniform fixed manner, and four high Wen Najuan fixing bracket connecting rods 70 are arranged at the high-temperature end of the middle connecting rod in a 90-degree uniform fixed manner.

The invention also provides a gas turbine comprising the magnetic suspension supporting system. In this embodiment, the magnetic suspension support system is disposed in the gas turbine to realize the support of the thermoelastic coupling vibration thin-wall drum rotor system, so as to weaken the influence of the high-temperature environment on the thin-wall drum rotor and improve the running stability of the thin-wall drum rotor.

Claims (12)

1. The magnetic suspension supporting system of the thin-wall drum blade disc rotor is characterized by comprising a low-temperature end magnetic bearing system, a casing, a gas turbine rotor, a sealing structure, a high-temperature end magnetic bearing system, a temperature detection and control system and a high-temperature-resistant busbar; the gas turbine rotor is arranged in the casing, and is supported by the low-temperature end magnetic bearing system and the high-temperature end magnetic bearing system; the sealing structure is used for sealing the high-temperature end magnetic bearing system and the low-temperature end magnetic bearing system with the rotor of the gas turbine; the high-temperature-resistant bus at the high-low temperature end is led out from the magnetic bearing system and is connected to a control terminal box in the temperature detection and control system; a control execution unit is arranged in the high-temperature end magnetic bearing system and the low-temperature end magnetic bearing system and is used for generating magnetic force to support the rotor of the gas turbine; the temperature detection and control system is used for detecting, controlling and regulating the stable operation of the gas turbine; the control execution unit comprises an outer ring actuator, an inner ring actuator and a displacement sensor.

2. A magnetically levitated support system for a thin wall drum blisk rotor as in claim 1, wherein the gas turbine rotor is provided with magnetic bearing systems at both ends, the low temperature end being supported by the low temperature end magnetic bearing system and the high temperature end being supported by the high temperature end magnetic bearing system.

3. A magnetic levitation support system for a thin-walled drum blisk rotor as in claim 1, wherein the gas turbine rotor is a gas turbine multi-stage blisk rotor and the high temperature end magnetic bearing system is a multi-stage blisk rotor high temperature end magnetic bearing system; the low-temperature end of the multistage leaf disc rotor of the gas turbine is supported by a low-temperature end magnetic bearing system, and the high-temperature end magnetic bearing system of the multistage leaf disc rotor is arranged in the middle of the gas turbine rotor so as to support the gas turbine rotor.

4. A magnetic levitation support system for a thin-walled drum blisk rotor as in claim 3, further comprising a multistage blisk rotor inner ring actuator connection bracket, the gas turbine rotor being of hollow thin-walled drum construction; the multistage leaf disc rotor inner ring actuator connecting bracket is arranged inside the gas turbine rotor, the low-temperature end of the multistage leaf disc rotor inner ring actuator connecting bracket is fixedly connected with the low-temperature end magnetic bearing system, and the high-temperature end of the multistage leaf disc rotor inner ring actuator connecting bracket is fixedly connected with the high-temperature end magnetic bearing system.

5. A magnetic levitation support system of a thin-walled drum blisk rotor as in claim 2, wherein the low temperature end magnetic bearing system and the high temperature end magnetic bearing system each comprise a stationary diaphragm, an inner and outer actuator support, a magnetic core, and a control execution unit; the outer ring of the static diversion impeller is fixed on the inner wall of the casing, and the inner ring is fixedly connected with the outer ring of the inner and outer actuator brackets; the outer ring of the magnetic core and the inner ring of the inner and outer actuator brackets are concentrically and rotatably arranged; the inner ring of the magnetic core is fixedly connected with the rotor of the gas turbine; the control execution units are uniformly and fixedly arranged in the inner and outer actuator brackets along the circumferential discrete type.

6. The magnetic levitation supporting system of the thin-wall drum impeller rotor according to claim 5, wherein the static flow guiding impeller in the low-temperature end magnetic bearing system is a low-temperature end static flow guiding impeller, and the static flow guiding impeller in the high-temperature end magnetic bearing system is a high-temperature end static flow guiding impeller, and the magnetic levitation supporting system comprises a first thickened blade, a casing flow guiding impeller connecting plate, a flow guiding impeller arc-shaped flow guiding plate and a high-temperature resistant busbar threading hole; the machine case guide plate connecting plate is fixedly connected with the machine case, the first thickened blades are arranged in the machine case guide plate connecting plate, the inner rings of the blades are fixedly provided with guide blade plate arc-shaped guide plates, and high-temperature-resistant bus threading hole through holes are formed from the machine case guide plate connecting plate to the first thickened blades;

The high-temperature end static guide vane disk is of an inner-outer double-layer structure and is a hollow cavity; and the inner ring sheet is fixedly connected to the inner and outer actuator brackets, and the outer ring sheet is provided with a thermal insulation coating for preventing high-temperature airflow heat conduction in the casing.

7. A thin-walled drum blisk rotor magnetic levitation support system as in claim 5, wherein the inner and outer actuator supports include a displacement sensor mount, an inner and outer actuator support outer actuator mounting plate, an inner and outer actuator support inner actuator mounting plate, a control actuator lead integration box, a control actuator collector slot, an outer actuator mounting hole, an inner actuator mounting hole, and a stiffener; the inner ring of the inner and outer actuator brackets is uniformly provided with displacement sensor mounting seats along the circumferential direction and is used for mounting the displacement sensors; the execution unit lead integration box is arranged at the radial position of the outer side surface of the inner and outer executor support, and the outer executor fixing and mounting hole is arranged on the outer executor fixing plate of the inner and outer executor support and is used for mounting the outer executor; the inner actuator fixing and mounting hole is arranged on an inner actuator fixing plate of the inner actuator bracket and is used for mounting the inner actuator; the outer rings of the inner and outer actuator brackets are uniformly distributed with reinforcing ribs along the circumferential direction and are used for enhancing the strength and rigidity of the guide vane disk; the inner and outer actuator support controls the execution unit line collecting groove to be located at the low temperature end, the outer side surface of the inner and outer actuator support is in a circular shape, and the circle center of the circular ring is concentric with the outer side surface.

8. A thin-walled drum bladed rotor magnetic levitation support system according to claim 7 wherein the control actuator leads are led from the control actuator, pass through the displacement sensor mounting base, extend into the inner and outer actuator support control actuator wire collection slots, collect in the control actuator lead integration box, and collect into a high temperature resistant busbar through the high temperature resistant busbar wire holes, and then out of the casing wall, connect to the terminal control box.

9. A magnetic levitation support system of a thin-walled drum blisk rotor as in claim 4, wherein the multi-stage blisk rotor high temperature end magnetic bearing system comprises a multi-stage blisk high Wen Daoliu blisk, a multi-stage blisk high Wen Waijuan actuator support, a multi-stage blisk high Wen Najuan actuator support, a magnetic core, a control execution unit; the inner ring of the guide vane disk at the high temperature end of the multi-stage vane disk is fixedly connected with the outer ring of the multi-stage vane disk high Wen Waijuan actuator bracket, and the multi-stage vane disk high Wen Najuan actuator bracket is concentrically and rotatably connected with the multi-stage vane disk high Wen Waijuan actuator bracket; the outer ring actuator in the control execution unit is arranged in the multistage leaf disc height Wen Waijuan actuator bracket, and the inner ring actuator and the displacement sensor in the control execution unit are fixedly arranged in the multistage leaf disc height Wen Najuan actuator bracket; the outer ring of the magnetic core and the inner ring of the actuator support in the multi-stage blade height Wen Najuan actuator support are concentrically and rotatably arranged; the inner ring of the magnetic core is fixedly connected with the rotor of the gas turbine.

10. A thin-walled drum bladed rotor magnetic levitation support system as in claim 9 wherein the multi-stage bladed high Wen Daoliu bladed comprises a first thickened blade, a high Wen Daoliu bladed hollow sheet structure, a multi-stage bladed cartridge receiver baffle web, a multi-stage bladed high Wen Daoliu bladed arcuate baffle, and a high temperature resistant busbar threading aperture; the high-temperature guide vane hollow sheet structure is an inner-outer double-layer structure, the inner ring sheet is fixedly connected with the multistage vane high-temperature end outer actuator bracket, and the outer ring sheet is added with a heat-insulating coating; the multi-stage blade disc casing guide plate is fixedly connected with the casing, the first thickened blades are arranged in the multi-stage blade disc casing guide plate, the inner rings of the blades are fixedly provided with multi-stage blade disc height Wen Daoliu blade disc arc guide plates, and the multi-stage blade disc height Wen Daoliu blade disc arc guide plates are arranged on two sides of the multi-stage blade disc casing guide plate; and a high-temperature-resistant bus threading hole through hole is formed from the guide plate connecting plate of the multistage leaf disc casing to the first thickened blade.

11. A magnetic suspension support system for a thin-walled drum blisk rotor as claimed in claim 10, wherein two ends of the multi-stage blisk rotor inner ring actuator connection bracket are fixedly connected to the multi-stage blisk rotor low temperature end magnetic bearing system and the multi-stage blisk height Wen Najuan actuator bracket, respectively; the connecting support of the multi-stage leaf disc rotor inner ring actuator of the gas turbine comprises a middle connecting rod, a low-temperature inner ring fixing support connecting rod and a high-temperature inner ring fixing support connecting rod, wherein four low-temperature inner ring fixing support connecting rods are arranged at the low-temperature end of the middle connecting rod in a 90-degree uniform fixed mode, and four high Wen Najuan fixing support connecting rods are arranged at the high-temperature end of the middle connecting rod in a 90-degree uniform fixed mode.

12. A gas turbine comprising a magnetically levitated support system of a thin-walled drum blisk rotor according to any of claims 1-11.