Rotor system and gas turbine

Abstract

The rotor system comprises a rotating shaft, an impeller and a first radial bearing, the impeller is fixedly installed on the rotating shaft, and the first radial bearing is fixedly installed in a stator component; the impeller extends towards the first radial bearing to form a first boss, and the first boss comprises a first radial bearing surface; the first radial bearing extends to the radial inner side or the radial outer side of the first boss and is arranged around the circumference of the rotating shaft, the first radial bearing is provided with a bearing face corresponding to the first radial bearing face, and the first radial bearing is a non-contact bearing. The axial distance between a radial bearing supporting point and the impeller is shortened, so that the supporting capacity of the bearing to the impeller is improved, and a rotor system with the impeller can run more stably.

Description

TECHNICAL FIELD

[0001] The utility model relates to a rotor system and gas turbine in the technical field of heat engine. BACKGROUND

[0002] Rotor systems with impellers are widely used in various rotating machines, for example, can be used in gas turbines.

[0003] The gas turbine is a kind of rotary impeller type heat engine, which uses continuous flow gas as working medium to drive impeller high-speed rotation, converts the energy of fuel into useful work, and mainly includes compressor, combustion chamber and turbine three major components: compressor inhales air from external atmosphere and compresses to make it pressurized, while air temperature also increases accordingly;Compressed air is sent to the combustion chamber and mixed with the injected fuel to generate high-temperature and high-pressure gas;Then, it enters the turbine to expand and do work, drives the compressor (and external load rotor) high-speed rotation, can realize the partial conversion of chemical energy of gas or liquid fuel into mechanical work and heat energy, and also can output electric energy through connected generator.

[0004] However, the radial bearing arrangement at the impeller is a problem in the arrangement of the rotor system, so an urgent need exists for a rotor system that can provide better support for the impeller. UTILITY MODEL CONTENT

[0005] The utility model aims at the deficiencies in the prior art, and provides a rotor system and gas turbine.

[0006] A rotor system, comprising a rotating shaft, an impeller and a first radial bearing, the impeller is fixedly installed on the rotating shaft, and the first radial bearing is fixedly installed in a stator component;

[0007] The impeller extends a first boss towards the first radial bearing, and the first boss comprises a first radial bearing surface;

[0008] The first radial bearing extends to the radial inner side or the radial outer side of the first boss and is arranged around the circumference of the rotating shaft, the first radial bearing has a bearing surface corresponding to the first radial bearing surface, and the first radial bearing is a non-contact bearing.

[0009] Further, the first radial bearing is a static pressure air bearing.

[0010] Further, the first radial bearing is a dynamic pressure foil bearing.

[0011] Furthermore, the impeller also includes a second boss extending toward the first radial bearing. The second boss includes a second radial bearing surface. The first radial bearing has several openings toward the first radial bearing surface and / or the second radial bearing surface. The several first radial bearing holes are distributed in an array along the periphery of the first radial bearing and are connected by an annular air groove, which is connected to an air source.

[0012] Furthermore, the first radial bearing surface is located on the outer peripheral surface of the groove, and the first radial bearing hole is axially outward and faces the first radial bearing surface.

[0013] Furthermore, the first radial bearing surface is located on the inner circumferential surface of the groove, and the first radial bearing hole is axially disposed inward, facing the first radial bearing surface.

[0014] Furthermore, it also includes a second radial bearing surface and a second radial bearing hole. The first radial bearing surface is disposed on the outer peripheral surface of the groove, and the inner peripheral surface of the groove has a second radial bearing surface. The first radial bearing hole faces the first radial bearing surface, and the second radial bearing hole faces the second radial bearing surface.

[0015] Furthermore, the package also includes a first axial bearing hole, the opening of which faces the axial side of the groove.

[0016] Furthermore, the first radial bearing hole is a stepped hole with a smaller upper diameter and a larger lower diameter. The internal components of the smaller upper hole are installed into the larger lower hole by an interference fit, forming a stepped hole.

[0017] Furthermore, it also includes a compressor, a thrust disk, and a second radial bearing. The compressor is installed on the side of the shaft away from the impeller, the thrust disk is located between the compressor and the impeller, and a first thrust bearing and a second thrust bearing are respectively provided on both sides of the thrust disk. The second radial bearing is installed between the thrust disk and the compressor.

[0018] Furthermore, it also includes a compressor and a thrust plate. The compressor is installed on the side of the shaft away from the impeller, and the thrust plate is located between the compressor and the impeller. A first thrust bearing and a second thrust bearing are respectively provided on both sides of the thrust plate.

[0019] The compressor adopts a closed impeller structure, and a fourth radial bearing is provided on the air inlet side of the compressor.

[0020] Furthermore, it also includes a third radial bearing, which is located between the thrust disc and the impeller.

[0021] Furthermore, it also includes a second radial bearing located between the thrust disk and the compressor.

[0022] Furthermore, it also includes a compressor and an inclined bearing, wherein the compressor adopts a closed impeller structure and the inclined bearing is located between the air inlet side and the air outlet side of the compressor.

[0023] A third thrust bearing is located on the back side of the compressor facing the impeller.

[0024] Furthermore, it also includes a second radial bearing located between the compressor and the impeller.

[0025] It also includes a coupling and a second shaft, the second shaft being connected to the shaft via the coupling;

[0026] An external load component is provided on the second rotating shaft, and a fifth radial bearing and a sixth radial bearing are respectively installed on both sides of the external load component on the second rotating shaft.

[0027] Furthermore, a gas turbine, equipped with a rotor system as described in any of the above claims, further includes a combustion chamber, a bearing housing, and a shaft supported on the bearing housing by bearings;

[0028] The combustion chamber is an annular combustion chamber arranged around a rotating shaft. The inlet end of the combustion chamber is connected to the exhaust end of the compressor. The outlet end of the combustion chamber is also provided with a guide vane assembly, which is located in front of the impeller.

[0029] The advantages of this utility model compared with the prior art are as follows:

[0030] 1. This solution improves the bearing's support capacity for the impeller by setting a first boss at the impeller of the rotor system to accommodate the radial bearing, thereby shortening the axial distance between the radial bearing support point and the impeller. This helps the rotor system with the impeller to operate more stably.

[0031] 2. This solution sprays air onto the first radial bearing surface through the first radial bearing hole to form a bearing air film, which provides radial support to the impeller. Furthermore, since the bearing hole support point of the first radial bearing is closer to the center line of gravity of the impeller, it can improve the bearing's support capacity for the impeller, which helps the rotor system with the impeller to operate more stably.

[0032] 3. This design sets up a first radial bearing close to the impeller, which can minimize the vibration at the turbine end and enhance the support capacity. Furthermore, the first radial bearing forms an air seal structure at one end of the static pressure zone, and the third radial bearing also forms an air seal structure at the other end of the static pressure zone. The static pressure between the air seals helps the rotor system to operate more stably.

[0033] 4. This solution eliminates the need for radial bearings between the compressor and impeller by installing radial bearings at the compressor and impeller, which shortens the axial dimension of the rotor system. Furthermore, an air seal structure can be formed between the first and third radial bearings, and the static pressure between the air seals helps the rotor system operate more stably.

[0034] 5. This solution eliminates the need for radial bearings and thrust bearings between the compressor and impeller by installing radial bearings at the compressor and impeller, and by installing thrust bearings at the compressor, thus shortening the axial dimension of the rotor system.

[0035] 6. This solution shortens the axial dimension of the rotor system section where the first shaft is located, allowing for additional load-bearing capacity to be used for the coupling and the second shaft section. At the same time, the integrated starter motor can provide starting torque when the gas turbine including the rotor system starts, which is especially beneficial for the smooth start of the gas turbine when the bearing is a hydrodynamic bearing or foil bearing. Attached Figure Description

[0036] Figure 1 A schematic diagram of the rotor system applicable to this scheme;

[0037] Figure 2 A schematic diagram of the rotor system proposed in Embodiment 1 of this scheme;

[0038] Figure 3 A schematic diagram of the rotor system proposed in Embodiment 2 of this scheme;

[0039] Figure 4 A schematic diagram of the rotor system proposed in Embodiment 3 of this scheme;

[0040] Figure 5 A schematic diagram of the rotor system proposed in Embodiment 4 of this scheme;

[0041] Figure 6 A schematic diagram of the rotor system proposed in Embodiment 5 of this scheme;

[0042] Figure 7 A schematic diagram of the rotor system proposed in Embodiment 6 of this scheme;

[0043] Figure 8 A schematic diagram of the rotor system applicable to Embodiment 7 of this scheme;

[0044] Figure 9 A schematic diagram of the rotor system proposed in Embodiment 8 of this scheme;

[0045] Figure 10 A schematic diagram of the rotor system applicable to Embodiment 9 of this scheme;

[0046] Figure 11 This is a schematic diagram of the rotor system proposed in Embodiment 10 of this scheme;

[0047] Figure 12 A schematic diagram of the rotor system applicable to Embodiment 11 of this scheme;

[0048] Figure 13 This is a schematic diagram of the rotor system proposed in Embodiment 12 of this scheme;

[0049] Figure 14 This is a structural schematic diagram of the gas turbine proposed in Embodiment 13 of this scheme.

[0050] Reference numerals: 100, shaft; 300, impeller; 400, combustion chamber; 600, bearing housing; 700, guide vane assembly; 800, compressor; 900, integrated starter motor;

[0051] 110. First rotating shaft; 120. Second rotating shaft; 130. Coupling;

[0052] 210. First radial bearing; 211. First radial bearing bore; 212. Bearing body; 213. Second radial bearing bore; 214. First axial bearing bore;

[0053] 220, Second radial bearing; 230, First thrust bearing; 240, Second thrust bearing; 250, Third radial bearing; 260, Fourth radial bearing; 270, Third thrust bearing; 280, Fifth radial bearing; 290, Sixth radial bearing;

[0054] 310. Groove; 311. First radial bearing surface; 312. Second radial bearing surface. Detailed Implementation

[0055] Example 1

[0056] As per the instruction manual Figures 1-2 As shown, this embodiment provides a rotor system including a shaft 100, an impeller 300, and a first radial bearing 210. The impeller 300 is fixedly mounted on the shaft 100, and the first radial bearing 210 is fixedly mounted on the stator component of the rotor system.

[0057] The impeller 300 extends a first boss 320 toward the first radial bearing 210, the first boss 320 including the first radial bearing surface;

[0058] The first radial bearing 210 extends to the radial inner side or radial outer side of the first boss 320 and is arranged around the circumference of the rotating shaft 100. The first radial bearing 210 has a bearing surface corresponding to the first radial bearing surface 311. The first radial bearing 210 is a non-contact bearing.

[0059] The first radial bearing 210 can be a hydrostatic bearing or a hydrodynamic bearing, wherein the hydrostatic bearing includes, but is not limited to, a hydrostatic air bearing, and the hydrodynamic bearing includes, but is not limited to, a hydrodynamic foil bearing.

[0060] When the first radial bearing 210 is a hydrostatic air bearing, the first radial bearing 210 has a first radial bearing hole 211 with an opening facing the first radial bearing surface 311, and the first radial bearing hole 211 is formed on the bearing body 212. Multiple first radial bearing holes 211 arranged circumferentially along the first radial bearing 210 can be connected by an annular air groove. The first radial bearing hole 211 can be obtained by laser drilling, perforation, or other methods.

[0061] When the first radial bearing bore 211 is a stepped bore, the component with the smaller bore diameter (e.g., cylindrical) can be installed into the bore with the larger bore diameter, for example, by interference fit, to form a stepped bore. The first radial bearing 210, which is a hydrostatic air bearing, can be connected to an air source.

[0062] Pressurized air from the air source is sprayed onto the first radial bearing surface 311 through the first radial bearing hole 211, forming a bearing air film to provide radial support for the impeller 300. Since the bearing hole support point of the first radial bearing 210 is closer to the center line of gravity of the impeller 300, it can improve the bearing's support capacity for the impeller, which helps the rotor system with the impeller to operate more stably.

[0063] Furthermore, such as Figure 2 As shown, the first radial bearing surface 311 can be located on the outer peripheral surface of the groove 310, and the first radial bearing hole 211 is axially outward.

[0064] Example 2

[0065] As per the instruction manual Figure 3 As shown, the difference between this embodiment and embodiment 1 is that the impeller 300 further includes a second boss 330 extending toward the first radial bearing 210. The second boss 330 includes a second radial bearing surface. The first radial bearing 210 has several openings toward the first radial bearing surface or the second radial bearing surface. The several first radial bearing holes 211 are distributed in an array along the periphery of the first radial bearing 210 and are connected by an annular air groove. The annular air groove is connected to an air source.

[0066] In embodiments 1-2, the first boss 320 and the second boss 330 are both formed by cut grooves 310, wherein the first boss 320 is the outer side wall of the groove 310 and the second boss 330 is the inner side wall of the groove 310.

[0067] Example 3

[0068] As per the instruction manual Figure 4 As shown, the difference between this embodiment and embodiment 1 is that the outer peripheral surface of the groove 310 has a first radial bearing surface 311, the inner peripheral surface has a second radial bearing surface 312, the first radial bearing 210 has a first radial bearing hole 211 facing the first radial bearing surface 311, and a second radial bearing hole 213 facing the second radial bearing surface 312.

[0069] Pressurized air from the air source is sprayed through the first radial bearing hole 211 and the second radial bearing hole 213 onto the first radial bearing surface 311 and the second radial bearing surface 312 respectively, forming a bearing air film, which can further improve the support capacity of the first radial bearing 210.

[0070] Example 4

[0071] As per the instruction manual Figure 5 As shown, the difference between this embodiment and embodiment 1 is that the first radial bearing 210 further includes a first axial bearing hole 214. The opening of the first axial bearing hole 214 faces the axial side of the groove 310. At this time, the pressurized air from the air source is sprayed through the first radial bearing hole 211 and the first axial bearing hole 214 onto the first radial bearing surface 311 and the side of the groove 310 respectively to provide axial support for the impeller 300, which can further improve the support capacity of the first radial bearing 210.

[0072] Example 5

[0073] As per the instruction manual Figure 6 As shown, this embodiment provides a rotor system for a gas turbine, including a compressor 800 and an impeller 300 fixedly mounted on a shaft 100. The impeller 300 of the gas turbine is a turbine and has a groove 310. The rotor system also includes a first radial bearing 210 extending into the groove 310. The shaft 100 has a thrust disk located between the compressor 800 and the impeller 300. Figure 6 As shown, the thrust disk and the rotating shaft 100 are arranged in a cross shape.

[0074] The rotor system also includes a second radial bearing 220 located between the compressor 800 and the thrust disk, and a first thrust bearing 230 and a second thrust bearing 240 are respectively provided on both sides of the thrust disk.

[0075] Because the impeller 300 used in the gas turbine needs to withstand high temperatures and has high density and mass, the side of the impeller 300 away from the compressor 800 has a high temperature, making it generally impossible to install bearings for support there. This is because bearings installed in this location would deform due to the high temperature, making it difficult to guarantee dimensional accuracy and lifespan. Installing a radial bearing on the side of the impeller 300 facing the compressor 800 would create a cantilever structure at the impeller 300, which could easily lead to vibration during high-speed operation of the rotor system. Therefore, this invention uses a first radial bearing 210 close to the impeller 300 to minimize vibration at the turbine end and enhance support capacity.

[0076] Example 6

[0077] As per the instruction manual Figure 7 As shown, this embodiment, based on embodiment 5, further includes a third radial bearing 250 located between the thrust disk and the impeller 300 to further enhance the radial support force at the impeller 300. The first radial bearing 210 forms an air seal structure at one end of the static pressure zone, and the third radial bearing 250 can also form an air seal structure at the other end of the static pressure zone. The static pressure between the air seals helps the rotor system to operate more stably.

[0078] Example 7

[0079] As per the instruction manual Figure 8 As shown, this embodiment provides a rotor system for a gas turbine, including a compressor 800 and an impeller 300 fixedly mounted on a shaft 100. The impeller 300 of the gas turbine is a turbine. The impeller 300 has a groove 310, and the rotor system also includes a first radial bearing 210 extending into the groove 310. The compressor 800 adopts a closed impeller structure, and a slanted bearing 261 is provided on the inlet side of the compressor 800.

[0080] The rotating shaft 100 has a thrust disk, which is located between the compressor 800 and the impeller 300. Figure 8 As shown, the thrust disk and the rotating shaft 100 are arranged in a cross shape. The thrust disk of the rotating shaft 100 is provided with a first thrust bearing 230 and a second thrust bearing 240 on both sides.

[0081] By employing a closed impeller structure in the compressor 800 and installing a radial oblique bearing 261 in the radial direction of the compressor 800, the support capacity of the compressor 800 can be improved. Furthermore, by installing radial bearings at the compressor 800 and impeller 300, the radial bearing between the compressor 800 and impeller 300 can be eliminated, thereby shortening the axial dimension of the rotor system.

[0082] Example 8

[0083] As per the instruction manual Figure 9As shown, this embodiment, based on embodiment 8, also includes a third radial bearing 250 located between the thrust disk and the impeller 300 to further enhance the radial support force at the impeller 300. Furthermore, an air seal structure can be formed between the first radial bearing 210 and the third radial bearing 250, and the static pressure between the air seals helps the rotor system to operate more stably.

[0084] Example 9

[0085] As per the instruction manual Figure 10 As shown, this embodiment, based on embodiment 9, also includes a second radial bearing 220 located between the thrust disk and the compressor 800 to further enhance the radial support force of the rotor system.

[0086] Example 10

[0087] As per the instruction manual Figure 11 As shown, this embodiment provides a rotor system for a gas turbine, including a compressor 800 and an impeller 300 fixedly mounted on a shaft 100. The impeller 300 of the gas turbine is a turbine. The impeller 300 has a groove 310, and the rotor system also includes a first radial bearing 210 extending into the groove 310. The compressor 800 adopts a closed impeller structure, and the compressor 800 is provided with an inclined slant bearing 261, located between the inlet and outlet sides of the compressor 800. The slant bearing 261 can provide radial and axial support. A third thrust bearing 270 is provided on the back side of the compressor 800 facing the impeller 300.

[0088] By adopting a closed impeller structure for the compressor 800 and installing a skew bearing 261 at the compressor 800, the radial and axial support capabilities of the compressor 800 can be improved.

[0089] Furthermore, by installing radial bearings at the compressor 800 and impeller 300, and a thrust bearing at the compressor 800, the radial bearing and thrust bearing between the compressor 800 and impeller 300 can be eliminated, thus shortening the axial dimension of the rotor system.

[0090] Example 11

[0091] As per the instruction manual Figure 12 As shown, this embodiment, based on embodiment 10, also includes a second radial bearing 220 located between the compressor 800 and the impeller 300 to further enhance the radial support force of the rotor system.

[0092] Example 12

[0093] As per the instruction manual Figure 13As shown, this embodiment, based on embodiment 10, further includes a coupling 130 and a second rotating shaft 120, and the rotating shaft 100 in embodiment 10 corresponds to the first rotating shaft 110 in this embodiment. An external load component is provided on the second rotating shaft 120. This external load component can be an integrated starter motor 900, a second compressor, a second turbine, etc. In this embodiment, the integrated starter motor 900 is used as an example. A fifth radial bearing 280 and a sixth radial bearing 290 are respectively installed on both sides of the integrated starter motor 900 and mounted on the second rotating shaft 120. The fifth radial bearing 280 and the sixth radial bearing 290 can be non-contact bearings, including but not limited to hydrostatic bearings or hydrodynamic bearings such as hydrodynamic foil bearings.

[0094] Since the diameter of the second rotating shaft 120 is smaller than that of the first rotating shaft 110, the outer circumferential linear velocity of the second rotating shaft 120 is lower than that of the first rotating shaft 110. The fifth radial bearing 280 and the sixth radial bearing 290 can be contact bearings, including but not limited to ball bearings.

[0095] Thanks to the reduced axial dimension of the rotor system portion where the first shaft 110 is located, additional load-bearing capacity is available for the coupling 130 and the second shaft 120 portion. The integrated starter motor 900 can provide starting torque when the gas turbine, which includes this rotor system, is started, especially when the bearings are hydrodynamic bearings or foil bearings, which facilitates smooth start-up of the gas turbine.

[0096] Example 13

[0097] As per the instruction manual Figures 1-14 As shown, this embodiment provides a gas turbine, which includes any one of the rotor systems in embodiments 1-12 above. It also includes a combustion chamber 400, a bearing housing 600, and a guide vane assembly 700.

[0098] The rotating shaft 100 can be supported by bearings on the gas turbine casing or bearing housing 600.

[0099] Combustion chamber 400 can be an annular combustion chamber, a single-tube combustion chamber, an annular tube combustion chamber, etc. Figure 14 The diagram shows an annular combustion chamber. The combustion chamber 400 can be arranged around the rotating shaft 100, and the inlet end of the combustion chamber 400 is connected to the exhaust end of the compressor 800. The outlet end of the combustion chamber 400 is also provided with a guide vane assembly 700, which is located in front of the impeller 300.

[0100] The gas turbine structure provided in this embodiment can refer to a gas turbine disclosed in the applicant's earlier application CN115773182A and a gas turbine disclosed in the applicant's earlier application CN118375519A, etc., so it will not be described in detail here.

[0101] In the description of this utility model, it should be understood that the terms "center," "longitudinal," "transverse," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential," etc., indicating the orientation or positional relationship shown in the accompanying drawings, are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model. Furthermore, features defined with "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this utility model, unless otherwise stated, "a plurality of" means two or more.

[0102] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0103] In the description of this utility model, the terms "one embodiment," "some embodiments," "illustrative embodiment," "example," "specific example," or "some examples," etc., refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which are included in at least one embodiment or example of this utility model. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0104] Although embodiments of the present invention have been shown and described, those skilled in the art will understand that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the claims and their equivalents.

Claims

1. A rotor system, characterized in that: It includes a rotating shaft (100), an impeller (300) and a first radial bearing (210), wherein the impeller (300) is fixedly mounted on the rotating shaft (100) and the first radial bearing (210) is fixedly mounted in the stator component; The impeller (300) extends a first boss (320) toward the first radial bearing (210), the first boss (320) including a first radial bearing surface; The first radial bearing (210) extends to the radial inner or radial outer side of the first boss (320) and is arranged around the circumference of the rotating shaft (100). The first radial bearing (210) has a bearing surface corresponding to the first radial bearing surface (311). The first radial bearing (210) is a non-contact bearing.

2. A rotor system according to claim 1, characterized in that: The impeller (300) further includes a second boss (330) extending toward the first radial bearing (210). The second boss (330) includes a second radial bearing surface. The first radial bearing (210) has a plurality of openings facing the first radial bearing surface and / or the second radial bearing surface. The plurality of first radial bearing holes are distributed in an array along the periphery of the first radial bearing (210) and are connected by an annular air groove. The annular air groove is connected to an air source.

3. A rotor system according to claim 2, characterized in that: It also includes a first axial bearing hole (214), the opening of which faces the axial side of the groove (310).

4. A rotor system according to claim 1, characterized in that: It also includes a compressor (800), a thrust disk, and a second radial bearing (220). The compressor (800) is installed on the side of the shaft (100) away from the impeller (300). The thrust disk is located between the compressor (800) and the impeller (300). A first thrust bearing (230) and a second thrust bearing (240) are respectively provided on both sides of the thrust disk. The second radial bearing (220) is installed between the thrust disk and the compressor (800).

5. A rotor system according to claim 1, characterized in that: It also includes a compressor (800) and a thrust plate. The compressor (800) is installed on the side of the shaft (100) away from the impeller (300). The thrust plate is located between the compressor (800) and the impeller (300). A first thrust bearing (230) and a second thrust bearing (240) are respectively provided on both sides of the thrust plate. The compressor (800) adopts a closed impeller structure, and a fourth radial bearing (260) is provided on the air inlet side of the compressor (800).

6. A rotor system according to claim 4 or 5, characterized in that: It also includes a third radial bearing (250) located between the thrust disc and the impeller (300).

7. A rotor system according to claim 5, characterized in that: It also includes a second radial bearing (220) located between the thrust plate and the compressor (800).

8. A rotor system according to claim 1, characterized in that: It also includes a compressor (800) and an inclined bearing (261), wherein the compressor (800) adopts a closed impeller structure and the inclined bearing (261) is located between the air inlet side and the air outlet side of the compressor (800). A third thrust bearing (270) is provided on the back side of the compressor (800) facing the impeller (300).

9. A rotor system according to claim 8, characterized in that: It also includes a second radial bearing (220) located between the compressor (800) and the impeller (300).

10. A rotor system according to claim 8, characterized in that: It also includes a coupling (130) and a second rotating shaft (120), the second rotating shaft (120) being connected to the rotating shaft (100) via the coupling (130); An external load component is provided on the second rotating shaft (120), and a fifth radial bearing (280) and a sixth radial bearing (290) are respectively installed on both sides of the external load component on the second rotating shaft (120).

11. A gas turbine comprising a rotor system as described in any one of claims 1-10, characterized in that: It also includes a combustion chamber (400), a bearing housing (600), and a rotating shaft (100) supported on the bearing housing (600) by bearings.

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