Rotor system and gas turbine
By providing a first boss and a non-contact bearing at the impeller, the problem of setting up the impeller radial bearing in the prior art is solved, the stability and support capacity of the rotor system are improved, and the axial size is shortened.
Patent Information
- Application Number
- CN202510373986.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-03-27
- Publication Date
- 2025-06-06
AI Technical Summary
In the prior art, there are difficulties in setting up radial bearings at the impeller, which is difficult to provide better support for the impeller, resulting in unstable operation of the rotor system.
A rotor system is designed, by providing a first boss at the impeller to accommodate the radial bearing, and using a non-contact static pressurized air bearing or a dynamic foil bearing, the axial distance between the bearing support point and the impeller is shortened to form an air film support impeller.
The bearing supports the impeller, reduces vibration at the turbine end, enhances the stability of the rotor system, and shortens the axial dimension of the rotor system.
Smart Images
Figure CN120100542A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the technical field of thermal engines, and in particular to a rotor system and a gas turbine. Background Art
[0002] A rotor system having an impeller is widely used in various rotating machines, for example, a gas turbine.
[0003] A gas turbine uses a continuously flowing gas as a working fluid to drive the impeller to rotate at high speed, converting the energy of the fuel into useful work. It is a rotating impeller heat engine. It mainly includes three parts: a compressor, a combustion chamber, and a turbine. The compressor inhales air from the external atmosphere and compresses it to increase the pressure, and the air temperature is also increased accordingly; the compressed air is sent to the combustion chamber to mix with the injected fuel and burn to generate high-temperature and high-pressure gas; then it enters the turbine to expand and do work, driving the turbine to drive the compressor (and the external load rotor) to rotate at high speed, which can realize the partial conversion of the chemical energy of the gas or liquid fuel into mechanical work and heat energy, and can also output electrical energy by connecting to a generator.
[0004] However, the radial bearing arrangement at the impeller is a difficult problem in the arrangement of the rotor system, and therefore a rotor system is urgently needed so that the bearing can provide better support for the impeller. Summary of the invention
[0005] The purpose of the present invention is to provide a rotor system and a gas turbine in view of the deficiencies in the prior art.
[0006] A rotor system comprises a rotating shaft, an impeller and a first radial bearing, wherein the impeller is fixedly mounted on the rotating shaft, and the first radial bearing is fixedly mounted in a stator component;
[0007] The impeller extends a first boss toward the first radial bearing, wherein the first boss includes a first radial bearing surface;
[0008] The first radial bearing extends to the radial inside or outside 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. The first radial bearing is a non-contact bearing.
[0009] Furthermore, the first radial bearing is a static pressure air bearing.
[0010] Furthermore, the first radial bearing is a hydrodynamic 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 a plurality of first radial bearing holes opening toward the first radial bearing surface and / or the second radial bearing surface, and the plurality of first radial bearing holes are distributed in an array along the circumference of the first radial bearing and are connected through an annular air groove, and the annular air groove is connected to an air source.
[0012] Furthermore, the first radial bearing surface is located on the outer circumferential surface of the groove, and the first radial bearing hole is arranged axially outwardly toward the first radial bearing surface.
[0013] Further, the first radial bearing surface is located on the inner circumferential surface of the groove, and the first radial bearing hole is arranged axially inwardly toward 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 arranged on the outer circumference of the groove, the inner circumference 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 bag 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 hole diameter at the upper end and a larger hole diameter at the lower end. The internal component with a small hole diameter at the upper end is installed in the large-diameter hole at the lower end by interference fit to form a stepped hole.
[0017] Furthermore, it also includes a compressor, a thrust plate and a second radial bearing. The compressor is installed on the side of the rotating shaft away from the impeller, the thrust plate is located between the compressor and the impeller, and the first thrust bearing and the second thrust bearing are respectively arranged on both sides of the thrust plate. The second radial bearing is installed between the thrust plate and the compressor.
[0018] Furthermore, it also includes a compressor and a thrust plate, wherein the compressor is installed on a side of the rotating shaft away from the impeller, the thrust plate is located between the compressor and the impeller, and a first thrust bearing and a second thrust bearing are respectively arranged on both sides of the thrust plate;
[0019] The compressor adopts a closed impeller structure, and a fourth radial bearing is arranged on the air inlet side of the compressor.
[0020] Furthermore, it also includes a third radial bearing, and the third radial bearing is located between the thrust plate and the impeller.
[0021] Furthermore, it also includes a second radial bearing located between the thrust plate and the compressor.
[0022] Furthermore, it also includes a compressor and an oblique bearing arranged obliquely, wherein the compressor adopts a closed impeller structure, and the oblique bearing is located between the air inlet side and the air outlet side of the compressor;
[0023] A third thrust bearing is arranged 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] Also includes a coupling and a second rotating shaft, wherein the second rotating shaft is connected to the rotating shaft through the coupling;
[0026] An external bearing component is disposed on the second rotating shaft, and a fifth radial bearing and a sixth radial bearing installed on the second rotating shaft are respectively disposed on both sides of the external bearing component.
[0027] Furthermore, a gas turbine is provided with a rotor system as described in any one of the above, further comprising a combustion chamber, a bearing seat, and a rotating shaft supported on the bearing seat through bearings;
[0028] The combustion chamber is an annular combustion chamber, which is arranged around the rotating axis. 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, and the guide vane assembly is located in front of the impeller.
[0029] The advantages of the present invention compared with the prior art are:
[0030] 1. This solution improves the bearing's support capacity for the impeller by arranging a first boss at the impeller of the rotor system to accommodate the radial bearing, shortening the axial distance between the radial bearing support point and the impeller, and helping the rotor system with the impeller to run 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 to radially support the impeller. Moreover, since the bearing hole support point of the first radial bearing is closer to the center of gravity of the impeller, the bearing's support capacity for the impeller can be improved, which helps the rotor system with the impeller to run more stably.
[0032] 3. This solution sets a first radial bearing close to the impeller, which can minimize the vibration of the turbine end and enhance the supporting capacity. 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 can omit the radial bearing between the compressor and the impeller by arranging radial bearings at the compressor and the impeller, thereby shortening the axial dimension of the rotor system, and forming an air seal structure between the first radial bearing and the third radial bearing. The static pressure between the air seals helps the rotor system to operate more stably.
[0034] 5. This solution can omit the radial bearing and thrust bearing between the compressor and the impeller by arranging radial bearings at the compressor and impeller, and can shorten the axial dimension of the rotor system;
[0035] 6. This solution shortens the axial dimension of the rotor system portion where the first shaft is located, so that additional bearing capacity can be spared for setting the coupling and the second shaft portion. At the same time, the integrated motor can provide a starting torque when the gas turbine including the rotor system is started, especially when the bearing is a hydrodynamic bearing or a foil bearing, which is conducive to the smooth starting of the gas turbine. BRIEF DESCRIPTION OF THE DRAWINGS
[0036] Figure 1 It is a schematic diagram of the structure of the rotor system proposed in this scheme;
[0037] Figure 2 A schematic diagram of the structure of the rotor system proposed in Example 1 of this scheme;
[0038] Figure 3 A schematic diagram of the structure of the rotor system proposed in Example 2 of this scheme;
[0039] Figure 4 A schematic diagram of the structure of the rotor system proposed in Example 3 of this scheme;
[0040] Figure 5 This is a schematic diagram of the structure of the rotor system proposed in Example 4 of this solution;
[0041] Figure 6 A schematic diagram of the structure of the rotor system proposed in Example 5 of this scheme;
[0042] Figure 7 A schematic diagram of the structure of the rotor system proposed in Example 6 of this scheme;
[0043] Figure 8 A schematic diagram of the structure of the rotor system proposed in Example 7 of this scheme;
[0044] Fig. 9 A schematic diagram of the structure of the rotor system proposed in Example 8 of this scheme;
[0045] Fig.10 A schematic diagram of the structure of the rotor system proposed in Example 9 of this solution;
[0046] Fig.11 A schematic diagram of the structure of the rotor system proposed in Example 10 of the present invention;
[0047] Fig.12 A schematic diagram of the structure of the rotor system proposed in Example 11 of the present invention;
[0048] Fig.13 A schematic diagram of the structure of the rotor system proposed in Example 12 of the present invention;
[0049] Fig.14 This is a schematic diagram of the structure of the gas turbine proposed in Example 13 of this scheme.
[0050] Reference numerals: 100, rotating shaft; 300, impeller; 400, combustion chamber; 600, bearing seat; 700, guide vane assembly; 800, compressor; 900, inspiration integrated motor;
[0051] 110, first rotating shaft; 120, second rotating shaft; 130, coupling;
[0052] 210, first radial bearing; 211, first radial bearing hole; 212, bearing body; 213, second radial bearing hole; 214, first axial bearing hole;
[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 DESCRIPTION
[0055] Example 1
[0056] As the instruction manual Figure 1-2 As shown, this embodiment provides a rotor system, including 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 on the stator component of the rotor system.
[0057] The impeller 300 extends a first boss 320 toward the first radial bearing 210 , and the first boss 320 includes a first radial bearing surface;
[0058] The first radial bearing 210 extends to the radial inside or outside 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 may be a static pressure bearing or a dynamic pressure bearing, wherein the static pressure bearing includes but is not limited to a static pressure air bearing, and the dynamic pressure bearing includes but is not limited to a dynamic pressure foil bearing.
[0060] When the first radial bearing 210 is a static pressure air bearing, the first radial bearing 210 has a first radial bearing hole 211 opening toward the first radial bearing surface 311, and the first radial bearing hole 211 is opened on the bearing body 212. A plurality of first radial bearing holes 211 arranged circumferentially along the first radial bearing 210 can be connected through an annular air groove. The first radial bearing hole 211 can be obtained by laser drilling, drilling, etc.
[0061] When the first radial bearing hole 211 is a stepped hole, a component with a smaller aperture (eg, a cylindrical shape) can be installed in a hole with an increased aperture by interference fit to form a stepped hole. The first radial bearing 210 as a static pressure air bearing can be connected to an air source.
[0062] The pressurized gas from the gas source is sprayed toward the first radial bearing surface 311 through the first radial bearing hole 211 to form a bearing gas film to radially support the impeller 300. Since the bearing hole support point of the first radial bearing 210 is closer to the center of gravity of the impeller 300, the bearing's support capacity for the impeller can be improved, which helps the rotor system with the impeller to run more stably.
[0063] Furthermore, if Figure 2 As shown, the first radial bearing surface 311 may be located on the outer circumferential surface of the groove 310 , and the first radial bearing hole 211 is arranged axially outward.
[0064] Example 2
[0065] As the instruction manual Figure 3 As shown, the difference between this embodiment and embodiment 1 is that: the impeller 300 also 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 is provided with a plurality of first radial bearing holes 211 opening toward the first radial bearing surface or the second radial bearing surface, the plurality of first radial bearing holes 211 are distributed in an array along the circumference of the first radial bearing 210 and are connected through an annular air groove, and the annular air groove is connected to an air source.
[0066] In Embodiment 1-2, the first boss 320 and the second boss 330 are both formed by the cut groove 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 the instruction manual Figure 4 As shown, the difference between this embodiment and embodiment 1 is that the outer circumferential surface of the groove 310 has a first radial bearing surface 311, the inner circumferential 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] The pressurized gas from the gas source is sprayed toward the first radial bearing surface 311 and the second radial bearing surface 312 through the first radial bearing hole 211 and the second radial bearing hole 213 respectively, forming a bearing gas film, which can further improve the supporting capacity of the first radial bearing 210 .
[0070] Example 4
[0071] As the instruction manual Figure 5 As shown, the difference between this embodiment and embodiment 1 is that: the first radial bearing 210 also includes a first axial bearing hole 214, and the opening of the first axial bearing hole 214 faces the axial side of the groove 310. At this time, the pressurized gas from the gas source passes through the first radial bearing hole 211 and the first axial bearing hole 214 and is sprayed toward the first radial bearing surface 311 and the side of the groove 310 respectively, so as to axially support the impeller 300, which can further improve the supporting capacity of the first radial bearing 210.
[0072] Example 5
[0073] As 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 rotating shaft 100. The impeller 300 of the gas turbine is a turbine, and the impeller 300 has a groove 310. The rotor system also includes a first radial bearing 210 extending into the groove 310. The rotating shaft 100 has a thrust plate and the thrust plate is located between the compressor 800 and the impeller 300. Figure 6 As shown in FIG. 1 , the thrust plate and the rotating shaft 100 are cross-distributed to form a cross shape.
[0074] The rotor system further includes a second radial bearing 220 located between the compressor 800 and the thrust plate, and a first thrust bearing 230 and a second thrust bearing 240 are respectively disposed on both sides of the thrust plate.
[0075] Since the impeller 300 used in the gas turbine needs to be resistant to high temperatures, has high density and large mass, the temperature of the side of the impeller 300 away from the compressor 800 is high, and it is generally impossible to set a bearing for support, because the bearing set here will deform due to the high temperature, and it is difficult to ensure dimensional accuracy and life. If a radial bearing is set on the side of the impeller 300 facing the compressor 800, a cantilever structure will be formed at the impeller 300, which will easily cause vibration when the rotor system runs at high speed. Therefore, the present invention sets a first radial bearing 210 close to the impeller 300, which can minimize the vibration of the turbine end and enhance the supporting capacity.
[0076] Example 6
[0077] As the instruction manual Figure 7 As shown, this embodiment is based on Embodiment 5: it also includes a third radial bearing 250 located between the thrust plate and the impeller 300 to further enhance the radial support force at the impeller 300, and 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 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 rotating shaft 100, wherein the impeller 300 of the gas turbine is a turbine. The impeller 300 has a groove 310, and the rotor system further includes a first radial bearing 210 extending into the groove 310. The compressor 800 adopts a closed impeller structure, and an oblique bearing 261 is provided on the intake side of the compressor 800.
[0080] The rotating shaft 100 has a thrust plate and the thrust plate is located between the compressor 800 and the impeller 300. Figure 8 As shown in FIG. 1 , the thrust disc and the rotating shaft 100 are arranged in a cross shape. A first thrust bearing 230 and a second thrust bearing 240 are arranged on both sides of the thrust disc of the rotating shaft 100 .
[0081] By adopting the compressor 800 with a closed impeller structure and arranging the oblique bearing 261 in the radial direction of the compressor 800, the supporting capacity of the compressor 800 can be improved. In addition, by arranging radial bearings at the compressor 800 and the impeller 300, the radial bearing between the compressor 800 and the impeller 300 can be omitted, and the axial dimension of the rotor system can be shortened.
[0082] Example 8
[0083] As the instruction manual Fig. 9As shown, based on Example 8, this embodiment further includes a third radial bearing 250 located between the thrust plate and the impeller 300 to further enhance the radial support force at the impeller 300, and an air seal structure can be formed between the first radial bearing 210 and the third radial bearing 250. The static pressure between the air seals helps the rotor system to operate more stably.
[0084] Example 9
[0085] As the instruction manual Fig.10 As shown, based on Example 9, this embodiment further includes a second radial bearing 220 located between the thrust plate and the compressor 800 to further increase the radial support force of the rotor system.
[0086] Example 10
[0087] As the instruction manual Fig.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 rotating shaft 100, wherein the impeller 300 of the gas turbine is a turbine. The impeller 300 has a groove 310, and the rotor system further 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 obliquely arranged oblique bearing 261, which is located between the air inlet side and the air outlet side of the compressor 800. The oblique bearing 261 can provide radial support 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 compressor 800 with a closed impeller structure and providing an oblique bearing 261 at the compressor 800, the radial and axial supporting capabilities of the compressor 800 can be improved.
[0089] Furthermore, by providing radial bearings at the compressor 800 and the impeller 300 and providing a thrust bearing at the compressor 800, the radial bearings and thrust bearings between the compressor 800 and the impeller 300 can be omitted, thereby shortening the axial dimension of the rotor system.
[0090] Embodiment 11
[0091] As the instruction manual Fig.12 As shown, based on Example 10, this embodiment further 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 the instruction manual Fig.13As shown, this embodiment further includes a coupling 130 and a second rotating shaft 120 on the basis of embodiment 10, and the rotating shaft 100 in embodiment 10 corresponds to the first rotating shaft 110 in this embodiment. An external load component is arranged on the second rotating shaft 120, and the external load component may be an inspiration integrated motor 900, a second compressor, a second turbine, etc. In this embodiment, the inspiration integrated motor 900 is taken as an example, and the inspiration integrated motor 900 is respectively provided with a fifth radial bearing 280 and a sixth radial bearing 290 installed on the second rotating shaft 120 on both sides. The fifth radial bearing 280 and the sixth radial bearing 290 may be non-contact bearings, including but not limited to static pressure bearings or dynamic pressure bearings such as dynamic pressure foil bearings.
[0094] Since the diameter of the second rotating shaft 120 is smaller than that of the first rotating shaft 110 , the peripheral 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 may be contact bearings including but not limited to ball bearings.
[0095] Thanks to the shortened axial dimension of the rotor system portion where the first rotating shaft 110 is located, additional bearing capacity is available for setting the coupling 130 and the second rotating shaft 120. The integrated motor 900 can provide a starting torque when the gas turbine including the rotor system is started, especially when the bearing is a hydrodynamic bearing or a foil bearing, which is conducive to the smooth start of the gas turbine.
[0096] Example 13
[0097] As the instruction manual Figure 1-14 As shown, this embodiment provides a gas turbine, which includes any rotor system of the above embodiments 1-12. In addition, it also includes a combustion chamber 400, a bearing seat 600, and a guide vane assembly 700;
[0098] The rotating shaft 100 may be supported on a casing or a bearing seat 600 of the gas turbine through bearings.
[0099] The combustion chamber 400 may be an annular combustion chamber, a single-tube combustion chamber, an annular tube combustion chamber, etc. Fig.14 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 , and 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 structure of the gas turbine provided in this embodiment can refer to a gas turbine disclosed in the applicant's prior application CN115773182A and a gas turbine disclosed in the applicant's prior application CN118375519A, etc., so no further details will be given here.
[0101] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In addition, features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.
[0102] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.
[0103] In the description of the present invention, the description with reference to the terms "one embodiment", "some embodiments", "illustrative embodiments", "examples", "specific examples", or "some examples" means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner.
[0104] Although the embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the claims and their equivalents.
Claims
1. A rotor system, characterized in that: It comprises 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 a stator component; The impeller (300) extends a first boss (320) toward the first radial bearing (210), and the first boss (320) includes a first radial bearing surface; The first radial bearing (210) extends to the radial inside or outside 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); and 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) including a second radial bearing surface, the first radial bearing (210) having a plurality of first radial bearing holes opening toward the first radial bearing surface and / or the second radial bearing surface, the plurality of first radial bearing holes being distributed in an array along the circumference of the first radial bearing (210) and connected through an annular air groove, and the annular air groove being 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), wherein the opening of the first axial bearing hole (214) faces the axial side surface of the groove (310).
4. A rotor system according to claim 1, characterized in that: The invention also includes a compressor (800), a thrust plate and a second radial bearing (220). The compressor (800) is installed on a side of the rotating 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 arranged on both sides of the thrust plate. The second radial bearing (220) is installed between the thrust plate 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, wherein the compressor (800) is installed on a side of the rotating shaft (100) away from the impeller (300), the thrust plate is located between the compressor (800) and the impeller (300), and a first thrust bearing (230) and a second thrust bearing (240) are respectively arranged 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 intake side of the compressor (800).
6. A rotor system according to claim 4 or 5, characterized in that: The invention also comprises a third radial bearing (250), wherein the third radial bearing (250) is located between the thrust plate and the impeller (300).
7. A rotor system according to claim 5, characterized in that: The invention 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) arranged obliquely, wherein the compressor (800) adopts a closed impeller structure, and the oblique 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: The invention 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), wherein the second rotating shaft (120) is connected to the rotating shaft (100) through the coupling (130); An external bearing component is disposed on the second rotating shaft (120), and a fifth radial bearing (280) and a sixth radial bearing (290) mounted on the second rotating shaft (120) are respectively disposed on both sides of the external bearing component.
11. A gas turbine, comprising a rotor system according to any one of claims 1 to 10, characterized in that: It also includes a combustion chamber (400), a bearing seat (600), and a rotating shaft (100) supported on the bearing seat (600) via a bearing.