Rotating device and gas turbine

Abstract

The present invention discloses a rotating device, which includes a rotating shaft, a turbine and a housing. The turbine is fixedly installed on the rotating shaft, and the rotating shaft and the turbine are installed in the housing. The rotating device further includes a limiting component installed on the rotating shaft. The limiting component includes a bearing portion, a connecting portion and a supporting portion that is supported and connected between the bearing portion and the connecting portion. The limiting component is connected to the rotating shaft through the connecting portion. There is a gap between the bearing portion and the housing, and this gap forms the air film gap of a gas bearing. The bearing portion, the housing and the gap form a gas bearing. The present invention also discloses a gas turbine including the rotating device. In the present invention, a limiting component is provided on one side of the turbine. There is a gap between the bearing portion of the limiting component and the housing, and the bearing portion, the housing and the gap form a gas bearing. When the limiting component rotates relative to the housing around the axis, an air film is formed to support the limiting component relative to the housing, thereby supporting the rotating shaft and increasing the stability when the turbine and the rotating shaft rotate.

Description

Technical Field

[0001] The present invention relates to a rotating device and a gas turbine, belonging to the technical field of gas turbines. Background Art

[0002] A gas turbine uses continuously flowing gas as the working medium to drive the impeller to rotate at a high speed, converting the energy of the fuel into useful work. It is a rotating impeller type heat engine, which mainly includes three major components: a compressor, a combustion chamber, and a turbine. Among them, the compressor inhales air from the external atmospheric environment and compresses it step by step to increase the pressure, and at the same time, the air temperature also increases accordingly; the compressed air is sent to the combustion chamber to be mixed with the injected fuel and burned to generate high-temperature and high-pressure gas; then it enters the turbine to expand and do work, pushing the turbine to drive the compressor and the external load rotor to rotate at a high speed together, realizing the partial conversion of the chemical energy of gas or liquid fuel into mechanical work, and electric energy can be output by connecting a generator.

[0003] In the rotor system of a gas turbine, the turbine needs to rotate at a high speed and has a high working temperature. For example, for a small-power gas turbine, the rotational speed of the rotor system of the gas turbine can reach or exceed 140000 RPM (revolutions per minute), the working temperature of the turbine can reach 950 - 1000 °C, the working linear velocity of the turbine impeller is extremely high, and thus the centrifugal force borne is as high as 100 MPa. The turbine often uses materials with high strength and high temperature resistance (such as nickel) to meet the working conditions at high rotational speed and high temperature, and such materials usually have a high density, the turbine has a large mass, and the turbine is usually located at the cantilever end of the rotor system. Thus, when the rotor system rotates at a high speed, the turbine will have a large amplitude of swing.

[0004] Non-contact bearings (such as gas bearings) are becoming more and more commonly used in some high-speed occasions due to their small friction coefficient and friction torque, high motion accuracy, etc. A gas bearing relies on the pressure gas film in the bearing clearance to support the rotor system. Gas bearings have various forms such as hydrostatic bearings, hydrodynamic bearings, or hybrid hydrostatic and hydrodynamic bearings. Summary of the Invention

[0005] In view of the above-mentioned prior art, in order to improve the rotational stability of the turbine and the rotating shaft, the present invention provides a rotating device and a gas turbine. The present invention effectively improves the rotational stability of the turbine and the rotating shaft by providing a gas bearing on one side of the turbine of the rotating device / gas turbine to support the rotating shaft.

[0006] The present invention is realized through the following technical solutions:

[0007] A rotating device includes a rotating shaft, a turbine, and a housing. The turbine is fixedly installed on the rotating shaft, and the rotating shaft and the turbine are installed inside the housing. It further includes a limiting component installed on the rotating shaft. The limiting component includes a bearing part, a connecting part, and a supporting part that supports and connects between the bearing part and the connecting part. The limiting component is connected to the rotating shaft through the connecting part. There is a gap between the bearing part and the housing (specifically, the outer ring surface of the bearing part is called the first bearing surface, the surface of the housing corresponding to the first bearing surface is called the second bearing surface, and there is a gap between the first bearing surface and the second bearing surface). This gap can form the air film gap of a gas bearing. The bearing part, the housing, and the gap form a gas bearing. When the limiting component rotates relative to the housing around the axis, an air film gap for forming an air film is formed in this gap to support the limiting component relative to the housing, thereby supporting the rotating shaft and increasing the stability when the turbine and the rotating shaft rotate.

[0008] Further, the gas bearing formed by the bearing part, the housing, and their gap is any one of a hydrostatic bearing, a hydrodynamic bearing, or a hybrid hydrostatic and hydrodynamic bearing.

[0009] Further, the bearing part can be a bearing ring in a circular ring shape.

[0010] Further, the surface of the connecting part facing the rotating shaft has an internal thread, and correspondingly, the rotating shaft has an external thread. The limiting component is threadedly connected to the rotating shaft through the connecting part to limit the turbine. When the turbine rotates, the limiting component rotates synchronously with the turbine. In addition, besides being a nut, the connecting part can also be connected to the rotating shaft through a chuck / slot, etc.

[0011] Further, the supporting part can be in a spoke shape.

[0012] Further, the number of the supporting parts is greater than or equal to 3, and air channels are formed between the supporting parts, so that the exhaust gas of the turbine is discharged through the air channels.

[0013] Further, the cross-section of the supporting part can be a shuttle shape.

[0014] Further, the turbine is a centripetal turbine. The turbine has a radially large end and a radially small end that are axially opposite. The limiting component is located on one side of the radially small end of the turbine, and the inner diameter of the bearing part is greater than the outer diameter of the radially small end of the turbine.

[0015] Further, the turbine is an axial flow turbine. The housing has an annular groove corresponding to the bearing part. The second bearing surface of the housing is located on the outer ring surface of the annular groove, and part or all of the bearing part is accommodated in the annular groove.

[0016] Further, the turbine is an axial flow turbine. The housing is provided with a housing bearing part and a housing supporting part. The housing bearing part is connected to the housing through the housing supporting part, and the second bearing surface of the housing is located on the surface of the housing bearing part facing the rotating shaft.

[0017] Further, the housing support portion may be in the shape of a spoke.

[0018] Further, the number of the housing support portions is greater than or equal to 3, and an air passage is formed between the housing support portions, so that the exhaust gas of the turbine is discharged through the air passage.

[0019] Further, the cross section of the housing support portion may be spindle-shaped.

[0020] Further, there is a gap between the housing bearing portion and the turbine in the axial direction to prevent the turbine and the housing bearing portion from colliding due to vibration or swing during high-speed rotation. Specifically, in the axial direction, the connecting portion facing the turbine side is higher than the bearing portion and / or the housing bearing portion, and / or: a gasket is provided between the turbine and the connecting portion.

[0021] Further, in the axial direction, the bearing portion and / or the housing bearing portion on the side facing away from the turbine is higher than the connecting portion to increase the air film area between the bearing portion and the housing bearing portion and enhance the support effect.

[0022] A gas turbine includes a rotating device and a compressor having the above structure, and the compressor is fixedly installed on the rotating shaft. The structure of the gas turbine further includes a combustion chamber, an exhaust section, etc.

[0023] Further, a first radial bearing and a thrust disk are further provided on the rotating shaft; the rotating shaft has an axial first end and an axial second end that are axially opposite, the first radial bearing and the thrust disk are located at the axial first end of the rotating shaft, the turbine is located at or near the axial second end of the rotating shaft, the thrust disk is located between the first radial bearing and the turbine, and the compressor is located between the thrust disk and the turbine; a thrust bearing is provided on one side or both sides of the thrust disk.

[0024] Further, the housing may be a gas turbine housing, a combustion chamber housing, an exhaust section housing or an intermediate housing connected to these housings.

[0025] Further, the first radial bearing and the thrust bearing may be gas bearings. The gas bearing is any one of a static pressure bearing, a dynamic pressure bearing or a hybrid static and dynamic pressure bearing.

[0026] Further, the gas turbine further includes a reinforcing ring, the reinforcing ring is annular, and the reinforcing ring is fixedly connected between the turbine and the compressor.

[0027] Further, a second radial bearing is provided on the radially outer side of the reinforcing ring; the second radial bearing may be a gas bearing.

[0028] Further, positioning structures for positioning the reinforcing ring are provided on the opposite surfaces of the compressor and the turbine; the positioning structures are as follows: a positioning ring groove is provided on the surface of the compressor close to the turbine, and a protrusion is provided on the surface of the turbine close to the compressor. The protrusion forms an annular positioning stop. One end of the reinforcing ring is inserted into the positioning ring groove, and the other end is inserted into the inner circumference of the annular positioning stop.

[0029] Further, exhaust holes are provided on the side wall of the reinforcing ring, and the number of exhaust holes can be 4.

[0030] In the rotating device and the gas turbine of the present invention, a limiting member is provided on one side of the turbine. There is a gap between the bearing portion of the limiting member and the housing, and this gap forms the air film gap of the gas bearing. The bearing portion, the housing, and the gap form the gas bearing. When the limiting member rotates relative to the housing around the axis, an air film is formed in this gap to support the limiting member relative to the housing, thereby supporting the rotating shaft and increasing the stability when the turbine and the rotating shaft rotate.

[0031] In some further solutions, the supporting portion of the limiting member can be in a spoke shape, the number can be more than 3, and the cross-section can be spindle-shaped to achieve a better exhaust effect.

[0032] In some further solutions, an annular groove for accommodating part or all of the bearing portion can be provided on the housing, or a housing bearing portion and a housing supporting portion can be provided to achieve a better supporting effect and exhaust effect.

[0033] When the bearing structure mentioned in this article is a hydrostatic bearing, it has the following structure: including a bearing body and a bearing sleeve nested from the outside to the inside. The bearing sleeve has a predetermined radial clearance with the rotating shaft in the radial direction (when the bearing is a radial bearing), or the bearing sleeve and the thrust disk are oppositely installed in the axial direction of the rotating shaft and have a predetermined axial clearance (when the bearing is a thrust bearing); an annular air cavity is provided on the outer peripheral surface of the bearing sleeve, and through holes for communicating the annular air cavity with the gap (radial clearance or axial clearance) are provided on the bearing sleeve; air holes for communicating the annular air cavity with an external air source are provided on the bearing body; for the convenience of processing and without affecting the gas pressure in the gap, the through holes can be stepped holes, that is, the diameter of the through hole on the side far from the gap is large, and the diameter on the side close to the gap is small.

[0034] When the bearing structure mentioned in this article is a hydrodynamic bearing, it has the following structure: including a bearing body. The bearing body has a predetermined radial clearance with the rotating shaft in the radial direction (when the bearing is a radial bearing), and a hydrodynamic generating groove is provided on the inner diameter surface of the bearing body or the part of the rotating shaft for installing the bearing body; or: the bearing body and the thrust disk are oppositely installed in the axial direction of the rotating shaft and have a predetermined axial clearance (when the bearing is a thrust bearing), and a hydrodynamic generating groove is provided on the end face of the bearing body facing the thrust disk or the end face of the thrust disk facing the bearing body.

[0035] When the bearing structure mentioned in this article is a hybrid hydrostatic and hydrodynamic bearing, its structure has the characteristics of both hydrostatic bearings and hydrodynamic bearings at the same time. The present invention will not elaborate further on this.

[0036] The various terms and phrases used in the present invention have the general meanings well-known to those skilled in the art. If the terms and phrases mentioned are inconsistent with the well-known meanings, the meanings expressed in the present invention shall prevail. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] Figure 1 : Schematic structural diagram of the rotating device of Embodiment 1.

[0038] Figure 2 : Schematic structural diagram of the limiting component.

[0039] Figure 3 : Schematic structural diagram of the limiting component (the cross-section of the supporting part is spindle-shaped).

[0040] Figure 4 : Schematic structural diagram of the gas turbine of Embodiment 1.

[0041] Figure 5 : Schematic structural diagram of the rotating device of Embodiment 2.

[0042] Figure 6 : Schematic structural diagram of the gas turbine of Embodiment 2.

[0043] Figure 7 : Schematic structural diagram of the rotating device of Embodiment 3.

[0044] Figure 8 : Schematic structural diagram of the gas turbine of Embodiment 3.

[0045] Figure 9 : Schematic structural diagram of the rotating device of Embodiment 4.

[0046] Figure 10 : Schematic structural diagram of the housing bearing part and the housing support part of Embodiment 4.

[0047] Figure 11 : Schematic structural diagram of the gas turbine of Embodiment 4.

[0048] Among them, 100, rotating shaft; 110, thrust disk; 200, turbine; 300, housing; 310, housing bearing part; 320, housing support part; 400, limiting component; 410, bearing part; 420, support part; 430, connecting part; 500, compressor; 610, first radial bearing; 620, thrust bearing. DETAILED DESCRIPTION OF THE INVENTION

[0049] The present invention will be further described below in conjunction with embodiments. However, the scope of the present invention is not limited to the following embodiments. Those skilled in the art can understand that various changes and modifications can be made to the present invention without departing from the spirit and scope of the present invention.

[0050] Embodiment 1 A rotating device and a gas turbine

[0051] A rotating device includes a rotating shaft 100, a turbine 200, and a housing 300. The turbine 200 is fixedly installed on the rotating shaft 100, and the rotating shaft 100 and the turbine 200 are installed in the housing 300. The turbine 200 is a centripetal turbine, as Figure 1 shown ( Figure 1 only a part of the housing 300 is shown); it further includes a limiting component 400 installed on the rotating shaft 100. The limiting component 400 includes a bearing portion 410, a connecting portion 430, and a supporting portion 420 supported and connected between the bearing portion 410 and the connecting portion 430. The limiting component 400 is connected to the rotating shaft 100 through the connecting portion 430: the surface of the connecting portion 430 facing the rotating shaft 100 has an internal thread, and correspondingly, the rotating shaft 100 has an external thread. The limiting component 400 is threadedly connected to the rotating shaft 100 through the connecting portion 430 to limit the turbine 200. When the turbine 200 rotates, the limiting component 400 rotates synchronously with the turbine 200.

[0052] The bearing portion 410 can be an annular bearing ring, as Figure 2 shown; there is a gap between the bearing portion 410 and the housing 300 (specifically, the outer ring surface of the bearing portion 410 is called the first bearing surface, and the surface of the housing 300 corresponding to the first bearing surface is called the second bearing surface. There is a gap between the first bearing surface and the second bearing surface). This gap can form the air film gap of a gas bearing. The bearing portion 410, the housing 300, and the gap form a gas bearing. When the limiting component 400 rotates relative to the housing 300 around the axis, an air film is formed in this gap to support the limiting component 400 relative to the housing 300, thereby supporting the rotating shaft 100 and increasing the stability when the turbine 200 and the rotating shaft 100 rotate.

[0053] The gas bearing formed by the bearing portion 410, the housing 300, and their gap can be any one of a hydrostatic bearing, a hydrodynamic bearing, or a hybrid hydrostatic and hydrodynamic bearing.

[0054] The supporting portion 420 can be in a spoke shape, and the number of the supporting portions 420 can be 3 or more, as Figure 2 shown. An air passage is formed between the supporting portions 420, so that the exhaust gas of the turbine 200 is discharged through the air passage.

[0055] The cross-section of the supporting portion 420 can be spindle-shaped, as Figure 3As shown, such a structure can reduce gas resistance, which is beneficial to the exhaust of the turbine 200.

[0056] The turbine 200 has axially opposite radially large ends and radially small ends. The limiting member 400 is located on one side of the radially small end of the turbine 200. The inner diameter of the bearing portion 410 is larger than the outer diameter of the radially small end of the turbine 200, avoiding the bearing portion 410 from blocking the exhaust of the turbine 200, which is beneficial to the exhaust of the turbine 200.

[0057] A gas turbine includes a rotating device and a compressor 500 having the above structure. The compressor 500 is fixedly installed on the rotating shaft 100, as Figure 4 shown.

[0058] The rotating shaft 100 is further provided with a first radial bearing 610 and a thrust disk 110; the rotating shaft 100 has axially opposite first axial end and second axial end. The first radial bearing 610 and the thrust disk 110 are located at the first axial end of the rotating shaft 100. The turbine 200 is located at or near the second axial end of the rotating shaft 100. The thrust disk 110 is located between the first radial bearing 610 and the turbine 200. The compressor 500 is located between the thrust disk 110 and the turbine 200; Thrust bearings 620 are arranged on both sides of the thrust disk 110.

[0059] When the gas turbine is working, the rotating shaft 100, the compressor 500, and the turbine 200 rotate at a high speed around the axis relative to the housing 300. The first radial bearing 610 provides support at the first axial end, controlling the radial swing or movement of the rotating shaft 100. The thrust bearing 620 provides support axially, controlling the axial swing or movement of the rotating shaft 100; At the same time, during the high-speed rotation of the rotating shaft 100 and the turbine 200, an air film is formed in the gap between the bearing portion 410 and the housing 300. The bearing portion 410, the housing 300 and the gap form a gas bearing, providing support at the second axial end, controlling the radial swing or movement of the rotating shaft 100 and the turbine 200; The first radial bearing 610, the thrust bearing 620, and the gas bearing formed by the bearing portion 410, the housing 300 and the gap cooperate with each other to jointly play a supporting role, increasing the stability of the gas turbine during operation and avoiding large-amplitude swing or movement of the rotating shaft 100, the compressor 500, and the turbine 200.

[0060] It can be understood that Figure 4 only one example of the gas turbine according to the embodiment of the present invention is shown. In some other alternative examples, the thrust disk 110 and its corresponding bearings may be located between the compressor 500 and the turbine 200. A bearing ring sleeved on the outer side of the turbine 200, the housing 300 and the gap therebetween can form a gas bearing, which can support the turbine 200 relative to the housing 300. Especially when the weight of the turbine 200 is large, it can increase the stability of the turbine 200 during rotation.

[0061] The housing 300 can be a gas turbine housing, a combustion chamber (not shown in the figure) housing, an exhaust section (not shown in the figure) housing, or an intermediate housing connected to the above-mentioned housings.

[0062] The first radial bearing 610 and the thrust bearing 620 can be gas bearings. The gas bearing can be any one of a static pressure bearing, a dynamic pressure bearing, or a hybrid static and dynamic pressure bearing.

[0063] When the compressor 500 is located between the thrust disk 110 and the turbine 200, a reinforcing ring can also be provided on the gas turbine. The reinforcing ring is annular and is fixedly connected between the turbine 200 and the compressor 500. By setting the reinforcing ring, the rigidity of the compressor 500 and the turbine 200 can be improved, and indirectly, the rigidity of the rotating shaft 100 between the compressor 500 and the turbine 200 can also be improved, the critical speed of the rotor system can be increased to adapt to the normal operating speed, and at the same time, the vibration of the rotating shaft 100 can be reduced to avoid the resonance region.

[0064] A second radial bearing is provided on the radially outer side of the reinforcing ring; the second radial bearing is a gas bearing.

[0065] A positioning structure for positioning the reinforcing ring can also be provided on the surfaces of the compressor 500 and the turbine 200 facing each other; the positioning structure can be: a positioning ring groove is provided on the surface of the compressor 500 close to the turbine 200, and a protrusion is provided on the surface of the turbine 200 close to the compressor 500. The protrusion forms an annular positioning stop. One end of the reinforcing ring is inserted into the positioning ring groove, and the other end is inserted into the inner circumference of the annular positioning stop.

[0066] Exhaust holes can be provided on the side wall of the reinforcing ring, and the number of exhaust holes can be 4. The exhaust holes are used to discharge the gas inside the reinforcing ring to ensure that the pressure inside and outside the reinforcing ring is equal, and to avoid the increase in heat inside the reinforcing ring caused by the heat generated by the working air flow during the operation of the compressor 500 and the turbine 200, the increase in the internal pressure of the ring, which affects the service life of the reinforcing ring or even damages the reinforcing ring.

[0067] Embodiment 2 A rotating device and a gas turbine

[0068] The structure of the rotating device is the same as that of Embodiment 1, except that: the turbine 200 is an axial flow turbine. As Figure 5 shown, the axial flow turbine has the advantages of a small cross-section, simple structure, low cost, and strong flow capacity.

[0069] The structure of the gas turbine is the same as that of Embodiment 1, except that: the turbine 200 is an axial flow turbine. As Figure 6 shown.

[0070] The axial-flow turbine refers to a turbine through which the working fluid flows axially through the turbine impeller. Its working principle is that the blades on the turbine are rotated by the action of the gas flow. Since the main direction of the gas flow is parallel to the turbine shaft, it is called an axial-flow turbine. Its structure usually includes a central hub and a plurality of blades circumferentially located on the central hub. The blades extend radially outward from the central hub, and the gas flow channel formed by the blades is convergent.

[0071] Embodiment 3: A rotating device and a gas turbine

[0072] The structure of the rotating device is the same as that in Embodiment 2, except that: the housing 300 has an annular groove corresponding to the bearing portion 410, as Figure 7 shown. The second bearing surface of the housing 300 is located on the outer ring surface of the annular groove, and part or all of the bearing portion 410 is received in the annular groove. In this way, while not blocking the exhaust of the turbine 200, the gap between the radially outer side surface of the turbine 200 and the housing 300 is reduced, improving the aerodynamic efficiency of the turbine 200.

[0073] The structure of the gas turbine is the same as that in Embodiment 2, except that: the housing 300 has an annular groove corresponding to the bearing portion 410, as Figure 8 shown. The second bearing surface of the housing 300 is located on the outer ring surface of the annular groove, and part or all of the bearing portion 410 is received in the annular groove. In this way, while not blocking the exhaust of the turbine 200, the gap between the radially outer side surface of the turbine 200 and the housing 300 is reduced, improving the aerodynamic efficiency of the turbine 200.

[0074] Embodiment 4: A rotating device and a gas turbine

[0075] The structure of the rotating device is the same as that in Embodiment 2, except that: the housing 300 is provided with a housing bearing portion 310 and a housing support portion 320. The housing bearing portion 310 is connected to the housing 300 through the housing support portion 320. The second bearing surface of the housing 300 is located on the surface of the housing bearing portion 310 facing the rotating shaft 100, as Figure 9 shown.

[0076] The housing support portion 320 can be in a spoke shape, and the number of the housing support portions 320 can be 3 or more, as Figure 10 shown. An air duct is formed between the housing support portions 320, so that the exhaust of the turbine 200 is discharged through the air duct.

[0077] The cross-section of the housing support portion 320 can be spindle-shaped to reduce the gas resistance and facilitate the exhaust of the turbine 200.

[0078] The housing bearing portion 310 and the turbine 200 have a gap in the axial direction (the connecting portion 430 abuts against the turbine 200 to limit the position of the turbine 200), so as to prevent the turbine 200 and the housing bearing portion 310 from colliding due to vibration or swing during high-speed rotation. In some examples, in the axial direction, the connecting portion 430 facing the turbine 200 side is higher than the bearing portion 410 and / or the housing bearing portion 310; in other examples, a gasket can be provided between the turbine 200 and the connecting portion 430, so that there is a gap between the housing bearing portion 310 and the turbine 200. In the axial direction, the bearing portion 410 and / or the housing bearing portion 310 on the side facing away from the turbine 200 can be higher than the connecting portion 430 to increase the air film area between the bearing portion 410 and the housing bearing portion 310 and enhance the support effect.

[0079] The structure of the gas turbine is the same as that of Embodiment 2, except that: a housing bearing portion 310 and a housing support portion 320 are provided on the housing 300, the housing bearing portion 310 is connected to the housing 300 through the housing support portion 320, and the second bearing surface of the housing 300 is located on the surface of the housing bearing portion 310 facing the rotating shaft 100, as Figure 11 shown.

[0080] The housing support portion 320 can be in a spoke shape, and the number of the housing support portions 320 can be 3 or more. An air passage is formed between the housing support portions 320, so that the exhaust gas of the turbine 200 is discharged through the air passage.

[0081] The cross-section of the housing support portion 320 can be spindle-shaped to reduce gas resistance and facilitate the discharge of the exhaust gas of the turbine 200.

[0082] The housing bearing portion 310 and the turbine 200 have a gap in the axial direction (the connecting portion 430 abuts against the turbine 200 to limit the position of the turbine 200), so as to prevent the turbine 200 and the housing bearing portion 310 from colliding due to vibration or swing during high-speed rotation. In some examples, in the axial direction, the connecting portion 430 facing the turbine 200 side is higher than the bearing portion 41 and / or the housing bearing portion 310; in other examples, a gasket can be provided between the turbine 200 and the connecting portion 430, so that there is a gap between the housing bearing portion 310 and the turbine 200. In the axial direction, the bearing portion 410 and / or the housing bearing portion 310 on the side facing away from the turbine 200 can be higher than the connecting portion 430 to increase the air film area between the bearing portion 410 and the housing bearing portion 310 and enhance the support effect.

[0083] Although the specific embodiments of the present invention have been described above in conjunction with the embodiments, it is not a limitation on the protection scope of the present invention. Those skilled in the art should understand that, based on the technical solutions of the present invention, various modifications or deformations that can be made by those skilled in the art without creative efforts are still within the protection scope of the present invention.

Claims

1. A rotating device, comprising a rotating shaft, a turbine and a housing, the turbine is fixedly installed on the rotating shaft, and the rotating shaft and the turbine are installed in the housing, characterized in that: It further includes a limiting component installed on the rotating shaft. The limiting component includes a bearing part, a connecting part, and a supporting part that is supported and connected between the bearing part and the connecting part. The limiting component is connected to the rotating shaft through the connecting part; there is a gap between the bearing part and the housing, and this gap forms the air film gap of the gas bearing. The bearing part, the housing, and the gap form the gas bearing; The bearing part is a circular bearing ring; The surface of the connecting part facing the rotating shaft has internal threads. Correspondingly, the rotating shaft has external threads. The limiting component is threadedly connected to the rotating shaft through the connecting part to limit the turbine. When the turbine rotates, the limiting component rotates synchronously with the turbine; The supporting part is in a spoke shape, and the number of the supporting parts is greater than or equal to 3. An air passage is formed between the supporting parts; The cross-section of the supporting part is spindle-shaped; The turbine is a centripetal turbine. The turbine has a radially large end and a radially small end that are axially opposite. The limiting component is located on one side of the radially small end of the turbine, and the inner diameter of the bearing part is greater than the outer diameter of the radially small end of the turbine.

2. The rotating device according to claim 1, wherein: The turbine is replaced with an axial-flow turbine. A housing bearing part and a housing supporting part are provided on the housing. The housing bearing part is connected to the housing through the housing supporting part. The second bearing surface of the housing is located on the surface of the housing bearing part facing the rotating shaft; The outer ring surface of the bearing part is called the first bearing surface, and the surface of the housing bearing part of the housing corresponding to the first bearing surface is called the second bearing surface. There is a gap between the first bearing surface and the second bearing surface; The housing supporting part is in a spoke shape, and the number of the housing supporting parts is greater than or equal to 3. An air passage is formed between the housing supporting parts; The cross-section of the housing supporting part is spindle-shaped; There is a gap between the housing bearing part and the turbine axially; Axially, the connecting part facing the turbine side is higher than the bearing part and / or the housing bearing part; Axially, the bearing part and / or the housing bearing part on the side away from the turbine is higher than the connecting part; A gasket is provided between the turbine and the connecting part.

3. A gas turbine, including the rotating device according to claim 1 or 2 and a compressor, and the compressor is fixedly installed on the rotating shaft.

4. The gas turbine according to claim 3, characterized in that: A first radial bearing and a thrust disk are further provided on the rotating shaft; the rotating shaft has an axially first end and an axially second end that are axially opposite. The first radial bearing and the thrust disk are located at the axially first end of the rotating shaft, the turbine is located at or near the axially second end of the rotating shaft, the thrust disk is located between the first radial bearing and the turbine, and the compressor is located between the thrust disk and the turbine; a thrust bearing is provided on one side or both sides of the thrust disk.

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