阅读说明：本技术 转动装置及燃气轮机 (Turning device and gas turbine ) 是由 靳普 于 2021-07-27 设计创作，主要内容包括：本发明公开了一种转动装置,包括转轴、涡轮和壳体,涡轮固定安装于转轴上,转轴和涡轮安装于壳体内；还包括安装于转轴上的限位部件,所述限位部件包括轴承部、连接部和支撑连接于轴承部与连接部之间的支撑部,限位部件通过连接部与转轴连接；轴承部与壳体之间具有间隙,该间隙形成气体轴承的气膜间隙,轴承部、壳体及间隙形成气体轴承。本发明还公开了包括该转动装置的燃气轮机。本发明在涡轮一侧设置限位部件,限位部件的轴承部与壳体之间具有间隙,轴承部、壳体及间隙形成气体轴承；在限位部件围绕轴线相对于壳体转动时形成气膜,以相对于壳体对限位部件形成支撑,从而对转轴形成支撑,增加涡轮和转轴转动时的稳定性。(The invention discloses a rotating device which comprises a rotating shaft, a turbine and a shell, wherein the turbine is fixedly arranged on the rotating shaft; the limiting component comprises a bearing part, a connecting part and a supporting part which is connected between the bearing part and the connecting part in a supporting way, and is connected with the rotating shaft through the connecting part; a gap is formed between the bearing portion and the housing, the gap forms a gas film gap of the gas bearing, and the bearing portion, the housing and the gap form the gas bearing. The invention also discloses a gas turbine comprising the rotating device. The invention sets up the spacing part on one side of the turbine, there is a interval between bearing part and body of the spacing part, bearing part, body and interval form the gas bearing; the limiting component forms an air film when rotating around the axis relative to the shell so as to support the limiting component relative to the shell, thereby supporting the rotating shaft and increasing the stability of the turbine and the rotating shaft during rotation.)

1. The utility model provides a rotating device, includes pivot, turbine and casing, and turbine fixed mounting is in the pivot, and pivot and turbine are installed in the casing, its characterized in that: the limiting component comprises a bearing part, a connecting part and a supporting part which is connected between the bearing part and the connecting part in a supporting way, and is connected with the rotating shaft through the connecting part; a gap is formed between the bearing portion and the housing, the gap forms a gas film gap of the gas bearing, and the bearing portion, the housing and the gap form the gas bearing.

2. The rotating device according to claim 1, wherein: the bearing part is a ring-shaped bearing ring;

and/or: the surface of connecting portion towards the pivot has the internal thread, has the external screw thread in the corresponding pivot, and spacing part passes through connecting portion and pivot threaded connection to carry on spacingly to the turbine, when the turbine rotated, spacing part rotated with the turbine is synchronous.

3. The rotating device according to claim 1, wherein: the supporting parts are spoke-shaped, the number of the supporting parts is more than or equal to 3, and air passages are formed among the supporting parts;

and/or: the cross section of the supporting part is shuttle-shaped.

4. The rotating device according to claim 1, wherein: the turbine is a centripetal turbine, the turbine is provided with a radial large end and a radial small end which are opposite in the axial direction, the limiting part is positioned on one side of the radial small end of the turbine, and the inner diameter of the bearing part is larger than the outer diameter of the radial small end of the turbine;

or: the turbine is an axial flow turbine, the shell is provided with an annular groove corresponding to the bearing part, the second bearing surface of the shell is positioned on the outer annular surface of the annular groove, and part or all of the bearing part is accommodated in the annular groove;

the outer ring surface of the bearing portion is referred to as a first bearing surface, the surface of the housing corresponding to the first bearing surface is referred to as a second bearing surface, and a gap is formed between the first bearing surface and the second bearing surface.

5. The rotating device according to claim 1, wherein: the turbine is an axial flow turbine, a shell bearing part and a shell supporting part are arranged on the shell, the shell bearing part is connected with the shell through the shell supporting part, and a second bearing surface of the shell is positioned on the surface, facing the rotating shaft, of the shell bearing part;

the outer circumferential surface of the bearing portion is referred to as a first bearing surface, the surface of the housing bearing portion of the housing corresponding to the first bearing surface is referred to as a second bearing surface, and a gap is provided between the first bearing surface and the second bearing surface.

6. The rotating device according to claim 5, wherein: the shell supporting parts are spoke-shaped, the number of the shell supporting parts is more than or equal to 3, and air passages are formed among the shell supporting parts;

and/or: the cross section of the shell supporting part is shuttle-shaped.

7. The rotating device according to claim 5, wherein: the housing bearing portion has a clearance in the axial direction from the turbine.

8. The rotary device of claim 7, wherein: the connecting portion toward the turbine side is higher than the bearing portion and/or the housing bearing portion in the axial direction;

and/or: the bearing section facing away from the turbine side and/or the housing bearing section is/are higher than the connecting section in the axial direction;

and/or: a gasket is provided between the turbine and the connecting portion.

9. A gas turbine comprising the rotating device according to any one of claims 1 to 8 and a compressor fixedly mounted on the rotating shaft.

10. The gas turbine of claim 9, wherein: the rotating shaft is also provided with a first radial bearing and a thrust disc; the rotating shaft is provided with a first axial end and a second axial end which are opposite in the axial direction, the first radial bearing and the thrust disc are positioned at the first axial end of the rotating shaft, the turbine is positioned at or close to the second axial end of the rotating shaft, the thrust disc is positioned between the first radial bearing and the turbine, and the gas compressor is positioned between the thrust disc and the turbine; one side or two sides of the thrust disc are provided with thrust bearings.

Technical Field

The invention relates to a rotating device and a gas turbine, and belongs to the technical field of gas turbines.

Background

The gas turbine drives the impeller to rotate at high speed by taking continuously flowing gas as a working medium, converts the energy of fuel into useful work, and is a rotary impeller type heat engine which mainly comprises a gas compressor, a combustion chamber and a turbine, wherein the gas compressor sucks air from the external atmospheric environment and compresses the air step by step to pressurize the air, and meanwhile, the air temperature is correspondingly increased; compressed air is pumped into a combustion chamber and is mixed with injected fuel to be combusted to generate high-temperature and high-pressure gas; then the gas or liquid fuel enters a turbine to do work through expansion, the turbine is pushed to drive the gas compressor and the external load rotor to rotate at a high speed, the chemical energy of the gas or liquid fuel is partially converted into mechanical work, and the mechanical work can be output by connecting a generator.

In a rotor system of a gas turbine, a turbine needs to rotate at a high speed and has a high working temperature, for example, for a low-power gas turbine, the rotating speed of the rotor system of the gas turbine can reach or exceed 140000RPM (revolutions per minute), the working temperature of the turbine can reach 950-1000 ℃, the working linear velocity of a turbine impeller is extremely high, and thus the bearing centrifugal force is as high as 100 MPa. The turbine usually uses a high-strength and high-temperature-resistant material (such as nickel) to work under high-speed and high-temperature conditions, and such a material is usually high in density and mass, and the turbine is usually located at a cantilever end of the rotor system, so that the turbine can swing to a large extent when the rotor system rotates at a high speed.

Non-contact bearings (e.g., gas bearings) are increasingly used in high-speed applications due to their low friction coefficient and torque, high motion accuracy, and the like. The gas bearing relies on a pressurized gas film in the bearing gap to provide support for the rotor system. The gas bearing has various forms such as a hydrostatic bearing, a dynamic pressure bearing or a hybrid dynamic and static pressure bearing.

Disclosure of Invention

In view of the above prior art, the present invention provides a rotating device and a gas turbine for improving the rotational stability of a turbine and a rotating shaft. The gas bearing is arranged on one side of the turbine of the rotating device/gas turbine to support the rotating shaft, so that the stability of the turbine and the rotating shaft during rotation is effectively improved.

The invention is realized by the following technical scheme:

a rotating device comprises a rotating shaft, a turbine and a shell, wherein the turbine is fixedly arranged on the rotating shaft, and the rotating shaft and the turbine are arranged in the shell; the limiting component comprises a bearing part, a connecting part and a supporting part which is connected between the bearing part and the connecting part in a supporting way, and is connected with the rotating shaft through the connecting part; the bearing part and the shell are provided with a gap (specifically, the outer ring surface of the bearing part is called a first bearing surface, the surface of the shell corresponding to the first bearing surface is called a second bearing surface, and a gap is arranged between the first bearing surface and the second bearing surface), the gap can form a gas film gap of the gas bearing, and the bearing part, the shell and the gap form the gas bearing.

Further, the gas bearing formed by the bearing portion, the housing, and the gap therebetween is any one of a hydrostatic bearing, a hydrodynamic bearing, and a hybrid hydrodynamic/hydrostatic bearing.

Further, the bearing portion may be a ring-shaped bearing ring.

Furthermore, the surface of the connecting portion facing the rotating shaft is provided with an internal thread, the rotating shaft is correspondingly provided with an external thread, the limiting component is in threaded connection with the rotating shaft through the connecting portion so as to limit the turbine, and when the turbine rotates, the limiting component and the turbine rotate synchronously. In addition, the connecting part can be a nut and can also be connected with the rotating shaft through a clamping head/a clamping groove and the like.

Further, the support portion may be spoke-shaped.

Further, the number of the supporting parts is more than or equal to 3, and an air passage is formed between the supporting parts, so that the exhaust gas of the turbine is discharged through the air passage.

Further, the cross section of the support portion may be a shuttle type.

Further, the turbine is centripetal turbine, the turbine has the relative radial main aspects of axial and radial tip, stop part is located the radial tip one side of turbine, and the internal diameter of bearing portion is greater than the external diameter of the radial tip of turbine.

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

Furthermore, the turbine is an axial-flow turbine, a housing bearing portion and a housing supporting portion are arranged on the housing, the housing bearing portion is connected with the housing through the housing supporting portion, and a second bearing surface of the housing is located on the surface, facing the rotating shaft, of the housing bearing portion.

Further, the housing support may be spoke-shaped.

Further, the number of the shell supporting parts is more than or equal to 3, and an air passage is formed between the shell supporting parts, so that the exhaust gas of the turbine is discharged through the air passage.

Further, the cross section of the housing support may be a shuttle type.

Further, the shell bearing portion and the turbine have a gap in the axial direction, and the turbine and the shell bearing portion are prevented from colliding due to vibration or swinging under the condition of high-speed rotation. In particular, in the axial direction, the connection portion towards 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.

Further, the bearing portion facing away from the turbine side and/or the housing bearing portion is higher than the connecting portion in the axial direction to increase the air film area between the bearing portion and the housing bearing portion, increasing the supporting effect.

A gas turbine comprises the rotating device and the compressor, wherein the rotating device and the compressor are of the structure, and the compressor is fixedly arranged on a rotating shaft. The structure of the gas turbine also includes a combustion chamber, an exhaust section, and the like.

Furthermore, a first radial bearing and a thrust disc are further arranged on the rotating shaft; the rotating shaft is provided with a first axial end and a second axial end which are opposite in the axial direction, the first radial bearing and the thrust disc are positioned at the first axial end of the rotating shaft, the turbine is positioned at or close to the second axial end of the rotating shaft, the thrust disc is positioned between the first radial bearing and the turbine, and the gas compressor is positioned between the thrust disc and the turbine; one side or two sides of the thrust disc are provided with thrust bearings.

Further, the casing may be a gas turbine casing, a combustor casing, an exhaust section casing or an intermediate casing connected to these casings.

Further, the first radial bearing, thrust bearing may be a gas bearing. The gas bearing is any one of a hydrostatic bearing, a dynamic pressure bearing or a dynamic and static pressure mixed bearing.

Further, the gas turbine also comprises a reinforcing ring, wherein the reinforcing ring is annular and is fixedly connected between the turbine and the compressor.

Further, a second radial bearing is arranged on the radial outer side of the reinforcing ring; the second radial bearing may be a gas bearing.

Furthermore, positioning structures for positioning the reinforcing ring are arranged on the opposite surfaces of the compressor and the turbine; the positioning structure is as follows: the surface of the compressor, which is close to the turbine, is provided with a positioning ring groove, the surface of the turbine, which is close to the compressor, is provided with a bulge, the bulge forms an annular positioning spigot, one end of the reinforcing ring is inserted into the positioning ring groove, and the other end of the reinforcing ring is inserted into the inner periphery of the annular positioning spigot.

Further, the reinforcing ring side wall is provided with vent holes, and the number of the vent holes can be 4.

The invention relates to a rotating device and a gas turbine.A limit component is arranged at one side of a turbine, a gap is arranged between a bearing part and a shell of the limit component, the gap forms a gas film gap of a gas bearing, and the bearing part, the shell and the gap form the gas bearing; when the limiting component rotates around the axis relative to the shell, an air film is formed in the gap so as to support the limiting component relative to the shell, so that the rotating shaft is supported, and the stability of the turbine and the rotating shaft during rotation is improved.

In some further schemes, the supporting parts of the limiting part can be spoke-shaped, the number of the supporting parts can be more than 3, and the cross section can be shuttle-shaped, so that the better air exhaust effect can be achieved.

In some further schemes, an annular groove for accommodating part or all of the bearing parts can be arranged on the shell, and a shell bearing part and a shell supporting part can also be arranged to play a better supporting role and an exhaust effect.

When the bearing structure referred to herein is a hydrostatic bearing, it has the following structure: the bearing sleeve and the rotating shaft are provided with a preset radial gap in the radial direction (when the bearing is a radial bearing), or the bearing sleeve and the thrust disc are oppositely arranged in the axial direction of the rotating shaft and provided with a preset axial gap (when the bearing is a thrust bearing); the peripheral surface of the bearing sleeve is provided with an annular air cavity, and the bearing sleeve is provided with a through hole which penetrates through the annular air cavity and a gap (a radial gap or an axial gap); the bearing body is provided with an air hole for communicating the annular air cavity with an external air source; for convenience of processing and without influencing the gas pressure in the gap, the through hole can be a reducing hole, namely the diameter of the side, far away from the gap, of the through hole is large, and the diameter of the side, close to the gap, of the through hole is small.

When the bearing structure referred to herein is a dynamic pressure bearing, it has the following structure: the dynamic pressure generating device comprises a bearing body, wherein a preset radial gap is formed between the bearing body and a rotating shaft in the radial direction (when the bearing is a radial bearing), and a dynamic pressure generating groove is formed in the inner diameter surface of the bearing body or the part of the rotating shaft, where the bearing body is installed, of the rotating shaft; or: the bearing body and the thrust disk are installed to face each other in the axial direction of the rotating shaft with a predetermined axial gap (when the bearing is a thrust bearing), and a dynamic pressure generating groove is provided in an end surface of the bearing body facing the thrust disk or an end surface of the thrust disk facing the bearing body.

When the bearing structure referred to herein is a hybrid dynamic and static bearing, the structure has both the features of a hydrostatic bearing and a hydrodynamic bearing. The present invention will not be described in detail.

The various terms and phrases used herein have the ordinary meaning as is well known to those skilled in the art. To the extent that the terms and phrases are not inconsistent with known meanings, the meaning of the present invention will prevail.

Drawings

FIG. 1: a schematic view of the structure of the rotating apparatus of embodiment 1.

FIG. 2: the structure schematic diagram of the limiting component.

FIG. 3: the structure of the limiting component is shown schematically (the cross section of the supporting part is shuttle-shaped).

FIG. 4: a schematic view of the structure of the gas turbine of example 1.

FIG. 5: the structure of the rotating device of embodiment 2 is schematically shown.

FIG. 6: a schematic view of the gas turbine of example 2.

FIG. 7: a schematic structural view of a rotating apparatus of embodiment 3.

FIG. 8: a schematic view of the structure of the gas turbine of example 3.

FIG. 9: a schematic view of the structure of the rotating apparatus of embodiment 4.

FIG. 10: the structure of the housing bearing portion and the housing support portion in embodiment 4 is schematically illustrated.

FIG. 11: a schematic view of the gas turbine of example 4.

100, a rotating shaft; 110. a thrust disc; 200. a turbine; 300. a housing; 310. a housing bearing portion; 320. a housing support portion; 400. a limiting component; 410. a bearing portion; 420. a support portion; 430. a connecting portion; 500. a compressor; 610. a first radial bearing; 620. and a thrust bearing.

Detailed Description

The present invention will be further described with reference to the following examples. However, the scope of the present invention is not limited to the following examples. It will be understood by those skilled in the art that various changes and modifications may be made to the invention without departing from the spirit and scope of the invention.

EXAMPLE 1A turning gear and a gas turbine

A rotating device comprises a rotating shaft 100, a turbine 200 and a shell 300, wherein the turbine 200 is fixedly arranged on the rotating shaft 100, the rotating shaft 100 and the turbine 200 are arranged in the shell 300, and the turbine 200 is a centripetal turbine, as shown in figure 1 (only part of the shell 300 is shown in figure 1); the rotating shaft 100 further comprises a limiting component 400 mounted on the rotating shaft 100, wherein the limiting component 400 comprises a bearing portion 410, a connecting portion 430 and a supporting portion 420 connected between the bearing portion 410 and the connecting portion 430 in a supporting manner, and the limiting component 400 is connected with the rotating shaft 100 through the connecting portion 430: the surface of the connecting part 430 facing the rotating shaft 100 is provided with an internal thread, correspondingly, the rotating shaft 100 is provided with an external thread, the limiting part 400 is in threaded connection with the rotating shaft 100 through the connecting part 430 to limit the turbine 200, and when the turbine 200 rotates, the limiting part 400 and the turbine 200 rotate synchronously.

The bearing portion 410 may be a ring-shaped bearing ring, as shown in fig. 2; there is a gap between the bearing portion 410 and the housing 300 (specifically, the outer ring surface of the bearing portion 410 is referred to as a first bearing surface, the surface of the housing 300 corresponding to the first bearing surface is referred to as a second bearing surface, and a gap is provided between the first bearing surface and the second bearing surface), the gap can form a gas film gap of the gas bearing, the bearing portion 410, the housing 300 and the gap form the gas bearing, when the limiting member 400 rotates around the axis relative to the housing 300, a gas film is formed in the gap to support the limiting member 400 relative to the housing 300, thereby supporting the shaft 100, and increasing the stability of the turbine 200 and the shaft 100 when rotating.

The gas bearing formed by the bearing portion 410, the housing 300 and the gap therebetween is any one of a hydrostatic bearing, a hydrodynamic bearing and a hybrid hydrodynamic/hydrostatic bearing.

The support portions 420 may be spoke-shaped, and the number of the support portions 420 may be 3 or more, as shown in fig. 2. The supports 420 form an air passage therebetween, so that exhaust gas of the turbine 200 is discharged through the air passage.

The cross-section of the support part 420 may be a shuttle type, as shown in fig. 3, which may reduce gas resistance, facilitating exhaust gas discharge of the turbine 200.

The turbine 200 is provided with a radial large end and a radial small end which are opposite in the axial direction, the limiting component 400 is located on one side of the radial small end of the turbine 200, and the inner diameter of the bearing portion 410 is larger than the outer diameter of the radial small end of the turbine 200, so that exhaust gas of the turbine 200 is prevented from being shielded by the bearing portion 410, and exhaust gas of the turbine 200 is favorably exhausted.

A gas turbine includes the rotating device and the compressor 500 constructed as above, and the compressor 500 is fixedly installed on the rotating shaft 100, as shown in fig. 4.

The rotating shaft 100 is further provided with a first radial bearing 610 and a thrust disc 110; the rotating shaft 100 has axially opposite axial first and second ends, the first radial bearing 610 and the thrust disc 110 are located at the axial first end of the rotating shaft 100, the turbine 200 is located at or adjacent to the axial second end of the rotating shaft 100, the thrust disc 110 is located between the first radial bearing 610 and the turbine 200, and the compressor 500 is located between the thrust disc 110 and the turbine 200; thrust disc 110 is provided with thrust bearings 620 on both sides.

During operation of the gas turbine, the rotating shaft 100, the compressor 500 and the turbine 200 rotate at a high speed around the axis relative to the casing 300, the first radial bearing 610 provides support at a first end in the axial direction to control the rotating shaft 100 to swing or move in the radial direction, and the thrust bearing 620 provides support in the axial direction to control the rotating shaft 100 to swing or move in the axial direction; meanwhile, during the high-speed rotation of the rotating shaft 100 and the turbine 200, a gas 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, and support is provided at the second end in the axial direction to control the rotating shaft 100 and the turbine 200 to swing or move in the radial direction; the first radial bearing 610, the thrust bearing 620, the bearing portion 410, the housing 300 and the gas bearing formed by the gap are mutually matched to play a supporting role together, so that the stability of the gas turbine during operation is improved, and the rotating shaft 100, the compressor 500 and the turbine 200 are prevented from swinging or moving to a large extent.

It should be understood that FIG. 4 illustrates only one example of a gas turbine engine in accordance with an embodiment of the present invention. In other alternative examples, the thrust disc 110 and the corresponding bearing may be located between the compressor 500 and the turbine 200, and the bearing ring 400 sleeved on the radial outer side of the turbine 200, the housing 300 and the gap therebetween may form a gas bearing, which can support the turbine 200 relative to the housing 300, and especially can increase the stability of the turbine 200 during rotation when the turbine 200 has a heavy weight.

The casing 300 may be a gas turbine casing, a combustor casing (not shown), an exhaust section casing (not shown), or an intermediate casing connected thereto.

The first radial bearing 610 and the thrust bearing 620 may be gas bearings. The gas bearing is any one of a hydrostatic bearing, a dynamic pressure bearing or a dynamic and static pressure mixed bearing.

When the compressor 500 is located between the thrust disc 110 and the turbine 200, the gas turbine may further include a reinforcement ring, which is annular and is fixedly connected between the turbine 200 and the compressor 500. The reinforcing ring is arranged, so that the rigidity of the compressor 500 and the turbine 200 can be improved, the rigidity of the rotating shaft 100 between the compressor 500 and the turbine 200 can also be indirectly improved, the critical rotating speed of a rotor system is improved, the normal working rotating speed is adapted, meanwhile, the vibration of the rotating shaft 100 is reduced, and a resonance area is avoided.

A second radial bearing is arranged on the radial outer side of the reinforcing ring; the second radial bearing is a gas bearing.

The opposite surfaces of the compressor 500 and the turbine 200 can be further provided with a positioning structure for positioning a reinforcing ring; the positioning structure may be: the surface of the compressor 500 close to the turbine 200 is provided with a positioning ring groove, the surface of the turbine 200 close to the compressor 500 is provided with a bulge, the bulge forms an annular positioning spigot, one end of the reinforcing ring is inserted into the positioning ring groove, and the other end of the reinforcing ring is inserted into the inner periphery of the annular positioning spigot.

The reinforcing ring side wall can be provided with vent holes, and the number of the vent holes can be 4. The exhaust holes are used for exhausting gas in the reinforcing ring to ensure that the internal pressure and the external pressure of the reinforcing ring are equal, and the phenomenon that the heat generated by working gas flow increases the heat in the reinforcing ring and the pressure in the reinforcing ring increases to influence the service life of the reinforcing ring and even damage the reinforcing ring when the gas compressor 500 and the turbine 200 work is avoided.

EXAMPLE 2A turning gear and gas turbine

The structure of the rotating device is the same as that of embodiment 1, except that: the turbine 200 is an axial flow turbine, and as shown in fig. 5, the axial flow turbine has the advantages of small cross section, simple structure, low cost and strong flow capacity.

The structure of the gas turbine is different from that of example 1 in that: the turbine 200 is an axial flow turbine, as shown in fig. 6.

The axial flow turbine refers to a turbine with working media flowing through a turbine working wheel in the axial direction, and the working principle is as follows: the turbine is called an axial turbine because the main direction of the gas flow is parallel to the turbine shaft. The structure is generally as follows: the blade type air conditioner comprises a central hub and a plurality of blades located on the periphery of the central hub, the blades extend outwards along the radial direction of the central hub, and an air flow channel formed by the blades is convergent.

EXAMPLE 3A turning gear and gas turbine

The structure of the rotating device is the same as that of embodiment 2, except that: the housing 300 has an annular groove corresponding to the bearing portion 410, and as shown in fig. 7, the second bearing surface of the housing 300 is located on the outer annular surface of the annular groove, and a part or the whole of the bearing portion 410 is accommodated in the annular groove, so that the clearance between the outer side surface in the radial direction of the turbine 200 and the housing 300 is reduced without shielding the exhaust gas of the turbine 200, and the aerodynamic efficiency of the turbine 200 is improved.

The structure of the gas turbine is different from that of example 2 in that: the housing 300 has an annular groove corresponding to the bearing portion 410, and as shown in fig. 8, the second bearing surface of the housing 300 is located on the outer annular surface of the annular groove, and a part or the whole of the bearing portion 410 is accommodated in the annular groove, so that the clearance between the outer side surface in the radial direction of the turbine 200 and the housing 300 is reduced without shielding the exhaust gas of the turbine 200, and the aerodynamic efficiency of the turbine 200 is improved.

EXAMPLE 4A turning gear and gas turbine

The structure of the rotating device is the same as that of 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, 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 shown in fig. 9.

The housing supports 320 may be spoke-shaped, and the number of the housing supports 320 may be 3 or more, as shown in fig. 10. The housing supports 320 form an air passage therebetween, so that exhaust gas of the turbine 200 is discharged through the air passage.

The cross-section of the housing support 320 may be shuttle-shaped to reduce gas drag to facilitate exhaust gas discharge of the turbine 200.

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 turbine 200), so that the turbine 200 and the housing bearing portion 310 are prevented from colliding due to vibration or oscillation in the case of high-speed rotation. In some examples, in the axial direction, connecting portion 430 toward the side of turbine 200 is higher than bearing portion 410 and/or case bearing portion 310; in other examples, shims may be disposed between turbine 200 and connection 430 such that there is a gap between housing bearing portion 310 and 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 may be higher than the connecting portion 430 to increase the air film area between the bearing portion 410 and the housing bearing portion 310, increasing the supporting effect.

The structure of the gas turbine is different from that of example 2 in 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, 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 shown in fig. 11.

The housing supports 320 may be spoke-shaped, and the number of the housing supports 320 may be 3 or more. The housing supports 320 form an air passage therebetween, so that exhaust gas of the turbine 200 is discharged through the air passage.

The cross-section of the housing support 320 may be shuttle-shaped to reduce gas drag to facilitate exhaust gas discharge of the turbine 200.

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 turbine 200), so that the turbine 200 and the housing bearing portion 310 are prevented from colliding due to vibration or oscillation in the case of high-speed rotation. In some examples, in the axial direction, connecting portion 430 toward the turbine 200 side is higher than bearing portion 41 and/or case bearing portion 310; in other examples, shims may be disposed between turbine 200 and connection 430 such that there is a gap between housing bearing portion 310 and 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 may be higher than the connecting portion 430 to increase the air film area between the bearing portion 410 and the housing bearing portion 310, increasing the supporting effect.

Although the specific embodiments of the present invention have been described with reference to the examples, the scope of the present invention is not limited thereto, and those skilled in the art will appreciate that various modifications and variations can be made without inventive effort by those skilled in the art based on the technical solution of the present invention.