CN215979614U

CN215979614U - Rotating device and gas turbine

Info

Publication number: CN215979614U
Application number: CN202121724342.XU
Authority: CN
Inventors: 靳普
Original assignee: Yongxu Tengfeng New Energy Power Technology Beijing Co ltd
Current assignee: Liu Muhua; Yongxu Tengfeng New Energy Power Technology Beijing Co ltd
Priority date: 2021-07-27
Filing date: 2021-07-27
Publication date: 2022-03-08
Anticipated expiration: 2031-07-27

Abstract

The utility model 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 radial outer side of the turbine is sleeved with a bearing ring, a gap between the bearing ring and the shell forms an air film gap of the gas bearing, the bearing ring, the shell and the gap form the gas bearing, and an air film is formed when the turbine rotates around an axis relative to the shell so as to support the turbine relative to the shell, so that the radial swing of the turbine during high-speed operation is improved, and the stability of the turbine during rotation is improved. The utility model also discloses a gas turbine comprising the rotating device.

Description

Rotating device and gas turbine

Technical Field

The utility model 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.

SUMMERY OF THE UTILITY MODEL

Aiming at the prior art, the utility model provides a rotating device and a gas turbine in order to improve the rotating stability of a turbine end. According to the utility model, the gas bearing is arranged at the turbine end of the rotating device/gas turbine to support the turbine end, so that the rotating stability of the turbine end is effectively improved.

The utility model 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 radial outside cover of turbine is equipped with the bearing ring, and the bearing ring is the ring form, has the clearance between bearing ring and the casing, and when the turbine rotated for the casing around the axis, this clearance can form the gas film clearance of gas film, and bearing ring, casing and clearance form gas bearing to form the support to the turbine for the casing to improve the radial swing of turbine when high-speed operation, stability when increasing the turbine and rotating.

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

Further, the turbine may be a centripetal turbine.

Further, the turbine has axially opposite large and small radial ends, and the bearing ring is located at the small radial end of the turbine.

Further, the bearing ring can be assembled to the turbine in a great interference mode, namely hot assembly or cold assembly of the turbine through the bearing ring.

Further, the bearing ring and the turbine wheel can be fixedly connected by welding, and can be welded by laser or by appropriate welding materials.

Furthermore, the bearing ring and the turbine can be fixedly connected in an interference and welding mode, so that the reliability of interference fit is improved.

Further, the turbine has a plurality of axially extending blades, and the inner ring surface of the bearing ring is welded to the radially outer edges of the plurality of blades.

Further, at the small end of the turbine in the radial direction, at least part of the blades are provided with protrusions extending outwards in the axial direction, the protrusions are fixedly connected with the bearing ring, the contact area between the turbine and the bearing ring can be increased due to the arrangement of the protrusions, the connection stability can be increased, the gas film area of the gas bearing can be increased, and the gas bearing supporting effect can be improved.

Further, when the partial blades have the protrusions thereon, the blades having the protrusions and the blades having no protrusions may be alternately disposed.

Further, all the blades of the turbine have a protrusion.

Further, the projection is provided at a position radially outside the small end in the radial direction of the turbine, providing support while minimizing the aerodynamic effect of the turbine.

Further, the turbine and the bearing ring can be made of high-temperature resistant materials selected from high-temperature resistant metals such as cast nickel.

Further, the turbine and the bearing ring are made of the same high-temperature-resistant material, and the joint strength after laser welding is improved.

A gas turbine comprises the rotating device and the compressor, wherein the compressor is arranged on the 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 housing may be a gas turbine housing, a combustor housing, an exhaust section housing or an intermediate housing connected to the above housing.

Further, the first radial bearing may be a gas bearing.

Further, the thrust bearing may be a gas bearing.

Further, the gas bearing is any one of a hydrostatic bearing, a hydrodynamic bearing or a hybrid hydrodynamic and hydrostatic 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.

According to the rotating device and the gas turbine, the bearing ring is arranged at the turbine end, the gap between the bearing ring and the shell forms a gas film gap of the gas bearing, the bearing ring, the shell and the gap form the gas bearing, and when the turbine rotates around the axis relative to the shell, a gas film is formed in the gap to support the turbine relative to the shell, so that radial swing of the turbine during high-speed operation is improved, and stability during rotation of the turbine is improved.

In some further solutions, the bearing ring may be arranged at the small radial end of the turbine, and the centrifugal force to which it is subjected is relatively small, so that the problems of deformation, denaturation or fracture of the bearing ring due to the centrifugal force can be avoided as much as possible under the same material.

In some further schemes, a small radial end of the turbine wheel can be provided with a protruding part which extends outwards along the axial direction, so that the contact area between the turbine wheel and the bearing ring is increased, the connection stability can be increased, the gas film area of the gas bearing can be increased, and the gas bearing supporting effect is improved.

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 of the bearing ring of the utility model is schematically shown.

FIG. 3: the structure of the rotating device of embodiment 2 is schematically shown.

FIG. 4: a schematic view of the structure of the gas turbine of example 3.

FIG. 5: a schematic view of the structure of the gas turbine of example 5.

100, a rotating shaft; 110. a thrust disc; 200. a turbine; 210. a protrusion; 300. a housing; 400. a bearing ring; 500. a compressor; 610. a first radial bearing; 620. a thrust bearing; 640. a second radial bearing; 700. a reinforcement ring.

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 utility model without departing from the spirit and scope of the utility model.

EXAMPLE 1A rotating apparatus

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); a bearing ring 400 is sleeved on the radial outer side of the turbine 200, and the bearing ring 400 is in a circular ring shape, as shown in fig. 2; the bearing ring 400 and the casing 300 have a gap therebetween (specifically, an outer annular surface of the bearing ring 400 is referred to as a first bearing surface, a surface of the casing 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 film gap of the gas bearing, and the bearing ring 400, the casing 300 and the gap form the gas bearing, and when the turbine 200 rotates around an axis relative to the casing 300, a film is formed in the gap to support the turbine 200 relative to the casing 300, so that radial oscillation of the turbine 200 during high-speed operation is improved, and stability of the turbine 200 during rotation is increased.

The gas bearing formed by the bearing ring 400, the housing 300 and the gap may be any one of a hydrostatic bearing, a hydrodynamic bearing or a hybrid bearing.

The turbine 200 has axially opposite large and small radial ends, and a bearing ring 400 is located at the small radial end of the turbine 200; when the turbine 200 rotates at a high speed, the bearing ring 400 is subjected to a large centrifugal force, and the magnitude of the centrifugal force is positively correlated with the diameter of the bearing ring 400 relative to the rotation axis, so that the centrifugal force applied to the small end in the radial direction of the turbine 200 is relatively small, and the problems of deformation, denaturation, fracture and the like of the bearing ring 400 due to the centrifugal force can be avoided as much as possible under the same material.

The bearing ring 400 may be assembled to the turbine 200 with great interference, i.e. by hot-fitting the bearing ring 400 or cold-fitting the turbine 200.

The bearing ring 400 and the turbine 200 may be fixedly connected by welding, such as laser welding, or by welding with a suitable solder. Specifically, the turbine 200 has a plurality of axially extending blades, and the inner annular surface of the bearing ring 400 is welded to the radially outer edges of the plurality of blades.

The bearing ring 400 and the turbine 200 may also be fixedly connected by interference and welding to improve the reliability of the interference fit.

Because the turbine 200 is located at the hot end of the gas turbine (the working temperature can reach 950-1000 ℃), the turbine 200 and the bearing ring 400 can be made of high-temperature resistant materials selected from high-temperature resistant metals such as cast nickel. Specifically, the turbine 200 and the bearing ring 400 are made of the same high-temperature-resistant material, which is beneficial to improving the joint strength after laser welding.

EXAMPLE 2A rotating apparatus

The structure is the same as that of the embodiment 1, except that: as shown in fig. 3, an axially outwardly extending protrusion 210 is provided at a position radially outside the small end of the turbine 200, and the protrusion 210 is fixedly connected to the bearing ring 400. The projections 210 may be located on blades of the turbine 200, and specifically, in some examples, all blades of the turbine 200 have projections 210. In other examples, at least some of the plurality of blades of the turbine have protrusions 210 thereon, and the blades with protrusions 210 may alternate with blades without protrusions 210. The arrangement of the protruding portion 210 can increase the contact area between the turbine 200 and the bearing ring 400, which can increase the connection stability, increase the gas film area of the gas bearing, improve the supporting effect of the gas bearing, and provide the support while not affecting the aerodynamic effect of the turbine 200 as much as possible.

EXAMPLE 3A gas turbine

A gas turbine comprises a rotating shaft 100, a turbine 200, a shell 300 and a compressor 500, wherein the turbine 200 and the compressor 500 are fixedly arranged on the rotating shaft 100, the turbine 200 and the compressor 500 are arranged in the shell 300, and the turbine 200 is a centripetal turbine as shown in figure 4; a bearing ring 400 is sleeved on the radial outer side of the turbine, and the bearing ring 400 is annular; a gap is formed between the bearing ring 400 and the housing 300 (specifically, an outer ring surface of the bearing ring 400 is referred to as a first bearing surface, a surface of the housing 300 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), the gap can form a gas film gap of the gas bearing, and the bearing ring 400, the housing 300, and the gap form the gas bearing.

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 ring 400 and the housing 300, the bearing ring 400, the housing 300 and the gap form a gas bearing, and the bearing ring 400, the housing 300 and the gap provide support at the second axial end to control the rotation or movement of the rotating shaft 100 and the turbine 200 in the radial direction; the first radial bearing 610, the thrust bearing 620, the bearing ring 400, 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.

The turbine 200 has axially opposite large and small radial ends, and a bearing ring 400 is located at the small radial end of the turbine 200; when the turbine 200 rotates at a high speed, the bearing ring 400 is subjected to a large centrifugal force, and the magnitude of the centrifugal force is positively correlated with the diameter of the bearing ring 400 relative to the rotation axis, so that the centrifugal force applied to the small end in the radial direction of the turbine 200 is relatively small, and the defects of deformation, denaturation, fracture and the like of the bearing ring 400 due to the centrifugal force can be avoided as much as possible under the same material.

The bearing ring 400 may be assembled to the turbine 200 with great interference, i.e. hot-assembled through the bearing ring 400 or cold-assembled through the turbine 200.

EXAMPLE 4A gas turbine

The structure is the same as that of the embodiment 3, except that: the turbine 200 has a radially small end with an axially outwardly extending protrusion 210, the protrusion 210 is fixedly connected with the bearing ring 400, and the protrusion 210 may be located on a blade of the turbine 200, and specifically, in some examples, all the blades of the turbine 200 have the protrusion 210. In other examples, at least some of the plurality of blades of the turbine have protrusions 210 thereon, and the blades with protrusions 210 may alternate with blades without protrusions 210. The arrangement of the protruding portion 210 can increase the contact area between the turbine 200 and the bearing ring 400, which can increase the connection stability, and can also increase the gas film area of the gas bearing, thereby improving the supporting effect of the gas bearing, increasing the stability of the gas turbine, and not affecting the aerodynamic effect of the turbine 200 while providing the support.

EXAMPLE 5A gas turbine

The structure is the same as that of the embodiment 3, except that: when the compressor 500 is located between the thrust disc 110 and the turbine 200, the compressor further includes a reinforcing ring 700, the reinforcing ring 700 is annular, and as shown in fig. 5, the reinforcing ring 700 is fixedly connected between the turbine 200 and the compressor 500. The reinforcing ring 700 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 700 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 640 is arranged on the radial outer side of the reinforcing ring 700; the second radial bearing 640 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 the reinforcing ring 700; 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 700 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 sidewall of the reinforcement ring 700 may be provided with vent holes, and the number of the vent holes may be 4. The exhaust holes are used for exhausting gas in the reinforcing ring to ensure that the pressure inside and outside the reinforcing ring is equal, and the phenomenon that the heat generated by working gas flow increases the heat in the reinforcing ring 700 and the pressure in the ring increases to influence the service life of the reinforcing ring 700 and even damage the reinforcing ring 700 when the compressor 500 and the turbine 200 work is avoided.

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.

Claims

1. 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 method is characterized in that: a bearing ring is sleeved on the radial outer side of the turbine, a gap is formed between the bearing ring and the shell, the gap forms an air film gap of the gas bearing, and the bearing ring, the shell and the gap form the gas bearing.

2. The rotating device according to claim 1, wherein: the gas bearing formed by the bearing ring, the shell and the clearance thereof is any one of a hydrostatic bearing, a dynamic pressure bearing or a hybrid dynamic and static pressure bearing.

3. 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, and the bearing ring is located at the radial small end of the turbine.

4. The rotating device according to claim 1, wherein: the bearing ring is assembled to the turbine in a great interference mode; and/or: and the bearing ring is fixedly connected with the turbine in a welding mode.

5. The rotating device according to claim 4, wherein: the turbine has a plurality of axially extending blades, and the inner ring surface of the bearing ring is welded to the radially outer edges of the plurality of blades.

6. The rotating device according to claim 5, wherein: at the small radial end of the turbine, at least some of the blades have axially outwardly extending projections which are fixedly connected to the bearing ring.

7. A gas turbine, characterized by: the rotary device comprises the rotary device and the compressor as claimed in claims 1 to 6, wherein the compressor is arranged on the rotary shaft.

8. The gas turbine of claim 7, 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.

9. The gas turbine of claim 8, wherein: the shell is a gas turbine shell, a combustion chamber shell, an exhaust section shell or a middle shell connected with the gas turbine shell, the combustion chamber shell or/and the exhaust section shell.

10. The gas turbine of claim 8, wherein: the gas turbine also comprises a reinforcing ring which is fixedly connected between the turbine and the compressor.