CN114320608A

CN114320608A - Gas turbine

Info

Publication number: CN114320608A
Application number: CN202210026828.9A
Authority: CN
Inventors: 靳普
Original assignee: Yongxu Tengfeng New Energy Power Technology Beijing Co ltd
Current assignee: Yongxu Tengfeng New Energy Power Technology Beijing Co ltd
Priority date: 2022-01-11
Filing date: 2022-01-11
Publication date: 2022-04-12
Also published as: WO2023134176A1

Abstract

The invention discloses a gas turbine, which comprises a rotating shaft, a gas compressor, a turbine and a combustion chamber, wherein the gas compressor is arranged on the rotating shaft; the compressor and the turbine are sleeved on the rotating shaft; a guide vane assembly is arranged at the outlet end of the combustion chamber; the guide vane assembly is connected with the bearing seat assembly through a heat guide part. According to the gas turbine, the heat guide part is arranged between the outlet end of the combustion chamber and the bearing seat which are mutually overlapped originally, and the heat at the outlet of the combustion chamber is guided to the part of the bearing seat far away from the bearing, so that the heat conducted to the bearing seat can be uniformly distributed in the bearing seat, the bearing and the bearing seat nearby the bearing seat are uniformly heated and further uniformly deformed, the local high temperature at the bearing is avoided, and the defects of air leakage, coaxiality change, non-uniform air film, rotating shaft clamping and the like caused by irregular deformation of the gas bearing due to non-uniform heating are overcome.

Description

Gas turbine

Technical Field

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

Background

The gas turbine uses continuously flowing gas as working medium to drive the impeller to rotate at high speed, and converts the energy of fuel into useful work, and is a rotary impeller type heat engine. The device mainly comprises three parts of a gas compressor, a combustion chamber and a turbine: the air compressor sucks air from the external atmospheric environment, compresses the air to pressurize the air, and simultaneously, 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 can be partially converted into mechanical work and heat energy, and the mechanical work and the heat energy can be output through connecting a generator.

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 bearings rely on a pressurized gas film in the bearing gap to effect support of the rotor system. The gas bearing may be applied to a gas turbine.

When the gas turbine works, the temperature of gas at the outlet of the combustion chamber reaches up to 900 ℃, and the high temperature at the outlet of the combustion chamber can be directly transmitted to a bearing and a bearing seat which are arranged adjacently; due to local high temperature and uneven heat distribution, irregular deformation of the bearing and the bearing seat can be caused; when the bearing is a gas bearing, the sealing failure of the gas bearing can be caused, so that the gas film of the gas bearing is unstable, the supporting force is insufficient, and the stable operation of the gas bearing is influenced.

Disclosure of Invention

Aiming at the prior art and aiming at overcoming the technical problems of uneven heating and local high temperature of a bearing and a bearing seat, the invention provides the gas turbine, wherein a heat guide part is arranged between the outlet end of a combustion chamber and the bearing seat, and can guide the heat at the outlet of the combustion chamber to the part of the bearing seat far away from the bearing, so that the heat conducted to the bearing seat is better and uniformly distributed, and the irregular deformation and the sealing failure caused by uneven heating and local high temperature are avoided.

The invention is realized by the following technical scheme:

a gas turbine comprises a rotating shaft, a gas compressor, a turbine and a combustion chamber; the compressor and the turbine are sleeved on the rotating shaft; the exhaust end of the compressor is communicated with the inlet end of the combustion chamber; the outlet end of the combustion chamber is provided with a guide vane assembly for guiding high-temperature gas discharged from the outlet end of the combustion chamber into the turbine; the guide vane assembly is connected with the bearing seat assembly through a heat guide part.

Furthermore, the connecting position of the heat guiding component and the bearing seat assembly is located at the position, far away from the bearing, of the bearing seat assembly, so that heat is guided to the position, far away from the bearing, a better guiding effect is achieved, and the heat is favorably and uniformly distributed in the bearing seat.

Further, the heat directing component is disposed about an axis of rotation.

Further, the heat guide member includes a first end portion, a second end portion, and a connecting portion connecting the first end portion and the second end portion; the first end part is connected with the guide vane assembly so as to form fixed support for the guide vane assembly and the combustion chamber; the second end is connected with a bearing block assembly. Furthermore, the heat guiding member further includes at least one sub-end portion, the sub-end portion is connected with the bearing seat assembly (each sub-end portion is connected at a different position of the bearing seat assembly, so that heat can be conducted to a plurality of positions of the bearing seat assembly, and uniform heating is facilitated), the sub-end portion is connected with the connecting portion through a branch portion, and the branch portion can be in a ring shape or a spoke shape.

Furthermore, the first end portion and the connecting portion of the heat guiding member are spaced from the bearing seat assembly (i.e., do not directly contact the bearing seat assembly), so that when the guide vane assembly conducts heat to the bearing seat assembly, a longer heat conduction path is formed, temperature reduction and uniform heat dissipation to the external environment are facilitated, and heat is prevented from being directly conducted to a portion, relatively close to the bearing, of the bearing seat assembly.

Furthermore, the part of the second end part, which is connected with the bearing seat assembly, is provided with a groove (which can be an annular groove or a structure of a plurality of small grooves arranged at intervals) so as to reduce the contact area between the heat guiding component and the bearing seat assembly, thereby reducing the heat conducted to the bearing seat assembly as much as possible (the heat is accumulated on the heat guiding component more by reducing the contact area, and then the heat guiding component is cooled by air of the air compressor; the heat conduction speed of the metal heat guiding component is far higher than that of the air, and the heat accumulated on the heat guiding component is radiated by heat radiation).

Further, the first end portion and the guide vane assembly are connected in a mode selected from welding, bolt connection, screw connection, limiting groove clamping and the like.

Furthermore, the connection mode of the second end part and the bearing seat assembly is selected from welding, bolt connection, screw connection, limiting groove clamping connection and the like.

Further, the bearing is selected from gas bearings. The gas bearing is selected from a hydrostatic bearing, a dynamic pressure bearing and/or a hybrid dynamic and static pressure bearing.

Further, the bearing is selected from a thrust bearing and/or a radial bearing.

Further, the number of the bearings is one, two or more, and the positions of the bearings may be any suitable positions on the rotating shaft, such as any one of two ends of the rotating shaft, any one of two sides of the compressor, and any one of two sides of the turbine. In a specific scheme, the bearing and the bearing seat assembly are positioned between the compressor and the turbine; the bearing seat assembly comprises an end cover, a first seat body and a second seat body, a thrust bearing and a thrust disc are arranged between the first seat body and the rotating shaft, a radial bearing is arranged between the second seat body and the rotating shaft, and the radial bearing is positioned between the thrust bearing and the turbine; lantern rings are sleeved outside the first seat body and the second seat body, the end cover is arranged on the first seat body, and the lantern rings are connected with the first seat body through the end cover; the combustion chamber is arranged around the rotating shaft and is arranged on the lantern ring; the guide vane assembly is connected with the first base body, the second base body and/or the end cover through a heat guide part, and the connection position is preferably the side far away from the radial bearing.

Further, the lantern ring is provided with an air hole, an air inlet of the air hole is communicated with an air outlet end of the air compressor, an air outlet of the air hole is communicated with an inner cavity (an inner cavity formed among the end cover, the first seat body, the second seat body and the lantern ring) where the heat guiding component is located, so that 'cold air' (the 'cold air' is relative to 'hot air' at the turbine end, is generally normal-temperature gas and can be used for cooling) from the air compressor is guided to the inner cavity of the bearing seat component, and the heat guiding component and the first seat body and the second seat body of the bearing seat component are cooled.

Furthermore, the heat guiding component is provided with a through hole, on one hand, the flow of the cold air from the compressor can be enhanced, and the cold air from the compressor can enter the annular cavity through the through hole after entering the inner cavity of the bearing seat assembly (because the connecting part and the bearing seat assembly are arranged at intervals, an annular cavity is formed between the connecting part and the bearing seat assembly), so that the bearing seat assembly is cooled, the cooling effect is enhanced, and the cooling area is increased; on the other hand, the weight of the heat guide member can be reduced.

Furthermore, the through hole can be arranged on the connecting part, between the connecting part and the first end part, between the connecting part and the second end part, between the connecting part, the first end part and the second end part, and between the bearing seat component and the connecting part (namely, the second end part of the heat guiding component is arranged in the through hole in a disconnected mode, and the edge of the through hole is changed into the bearing seat component from the second end part, so that the weight of the heat guiding component can be further reduced, the contact area between the heat guiding component and the bearing seat component is reduced, and the heat conducted to the bearing seat component is reduced), and the through hole can be arranged among the bearing seat component, the connecting part and the first end part. The shape of the through hole can be any shape such as circle, sector, ellipse, polygon (including convex polygon and concave polygon, such as triangle, rectangle, pentagon and hexagon); the number of the through holes is at least one, and the number of the through holes can be multiple.

Further, the guide vane assembly comprises two support seats, and a blade group with an axial air passage is arranged between the two support seats.

Further, the rotating shaft, the gas compressor, the turbine, the combustion chamber and the bearing seat assembly are integrally arranged in the shell, and a gas passage for communicating the gas compressor and the combustion chamber is located between the shell and the bearing seat assembly.

In the operation process of the gas turbine, the low-pressure end of the gas compressor sucks air (in an atmospheric environment) from the outside, the air is compressed and pressurized by the gas compressor, then enters the combustion chamber and is mixed and combusted with injected fuel to generate high-temperature and high-pressure gas, and the high-temperature gas (the temperature can reach 900 ℃) enters the turbine from the outlet end of the combustion chamber through the guide vane assembly to do work through expansion; the heat of stator subassembly leads to the part that the bearing frame subassembly kept away from the bearing relatively through hot guide part, and the material of this part bearing frame subassembly is relatively thick, does benefit to leading-in thermal equipartition for the bearing frame subassembly is whole to be heated and is out of shape evenly, and the deformation is close to whole enlargement, and relative size such as axiality influences not greatly, and can cooperate the thermal expansion of other parts and the adaptation.

In current conventional design, stator subassembly direct mount is in the one end that the bearing frame subassembly is close to the bearing, the bearing frame subassembly of this part is often thinner because size space's restriction, and stator subassembly's heat conduction path is shorter, the heat of conduction is here gathering easily, and the soaking ability of thinner material is poor, make bearing department form local high temperature and heat distribution very inhomogeneous, the deformation that leads to the bearing is not whole expansion but appears anomalous deformation, and then leads to the axiality change, influence the rotation accuracy. When the bearing is a gas bearing, the defects of sealing failure, gas leakage, uneven gas film, clamping of a rotating shaft and the like can be caused. In the gas turbine, the guide vane assembly is connected with one end of the bearing seat assembly far away from the bearing through the heat guide component, the part of the heat guide component except the joint with the bearing seat assembly is arranged at intervals with the bearing seat assembly, heat can be conducted to one end of the bearing seat assembly far away from the bearing, the heat is prevented from being accumulated at one end of the bearing seat assembly close to the bearing, the bearing seat assembly is heated uniformly as far as possible, and therefore deformation is uniform.

According to the gas turbine, the heat guide part is arranged between the outlet end of the combustion chamber and the bearing seat which are mutually overlapped originally, and the heat at the outlet of the combustion chamber is guided to the part of the bearing seat far away from the bearing, so that the heat conducted to the bearing seat can be uniformly distributed in the bearing seat, the bearing and the bearing seat nearby the bearing seat are uniformly heated and further uniformly deformed, the local high temperature at the bearing is avoided, and the defects of air leakage, coaxiality change, non-uniform air film, rotating shaft clamping and the like caused by irregular deformation of the gas bearing due to non-uniform heating are overcome.

When the gas bearing 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 gas bearing referred to herein is a hydrodynamic 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 gas bearing 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: the gas turbine of embodiment 1 is schematically constructed (the second end 830 is connected to the second housing 530).

FIG. 2: the structure of the heat guiding component is schematically shown.

FIG. 3: fig. 1 is a right side view of the heat directing member.

FIG. 4: right side view of the heat directing component (provided with through holes).

FIG. 5: right side view of the heat directing member (with fan shaped through holes).

FIG. 6: right side view of the heat directing component (second end break arrangement).

FIG. 7: the gas turbine of embodiment 2 is schematically constructed (the second end 830 is connected to the first housing 520).

FIG. 8: the gas turbine of example 3 is a schematic structural view (the second end 830 is connected to the end cover 510).

100, a rotating shaft; 200. a compressor; 300. a turbine; 400. a combustion chamber; 510. an end cap; 520. a first seat body; 530. a second seat body; 540. a collar; 600. a guide vane assembly; 710. a radial bearing; 800. a heat guide member; 810. a first end portion; 820. a connecting portion; 830. a second end portion; 840. a ring groove; 850. and a through hole.

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 1

A gas turbine includes a rotating shaft 100, a compressor 200, a turbine 300, and a combustor 400; as shown in fig. 1, the compressor 200 and the turbine 300 are sleeved on the rotating shaft 100 and can rotate synchronously; the exhaust end of the compressor 200 is communicated with the inlet end of the combustion chamber 400; the outlet end of the combustion chamber 400 is provided with a guide vane assembly 600 for guiding the high-temperature gas discharged from the outlet end of the combustion chamber into the turbine 300; the rotating shaft 100 is provided with a bearing and a bearing seat assembly, the bearing is located in the bearing seat assembly, and the guide vane assembly 600 is connected with the bearing seat assembly through a heat guiding component 800. The shaft 100, the compressor 200, the turbine 300, the combustion chamber 400 and the bearing seat assembly are integrally installed in a housing (only part of the housing is shown in fig. 1), and a gas passage of the compressor 200 communicating with the combustion chamber 400 is located between the housing and the bearing seat assembly.

The bearings are a thrust bearing and a radial bearing 710, and the thrust bearing, the radial bearing 710 and the bearing seat assembly are positioned between the compressor 200 and the turbine 300; the bearing seat assembly comprises an end cover 510, a first seat 520 and a second seat 530, a thrust bearing and a thrust disc are positioned between the first seat 520 and the rotating shaft 100, a radial bearing 710 is positioned between the second seat 530 and the rotating shaft 100, and the radial bearing 710 is positioned between the thrust bearing and the turbine 300 in the axial direction; the first holder body 520 and the second holder body 530 are sleeved with a collar 540, and the collar 540 is connected with the first holder body 520 through the end cover 510; the combustion chamber 400 is disposed around the shaft 100 and mounted on the collar 540.

The thrust bearing, radial bearing 710, may be a gas bearing. The gas bearing may be a hydrostatic bearing, a hydrodynamic bearing and/or a hybrid hydrodynamic and hydrostatic bearing.

The heat guiding member 800 is disposed around the rotating shaft 100, and as shown in fig. 2 and 3, includes a first end 810, a second end 830, and a connecting portion 820 connecting the first end 810 and the second end 830; the first end 810 is connected with the guide vane assembly 600 to form a fixed support for the guide vane assembly 600 and the combustion chamber 400; the second end 830 is connected to the second housing 530 at a position relatively far from the radial bearing 710 of the bearing housing assembly, so as to guide heat to a position far from the radial bearing 710, thereby achieving a better guiding effect and facilitating better uniform distribution of heat in the bearing housing.

The first end 810 and the connecting portion 820 of the heat guiding member 800 are spaced apart from the second seat 530 (i.e., do not directly contact with the second seat 530), so that when the guide vane assembly 600 conducts heat to the second seat 530, a longer heat conduction path is formed, which is helpful for reducing temperature and uniformly dissipating heat to the external environment, and avoids directly conducting heat to a portion of the second seat 530 relatively close to the radial bearing 710. Further, the heat guiding member 800 may further include a plurality of sub-end portions, each of which is connected to the bearing seat assembly (each of which is connected to a different position of the bearing seat assembly, so that heat can be conducted to a plurality of positions of the bearing seat assembly, which is more beneficial to uniform heating), each of which is connected to the connecting portion through a branch portion, and the branch portion may be in a ring shape or a spoke shape.

The portion of the second end 830 of the heat guiding member 800 connected to the bearing housing assembly may be provided with a ring groove 840, as shown in fig. 2, to reduce the contact area between the heat guiding member 800 and the second seat 530, thereby minimizing the amount of heat conducted to the second seat 530 (reducing the contact area causes more heat to be accumulated on the heat guiding member 800, and then the air pressure of the air compressor 200 cools the heat guiding member 800; the heat conducting speed of the metal heat guiding member 800 is much higher than that of air, and the heat accumulated on the heat guiding member 800 is dissipated by heat radiation).

The connection mode of the first end portion 810 and the guide vane assembly 600, and the connection mode of the second end portion 830 and the second seat 530 may be any one of welding, bolt connection, screw connection, limiting groove clamping, and the like.

The collar 540 may be provided with air holes, as shown in fig. 1, air inlets of the air holes are communicated with an air outlet end of the compressor 200, and air outlets of the air holes are communicated with a cavity where the heat guiding component 800 is located, so as to guide "cold air" ("cold air" is relative to "hot air" at the turbine end, which is generally a normal temperature gas and can be used for cooling) from the compressor 200 to an inner cavity (an inner cavity formed between the end cover 510, the first seat 520, the second seat 530 and the collar 540) of the bearing seat assembly, so as to cool the heat guiding component 800 and the first seat 520 and the second seat 530 of the bearing seat assembly.

The heat guiding component 800 may be provided with a through hole 850, on one hand, the flow of the "cold air" from the compressor can be enhanced, and the "cold air" from the compressor 200 enters the inner cavity of the bearing seat assembly and then enters the annular cavity through the through hole 850 (since the connecting portion 820 and the second seat 530 are arranged at an interval, an annular cavity is formed between the connecting portion and the second seat 530), so as to cool the second seat 530, enhance the cooling effect and increase the cooling area; on the other hand, the weight of the heat guide member 800 may be reduced.

The through hole 850 may be a plurality of through holes provided in the connecting portion 820, and as shown in fig. 4, the through hole has a circular shape.

The through hole 850 may also be a fan-shaped through hole (i.e., a through hole passing through the connecting portion 820 and having the first end portion 810 and the second end portion 830 as edges) disposed among the connecting portion 820, the first end portion 810 and the second end portion 830, as shown in fig. 5. On the basis, the second end 830 of the heat guiding member 800 can be disconnected at the through hole 850, so that the edge of the through hole 850 is changed from the second end 820 to the second seat 530, as shown in fig. 6; with such an arrangement, the weight of the heat guiding member 800 can be further reduced, the contact area between the heat guiding member 800 and the second housing 530 can be reduced, and the heat conducted to the second housing 530 can be reduced.

The guide vane assembly 600 may be configured as follows: the device comprises two supporting seats, and a blade group with an axial air passage is arranged between the two supporting seats.

In the operation process of the gas turbine of the embodiment, the low-pressure end of the compressor 200 sucks air (in the atmospheric environment) from the outside, the air is compressed and pressurized by the compressor 200, then enters the combustion chamber 400 and is mixed and combusted with the injected fuel to generate high-temperature and high-pressure gas, and the high-temperature gas (the temperature can reach 900 ℃) enters the turbine 300 from the outlet end of the combustion chamber 400 through the guide vane assembly 600 to do work through expansion; the heat of the guide vane assembly 600 is guided to the portion of the second base 530 relatively far away from the radial bearing 710 through the heat guiding component 800, the material of the bearing base assembly of the portion is relatively thick, which is beneficial to the uniform distribution of the guided heat, so that the second base 530 is heated and deformed uniformly, the deformation approaches to the overall expansion, the influence of the coaxiality and other relative dimensions is not large, and the guide vane assembly can be matched with the thermal expansion of other components for adaptation.

In the conventional design, the guide vane assembly 600 is directly installed at one end of the second seat 530 close to the radial bearing 710, the material of the second seat 530 of the portion is often relatively thin due to the limitation of the size and space, and the heat conduction path of the guide vane assembly 600 is short, the conducted heat is easily gathered at the position, and the heat-equalizing capacity of the thin material is poor, so that local high temperature is formed at the position of the radial bearing 710, the heat distribution is quite uneven, the deformation of the bearing is not the whole expansion but irregular deformation occurs, and further the change of the coaxiality is caused, and the rotation precision is affected. When the bearing is a gas bearing, the defects of sealing failure, gas leakage, uneven gas film, clamping of a rotating shaft and the like can be caused. In the gas turbine of the present invention, the guide vane assembly 600 is connected to one end of the second base 530 far away from the radial bearing 710 through the heat guiding member 800, and the portion of the heat guiding member 800 except the connection with the second base 530 is spaced apart from the second base 530, so that heat can be conducted to one end of the second base 530 far away from the radial bearing 710, thereby preventing heat from being collected at one end of the second base 530 near the radial bearing 710, and making the second base 530 heated uniformly as much as possible, so that the deformation is uniform, and when the bearing is a gas bearing, the heating is uniform, thereby preventing the occurrence of sealing failure and gas leakage.

Example 2

A gas turbine includes a rotating shaft 100, a compressor 200, a turbine 300, and a combustor 400; as shown in fig. 7, the compressor 200 and the turbine 300 are sleeved on the rotating shaft 100 and can rotate synchronously; the exhaust end of the compressor 200 is communicated with the inlet end of the combustion chamber 400; the outlet end of the combustion chamber 400 is provided with a guide vane assembly 600 for guiding the high-temperature gas discharged from the outlet end of the combustion chamber into the turbine 300; the rotating shaft 100 is provided with a bearing and a bearing seat assembly, the bearing is located in the bearing seat assembly, and the guide vane assembly 600 is connected with the bearing seat assembly through a heat guiding component 800. The shaft 100, the compressor 200, the turbine 300, the combustion chamber 400 and the bearing seat assembly are integrally installed in a housing (only part of the housing is shown in fig. 7), and a gas passage of the compressor 200 communicating with the combustion chamber 400 is located between the housing and the bearing seat assembly.

The heat guiding member 800 is disposed around the rotating shaft 100, and as shown in fig. 2 and 3, includes a first end 810, a second end 830, and a connecting portion 820 connecting the first end 810 and the second end 830; the first end 810 is connected with the guide vane assembly 600 to form a fixed support for the guide vane assembly 600 and the combustion chamber 400; the second end 830 is connected to the first housing 520 at a position relatively far away from the radial bearing 710 of the bearing housing assembly, so as to guide heat to a position far away from the radial bearing 710, thereby achieving a better guiding effect and facilitating better uniform distribution of heat in the bearing housing.

The first end 810 and the connecting portion 820 of the heat guiding member 800 are spaced from the first seat 520 (i.e., do not directly contact with the first seat 520 and the second seat 530), so that when the guide vane assembly 600 conducts heat to the first seat 520, a longer heat conduction path is formed, which is helpful for reducing temperature and uniformly dissipating heat to the external environment, and avoids directly conducting heat to a portion of the second seat 530 relatively close to the radial bearing 710.

The portion of the second end 830 of the heat guiding member 800 connected to the bearing seat assembly may be provided with a ring groove 840, as shown in fig. 2, to reduce the contact area between the heat guiding member 800 and the first housing 520, thereby minimizing the heat conducted to the first housing 520.

The connection mode of the first end 810 and the guide vane assembly 600, and the connection mode of the second end 830 and the first seat 520 may be any one of welding, bolt connection, screw connection, limiting groove clamping, and the like.

Example 3

A gas turbine includes a rotating shaft 100, a compressor 200, a turbine 300, and a combustor 400; as shown in fig. 8, the compressor 200 and the turbine 300 are sleeved on the rotating shaft 100 and can rotate synchronously; the exhaust end of the compressor 200 is communicated with the inlet end of the combustion chamber 400; the outlet end of the combustion chamber 400 is provided with a guide vane assembly 600 for guiding the high-temperature gas discharged from the outlet end of the combustion chamber into the turbine 300; the rotating shaft 100 is provided with a bearing and a bearing seat assembly, the bearing is located in the bearing seat assembly, and the guide vane assembly 600 is connected with the bearing seat assembly through a heat guiding component 800. The shaft 100, the compressor 200, the turbine 300, the combustion chamber 400 and the bearing seat assembly are integrally installed in a housing (only part of the housing is shown in fig. 8), and a gas passage of the compressor 200 communicating with the combustion chamber 400 is located between the housing and the bearing seat assembly.

The heat guiding member 800 is disposed around the rotating shaft 100, and as shown in fig. 2 and 3, includes a first end 810, a second end 830, and a connecting portion 820 connecting the first end 810 and the second end 830; the first end 810 is connected with the guide vane assembly 600 to form a fixed support for the guide vane assembly 600 and the combustion chamber 400; the second end 830 is connected to the end cap 510 at a location relative to the radial bearing 710 of the housing assembly to direct heat to a location away from the radial bearing 710, thereby providing better heat conduction and facilitating better heat distribution within the housing.

The first end 810 and the connecting portion 820 of the heat guiding member 800 are spaced from the end cover 510 (i.e., do not directly contact with the end cover 510, the first seat 520, and the second seat 530), so that when the guide vane assembly 600 conducts heat to the end cover 510, a longer heat conduction path is formed, which is helpful for reducing temperature and uniformly dissipating heat to the external environment, and avoids directly conducting heat to a portion of the second seat 530 relatively close to the radial bearing 710.

The portion of the second end 830 of the heat guide member 800 connected to the bearing housing assembly may be provided with an annular groove 840, as shown in fig. 2, to reduce the contact area of the heat guide member 800 with the end cap 510, thereby minimizing the amount of heat transferred to the end cap 510.

The first end 810 and the guide vane assembly 600 are connected, and the second end 830 and the end cover 510 are connected by welding, bolting, screwing, clipping with a limiting groove, or the like.

The above examples are provided to those of ordinary skill in the art to fully disclose and describe how to make and use the claimed embodiments, and are not intended to limit the scope of the disclosure herein. Modifications apparent to those skilled in the art are intended to be within the scope of the appended claims.

Claims

1. A gas turbine, characterized by: comprises a rotating shaft, a gas compressor, a turbine and a combustion chamber; the compressor and the turbine are sleeved on the rotating shaft; a guide vane assembly is arranged at the outlet end of the combustion chamber; the guide vane assembly is connected with the bearing seat assembly through a heat guide part.

2. The gas turbine of claim 1, wherein: the connection location of the heat directing member to the bearing housing assembly is at a location of the bearing housing assembly relatively distant from the bearing.

3. The gas turbine of claim 1, wherein: the heat guide member includes a first end portion, a second end portion, and a connecting portion connecting the first end portion and the second end portion; the first end is connected with a guide vane assembly; the second end is connected with a bearing block assembly.

4. The gas turbine of claim 3, wherein: the first end part and the connecting part of the heat guiding component are arranged at intervals with the bearing seat component.

5. The gas turbine of claim 3, wherein: the portion of the second end connected to the bearing block assembly is provided with a groove.

6. The gas turbine of claim 1, wherein: the bearing is selected from gas bearings.

7. The gas turbine of claim 1, wherein: the bearing and the bearing seat assembly are positioned between the compressor and the turbine; the bearing seat assembly comprises an end cover, a first seat body and a second seat body, a thrust bearing and a thrust disc are arranged between the first seat body and the rotating shaft, a radial bearing is arranged between the second seat body and the rotating shaft, and the radial bearing is positioned between the thrust bearing and the turbine; lantern rings are sleeved outside the first seat body and the second seat body and are connected with the first seat body through end covers; the combustion chamber is arranged around the rotating shaft and is arranged on the lantern ring; the guide vane assembly is connected with the first holder body, the second holder body and/or the end cover through a heat guide part.

8. The gas turbine of claim 7, wherein: the lantern ring is provided with an air hole, an air inlet of the air hole is communicated with an air outlet end of the air compressor, and an air outlet of the air hole is communicated with a cavity where the heat guide part is located.

9. The gas turbine of claim 8, wherein: the heat guide member is provided with a through hole.

10. The gas turbine of claim 1, wherein: the guide vane assembly comprises two support seats, and a vane group with an axial air passage is arranged between the two support seats;

and/or: the rotating shaft, the gas compressor, the turbine, the combustion chamber and the bearing seat assembly are integrally arranged in the shell, and a gas passage for communicating the gas compressor and the combustion chamber is positioned between the shell and the bearing seat assembly.