CN114017140B

CN114017140B - Turbine arrangement with cooling passage

Info

Publication number: CN114017140B
Application number: CN202111300415.7A
Authority: CN
Inventors: 诸葛伟林; 江泓升; 薛彪; 高超; 张扬军; 钱煜平
Original assignee: Xace Turbo Technologies Beijing Co ltd; Tsinghua University
Current assignee: Xace Turbo Technologies Beijing Co ltd; Tsinghua University
Priority date: 2021-11-04
Filing date: 2021-11-04
Publication date: 2022-08-30
Anticipated expiration: 2041-11-04
Also published as: CN114017140A

Abstract

A turbine arrangement having a cooling passage is provided. The turbine assembly includes a housing assembly; a shaft assembly having a cavity formed therein; and the bearing is arranged in the shell assembly and positioned between the shell assembly and the shaft assembly, and is used for supporting the shaft assembly to rotate relative to the shell assembly. Wherein the cooling passage is routed through the bearing and the cavity such that cooling fluid passing through the cooling passage can cool the bearing and the shaft assembly. In this way, the cooling passage can cool the bearing and the shaft assembly and greatly reduce the amount of heat conducted to the bearing. The reliability of the turbine device is improved, and the production and maintenance costs of the turbine device are reduced.

Description

Turbine arrangement with cooling passage

Technical Field

The present application relates to the field of turbomachines, and more particularly, to a turbine device having a cooling passage.

Background

A turbine is a component that converts energy in a fluid medium into mechanical energy. The high temperature, high pressure fluid, when flowing through the rotor, impacts the turbine blades, which turn the drive shaft into rotation. The shaft drives other machines directly or through a transmission mechanism, thereby outputting mechanical work.

When the turbine device works under high temperature conditions, heat can be conducted to the bearing. The increase in the temperature of the bearing will result in a reduction in the service life of the bearing, which in turn will lead to a reduction in the reliability of the turbine installation and an increase in the maintenance costs of the turbine installation.

Disclosure of Invention

The present application has been made in view of the state of the art described above. It is an object of the present application to provide a turbine arrangement with cooling passages that overcomes at least one of the disadvantages described in the background above.

In order to achieve the above object, the present application adopts the following technical solutions.

The present application provides a turbine arrangement having a cooling passage, the turbine arrangement including a housing assembly; a shaft assembly having a cavity formed therein; and a bearing disposed within the housing assembly between the housing assembly and the shaft assembly for supporting the shaft assembly for rotation relative to the housing assembly, wherein the cooling passage is routed through the bearing and the cavity such that cooling fluid passing through the cooling passage can cool the bearing and the shaft assembly.

In an alternative, the housing assembly includes a volute, and the turbine assembly further includes an impeller coaxially secured to the shaft assembly and located within the volute, the impeller being configured to drive the shaft assembly for rotation.

In an alternative, the impeller and the shaft assembly are independent of each other and fixed to each other, or the impeller and the shaft assembly are formed integrally.

In an alternative arrangement, the impeller and the shaft assembly have a gap in a radial direction of the shaft assembly, the cavity being in communication with the gap such that the impeller is exposed to the cavity and the path of the cooling passage passes through the impeller such that cooling fluid passing through the cooling passage can cool the impeller.

In an optional aspect, the housing assembly includes a first cavity, a second cavity, an inlet, and an outlet, the first cavity and the second cavity are located inside the housing assembly, the first cavity and the second cavity are located on two sides of the bearing in the axial direction of the bearing, the first cavity is located on a side close to the impeller compared with the second cavity, the inlet communicates with the first cavity and an outside of the housing assembly, the outlet communicates with the second cavity and the outside of the housing assembly, and a path of the cooling passage passes through the inlet, the first cavity, the second cavity, and the outlet.

In an alternative aspect, the housing assembly includes a thermal insulation disc assembly located between the first cavity and the impeller such that the thermal insulation disc assembly is capable of reducing conduction of heat from the impeller side to the first cavity, the thermal insulation disc assembly including a first thermal insulation disc, a second thermal insulation disc, and a thermal insulation pad, the first thermal insulation disc, the second thermal insulation disc, and the thermal insulation pad being arranged in a stacked manner in the axial direction, the thermal insulation pad being located between the first thermal insulation disc and the second thermal insulation disc.

In an alternative, the turbine assembly further includes a labyrinth seal structure disposed on an outer surface of the shaft assembly, the labyrinth seal structure being located between the thermal shield disk assembly and the shaft assembly.

In an alternative aspect, the shaft assembly includes a shaft and a sleeve, the sleeve is sleeved on the shaft, an area between the sleeve and the shaft forms the cavity, the sleeve includes a first through hole and a second through hole, the first through hole and the second through hole are respectively located on both sides of the bearing in an axial direction of the bearing, the first through hole is located on a side close to the impeller compared to the second through hole, and a path of the cooling passage sequentially passes through the first through hole, the cavity, and the second through hole, so that the cooling fluid passing through the cooling passage can enter the cavity through the first through hole and exit the cavity through the second through hole.

In an alternative arrangement, the shaft assembly includes a shaft and a sleeve, the sleeve being sleeved on the shaft, the region between the sleeve and the shaft forming the cavity, the sleeve including a third through-hole through which the cooling passage is routed such that cooling fluid can enter and exit the cavity via the third through-hole.

In an alternative, the bearing is an air bearing, and the cooling passage is routed through a gap between the air bearing and the shaft assembly.

By adopting the technical scheme, the cooling passage can cool the bearing and the shaft assembly and greatly reduce the heat conduction to the bearing. The bearing can work under the lower operating mode of temperature, has effectively promoted the life-span of bearing, and then has promoted turbine device's reliability, has reduced turbine device's maintenance cost. Therefore, the turbine device does not need to select a bearing made of high-temperature-resistant alloy, and the production cost of the turbine device is effectively reduced.

Drawings

FIG. 1 illustrates a cross-sectional view of a turbine arrangement having cooling passages in accordance with a first embodiment of the present application.

FIG. 2 illustrates a cross-sectional view of a turbine arrangement having cooling passages in accordance with a second embodiment of the present application.

Description of the reference numerals

1a housing assembly; 1a cooling passage; 11a housing; 111 a bearing seat; 11a first cavity; 11b a second cavity; 11c an inlet; 11d an outlet; 112, a clamp spring; 113 an air inlet joint; 114 an exhaust fitting; 12 a volute; 13 a thermally insulated tray assembly; 131 a first insulating tray; 132 a second thermally insulating disk; 133 a heat insulating mat; 14, a cover plate;

2, an air bearing;

3, shaft assembly; 31a shaft; 31a first shaft portion; 31b a second shaft portion; 31c a third shaft portion; 31d a fourth shaft portion; 31e a fifth shaft portion; 31f a sixth shaft portion; 32 shaft sleeves; 32a cavity; 32b a first via; 32c a second via; 32d a first boss portion; 32e second bushing portion; 32f a third via; 33 fixing the end head; 34 a coupling device; 35 a nut;

4, an impeller; 4a blade; 4b, a shaft hole; 4c a first shaft hole part; 4d second shaft hole portion;

5 sealing the teeth.

Detailed Description

Exemplary embodiments of the present application are described below with reference to the accompanying drawings. It should be understood that the detailed description is only intended to teach one skilled in the art how to practice the present application, and is not intended to be exhaustive or to limit the scope of the application.

In the present application, an "assembly" is not limited to being composed of a plurality of parts and components, but may be a single part or component. The through holes are used for indicating a first through hole, a second through hole and a third through hole which are arranged in the shaft sleeve.

(first embodiment)

FIG. 1 illustrates a turbine arrangement having cooling passages in accordance with a first embodiment of the present application. The turbine device comprises a shell assembly 1, an air bearing 2, a shaft assembly 3, an impeller 4 and a sealing tooth 5, wherein a cooling passage 1a is formed inside the shell assembly 1.

The housing assembly 1 includes an outer shell 11, a scroll 12, a thermally insulating disk assembly 13, and a cover plate 14. The housing 11 has a cylindrical structure, and both side ends thereof are open. The housing 11 is formed with an annular bearing seat 111 projecting toward the inside thereof. The air bearing 2 is mounted on a bearing housing 111. The circlip 112 abuts against the end of the air bearing 2, so that the air bearing 2 is fixed relative to the bearing seat 111. The bearing housing 111 partitions the inside of the housing 11 into a first cavity 11a and a second cavity 11b in the axial direction of the housing 11. An inlet 11c and an outlet 11d are provided on the outer peripheral wall of the housing 11, the inlet 11c communicates with the first cavity 11a and the outside of the housing 11, and the outlet 11d communicates with the second cavity 11b and the outside of the housing 11. An intake joint 113 corresponding to the inlet 11c and an exhaust joint 114 corresponding to the outlet 11d are attached to the outer peripheral wall of the housing 11, and an external pipe can be connected to the turbine device through the intake joint 113 and the exhaust joint 114.

The inlet 11c communicates with the first cavity 11a, the outlet 11d communicates with the second cavity 11b, and the path of the cooling passage 1a extends from the first cavity 11a with a higher temperature to the second cavity 11b with a lower temperature, so that the cooling passage 1a has a higher cooling efficiency.

The end of the housing 11 adjacent the first cavity 11a mounts a volute 12 and an insulating disk assembly 13. The insulating disk assembly 13 has an annular structure. The heat insulating disk assembly 13 is disposed inside the scroll 12, and an end of the heat insulating disk assembly 13 is mounted on an end of the housing 11 close to the first cavity 11 a. A static seal structure is provided between the outer peripheral portion of the heat insulating disk assembly 13 and the scroll 12. The heat insulating disk assembly 13 includes a first heat insulating disk 131, a second heat insulating disk 132, and a heat insulating mat 133, the first heat insulating disk 131, the second heat insulating disk 132, and the heat insulating mat 133 being arranged in a stacked manner in the axial direction of the housing assembly 1, the heat insulating mat 133 being located between the first heat insulating disk 131 and the second heat insulating disk 132. The first and second

insulating disks

131 and 132 are hard mica boards, and the insulating pad 133 is ceramic fiber wool. The end of the housing 11 near the second cavity 11b is fitted with a cover plate 14. The cover plate 14 has a ring structure, and an outer circumferential portion of the cover plate 14 is connected to an inner circumferential portion of the housing 11 for forming the second cavity 11 b.

The heat insulation disc assembly 13 is located between the first cavity 11a and the impeller 4, so that the heat insulation disc assembly 13 can reduce heat conduction from the impeller 4 side to the first cavity 11a and the second cavity 11 b. The heat insulation disc assembly 13 has a multi-layered structure such that the heat insulation disc assembly 13 has better heat insulation performance.

The shaft assembly 3 comprises a shaft 31, a sleeve 32, a fixed head 33 and a coupling device 34. The shaft 31 is provided with a stepped structure such that the shaft 31 is formed with a first shaft portion 31a having a larger diameter (cross-sectional diameter, the same applies hereinafter) and a second shaft portion 31b having a smaller diameter. The sleeve 32 is fitted over the shaft 31. The inner peripheral surface of the boss 32 is fitted to the first shaft portion 31a, and a cavity 32a is formed in a region between the boss 32 and the second shaft portion 31 b. The outer peripheral surface of the sleeve 32 is provided with a first through hole 32b and a second through hole 32c, and the first through hole 32b and the second through hole 32c communicate the outside of the sleeve 32 with the cavity 32 a. The number of the first through holes 32b and the second through holes 32c is plural, and the plural first through holes 32b and the plural second through holes 32c are respectively arranged uniformly in the circumferential direction of the boss 32. The first through hole 32b extends at an angle to the radial direction of the sleeve 32, and the second through hole 32c extends in a direction substantially coincident with the radial direction of the sleeve 32. The plurality of through

holes

32b and 32c are formed in the shaft sleeve 32, and the plurality of through

holes

32b and 32c enable cooling fluid outside the cavity 32a to easily flow through the cavity 32a, so that the exchange efficiency of the cooling fluid is improved, and the cooling efficiency is further improved.

The impeller 4 is arranged coaxially with the shaft 31, and an end portion of the shaft 31 (first shaft portion 31a) is formed integrally with the impeller 4. The impeller 4 is provided with blades 4 a. The sealing teeth 5 have an annular structure, and a toothed structure extending along the circumferential direction of the sealing teeth 5 over the entire circumference is provided on the outer circumferential surface of the sealing teeth 5. The sealing teeth 5 are sleeved on the first shaft part 31a, and a static sealing structure is arranged between the sealing teeth 5 and the first shaft part 31 a. The sealing teeth 5 are located between the shaft sleeve 32 and the impeller 4 in the axial direction of the shaft assembly 3, one end of each sealing tooth 5 abuts against the end of the impeller 4, and the other end of each sealing tooth 5 abuts against the end of the shaft sleeve 32. The fixing head 33 has a cylindrical structure, which is fitted over the outside of the shaft 31 and fixedly connected to the second shaft portion 31 b. The fixing head 33 abuts against the end of the sleeve 32 remote from the impeller 4, so that the sleeve 32 and the obturating teeth 5 are fixed relative to the shaft 31. The coupling device 34 is fixedly connected to the end of the fixed end head 33 remote from the impeller 4, so that the turbine device can perform work externally via the coupling device 34. Furthermore, the cover plate 14 of the housing assembly 1 is located radially outside the coupling device 34, and may have a slight gap therebetween.

The shaft assembly 3, impeller 4 and seal teeth 5 are mounted inside the housing assembly 1. The air bearing 2 is sleeved outside the shaft sleeve 32, so that the air bearing 2 can support the shaft assembly 3 to rotate relative to the housing assembly 1. Shaft assembly 3 extends through insulating disk assembly 13 and cover plate 14. The cavity 32a is located radially inward of the air bearing 2. The first through hole 32b and the second through hole 32c are located on both sides of the air bearing 2 in the axial direction of the air bearing 2 such that the first through hole 32b communicates the first cavity 11a with the cavity 32a, and the second through hole 32c communicates the second cavity 11b with the cavity 32 a. The insulating disc assembly 13 is located radially outward of the packing teeth 5. The inner circumferential surface of the heat insulating disk assembly 13 and the tooth-shaped structure of the outer circumferential surface of the packing tooth 5 form a labyrinth structure, so that the first cavity 11a and the inner space of the scroll 12 are substantially isolated by the labyrinth structure. The impeller 4 is located inside the scroll 12 and the heat shield disc assembly 13 is located between the impeller 4 and the first chamber 11 a. The coupling device 34 passes through the cover plate 14 and projects partially outside the housing assembly 1.

The shaft assembly 3 is supported to rotate using the air bearing 2 fixed to the housing assembly 1, so that the turbo device can have a high rotation speed, low friction loss, and low vibration, thereby improving the performance of the turbo device. The cavity 32a is provided radially inside the air bearing 2 so that the cooling fluid can reduce the conduction of heat of the shaft 31 to the air bearing 2. The heat insulation disc assembly 13 and the sealing teeth 5 jointly form a labyrinth seal structure, so that high-temperature gas on the impeller 4 side is basically isolated from the cooling passage 1a, and the high-temperature gas is prevented from entering the cooling passage 1a and causing negative influence on the cooling effect.

The flow process of the cooling fluid (high-pressure air) in the cooling passage 1a is explained below. The external pipe is connected to the turbine device via an inlet connection 113 and an outlet connection 114. High-pressure air enters the first chamber 11a from the inlet 11c as a cooling fluid, and the high-pressure air entering the first chamber 11a contacts the housing 11, the bearing housing 111, the heat insulating disk assembly 13, the air bearing 2, and the sleeve 32. A part of the high-pressure air in the first cavity 11a flows through the gap between the air bearing 2 and the boss 32 in the axial direction of the air bearing 2. The high-pressure air flowing through the air bearing 2 contacts the bearing housing 111, the air bearing 2, and the boss 32. Another part of the high pressure air in the first chamber 11a enters the cavity 32a through the first through hole 32b, and the high pressure air flowing through the cavity 32a contacts the first shaft portion 31a, the second shaft portion 31b, the sleeve 32 and the fixed head 33. The high-pressure air in the cavity 32a exits the cavity 32a through the second through hole 32c, and the high-pressure air exiting the cavity 32a and the high-pressure air flowing through the air bearing 2 are merged in the second cavity 11 b. The high-pressure air introduced into the second chamber 11b contacts the housing 11, the bearing housing 111, the cover plate 14, the air bearing 2, the boss 32, the fixed end 33, and the coupling 34. The high pressure air in the second chamber 11b is discharged from the turbine device through the outlet 11d and into the external circuit.

The cooling passage 1a is routed through the air bearing 2 so that the cooling fluid can directly cool the air bearing 2. The cooling passage 1a is routed through the cavity 32a so that the cooling fluid can cool the shaft 31 and the sleeve 32, reducing heat transfer to the air bearing 2. High-pressure air is used as cooling fluid, and the high-pressure air can play a sealing role at the labyrinth seal structure, so that high-temperature gas on the impeller 4 side is prevented from entering the cooling passage 1 a. Using air as the cooling fluid, the cooling fluid can be matched to the air bearings 2 using air as the lubricant, such that the cooling fluid can be used to cool the air bearings 2.

(second embodiment)

FIG. 2 illustrates a turbine arrangement having cooling passages in accordance with a second embodiment of the present application. The second embodiment is a modification of the first embodiment, and the same reference numerals are used in the present embodiment for the same or similar features as those of the first embodiment, and detailed descriptions of these features are omitted. The turbine device comprises a shell assembly 1, an air bearing 2, a shaft assembly 3, an impeller 4 and a sealing tooth 5, wherein a cooling passage 1a is formed inside the shell assembly 1.

The housing assembly 1 includes an outer shell 11, a scroll 12, an insulating disk assembly 13, and a cover plate 14. The insulating disk assembly 13 has an annular structure. The heat insulating disk assembly 13 includes a first heat insulating disk 131, a second heat insulating disk 132, and a heat insulating mat 133, the first heat insulating disk 131, the second heat insulating disk 132, and the heat insulating mat 133 being arranged in a stacked manner in the axial direction of the housing assembly 1, the heat insulating mat 133 being located between the first heat insulating disk 131 and the second heat insulating disk 132. Sealing teeth 5 are provided on the inner peripheral surfaces of the first and second

heat insulating disks

131 and 132, and the sealing teeth 5 have a tooth-like structure extending over the entire circumference in the circumferential direction of the heat insulating disk assembly 13. The packing teeth 5 are formed integrally with the first and second

heat insulating disks

131 and 132.

The shaft assembly 3 includes a shaft 31, a sleeve 32, and a nut 35. The shaft 31 is a stepped shaft, and is formed with a third shaft portion 31c, a fourth shaft portion 31d, a fifth shaft portion 31e, and a sixth shaft portion 31f, which are successively reduced in diameter. The third shaft portion 31c, the fourth shaft portion 31d, the fifth shaft portion 31e, and the sixth shaft portion 31f are connected in this order in the axial direction of the shaft 31. The sleeve 32 includes a first sleeve portion 32d having a smaller inner diameter and a second sleeve portion 32e having a larger inner diameter. The sleeve 32 is fitted over the fourth shaft portion 31 d. The inner peripheral surface of the first boss portion 32d is fitted with the fourth boss portion 31d, and the area between the fourth boss portion 31d and the second boss portion 32e is formed as a cavity 32 a. The end of the first boss portion 32d of the boss 32 abuts against a shoulder between the third shaft portion 31c and the fourth shaft portion 31 d. The diameter of the outer peripheral surface of the sleeve 32 is the same as the diameter of the third shaft portion 31 c. The impeller 4 has a shaft hole 4b extending through the impeller 4 along the central axis of the impeller 4, and the shaft hole 4b includes a first shaft hole portion 4c having a large inner diameter and a second shaft hole portion 4d having a small inner diameter. The impeller 4 is fitted over the shaft 31 and the sleeve 32. The inner peripheral surface of the first shaft hole portion 4c is fitted to the outer peripheral surface of the sleeve 32, and the end of the second sleeve portion 32e of the sleeve 32 abuts against the stepped structure formed between the first shaft hole portion 4c and the second shaft hole portion 4 d. The shaft 31 passes through the shaft hole 4b and penetrates the impeller 4, and the sixth shaft portion 31f partially protrudes to the outside of the impeller 4. Gaps are formed in the radial direction of the shaft 31 between the second shaft hole portion 4d and the fifth and

sixth shaft portions

31e and 31f, and the gaps communicate with the cavity 32 a. The sixth shaft portion 31f has a threaded structure on its outer peripheral surface, and the nut 35 is screwed to the sixth shaft portion 31 f. The nut 35 abuts against the end of the impeller 4 near the blades 4a, so that the impeller 4 and the hub 32 are fixed relative to the shaft 31. The outer peripheral surface of the sleeve 32 is provided with a third through hole 32f, and the third through hole 32f communicates the outside of the sleeve 32 with the cavity 32 a. The third through hole 32f extends at an angle to the radial direction of the sleeve 32. The number of the third through holes 32f is plural, and the plural third through holes 32f are uniformly arranged in the circumferential direction of the boss 32.

The impeller 4 is exposed to the cavity 32a so that the cooling fluid can cool the impeller 4. A gap communicating with the cavity 32a exists between the impeller 4 and the shaft 31, so that the cooling fluid can reduce the conduction of heat of the impeller 4 to the air bearing 2 and the shaft assembly 3. The plurality of through holes 32f on the sleeve 32 make the cooling fluid outside the cavity 32a easily flow through the cavity 32a, thereby promoting the exchange efficiency of the cooling fluid and further improving the cooling efficiency.

The shaft assembly 3, impeller 4 and seal teeth 5 are mounted inside the housing assembly 1. The air bearing 2 is fitted over the outside of the third shaft portion 31c such that the air bearing 2 can support the shaft assembly 3 for rotation relative to the housing assembly 1. Shaft assembly 3 extends through insulating disk assembly 13 and cover plate 14. The heat insulating disk assembly 13 is located at the radial outer side of the shaft sleeve 32, and the outer circumferential surface of the shaft sleeve 32 and the sealing teeth 5 of the heat insulating disk assembly 13 form a labyrinth structure, so that the first cavity 11a and the space inside the scroll 12 are substantially isolated. The third through hole 32f communicates the first chamber 11a and the cavity 32 a. The third shaft portion 31c passes through the cover plate 14 and partially protrudes to the outside of the housing assembly 1.

The shaft assembly 3 and the sealing teeth 5 jointly form a labyrinth seal structure, so that high-temperature gas on the impeller 4 side is basically isolated from the cooling passage 1a, and the high-temperature gas is prevented from entering the cooling passage 1a and causing negative influence on the cooling effect.

The flow process of the cooling fluid (high-pressure air) in the cooling passage 1a is explained below. High-pressure air enters the first chamber 11a from the inlet 11c as a cooling fluid, and the high-pressure air entering the first chamber 11a contacts the housing 11, the bearing housing 111, the heat insulating disk assembly 13, the air bearing 2, the third shaft portion 31c, and the boss 32. A part of the high pressure air in the first chamber 11a enters the cavity 32a through the third through hole 32f, and the high pressure air flowing through the cavity 32a contacts the fourth shaft 31d, the fifth shaft 31e, the sixth shaft 31f, the sleeve 32, the nut 35, and the impeller 4. The high-pressure air in the cavity 32a also leaves the cavity 32a through the third through hole 32f, and the high-pressure air leaving the cavity 32a returns to the first chamber 11 a. The high-pressure air flowing through the cavity 32a joins another portion of the high-pressure air in the first cavity 11a, and the high-pressure air also flows through the air bearing 2 in the axial direction of the air bearing 2. The high-pressure air flowing through the air bearing 2 enters the second chamber 11b, and the high-pressure air entering the second chamber 11b contacts the housing 11, the bearing housing 111, the cover plate 14, the air bearing 2, and the third shaft portion 31 c. The high pressure air in the second cavity 11b is discharged from the turbine device through the outlet 11d and into the external duct.

The application has at least the following advantages:

(i) the cooling passage 1a is routed through the air bearing 2 so that the cooling fluid can directly cool the air bearing 2. The cooling path 1a is routed through the cavity 32a so that the cooling fluid can cool the shaft 31 and the sleeve 32, reducing heat transfer to the airfoil bearing 2. The cavity 32a is provided radially inside the air bearing 2 so that the cooling fluid can reduce the conduction of heat of the shaft 31 to the air bearing 2. The impeller 4 is exposed to the cavity 32a so that the cooling fluid can cool the impeller 4. A gap communicating with the cavity 32a exists between the impeller 4 and the shaft 31, so that the cooling fluid can reduce the heat transfer of the impeller 4 to the shaft assembly 3 and the air bearing 2.

(ii) The heat insulation disc assembly 13 is located between the first cavity 11a and the impeller 4, so that the heat insulation disc assembly 13 can reduce heat conduction from the impeller 4 side to the first cavity 11a and the second cavity 11 b. The heat insulation disc assembly 13 has a multi-layered structure such that the heat insulation disc assembly 13 has better heat insulation performance.

(iii) The heat insulation disc assembly 13 or the shaft assembly 3 and the sealing teeth 5 jointly form a labyrinth seal structure, so that high-temperature gas on the impeller 4 side is basically isolated from the cooling passage 1a, and the high-temperature gas is prevented from entering the cooling passage 1a to cause negative influence on the cooling effect. The high-pressure air is used as a cooling fluid, and can play a sealing role at the labyrinth seal structure, so that high-temperature gas on the impeller 4 side is prevented from entering the cooling passage 1 a.

(iv) The shaft assembly 3 is supported to rotate using the air bearing 2 fixed to the housing assembly 1, so that the turbo device can have a high rotation speed, low frictional loss, and low vibration, thereby improving the performance of the turbo device. Using air as the cooling fluid, the cooling fluid can be matched to the air bearing 2 using air as the lubricant, so that the cooling fluid can be used to cool the air bearing 2.

(v) The plurality of through

holes

32b, 32c, 32f on the sleeve 32 make the cooling fluid outside the cavity 32a easily flow through the cavity 32a, promote the exchange efficiency of the cooling fluid, and further improve the cooling efficiency. The inlet 11c communicates with the first cavity 11a, the outlet 11d communicates with the second cavity 11b, and the path of the cooling passage 1a extends from the first cavity 11a with a higher temperature to the second cavity 11b with a lower temperature, so that the cooling passage 1a has a higher cooling efficiency.

It should be understood that the above embodiments are merely exemplary, and are not intended to limit the present application. Various modifications and alterations to the above-described embodiments may be made by those skilled in the art in light of the teachings of this application without departing from the scope thereof.

It should be understood that the cooling passages 1a may be collectively formed by any possible structure inside the turbine device. It should be understood that the cooling passage 1a is not limited to being formed inside the housing assembly 1, but may be partially located outside the housing assembly 1. It should be understood that the path of the cooling passage 1a is not limited to the manner shown in the embodiment. The path of the cooling passage 1a may be formed in a more complicated shape, for example, a serpentine-like reciprocating path to increase the cooling area.

It should be understood that the cavity 32a is not limited to being formed by the shaft 31 and the bushing 32, but may also be formed directly inside the shaft 31, for example by removing material inside the shaft 31 to form a cavity. It should be understood that the through hole provided in the sleeve 32 is not limited to being a circular hole, and may have any possible shape, such as an elongated hole extending in the circumferential or axial direction of the sleeve 32. It should be understood that the arrangement of the through holes is not limited to that shown in the embodiments, and may be arranged in any possible manner.

It should be understood that the bearing is not limited to the air bearing 2, but may be any other kind of bearing such as a rolling bearing.

It should be understood that the cooling fluid is not limited to air, but may be any fluid that can be used for cooling purposes, such as carbon dioxide, helium, and the like. It should be understood that the cooling fluid is not limited to gas, and the purpose of using gas as the cooling fluid is to match the cooling fluid to the airfoil bearing 2. When the bearing used is of another kind than the air bearing 2, the cooling fluid may also be a liquid. It will be appreciated that the cooling fluid may be the same type of fluid as the working fluid that drives the impeller 4 in rotation, for example both the cooling fluid and the working fluid are air.

It should be understood that the housing assembly 1 is not limited to include the first cavity 11a and the second cavity 11b, and any shape and any number of cavities may be formed inside thereof. The arrangement of the cavities inside the housing assembly 1 is not limited to that shown in the embodiments, and may be arranged in any possible manner.

It should be understood that the insulation tray assembly 13 is not limited to including the first insulation tray 131, the second insulation tray 132, and the insulation pad 133. The insulated disk assembly 13 may be a single layer of insulated disks or mats or a combination of any number of insulated disks and any number of insulated mats. It should be understood that the material of the thermal shield disk assembly 13 is not limited to hard mica boards and ceramic fiber wool, but may be any possible material such as titanium alloy.

It should be understood that the dynamic seal of the turbine device is not limited to the labyrinth seal, and may be a dynamic seal such as a brush seal or a graphite seal.

It should be understood that the turbine arrangement provided herein may be used as a stand-alone device or system, or may be part of a device or system such as a gas turbine generator, an air compressor, a turbocharger system, etc.

Claims

1. A turbine arrangement having a cooling passage, the turbine arrangement comprising:

a housing assembly (1) comprising a volute (12);

a shaft assembly (3) including a shaft (31) and a sleeve (32), the sleeve (32) being fitted over the shaft (31), a region between the sleeve (32) and the shaft (31) being formed with a cavity (32 a);

the bearing is arranged inside the shell assembly (1) and positioned between the shell assembly (1) and the shaft assembly (3) and is used for supporting the shaft assembly (3) to rotate relative to the shell assembly (1); and

an impeller (4) coaxially fixed to the shaft assembly (3) and located inside the volute (12), the impeller (4) being capable of driving the shaft assembly (3) in rotation, the impeller (4) being exposed to the cavity (32a), the impeller (4) having a clearance from the shaft assembly (3) in a radial direction of the shaft assembly (3), the cavity (32a) communicating with the clearance,

wherein the cooling passage (1a) is routed through the bearing, the cavity (32a) and the impeller (4) such that cooling fluid within the cavity (32a) is in contact with the impeller (4), the cooling fluid passing through the cooling passage (1a) being capable of cooling the bearing, the shaft assembly (3) and the impeller (4).

2. Turbine arrangement with cooling channels according to claim 1,

the impeller (4) and the shaft assembly (3) are independent of each other and fixed to each other, or the impeller (4) and the shaft assembly (3) are formed integrally.

3. Turbine arrangement with cooling channels according to claim 1,

the housing assembly (1) includes a first cavity (11a), a second cavity (11b), an inlet (11c) and an outlet (11d), the first cavity (11a) and the second cavity (11b) are located inside the housing assembly (1), the first cavity (11a) is located on one side of the bearing in the axial direction of the bearing, the second cavity (11b) is located on the other side of the bearing in the axial direction of the bearing, the first cavity (11a) is located on a side close to the impeller (4) compared with the second cavity (11b), the inlet (11c) communicates the first cavity (11a) with the outside of the housing assembly (1), the outlet (11d) communicates the second cavity (11b) with the outside of the housing assembly (1), and the path of the cooling passage (1a) passes through the inlet (11c), The first cavity (11a), the second cavity (11b) and the outlet (11 d).

4. The turbine device with cooling passage according to claim 3,

the housing assembly (1) comprises a heat insulation disc assembly (13), the heat insulation disc assembly (13) is positioned between the first cavity (11a) and the impeller (4), so that the heat insulation disc assembly (13) can reduce the conduction of heat on the impeller (4) side to the first cavity (11a), the heat insulation disc assembly (13) comprises a first heat insulation disc (131), a second heat insulation disc (132) and a heat insulation pad (133), the first heat insulation disc (131), the second heat insulation disc (132) and the heat insulation pad (133) are arranged in a stacked manner in the axial direction, and the heat insulation pad (133) is positioned between the first heat insulation disc (131) and the second heat insulation disc (132).

5. The turbine device with cooling passage according to claim 4,

the turbine device further comprises a labyrinth seal structure which is arranged on the outer surface of the shaft assembly (3) and is positioned between the heat insulation disc assembly (13) and the shaft assembly (3).

6. The turbine device with a cooling passage according to any one of claims 1 to 5,

the bushing (32) comprises a third through hole (32f), the cooling passage (1a) being routed through the third through hole (32f) such that a cooling fluid can enter and exit the cavity (32a) via the third through hole (32 f).

7. The turbine device with a cooling passage according to any one of claims 1 to 5,

the bearing is an air bearing (2), and the cooling passage (1a) is routed through a gap between the air bearing (2) and the shaft assembly (3).