CN217400971U - Integrated high-temperature-resistant turbine shaft - Google Patents
Integrated high-temperature-resistant turbine shaft Download PDFInfo
- Publication number
- CN217400971U CN217400971U CN202123194762.4U CN202123194762U CN217400971U CN 217400971 U CN217400971 U CN 217400971U CN 202123194762 U CN202123194762 U CN 202123194762U CN 217400971 U CN217400971 U CN 217400971U
- Authority
- CN
- China
- Prior art keywords
- blind hole
- axis body
- shaft
- axis
- louvre
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
- 239000011241 protective layer Substances 0.000 claims abstract description 7
- 230000017525 heat dissipation Effects 0.000 claims abstract description 6
- 239000000463 material Substances 0.000 claims description 3
- 238000000034 method Methods 0.000 abstract description 4
- 238000010586 diagram Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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Classifications
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/20—Hydro energy
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model discloses a high temperature resistant turbine shaft of integral type, including the axis body, be equipped with the turbine on the axis body, axis body and turbine formula structure as an organic whole, the surface of axis body is equipped with heat-resisting protective layer, one side of axis body is equipped with the blind hole, the central axis of blind hole coincides with the central axis of axis body, be equipped with the louvre on the axis body, the one end and the blind hole intercommunication of louvre, the louvre is arranged along the circumferencial direction spiral of blind hole. Compared with the prior art, the utility model the advantage lie in: the blind holes are arranged, so that the shaft body is of a hollow structure, the radiating fins are arranged inside the shaft body, the radiating area is increased, gas is exhausted through the radiating holes, the strength of the shaft body is supported, the air is exhausted in a rotating mode around the shaft body through the spirally arranged radiating holes, and the radiating capacity is enhanced in the high-speed rotating process of the shaft body; the arrangement of the groove increases the heat dissipation area and transmits the heat to the external air through the heat conducting strip.
Description
Technical Field
The utility model relates to a turbine shaft technical field specifically indicates a high temperature resistant turbine shaft of integral type.
Background
The turbine shaft is a rotating shaft for driving a turbine, and has a wide application in the fields of water turbines or propellers and the like, and the turbine shaft needs to be fixedly connected with a driving rotating shaft or a driven rotating shaft through a connecting structure such as a flange. Because the service environment of turbine shaft can produce a large amount of heats, the radiating effect of turbine shaft is relatively poor, causes local overheat easily, and then influences normal work.
SUMMERY OF THE UTILITY MODEL
The to-be-solved technical problem of the utility model is to overcome the defect of above-mentioned technique, provide a high temperature resistant turbine shaft of integral type.
In order to solve the technical problem, the utility model provides a technical scheme does: the utility model provides a high temperature resistant turbine shaft of integral type, includes the axis body, be equipped with the turbine on the axis body, axis body and turbine formula structure as an organic whole, the surface of axis body is equipped with heat-resisting protective layer, one side of axis body is equipped with the blind hole, the central axis of blind hole coincides with the central axis of axis body, be equipped with the louvre on the axis body, the one end and the blind hole intercommunication of louvre, the louvre is arranged along the circumferencial direction spiral of blind hole, the blind hole is equipped with radiating fin towards the direction of central axis, radiating fin evenly arranges along the circumferencial direction of blind hole inner wall.
As an improvement, the cross section of each radiating fin is of a triangular structure, and the radiating fins are gradually reduced towards the central axis.
As an improvement, the blind holes are filled with porous heat dissipation materials.
As an improvement, a groove is arranged on the shaft body.
As an improvement, a heat conducting strip is arranged in the groove.
As an improvement, the heat conducting strip is of a T-shaped structure.
Compared with the prior art, the utility model the advantage lie in: the blind holes are arranged, so that the shaft body is of a hollow structure, the radiating fins are arranged inside the shaft body, the radiating area is increased, gas is exhausted through the radiating holes, the strength of the shaft body is supported, the air is exhausted in a rotating mode around the shaft body through the spirally arranged radiating holes, and the radiating capacity is enhanced in the high-speed rotating process of the shaft body; the arrangement of the groove increases the heat dissipation area and the heat is transferred to the outside air through the heat conducting strip; the setting of protective layer can effectively strengthen the heat resistance of axis body.
Drawings
Fig. 1 is a schematic view of an assembly structure of a heat conducting strip and a shaft body of the integrated high-temperature resistant turbine shaft of the present invention.
Fig. 2 is a schematic cross-sectional structure diagram of the heat dissipating hole of the integrated high-temperature resistant turbine shaft of the present invention.
Fig. 3 is a schematic structural diagram of the shaft body and the turbine of the integrated high-temperature resistant turbine shaft according to the present invention.
As shown in the figure: 1. shaft body, 2, turbine, 3, protective layer, 4, blind hole, 5, louvre, 6, radiating fin, 7, recess, 8, heat conduction strip.
Detailed Description
The following describes the integrated high temperature resistant turbine shaft in further detail with reference to the accompanying drawings.
Combine the attached drawing, a high temperature resistant turbine shaft of integral type, including axis body 1, be equipped with turbine 2 on the axis body 1, axis body 1 and turbine 2 formula structure as an organic whole, the surface of axis body 1 is equipped with heat-resisting protective layer 3, one side of axis body 1 is equipped with blind hole 4, the central axis of blind hole 4 coincides with the central axis of axis body 1, be equipped with louvre 5 on the axis body 1, louvre 5's one end and blind hole 4 intercommunication, louvre 5 arranges along the circumferencial direction spiral of blind hole 4, blind hole 4 is equipped with radiating fin 6 towards the direction of central axis, radiating fin 6 evenly arranges along the circumferencial direction of blind hole 4 inner wall.
The cross section of the radiating fin 6 is of a triangular structure, and the radiating fin 6 is gradually reduced towards the central axis.
And the blind hole 4 is filled with porous heat dissipation materials.
The shaft body 1 is provided with a groove 7.
And a heat conducting strip 8 is arranged in the groove 7.
The heat conducting strip 8 is of a T-shaped structure.
When the utility model is implemented, the blind hole 4 is arranged to make the shaft body 1 be a hollow structure, the radiating fins 6 are arranged inside the shaft body to increase the radiating area, the gas is discharged through the radiating holes 5, the strength of the shaft body 1 is supported, and the radiating holes 5 are arranged spirally to make the air rotate around the shaft body 1 to be discharged, so that the radiating capacity is enhanced in the process of high-speed rotation of the shaft body 1; the arrangement of the groove 7 increases the heat dissipation area and transmits the heat to the outside air through the heat conduction strip 8; the protective layer 3 can effectively enhance the heat resistance of the shaft body 1.
The present invention and the embodiments thereof have been described above, but the description is not limited thereto, and the embodiment shown in the drawings is only one of the embodiments of the present invention, and the actual structure is not limited thereto. In summary, those skilled in the art should understand that they should not be limited to the embodiments described above, and that they can design the similar structure and embodiments without departing from the spirit of the invention.
Claims (6)
1. The utility model provides a high temperature resistant turbine shaft of integral type, includes axis body (1), be equipped with turbine (2) on axis body (1), axis body (1) and turbine (2) formula structure as an organic whole, its characterized in that: the surface of axis body (1) is equipped with heat-resisting protective layer (3), one side of axis body (1) is equipped with blind hole (4), the central axis of blind hole (4) coincides with the central axis of axis body (1), be equipped with louvre (5) on axis body (1), the one end and blind hole (4) intercommunication of louvre (5), louvre (5) are arranged along the circumferencial direction spiral of blind hole (4), blind hole (4) are equipped with radiating fin (6) towards the direction of central axis, radiating fin (6) are evenly arranged along the circumferencial direction of blind hole (4) inner wall.
2. The one-piece high temperature resistant turbine shaft of claim 1, wherein: the cross section of the radiating fin (6) is of a triangular structure, and the radiating fin (6) is gradually reduced towards the central axis.
3. The one-piece high temperature resistant turbine shaft of claim 1, wherein: and the blind hole (4) is filled with porous heat dissipation materials.
4. The one-piece high temperature resistant turbine shaft of claim 1, wherein: a groove (7) is formed in the shaft body (1).
5. The one-piece high temperature resistant turbine shaft of claim 4, wherein: and a heat conduction strip (8) is arranged in the groove (7).
6. The one-piece high temperature resistant turbine shaft of claim 5, wherein: the heat conducting strip (8) is of a T-shaped structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123194762.4U CN217400971U (en) | 2021-12-20 | 2021-12-20 | Integrated high-temperature-resistant turbine shaft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123194762.4U CN217400971U (en) | 2021-12-20 | 2021-12-20 | Integrated high-temperature-resistant turbine shaft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217400971U true CN217400971U (en) | 2022-09-09 |
Family
ID=83132443
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202123194762.4U Expired - Fee Related CN217400971U (en) | 2021-12-20 | 2021-12-20 | Integrated high-temperature-resistant turbine shaft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217400971U (en) |
-
2021
- 2021-12-20 CN CN202123194762.4U patent/CN217400971U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20220909 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |