CN216811788U - Integral rotor with blades - Google Patents
Integral rotor with blades Download PDFInfo
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- CN216811788U CN216811788U CN202220724022.2U CN202220724022U CN216811788U CN 216811788 U CN216811788 U CN 216811788U CN 202220724022 U CN202220724022 U CN 202220724022U CN 216811788 U CN216811788 U CN 216811788U
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- main shaft
- blades
- shaft
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Abstract
A whole rotor with blades relates to the technical field of turbines. The utility model aims to improve the rigidity of a turbine rotor and meet the requirements of small volume flow turbine on high efficiency and high shafting reliability. The utility model comprises a main shaft and a moving blade set, wherein the moving blade set and the main shaft are of an integrated structure, a front shaft neck, a front end part air seal section, a balance hub, a moving blade set, a rear end part air seal section, a rear shaft neck and a coupling are sequentially arranged on the outer circumferential side wall of the main shaft from front to back, the moving blade set comprises multiple stages of moving blades, and a static blade air seal is arranged between every two adjacent stages of moving blades. The utility model is used for improving the rigidity of the turbine rotor.
Description
Technical Field
The utility model relates to the technical field of turbines, in particular to an integral rotor with blades.
Background
The axial flow turbine rotor is mainly designed by adopting a moving blade and main shaft assembling structure, the moving blade is fixedly assembled and connected with a blade root groove which is pre-processed on a main shaft through a blade root, a small volume flow turbine usually adopts a higher rotating speed and a smaller blade root diameter in order to improve the efficiency, the rigidity of the main shaft is poorer, and the turbine bearing span has strict limitation in order to ensure better shafting stability. And the blade root structure further reduces the rigidity and the diameter of the main shaft, and brings great risk to the shafting reliability of the turbine.
SUMMERY OF THE UTILITY MODEL
The utility model provides an integral rotor with blades in order to improve the rigidity of a rotor of a turbine and meet the requirements of high efficiency and high shafting reliability of a small-volume-flow turbine.
The technical scheme adopted by the utility model for solving the technical problems is as follows:
the utility model provides a from whole rotor of taking blade includes main shaft and moving vane group, moving vane group and main shaft formula structure as an organic whole, is equipped with preceding axle journal, preceding tip atmoseal section, balanced hub, moving vane group, back tip atmoseal section, back axle journal and shaft coupling from front to back in proper order on the outer circumference lateral wall of main shaft, and moving vane group includes multistage moving blade, all is equipped with quiet leaf atmoseal between every two adjacent stages of moving blade.
Further, an oil throwing groove is arranged on the rear side of the front journal.
Furthermore, a shaft displacement measuring surface is arranged on the front end surface of the main shaft.
Furthermore, a plurality of speed measuring teeth are uniformly distributed at the end part of the front end of the main shaft along the circumferential direction.
Furthermore, the front part of the main shaft is provided with a front end shaft vibration measuring surface along the circumferential direction, and the front end shaft vibration measuring surface is arranged between the speed measuring teeth and the front shaft neck.
Furthermore, thrust surfaces are arranged at the front end and the rear end of the front shaft neck.
Furthermore, a rear end shaft vibration measuring surface is arranged at the rear part of the main shaft along the circumferential direction and is arranged between the rear shaft neck and the coupling.
Further, the vane gas seal includes three gas seal teeth.
Further, the number of the rotor blades is 6 stages.
Further, the main shaft is of a monobloc forging structure.
Compared with the prior art, the utility model has the following beneficial effects:
the rotor design of the present invention is applicable to various high speed, low volume flow turbines, such as supercritical CO2Turbines, industrial drive turbines, small-capacity steam power generation turbines and the like;
the rotor integral forging drum type structure is suitable for high-rotating-speed design, the moving blades and the main shaft are integrally machined, and compared with an assembled rotor, the rotor integral forging drum type structure has higher rotor rigidity and higher shafting reliability; no assembly deviation exists, and the structural strength is better;
according to the utility model, the moving blade and the main shaft are integrally processed, the requirement of blade assembly space is avoided, the structural size is small, the length of the rotor is more favorably compressed, the safety is higher, and the cost is lower;
the moving blade with smaller reaction degree is designed, so that the air leakage of the blade top is reduced, and the efficiency is improved;
the reasonable number of the moving blades is designed, so that the size of the throat part is ensured to have better processing manufacturability;
the balance hub structure is arranged in the utility model, so that the axial thrust of the rotor is reduced.
Drawings
Fig. 1 is a schematic view of the overall structure of the present invention.
Detailed Description
The first specific implementation way is as follows: the present embodiment is described with reference to fig. 1, and the integral rotor with blades according to the present embodiment includes a main shaft and a moving blade group, the moving blade group and the main shaft are of an integral structure, a front journal 5, a front end portion air seal section 7, a balance hub 8, the moving blade group, a rear end portion air seal section 11, a rear journal 12 and a coupling 14 are sequentially disposed on an outer circumferential side wall of the main shaft from front to rear, the moving blade group includes multiple stages of moving blades 9, and a stationary blade air seal 10 is disposed between each two adjacent stages of moving blades 9.
The second embodiment is as follows: in the present embodiment, an oil slinger 6 is provided on the rear side of the front journal 5, as described above with reference to fig. 1. Other components and connection modes are the same as those of the first embodiment.
The third concrete implementation mode: the present embodiment will be described with reference to fig. 1, and a shaft displacement measuring surface 1 is provided on the tip end surface of the spindle according to the present embodiment. Other components and connection modes are the same as those of the first embodiment.
The fourth concrete implementation mode: referring to fig. 1, the present embodiment is described, in which a plurality of speed measuring teeth 2 are uniformly arranged at an end of a front end of a main shaft in a circumferential direction. Other components and connection modes are the same as those of the first embodiment.
The fifth concrete implementation mode is as follows: in the present embodiment, the front portion of the spindle is provided with a front shaft vibration measuring surface 3 along the circumferential direction, and the front shaft vibration measuring surface 3 is disposed between the speed measuring teeth 2 and the front journal 5, as described with reference to fig. 1. The other components and the connection mode are the same as those of the fourth embodiment.
The sixth specific implementation mode: in the present embodiment, thrust surfaces 4 are provided at both the front and rear ends of the front journal 5, as described above with reference to fig. 1. Other components and connection modes are the same as those of the first embodiment.
The seventh embodiment: in the present embodiment, a rear end shaft vibration measuring surface 13 is provided in the rear portion of the main shaft in the circumferential direction, and the rear end shaft vibration measuring surface 13 is provided between the rear journal 12 and the coupling 14, as described with reference to fig. 1. Other components and connection modes are the same as those of the first embodiment.
The specific implementation mode is eight: referring to fig. 1, the vane gas seal 10 of the present embodiment includes three gas seal teeth. Other components and connection modes are the same as those of the first embodiment.
The specific implementation method nine: in the present embodiment, the number of rotor blades 9 is 6 stages in the present embodiment, which will be described with reference to fig. 1. Other components and connection modes are the same as those of the first embodiment.
The detailed implementation mode is ten: the present embodiment will be described with reference to fig. 1, and the main shaft of the present embodiment has a swaged structure. Other components and connection modes are the same as those of the first embodiment or the ninth embodiment.
In the embodiment, a front shaft neck 5 and a rear shaft neck 12 are respectively arranged on two sides of a rotor, and are used as a rotor height direction and a transverse supporting surface, a thrust surface 4 is arranged on two sides of the front shaft neck 5, and is used as a rotor axial positioning surface, a shaft displacement measuring surface 1 is arranged on a front end surface of the rotor, a front end shaft vibration measuring surface 3 is arranged near the front shaft neck 5, a rear end shaft vibration measuring surface 13 is arranged near the rear shaft neck 12, a speed measuring tooth 2 is arranged on the front side of the front shaft neck 5, an oil throwing groove 6 is arranged on the rear side of the front shaft neck 5, a balance hub 8 and a moving blade 9 are arranged in the middle of the rotor, a front end air seal section 7 is arranged outside the balance hub 8 and is used for installing a front end air seal, a rear end air seal section 11 is arranged outside the moving blade 9 and is used for installing a rear end air seal, the static blade air seal 10 and the moving blade 9 are arranged in a crossed manner, and a coupling 13 is arranged on the rear shaft neck side and is used as a shaft power output interface.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular is intended to include the plural unless the context clearly dictates otherwise, and it should be further understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of features, steps, operations, devices, components, and/or combinations thereof.
It should be noted that the terms "first," "second," and the like in the description and claims of this application and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used is interchangeable under appropriate circumstances such that the embodiments of the application described herein are capable of operation in sequences other than those illustrated or otherwise described herein. Moreover, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A monoblock rotor with blades is characterized in that: the novel gas turbine rotor blade set comprises a main shaft and a rotor blade set, wherein the rotor blade set and the main shaft are of an integrated structure, a front shaft neck (5), a front end part gas seal section (7), a balance hub (8), the rotor blade set, a rear end part gas seal section (11), a rear shaft neck (12) and a coupler (14) are sequentially arranged on the outer circumferential side wall of the main shaft from front to back, the rotor blade set comprises multiple stages of rotor blades (9), and a stationary blade gas seal (10) is arranged between every two adjacent stages of rotor blades (9).
2. The monobloc rotor with blades according to claim 1, wherein: an oil throwing groove (6) is arranged on the rear side of the front journal (5).
3. The monobloc rotor with blades according to claim 1, wherein: the front end face of the main shaft is provided with a shaft displacement measuring surface (1).
4. The monobloc rotor with blades according to claim 1, wherein: the end part of the front end of the main shaft is uniformly provided with a plurality of speed measuring teeth (2) along the circumferential direction.
5. The self-bladed unitary rotor of claim 4, further comprising: the front part of the main shaft is provided with a front end shaft vibration measuring surface (3) along the circumferential direction, and the front end shaft vibration measuring surface (3) is arranged between the speed measuring teeth (2) and the front shaft neck (5).
6. The monobloc rotor with blades according to claim 1, wherein: thrust surfaces (4) are arranged at the front end and the rear end of the front journal (5).
7. The monobloc rotor with blades according to claim 1, wherein: the rear part of the main shaft is provided with a rear end shaft vibration measuring surface (13) along the circumferential direction, and the rear end shaft vibration measuring surface (13) is arranged between the rear journal (12) and the coupler (14).
8. The monobloc rotor with blades according to claim 1, wherein: the vane gas seal (10) includes three gas seal teeth.
9. The monobloc rotor with blades according to claim 1, wherein: the number of the rotor blades (9) is 6.
10. The monobloc rotor with blades according to claim 1 or 9, wherein: the main shaft is of a monobloc forging structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220724022.2U CN216811788U (en) | 2022-03-30 | 2022-03-30 | Integral rotor with blades |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220724022.2U CN216811788U (en) | 2022-03-30 | 2022-03-30 | Integral rotor with blades |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216811788U true CN216811788U (en) | 2022-06-24 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202220724022.2U Active CN216811788U (en) | 2022-03-30 | 2022-03-30 | Integral rotor with blades |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216811788U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114592921A (en) * | 2022-03-30 | 2022-06-07 | 哈尔滨汽轮机厂有限责任公司 | Integral rotor with blades |
-
2022
- 2022-03-30 CN CN202220724022.2U patent/CN216811788U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114592921A (en) * | 2022-03-30 | 2022-06-07 | 哈尔滨汽轮机厂有限责任公司 | Integral rotor with blades |
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