CN203362236U - Turbine rotor weight reduction structure - Google Patents
Turbine rotor weight reduction structure Download PDFInfo
- Publication number
- CN203362236U CN203362236U CN 201320383160 CN201320383160U CN203362236U CN 203362236 U CN203362236 U CN 203362236U CN 201320383160 CN201320383160 CN 201320383160 CN 201320383160 U CN201320383160 U CN 201320383160U CN 203362236 U CN203362236 U CN 203362236U
- Authority
- CN
- China
- Prior art keywords
- rotor
- turbine
- cavity
- turbine rotor
- rotor disk
- 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
Images
Abstract
The utility model relates to a turbine rotor weight reduction structure which comprises a rotor disk. Turbine blades are arranged on the periphery of the rotor disk, a first cavity is arranged in the rotor disk, the turbine rotor weight reduction structure is optimization of an existing booster turbine structure, the weight of a turbine is effectively reduced on the basis that impeller shapes and runners are not changed and performance and structure strength of a booster are guaranteed, material consumption is reduced, and the purposes of saving cost and improving economical benefits are achieved. Due to reduction of the weight of a turbine rotor, mass distribution is reasonable, improvement of efficiency and reliability of a booster shaft system is facilitated, the rotation speed is higher, burden of an engine is reduced, and therefore production efficiency is improved, and the service life of the turbine rotor is prolonged.
Description
Technical field
The utility model relates to a kind of turbine rotor of turbosupercharger, specifically, relates to a kind of turbine rotor Lightened structure, belongs to technical field of internal combustion engines.
Background technique
At present, pressurized machine is widely used in Modern Engine.At present, the booster turbine rotor generally used is all solid basically, weight is heavier, rotating speed is lower, turbine material is the K418 nickel-base casting alloy, use cured mould precision casting process, numerical calculation and test show the burst speed of turbine wheel and fly broken factor of safety be much higher than the burst speed of compressor impeller and fly broken factor of safety, that is to say that the margin of safety of ratio of strength storage compressor impeller of turbine is high a lot.And turbine material is used expensive K418 nickel-base casting alloy, expensive, very important for the saving of material.
The model utility content
The technical problems to be solved in the utility model is for above deficiency, provide a kind of simple in structure, lightweight, rotating speed is fast, cost is low, the turbine rotor Lightened structure of long service life.
In order to solve above technical problem, the technical solution adopted in the utility model is as follows: a kind of turbine rotor Lightened structure, comprise rotor disk, and the periphery of rotor disk is provided with turbine blade, and the inside of rotor disk is provided with the first cavity.
As further improvement in the technical proposal:
Described rotor disk upper end is provided with contiguous block.
Be provided with the second through hole in described contiguous block, the second through hole communicates with the first cavity.
The lateral cross section of described the first cavity is shaped as circle, and the transverse cutting area of the first cavity increases from top to bottom gradually.
The bottom centre of described rotor disk is provided with rotor shaft, and rotor shaft is coaxial with rotor disk.
Be provided with the first through hole in described rotor shaft, the first through hole communicates with the first cavity.
Be provided with the second cavity in described rotor shaft, the second cavity communicates with the first cavity.
Described rotor shaft and rotor disk are structure as a whole.
The sectional shape of described contiguous block is Hexagon.
The utility model is taked above technological scheme, have the following advantages: the turbine rotor Lightened structure is the optimization that existing booster turbine structure is carried out, do not change blade profile and runner and guarantee booster performance and the basis of structural strength on effectively alleviate turbine weight, reduced the consumption of material, the purpose of reach cost-saving, increasing economic efficiency; Due to alleviating of turbine rotor weight, make mass distribution be tending towards rationally, also be conducive to improve efficiency and the reliability of pressurized machine axle system, rotating speed is faster, has alleviated the burden of motor, thereby has improved manufacturing efficiency, has extended the working life of turbine rotor.
Below in conjunction with drawings and Examples, the utility model is described in further detail.
The accompanying drawing explanation
Accompanying drawing 1 is the structural representation of turbine rotor Lightened structure in the utility model embodiment 1;
Accompanying drawing 2 is worm's eye views of accompanying drawing 1, accompanying drawing 8;
Accompanying drawing 3 is plan views of accompanying drawing 1, accompanying drawing 4;
Accompanying drawing 4 is structural representations of turbine rotor Lightened structure in the utility model embodiment 2;
Accompanying drawing 5 is worm's eye views of accompanying drawing 4, accompanying drawing 6;
Accompanying drawing 6 is structural representations of turbine rotor Lightened structure in the utility model embodiment 3;
Accompanying drawing 7 is plan views of accompanying drawing 6, accompanying drawing 8;
In figure,
The 1-rotor disk, 2-turbine blade, 3-contiguous block, 5-the first cavity, 6-the first through hole, 7-the second cavity, 8-rotor shaft, 9-the second through hole.
Embodiment
Embodiment 4, as accompanying drawing 8, shown in accompanying drawing 7 and accompanying drawing 2, a kind of turbine rotor Lightened structure, comprise rotor disk 1, the periphery of rotor disk 1 is provided with turbine blade 2, the bottom centre of rotor disk 1 is provided with rotor shaft 8, rotor shaft 8 is coaxial with rotor disk 1, rotor shaft 8 is structure as a whole with rotor disk 1, rotor disk 1 upper end is provided with contiguous block 3, the sectional shape of contiguous block 3 is Hexagon, location and assembling for turbine rotor, the inside of rotor disk 1 is provided with the first cavity 5, the lateral cross section of the first cavity 5 is shaped as circle, the transverse cutting area of the first cavity 5 increases from top to bottom gradually, be provided with the first through hole 6 in rotor shaft 8, the first through hole 6 communicates with the first cavity 5, be provided with the second through hole 9 in contiguous block 3, the second through hole 9 communicates with the first cavity 5.
Claims (9)
1. a turbine rotor Lightened structure, comprise rotor disk (1), and the periphery of rotor disk (1) is provided with turbine blade (2), it is characterized in that: the inside of rotor disk (1) is provided with the first cavity (5).
2. a kind of turbine rotor Lightened structure as claimed in claim 1, it is characterized in that: described rotor disk (1) upper end is provided with contiguous block (3).
3. a kind of turbine rotor Lightened structure as claimed in claim 2, it is characterized in that: be provided with the second through hole (9) in described contiguous block (3), the second through hole (9) communicates with the first cavity (5).
4. as one of them described a kind of turbine rotor Lightened structure of claim 1-3, it is characterized in that: the lateral cross section of described the first cavity (5) is shaped as circle, and the transverse cutting area of the first cavity (5) increases from top to bottom gradually.
5. a kind of turbine rotor Lightened structure as claimed in claim 4, it is characterized in that: the bottom centre of described rotor disk (1) is provided with rotor shaft (8), and rotor shaft (8) is coaxial with rotor disk (1).
6. a kind of turbine rotor Lightened structure as claimed in claim 5, it is characterized in that: be provided with the first through hole (6) in described rotor shaft (8), the first through hole (6) communicates with the first cavity (5).
7. a kind of turbine rotor Lightened structure as claimed in claim 5, it is characterized in that: be provided with the second cavity (7) in described rotor shaft (8), the second cavity (7) communicates with the first cavity (5).
8. a kind of turbine rotor Lightened structure as claimed in claim 5 is characterized in that: described rotor shaft (8) is structure as a whole with rotor disk (1).
9. a kind of turbine rotor Lightened structure as claimed in claim 2, it is characterized in that: the sectional shape of described contiguous block (3) is Hexagon.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320383160 CN203362236U (en) | 2013-07-01 | 2013-07-01 | Turbine rotor weight reduction structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320383160 CN203362236U (en) | 2013-07-01 | 2013-07-01 | Turbine rotor weight reduction structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203362236U true CN203362236U (en) | 2013-12-25 |
Family
ID=49810022
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201320383160 Expired - Fee Related CN203362236U (en) | 2013-07-01 | 2013-07-01 | Turbine rotor weight reduction structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203362236U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103790709A (en) * | 2014-02-19 | 2014-05-14 | 中国航空动力机械研究所 | Turbine disk |
| US10385695B2 (en) | 2014-08-14 | 2019-08-20 | Pratt & Whitney Canada Corp. | Rotor for gas turbine engine |
-
2013
- 2013-07-01 CN CN 201320383160 patent/CN203362236U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103790709A (en) * | 2014-02-19 | 2014-05-14 | 中国航空动力机械研究所 | Turbine disk |
| CN103790709B (en) * | 2014-02-19 | 2017-07-28 | 中国航空动力机械研究所 | Wheel disk of turbine |
| US10385695B2 (en) | 2014-08-14 | 2019-08-20 | Pratt & Whitney Canada Corp. | Rotor for gas turbine engine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN203362234U (en) | Turbine rotor | |
| CN102691527A (en) | Groove structure on back of open centripetal turbine blade | |
| CN203362236U (en) | Turbine rotor weight reduction structure | |
| CN204312394U (en) | With the turbosupercharger of diagonal impeller of compressor | |
| CN203362235U (en) | Weight reducing structure of booster turbine rotor | |
| CN203627302U (en) | Centrifugal fan impeller | |
| CN103557185A (en) | Axial pump vane airfoil optimizing design method | |
| CN202360152U (en) | Final blade in low-pressure-stage group of high-flow air cooling steam turbine | |
| CN203499729U (en) | Supercharger turbine rotor | |
| CN204591357U (en) | A kind of booster turbine rotor | |
| CN203272233U (en) | Integral backward-bending impeller of supercharger | |
| CN202360463U (en) | Split volute and water pump with the volute | |
| CN202250249U (en) | 1300mm final stage moving blade for full rotary speed steam turbine | |
| CN203081509U (en) | Turbine rotor with worm | |
| CN201610860U (en) | Compressor impeller of turbocharger | |
| CN204755389U (en) | Energy -conserving water pump of three -dimensional flow | |
| CN203081510U (en) | Turbine rotor with worm | |
| CN202596796U (en) | Turbine rotor with worm | |
| CN202048023U (en) | Primary blade of large-sized high-rotation-speed air compressor | |
| CN202065242U (en) | Intermediate stage blade of air compressor with hub diameter of Phi 762 | |
| CN201810585U (en) | Novel impeller capable of reducing axial force | |
| CN203214351U (en) | Vacuum molecular pump impeller | |
| CN202611772U (en) | Turbine rotor with worm | |
| CN201786744U (en) | Blades of cooling fan of engine | |
| CN202596795U (en) | Turbine rotor with worm |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20131225 Termination date: 20170701 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |