CN203362234U - Turbine rotor - Google Patents
Turbine rotor Download PDFInfo
- Publication number
- CN203362234U CN203362234U CN 201320383084 CN201320383084U CN203362234U CN 203362234 U CN203362234 U CN 203362234U CN 201320383084 CN201320383084 CN 201320383084 CN 201320383084 U CN201320383084 U CN 201320383084U CN 203362234 U CN203362234 U CN 203362234U
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- rotor
- turbine
- rotor disk
- disk
- turbine rotor
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Abstract
The utility model relates to a turbine rotor which comprises a rotor disk, turbine blades are arranged on the periphery of the rotor disk, a rotor disk end face is arranged at the lower end of the rotor disk and provided with an annular groove, the turbine rotor is one-time formed through metal injection molding, the turbine rotor 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, the weight of the turbine can be reduced by more than 15% sometimes, material consumption is reduced, and the purposes of saving cost and improving economical benefits are achieved. Due to reduction of the weight of the 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 the effect of the turbine booster is improved, the service life of the turbine rotor is prolonged, and oil consumption is reduced.
Description
Technical field
The utility model relates to a kind of turbine rotor of turbosupercharger, specifically, relates to a kind of turbine rotor, belongs to technical field of internal combustion engines.
Background technique
At present, pressurized machine is widely used in the Modern Internal-Combustion Engine motor.Current, the booster turbine rotor generally used is all solid basically, and weight is heavier, and during startup, greatly, the rotating speed speed-raising is slower in power consumption.Turbine material is the K418 nickel-base casting alloy, the cured mould precision casting process of additional use, do not use metal injection molded more advanced technology, its 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, the margin of safety of ratio of strength storage compressor impeller that is to say turbine is high a lot, and working condition is more severe.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 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, comprise rotor disk, and the periphery of rotor disk is provided with turbine blade, and the rotor disk lower end has the rotor disk end face, and the rotor disk end face is provided with annular groove.
As further improvement in the technical proposal:
The bottom centre of described rotor disk is provided with rotor shaft, and rotor shaft is coaxial with rotor disk, and rotor shaft and rotor disk are structure as a whole.
Described rotor disk upper end is provided with contiguous block.
Described rotor disk upper end is provided with connecting groove.
The below of described rotor shaft is provided with worm screw.
The below of described worm screw is provided with connecting rod.
Described worm screw, connecting rod are all coaxial with rotor disk.
Described rotor shaft, worm screw, connecting rod and rotor disk are structure as a whole.
The sectional shape of described contiguous block is Hexagon.
The sectional shape of described connecting groove is Hexagon.
The utility model is taked above technological scheme, have the following advantages: turbine rotor can be taked metal injection molded disposal molding, 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, sometimes loss of weight is much more than 15%, 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 the effect of turbosupercharger, extend the working life of turbine rotor, and reduced fuel consumption.
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 in the utility model embodiment 1;
Accompanying drawing 2 is plan views of accompanying drawing 1, accompanying drawing 4;
Accompanying drawing 3 is worm's eye views of accompanying drawing 1, accompanying drawing 6;
Accompanying drawing 5 is worm's eye views of accompanying drawing 4, accompanying drawing 8;
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, 4-annular groove, 5-worm screw, 6-connecting rod, 7-connecting groove, 8-rotor shaft, 9-rotor disk end face.
Embodiment
Embodiment 1, as shown in accompanying drawing 1, accompanying drawing 2 and accompanying drawing 3, a kind of turbine rotor, 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, and rotor disk 1 lower end has rotor disk end face 9, and rotor disk end face 9 is provided with annular groove 4, rotor disk 1 upper end exceeds the upper end of turbine blade 2, rotor disk 1 upper end is provided with contiguous block 3, and the sectional shape of contiguous block 3 is Hexagon, for location and the assembling of turbine rotor.
Claims (10)
1. a turbine rotor, comprise rotor disk (1), and the periphery of rotor disk (1) is provided with turbine blade (2), it is characterized in that: rotor disk (1) lower end has rotor disk end face (9), and rotor disk end face (9) is provided with annular groove (4).
2. a kind of turbine rotor as claimed in claim 1, 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), and rotor shaft (8) is structure as a whole with rotor disk (1).
3. a kind of turbine rotor as claimed in claim 2, it is characterized in that: described rotor disk (1) upper end is provided with contiguous block (3).
4. a kind of turbine rotor as claimed in claim 2, it is characterized in that: described rotor disk (1) upper end is provided with connecting groove (7).
5. a kind of turbine rotor as described as claim 3 or 4, it is characterized in that: the below of described rotor shaft (8) is provided with worm screw (5).
6. a kind of turbine rotor as claimed in claim 5, it is characterized in that: the below of described worm screw (5) is provided with connecting rod (6).
7. a kind of turbine rotor as claimed in claim 6, it is characterized in that: described worm screw (5), connecting rod (6) are all coaxial with rotor disk (1).
8. a kind of turbine rotor as claimed in claim 7, it is characterized in that: described rotor shaft (8), worm screw (5), connecting rod (6) and rotor disk (1) are structure as a whole.
9. a kind of turbine rotor as claimed in claim 8, it is characterized in that: the sectional shape of described contiguous block (3) is Hexagon.
10. a kind of turbine rotor as claimed in claim 9, it is characterized in that: the sectional shape of described connecting groove (7) is Hexagon.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320383084 CN203362234U (en) | 2013-07-01 | 2013-07-01 | Turbine rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320383084 CN203362234U (en) | 2013-07-01 | 2013-07-01 | Turbine rotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203362234U true CN203362234U (en) | 2013-12-25 |
Family
ID=49810020
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201320383084 Expired - Fee Related CN203362234U (en) | 2013-07-01 | 2013-07-01 | Turbine rotor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203362234U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104915500A (en) * | 2015-06-11 | 2015-09-16 | 萍乡市慧成精密机电有限公司 | Powder injection molding turbine and structure optimization design method thereof |
| CN105888734A (en) * | 2016-06-08 | 2016-08-24 | 湖南天雁机械有限责任公司 | Turbocharger turbine with internal-double-offset-ring petal-shaped head |
| US10385695B2 (en) | 2014-08-14 | 2019-08-20 | Pratt & Whitney Canada Corp. | Rotor for gas turbine engine |
-
2013
- 2013-07-01 CN CN 201320383084 patent/CN203362234U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10385695B2 (en) | 2014-08-14 | 2019-08-20 | Pratt & Whitney Canada Corp. | Rotor for gas turbine engine |
| CN104915500A (en) * | 2015-06-11 | 2015-09-16 | 萍乡市慧成精密机电有限公司 | Powder injection molding turbine and structure optimization design method thereof |
| CN104915500B (en) * | 2015-06-11 | 2017-10-13 | 萍乡市慧成精密机电有限公司 | Powder injection forming turbine and its optimum structure design method |
| CN105888734A (en) * | 2016-06-08 | 2016-08-24 | 湖南天雁机械有限责任公司 | Turbocharger turbine with internal-double-offset-ring petal-shaped head |
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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 | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20131225 Termination date: 20170701 |