CN203499729U - Supercharger turbine rotor - Google Patents
Supercharger turbine rotor Download PDFInfo
- Publication number
- CN203499729U CN203499729U CN201320383067.9U CN201320383067U CN203499729U CN 203499729 U CN203499729 U CN 203499729U CN 201320383067 U CN201320383067 U CN 201320383067U CN 203499729 U CN203499729 U CN 203499729U
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- rotor
- turbine
- supercharger
- turbine rotor
- hole
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Abstract
The utility model relates to a supercharger turbine rotor, which comprises a rotor disc. The periphery of the rotor disc is provided with turbine blades; the upper end of the rotor disc is flush with the upper end of each turbine blade; a through hole is formed in the rotor disc. The supercharger turbine rotor can be molded at a time by adopting metal injection molding. The supercharger turbine rotor is the optimization of a traditional supercharger turbine structure, i.e. the turbine weight is effectively reduced by no less than 15 percent sometimes on the basis that a blade profile or a runner is not changed and the performance and the structural strength of a supercharger are ensured, and therefore, the material consumption is reduced, and the goals that the cost is reduced and the economic benefit is improved are achieved. As the weight of the turbine rotor is reduced, the mass distribution tends to be reasonable, the efficiency and the reliability of the shaft system of the supercharger are also helped improved, the revolving speed is higher, and the load of an engine is relieved, and therefore, the effect of the turbosuperchager is improved, the service life of the supercharger turbine rotor is prolonged, and the oil consumption is reduced.
Description
Technical field
The utility model relates to a kind of booster turbine rotor, belongs to technical field of internal combustion engines.
Background technique
At present, pressurized machine is widely used in Modern Internal-Combustion Engine motor.Current, the booster turbine rotor generally using is all solid substantially, and weight is heavier, and during startup, greatly, rotating speed speed-raising is slower in power consumption.Turbine material is 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.
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 booster 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 booster turbine rotor, comprise rotor disk, and the periphery of rotor disk is provided with turbine blade, the upper end of rotor disk flushes with the upper end of turbine blade, and the inside of rotor disk is provided with through hole.
Further improvement as technique scheme:
The sectional shape of described through hole is circular.
The lateral cross section on described through hole top is shaped as Hexagon, and the lateral cross section of through hole bottom is shaped as circle.
The lateral cross section on described through hole top is shaped as Hexagon, and the lateral cross section of through hole bottom is shaped as circle, and the transverse cutting area of through hole bottom increases from top to bottom gradually.
The utility model is taked above technological scheme, have the following advantages: booster 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 object of reach cost-saving, increasing economic efficiency; Due to alleviating of turbine rotor weight, make mass distribution be tending towards reasonable, also be conducive to improve efficiency and the reliability of pressurized machine axle system, rotating speed is faster, alleviated the burden of motor, thereby improved the effect of turbosupercharger, extended the working life of booster turbine rotor, and reduced fuel consumption.
Below in conjunction with drawings and Examples, the utility model is described in further detail.
Accompanying drawing explanation
Accompanying drawing 1 is the structural representation of booster turbine rotor in the utility model embodiment 1;
Accompanying drawing 2 is plan views of accompanying drawing 1;
Accompanying drawing 3 is worm's eye views of accompanying drawing 1;
Accompanying drawing 4 is structural representations of booster turbine rotor in the utility model embodiment 2;
Accompanying drawing 5 is plan views of accompanying drawing 4;
Accompanying drawing 6 is worm's eye views of accompanying drawing 4;
Accompanying drawing 7 is structural representations of booster turbine rotor in the utility model embodiment 3;
Accompanying drawing 8 is plan views of accompanying drawing 7;
Accompanying drawing 9 is worm's eye views of accompanying drawing 7;
In figure,
1-rotor disk, 2-turbine blade, 3-through hole.
Embodiment
Embodiment 1, as shown in accompanying drawing 1, accompanying drawing 2 and accompanying drawing 3, and a kind of booster turbine rotor, comprise rotor disk 1, the periphery of rotor disk 1 is provided with turbine blade 2, and the upper end of rotor disk 1 flushes with the upper end of turbine blade 2, the inside of rotor disk 1 is provided with through hole 3, and the sectional shape of through hole 3 is circular.
Claims (4)
1. a booster turbine rotor, comprise rotor disk (1), the periphery of rotor disk (1) is provided with turbine blade (2), it is characterized in that: the upper end of rotor disk (1) flushes with the upper end of turbine blade (2), and the inside of rotor disk (1) is provided with through hole (3).
2. a kind of booster turbine rotor as claimed in claim 1, is characterized in that: the sectional shape of described through hole (3) is for circular.
3. a kind of booster turbine rotor as claimed in claim 1, is characterized in that: the lateral cross section on described through hole (3) top is shaped as Hexagon, and the lateral cross section of through hole (3) bottom is shaped as circle.
4. a kind of booster turbine rotor as claimed in claim 1, it is characterized in that: the lateral cross section on described through hole (3) top is shaped as Hexagon, the lateral cross section of through hole (3) bottom is shaped as circle, and the transverse cutting area of through hole (3) bottom increases from top to bottom gradually.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320383067.9U CN203499729U (en) | 2013-07-01 | 2013-07-01 | Supercharger turbine rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320383067.9U CN203499729U (en) | 2013-07-01 | 2013-07-01 | Supercharger turbine rotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203499729U true CN203499729U (en) | 2014-03-26 |
Family
ID=50330718
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320383067.9U Expired - Fee Related CN203499729U (en) | 2013-07-01 | 2013-07-01 | Supercharger turbine rotor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203499729U (en) |
Cited By (1)
| 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 |
-
2013
- 2013-07-01 CN CN201320383067.9U patent/CN203499729U/en not_active Expired - Fee Related
Cited By (2)
| 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 |
| 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 |
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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: 20140326 Termination date: 20170701 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |