CN203742671U - Turbine rotor of minitype gasoline engine turbocharger - Google Patents
Turbine rotor of minitype gasoline engine turbocharger Download PDFInfo
- Publication number
- CN203742671U CN203742671U CN201320881710.0U CN201320881710U CN203742671U CN 203742671 U CN203742671 U CN 203742671U CN 201320881710 U CN201320881710 U CN 201320881710U CN 203742671 U CN203742671 U CN 203742671U
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- China
- Prior art keywords
- turbine
- rotating shaft
- gasoline engine
- engine turbocharger
- turbine rotor
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- 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.)
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Abstract
The utility model belongs to the field of turbochargers, and particularly relates to a turbine rotor of a minitype gasoline engine turbocharger. The turbine rotor of the minitype gasoline engine turbocharger comprises a turbine and a rotating shaft, turbine blades are arranged in the turbine, a hollow cavity is formed in the connecting part of the turbine and the rotating shaft, a diameter shrinkage section is arranged on the shaft neck of the rotating shaft, the diameter shrinkage section and the inner wall face of a bearing form an oil storage cavity, and oil throwing grooves are formed in the peripheral face of the turbine connecting end of the rotating shaft. The turbine rotor of the minitype gasoline engine turbocharger has the advantages that thermal conductivity is lowered greatly, in a working process, heat transmitted to the floating bearing of a machine core is lowered greatly, the service life of the bearing is prolonged, and the working stability and reliability of the machine core are improved.
Description
Technical field
The utility model belongs to field of turbochargers, specifically a kind of miniature gasoline engine turbocharger turbine rotor.
Background technique
Wheel pressurized machine technology improves density of the induced air by turbosupercharging, can improve the combination properties such as power character, Economy and exhaust index of motor comprehensively, to motor, injects strong impetus, is described as second milestone in internal combustion engine development history.
Turbocharger turbine end and outlet pipe connect, and turbine is connected with compressor impeller by rotating shaft.Compressor can from the air compressing of suction tude to engine cylinder.The waste gas that during engine operation, cylinder is discharged does work to turbine, promotes blade and is rotated, and then drive compressor rotation, to air feed in cylinder.Turbine end working efficiency is higher, and compressor is also more to the air feed of engine cylinder, and the raising of air inflow in engine cylinder can improve the rate of combustion of fuel oil and the turbidity test of exhaust emissions.Therefore, the working efficiency of turbine directly affects the performance of whole pressurized machine.
At present, two aspect development of turbocharging technology forward: the one, to small-power petrol engine future development; The 2nd, to high pressure-charging and super high pressure-charging future development.Turbine rotor is the acting parts of pressurized machine, and the reliability of the height of its efficiency, the quality of performance, work has directly affected the performance of pressurized machine.Along with the development of turbocharging technology to internal-combustion engine of middle low power direction, more and more high to the requirement of the structural design of turbine rotor, function and strength.
Turbine rotor forms by turbine wheel with rotating shaft, and turbine and axle are bound up by friction welding, carry out afterwards fine finishing again.The turbine rotor of common structure, the welded joint place of turbine and rotating shaft is solid.
Summary of the invention
To be that turbine and rotating shaft welded joint are solid cause the shortcoming that heat conductivity is high to problem to be solved in the utility model, proposes a kind of miniature gasoline engine turbocharger turbine rotor.
The utility model provides following technological scheme:
Miniature gasoline engine turbocharger turbine rotor, it comprises turbine and rotating shaft, is provided with turbine blade in turbine, described turbine and rotating shaft joint are provided with the cavity of hollow; The axle journal place of described rotating shaft is provided with undergauge section, and this undergauge section and bearing inner wall face form oil storage chamber; The side face of the turbine connecting end of rotating shaft is provided with and gets rid of oil groove.
Described turbine blade comprises leading edge and trailing edge, and the angle α of leading edge and turbine end face is 51 °, and the angle β of described trailing edge and turbine end face is 10 °.
Described turbine blade is Oblique-flow turbine blade.
Described turbine end face is provided with duplicate removal band.
The utility model has the advantages that heat conductivity reduces greatly, in working procedure, the heat that conducts to movement floating bearing place also reduces greatly, in the working life of having improved bearing, has improved stability and the reliability of movement work.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model;
Fig. 2 is the partial sectional view that turbine is connected with rotating shaft;
Fig. 3 is the structural representation of turbine blade.
Embodiment
As shown in Figure 1, Figure 2, Figure 3 shows, miniature gasoline engine turbocharger turbine rotor, it comprises turbine 1, rotating shaft 2 and turbine blade 5, rotating shaft 2 connects turbine 1 and pinch roller, the outer bearing 4 that is provided with of rotating shaft 2, in turbine 1, be provided with turbine blade 5, the cavity 3 that described turbine 1 and rotating shaft 4 joints are provided with hollow; The axle journal place of described rotating shaft 2 is provided with undergauge section, and this undergauge section and bearing inner wall face form oil storage chamber 6; The side face of the turbine connecting end of rotating shaft 2 is provided with and gets rid of oil groove 7.
On the axle journal of turbine rotor dress floating bearing, open a groove as oil storage chamber 6, groove is of a size of 18.1, φ 4.Adopt the advantage of this structure to be: 1) when turbine rotor and integrated type floating bearing cooperating, can form an oil storage tank in the intermediate portion of axle, be conducive to the lubricated of rotor; 2) rotor shaft has reduced before comparing remodeling with the area of contact of floating bearing, experimental results show that the vibration of pressurized machine of this structure is less; 3) quality due to whole rotor has reduced, and the rotary centrifugal force of its barycenter is compared before remodeling less, is conducive to the VSR dynamic balancing of complete machine.
The seal ring of turbine adopts piston type seal ring, the material of seal ring adopts refractory steel AISI/SAE M2, turbine shaft sealing place adopts the structural design of double flute, the groove of left end is designed to get rid of the form of oil groove, adopts the advantage of this structure to be: 1) piston type seal ring has improved the sealability of whirlpool end and the reliability of sealing; 2) refractory steel adopting has successfully solved the heat resistance problem of turbine end sealing; 3) adopt and get rid of after the structure of oil groove, turbine rotor is when High Rotation Speed, and lubricant oil, under the effect of inertial centrifugal force, can reduce the oil mass that flows to seal ring place in the inclined-plane of 60 ° is thrown to the oil pocket of left end, has improved the sealing of whirlpool end.
Wherein, turbine blade 5 comprises leading edge 5a and trailing edge 5b, and the angle α of leading edge and turbine end face is 51 °, and described trailing edge 5a and the angle β of turbine end face are 10 °, the trailing edge of turbine wheel is designed to the oblique angle of 10 °, and its structure is as shown in figure below C left end.Conventionally the trailing edge of the turbine of structure is straight flange form, in working procedure, when the engine exhaust of high speed and high pressure flows to left end in turbine runner, breaks away from the constraint of turbine blade in air outlet moment, can cause and utter long and high-pitched sounds, and produces larger noise.In the structure of remodeling, its trailing edge is designed to the oblique angle form of 10 °, gas is in left end flow process, first from initial air outlet, free one's minds, then excessively to final air outlet, free one's minds reposefully, air-flow just to some extent buffering ground from pressurized machine, be discharged in outlet pipe, thereby reduce, utter long and high-pitched sounds, less noise.
Wherein, turbine blade is Oblique-flow turbine blade, by the suction port blade design of turbine wheel, it is diagonal flow type, because blade import is tilted, make air flow energy adapt to well the variation of blade profile and gently transit to axially, and can effectively prevent that impeller outer outlet external diameter from increasing the wheel rim place flow shedding phenomenon of bringing, and is greatly improved the inside fluency of impeller, compare with the radial turbine in same wheel footpath, negotiability increases greatly.In addition, adopt the design of multiple-blade and slim blade, improve as much as possible the efficiency of turbine.The turbine of this patent adopts 12 blades, and blade is the thinnest locates to be controlled at 0.5mm left and right.
Wherein, turbine end face is provided with duplicate removal band 8, has avoided the card strength decreased and the beauty defects that when turbine polishing duplicate removal, cause.
Claims (4)
1. miniature gasoline engine turbocharger turbine rotor, it comprises turbine and rotating shaft, is provided with turbine blade in turbine, it is characterized in that: described turbine and rotating shaft joint are provided with the cavity of hollow; The axle journal place of described rotating shaft is provided with undergauge section, and this undergauge section and bearing inner wall face form oil storage chamber; The side face of the turbine connecting end of rotating shaft is provided with and gets rid of oil groove.
2. miniature gasoline engine turbocharger turbine rotor according to claim 1, it is characterized in that: described turbine blade comprises leading edge and trailing edge, the angle α of leading edge and turbine end face is 51 °, and the angle β of described trailing edge and turbine end face is 10 °.
3. miniature gasoline engine turbocharger turbine rotor according to claim 1 and 2, is characterized in that: described turbine blade is Oblique-flow turbine blade.
4. miniature gasoline engine turbocharger turbine rotor according to claim 1 and 2, is characterized in that: described turbine end face is provided with duplicate removal band.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320881710.0U CN203742671U (en) | 2013-12-30 | 2013-12-30 | Turbine rotor of minitype gasoline engine turbocharger |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320881710.0U CN203742671U (en) | 2013-12-30 | 2013-12-30 | Turbine rotor of minitype gasoline engine turbocharger |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203742671U true CN203742671U (en) | 2014-07-30 |
Family
ID=51342487
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320881710.0U Withdrawn - After Issue CN203742671U (en) | 2013-12-30 | 2013-12-30 | Turbine rotor of minitype gasoline engine turbocharger |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203742671U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103925010A (en) * | 2013-12-30 | 2014-07-16 | 常州环能涡轮动力股份有限公司 | Turbine rotor of turbocharger of small gasoline engine |
-
2013
- 2013-12-30 CN CN201320881710.0U patent/CN203742671U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103925010A (en) * | 2013-12-30 | 2014-07-16 | 常州环能涡轮动力股份有限公司 | Turbine rotor of turbocharger of small gasoline engine |
| CN103925010B (en) * | 2013-12-30 | 2015-09-30 | 常州环能涡轮动力股份有限公司 | Miniature gasoline engine turbocharger turbine rotor |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20140730 Effective date of abandoning: 20150930 |
|
| RGAV | Abandon patent right to avoid regrant |