CN107288741A - A kind of band gets rid of the turbocharger of tank structure - Google Patents
A kind of band gets rid of the turbocharger of tank structure Download PDFInfo
- Publication number
- CN107288741A CN107288741A CN201710489437.XA CN201710489437A CN107288741A CN 107288741 A CN107288741 A CN 107288741A CN 201710489437 A CN201710489437 A CN 201710489437A CN 107288741 A CN107288741 A CN 107288741A
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- CN
- China
- Prior art keywords
- rid
- oil groove
- gets rid
- turbine
- armature spindle
- 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.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
- F02B39/14—Lubrication of pumps; Safety measures therefor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/18—Lubricating arrangements
Abstract
The invention belongs to internal combustion engine turbocharging technical field, and in particular to a kind of band gets rid of the turbocharger of tank structure.Technical scheme is as follows：A kind of band gets rid of the turbocharger of tank structure, including intermediate, armature spindle is provided with intermediate, armature spindle is fixedly connected with turbine wheel, floating bearing is provided between armature spindle and intermediate, turbine wheel, floating bearing, intermediate turbine end separate cavities are formed between armature spindle and intermediate, rotor shaft end and the crossover position that the turbine wheel back side is connected, which are evenly arranged with, a plurality of gets rid of oil groove, the oil groove that gets rid of includes axially getting rid of oil groove and radially gets rid of oil groove, get rid of oil groove and be arranged on rotor shaft end in the axial direction, the radial direction is got rid of oil groove and is arranged in the sealed step at the turbine wheel back side, get rid of oil groove and get rid of that oil groove is mutually corresponding one by one to link together with the radial direction in the axial direction.The present invention can prevent booster floating bearing position from producing high temperature.
Description
Technical field
The invention belongs to internal combustion engine turbocharging technical field, and in particular to a kind of band gets rid of the turbocharging of tank structure
Device.
Background technology
With the higher and higher technical standard of Engine Industry, turbocharging technology has turned into advanced engine and improved now
A kind of key means of power performance and the economy performance, its popularity rate on vehicular engine gradually increases.And vehicle engine
In machine, the turbocharger popularity rate highest of diesel engine；Gasoline engine is limited by detonation and the influence of high-temperature exhaust air, and supercharging is wanted
Ask more harsh, but with the development of in-cylinder direct-jet, new material and new technology for Turbocharger Manufacturing, situation is also being taken on a new look.
Floating bearing is the key components and parts for ensureing turbocharger normal work, and its installation site on booster is such as
Shown in accompanying drawing 1.The major issue that vehicular engine particularly gasoline engine fills booster presence be exactly to floating bearing and
The lubrication of miscellaneous part and the effect of cooling are poor, under special operation condition, and the heat produced in floating bearing in external series gap can not
Taken away in time by lubricating oil, raise the temperature of turbine rotor shaft, cause turbine rotor shaft high temperature deformation, or even failure damage,
So as to jeopardize using and run safely for booster.
In order to prevent floating bearing position from producing high temperature, the major programme generally used has following several：One is except normal
Outside lubrication channel, water-cooling channel is set in addition on intermediate；Two be to set waterway on the turbine shroud of turbine end；Three are
Double-deck turbine shroud is used to reduce radiant heat transfer.It can be found that the solution of the above can bring answering for supercharger structure
Polygamy, can substantially increase the manufacturing cost of booster.
As shown in Figure 2, its be existing booster close to the lubrication operating diagram at the floating bearing position of turbine end, can
To find out, lubricating oil flows to the oil-out of intermediate directly down after being come out from floating bearing, and further not cold
But floating bearing end face is to the top half of the sealed step separate cavities between sealed step, cause the more heat of turbine end from
Neighbouring intermediate is delivered to the position of floating bearing with sealed step separate cavities top half, raises its temperature, is degrading
Cooling effectiveness of the lubricating oil to floating bearing.
The content of the invention
The present invention provides the turbocharger that a kind of band gets rid of tank structure, can prevent booster floating bearing position from producing
High temperature.
Technical scheme is as follows：
A kind of band, which is got rid of, is provided with armature spindle, armature spindle and whirlpool in the turbocharger of tank structure, including intermediate, intermediate
Wheel impeller is fixedly connected, and floating bearing, turbine wheel, floating bearing, armature spindle and centre are provided between armature spindle and intermediate
Intermediate turbine end separate cavities are formed between body, the crossover position that rotor shaft end is connected with the turbine wheel back side is evenly arranged with
A plurality of to get rid of oil groove, the oil groove that gets rid of includes axially getting rid of oil groove and radially gets rid of oil groove, and the axial direction gets rid of oil groove and is arranged on armature spindle
On end, the radial direction is got rid of oil groove and is arranged in the sealed step at the turbine wheel back side, and oil groove and the radial direction are got rid of in the axial direction
Get rid of oil groove one by one mutually correspond to link together.
Described band gets rid of the turbocharger of tank structure, and its preferred scheme is that oil groove is got rid of in three-dimensional spiral in the axial direction
Shape, and rotation direction and booster turbine direction of rotation on the contrary, the angle that the axis of oil groove and armature spindle is constituted is got rid of in the axial direction
For definite value, the axial length that oil groove is got rid of in the axial direction is less than between the end face of floating bearing and turbine wheel sealing backside step
Distance.
Described band gets rid of the turbocharger of tank structure, and its preferred scheme is that the radial direction is got rid of oil groove and dissipated in two dimension
Helix shape, and rotation direction and booster turbine direction of rotation on the contrary, the radial direction get rid of oil groove lead directly to the turbine wheel back side it is close
Seal the edge of step.
Described band gets rid of the turbocharger of tank structure, and its preferred scheme is that the axial direction gets rid of oil groove and radially gets rid of oil
The depth of groove is the 5%-20% of rotor shaft diameter, and width is the 5%-30% of rotor shaft diameter.
The lubricating oil discharged from external series gap in floating bearing, which can be flowed into, axially to be got rid of in oil groove, utilizes the rotation of turbine rotor
The centrifugal force turned, lubricating oil is through axially getting rid of oil groove and radially getting rid of oil groove, and the end for getting rid of oil groove from radial direction is thrown away by centrifugal force, is splashed
Onto the wall of intermediate turbine end separate cavities top half, more heats are taken away, reach that cooling intermediate and protection are floated
The purpose of bearing.
Beneficial effects of the present invention are：The present invention is used after above technical scheme, the discharge from floating bearing external series gap
Lubricating oil enter and get rid of oil groove, using the rotary centrifugal force of turbine rotor, lubricating oil is thrown out of and is splashed to getting rid of oil groove end
The intermediate wall of intermediate turbine end separate cavities top half, takes away the heat that more turbine ends are passed over, and reduction is leaned on
The thermic load at nearly turbine end floating bearing position, so that the thermic load close to turbine end floating bearing position is effectively reduced, so that
Reduce the thermal deformation of turbine rotor, improve its reliability, extend the service life of booster.
Brief description of the drawings
Fig. 1 is schematic view of the mounting position of the floating bearing in turbocharger；
Fig. 2 is the operating diagram of existing structure floating bearing position lubricating oil；
Fig. 3 is the structural representation for the turbocharger that band of the present invention gets rid of tank structure；
Fig. 4 is the axial view for the turbocharger arrangement that band of the present invention gets rid of tank structure；
Fig. 5 is the operating diagram of floating bearing position lubricating oil in the present invention.
Marked in figure：1st, armature spindle, 101, axially get rid of oil groove, 102, radially get rid of oil groove, 103, rotor shaft end, 104, close
Seal step；2nd, turbine wheel, 3, intermediate, 301, intermediate turbine end separate cavities, 4, floating bearing, 5, floating bearing back-up ring.
Embodiment
Below against accompanying drawing, the turbocharger that tank structure is got rid of to a kind of band involved in the present invention makees further detailed
Describe in detail bright.
A kind of band gets rid of the turbocharger of tank structure, including intermediate 3, is arranged on the armature spindle 1 in intermediate 3, with
The turbine wheel 2 that armature spindle 1 is fixedly connected, is arranged on the floating bearing 4 on intermediate 3；The rotor shaft end 103 and turbine
The crossover position of the back side of impeller 2 connection is evenly arranged with six and gets rid of oil groove, and the oil groove that gets rid of includes axially getting rid of oil groove 101 and radial direction
Get rid of oil groove 102；The axial direction is got rid of oil groove 101 and is arranged on rotor shaft end 103, and oil groove 101 is got rid of in three-dimensional spiral in the axial direction
Shape, and rotation direction and booster turbine direction of rotation on the contrary, what the axis that oil groove 101 and armature spindle 1 are got rid of in the axial direction was constituted
Angle is definite value, and end face and turbine wheel 2 sealing backside of the axial length less than floating bearing 4 of oil groove 101 are got rid of in the axial direction
The distance between step 104；The radial direction is got rid of oil groove 102 and is arranged in the sealed step 104 at the back side of turbine wheel 2, the footpath
To get rid of oil groove 102 in two dimension diverging helix shape, and rotation direction and booster turbine direction of rotation on the contrary, the radial direction gets rid of oil
The edge of the feed-through seal step 104 of groove 102；Oil groove 101 is got rid of in the axial direction, and mutually correspondence is connected to one by one with oil groove 102 is radially got rid of
Together；It is the 10% of the diameter of armature spindle 1 that the axial direction, which gets rid of oil groove 101 and radially gets rid of the depth of oil groove 102, and width is rotor
The 15% of the diameter of axle 1.
During work, the lubricating oil discharged from the gap of floating bearing 4, which can be flowed into, axially to be got rid of in oil groove 101, utilizes turbine
The centrifugal force of the rotation of rotor, lubricating oil gets rid of the end of oil groove 102 from radial direction through axially getting rid of oil groove 101 and radially getting rid of oil groove 102
Thrown away by centrifugal force, on the wall for being splashed to the top half of intermediate turbine end separate cavities 301, take away more heats, reach
Cool down the purpose of intermediate 1 and protection floating bearing 4.
Above is the explanation carried out to the present invention, the present invention, which is implemented, is not limited to described above；For this area
Interior related personnel can recognize the improvement or replacement of specific embodiment disclosed herein, be in the spirit and scope of the present invention
Interior.
Claims (4)
1. a kind of band, which is got rid of, is provided with armature spindle, armature spindle and turbine in the turbocharger of tank structure, including intermediate, intermediate
Impeller is fixedly connected, and floating bearing, turbine wheel, floating bearing, armature spindle and intermediate are provided between armature spindle and intermediate
Between formed intermediate turbine end separate cavities, it is characterised in that the crossover position that rotor shaft end is connected with the turbine wheel back side
Be evenly arranged with it is a plurality of get rid of oil groove, the oil groove that gets rid of includes axially getting rid of oil groove and radially gets rid of oil groove, and the axial direction is got rid of oil groove and set
Put on rotor shaft end, the radial direction is got rid of oil groove and is arranged in the sealed step at the turbine wheel back side, oil groove is got rid of in the axial direction
Get rid of that oil groove is mutually corresponding one by one to link together with the radial direction.
2. band according to claim 1 gets rid of the turbocharger of tank structure, it is characterised in that gets rid of oil groove and is in the axial direction
Three-dimensional spiral shape, and rotation direction and booster turbine direction of rotation on the contrary, the axis institute structure of oil groove and armature spindle is got rid of in the axial direction
Into angle be definite value, the axial length that oil groove is got rid of in the axial direction is less than end face and the turbine wheel sealing backside platform of floating bearing
The distance between rank.
3. band according to claim 1 gets rid of the turbocharger of tank structure, it is characterised in that the radial direction gets rid of oil groove and is in
Two dimension diverging helix shape, and the direction of rotation of rotation direction and booster turbine leads directly to turbine leaf on the contrary, the radial direction gets rid of oil groove
Take turns the edge of sealing backside step.
4. band according to claim 1 gets rid of the turbocharger of tank structure, it is characterised in that the axial direction get rid of oil groove and
The depth for radially getting rid of oil groove is the 5%-20% of rotor shaft diameter, and width is the 5%-30% of rotor shaft diameter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710489437.XA CN107288741B (en) | 2017-06-24 | 2017-06-24 | A kind of band gets rid of the turbocharger of tank structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710489437.XA CN107288741B (en) | 2017-06-24 | 2017-06-24 | A kind of band gets rid of the turbocharger of tank structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107288741A true CN107288741A (en) | 2017-10-24 |
| CN107288741B CN107288741B (en) | 2019-03-15 |
Family
ID=60098944
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710489437.XA Active CN107288741B (en) | 2017-06-24 | 2017-06-24 | A kind of band gets rid of the turbocharger of tank structure |
Country Status (1)
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| CN (1) | CN107288741B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107588039A (en) * | 2017-10-26 | 2018-01-16 | 凤城市时代龙增压器制造有限公司 | A kind of sealing structure for generator terminal of being calmed the anger for ball bearing turbine supercharger |
| CN110410154A (en) * | 2019-07-30 | 2019-11-05 | 湖南天雁机械有限责任公司 | A kind of turbocharger thrust structure and its turbocharger |
| CN115853635A (en) * | 2023-03-02 | 2023-03-28 | 江苏毅合捷汽车科技股份有限公司 | Oil leakage prevention turbocharger |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4725206A (en) * | 1984-12-20 | 1988-02-16 | The Garrett Corporation | Thermal isolation system for turbochargers and like machines |
| EP1179655A2 (en) * | 2000-08-08 | 2002-02-13 | Hitachi, Ltd. | Oil slinger for turbocharger |
| CN1379184A (en) * | 2001-03-30 | 2002-11-13 | 奥尔塞特工程有限公司 | Lubricating oil control device |
| JP2013113412A (en) * | 2011-11-30 | 2013-06-10 | Mitsubishi Heavy Ind Ltd | Thrust bearing and rotary machine |
| CN103806960A (en) * | 2012-11-12 | 2014-05-21 | 康明斯有限公司 | Turbomachine bearing assembly preloading arrangement |
| CN204327272U (en) * | 2014-12-09 | 2015-05-13 | 山东合力增压器有限公司 | Exhaust-gas turbocharger |
-
2017
- 2017-06-24 CN CN201710489437.XA patent/CN107288741B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4725206A (en) * | 1984-12-20 | 1988-02-16 | The Garrett Corporation | Thermal isolation system for turbochargers and like machines |
| EP1179655A2 (en) * | 2000-08-08 | 2002-02-13 | Hitachi, Ltd. | Oil slinger for turbocharger |
| CN1379184A (en) * | 2001-03-30 | 2002-11-13 | 奥尔塞特工程有限公司 | Lubricating oil control device |
| JP2013113412A (en) * | 2011-11-30 | 2013-06-10 | Mitsubishi Heavy Ind Ltd | Thrust bearing and rotary machine |
| CN103806960A (en) * | 2012-11-12 | 2014-05-21 | 康明斯有限公司 | Turbomachine bearing assembly preloading arrangement |
| CN204327272U (en) * | 2014-12-09 | 2015-05-13 | 山东合力增压器有限公司 | Exhaust-gas turbocharger |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107588039A (en) * | 2017-10-26 | 2018-01-16 | 凤城市时代龙增压器制造有限公司 | A kind of sealing structure for generator terminal of being calmed the anger for ball bearing turbine supercharger |
| CN107588039B (en) * | 2017-10-26 | 2024-03-05 | 凤城市时代龙增压器制造有限公司 | Sealing structure for compressor end of ball bearing turbocharger |
| CN110410154A (en) * | 2019-07-30 | 2019-11-05 | 湖南天雁机械有限责任公司 | A kind of turbocharger thrust structure and its turbocharger |
| CN115853635A (en) * | 2023-03-02 | 2023-03-28 | 江苏毅合捷汽车科技股份有限公司 | Oil leakage prevention turbocharger |
| CN115853635B (en) * | 2023-03-02 | 2023-05-05 | 江苏毅合捷汽车科技股份有限公司 | Oil leakage prevention turbocharger |
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| Publication number | Publication date |
|---|---|
| CN107288741B (en) | 2019-03-15 |
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