CN107288741B - 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
- CN107288741B CN107288741B CN201710489437.XA CN201710489437A CN107288741B CN 107288741 B CN107288741 B CN 107288741B CN 201710489437 A CN201710489437 A CN 201710489437A CN 107288741 B CN107288741 B CN 107288741B
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- Prior art keywords
- oil groove
- rid
- gets rid
- turbine wheel
- turbine
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- 238000007667 floating Methods 0.000 claims abstract description 32
- 238000007789 sealing Methods 0.000 claims description 4
- 230000004323 axial length Effects 0.000 claims description 3
- 238000002485 combustion reaction Methods 0.000 abstract description 2
- 239000003921 oil Substances 0.000 description 43
- 239000010687 lubricating oil Substances 0.000 description 11
- 238000001816 cooling Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 238000005461 lubrication Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000000593 degrading effect Effects 0.000 description 1
- 238000005474 detonation Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000010181 polygamy Effects 0.000 description 1
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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Supercharger (AREA)
Abstract
The invention belongs to internal combustion engine turbocharging technical fields, 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 equipped in intermediate, armature spindle is fixedly connected with turbine wheel, floating bearing is equipped between armature spindle and intermediate, turbine wheel, floating bearing, intermediate turbine end separate cavities are formed between armature spindle and intermediate, the crossover position that rotor shaft end is connect with the turbine wheel back side, which is evenly arranged with, a plurality of gets rid of oil groove, the oil groove that gets rid of includes that axial oil groove and the radial direction of getting rid of gets rid of oil groove, the axial direction is got rid of oil groove and is arranged 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, the axial direction, which gets rid of oil groove and with the radial direction gets rid of oil groove and correspond to each other one by one, to link together.The present invention can prevent booster floating bearing position from generating high temperature.
Description
Technical field
The invention belongs to internal combustion engine turbocharging technical fields, and in particular to a kind of band gets rid of the turbocharging of tank structure
Device.
Background technique
With the higher and higher technical standard of Engine Industry, turbocharging technology has become advanced engine now and improves
A kind of key means of power performance and the economy performance, the popularity rate on vehicular engine gradually increase.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, wants to pressurization
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 guaranteeing turbocharger and working normally, and the installation site on booster is such as
Shown in attached drawing 1.A major issue existing for the filled booster of vehicular engine especially gasoline engine be exactly to floating bearing and
The lubrication of other component and the effect of cooling are poor, and under special operation condition, the heat generated in external series gap in floating bearing cannot
It is taken away in time by lubricating oil, increases the temperature of turbine rotor shaft, lead to turbine rotor shaft high temperature deformation or even failure damage,
To jeopardize the use and operational safety of booster.
Floating bearing position generates high temperature in order to prevent, the major programme generallyd use there are several types of: first is that except normal
Outside lubrication channel, in addition water-cooling channel is set on intermediate；Second is that waterway is arranged on the turbine shroud of turbine end；Third is that
Use the double-deck turbine shroud to reduce radiant heat transfer.It can be found that above solution can bring answering for supercharger structure
Polygamy can obviously increase the manufacturing cost of booster.
It as shown in Fig. 2, is existing booster close to the lubrication operation schematic diagram at the floating bearing position of turbine end, it can
To find out, lubricating oil flows to the oil outlet of intermediate directly down after coming out from floating bearing, and there is no further cold
But floating bearing end face to the sealed step separate cavities between sealed step top half, the heat for causing turbine end more from
Neighbouring intermediate is transmitted to the position of floating bearing with sealed step separate cavities top half, increases its temperature, is degrading
Cooling efficiency of the lubricating oil to floating bearing.
Summary 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 generating
High temperature.
Technical scheme is as follows:
A kind of band gets rid of the turbocharger of tank structure, including intermediate, is equipped with armature spindle, armature spindle and whirlpool in intermediate
Wheel impeller is fixedly connected, and floating bearing, turbine wheel, floating bearing, armature spindle and centre are equipped between armature spindle and intermediate
Intermediate turbine end separate cavities are formed between body, the crossover position that rotor shaft end is connect 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 that axial oil groove and the radial direction of getting rid of gets rid of oil groove, and the axial direction is got rid of oil groove and is arranged in 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 the axial direction gets rid of oil groove and the radial direction
It gets rid of oil groove and corresponds to each other one by one and link together.
The band gets rid of the turbocharger of tank structure, and preferred embodiment is that the axial direction gets rid of oil groove in three-dimensional spiral
Shape, and the direction of rotation of rotation direction and booster turbine is on the contrary, the axial direction gets rid of the angle that the axis of oil groove and armature spindle is constituted
For definite value, the axial length that the axial direction gets rid of oil groove is less than between the end face and turbine wheel sealing backside step of floating bearing
Distance.
The band gets rid of the turbocharger of tank structure, and preferred embodiment is that the radial direction gets rid of oil groove in two dimension diverging
Helix shape, and the direction of rotation of rotation direction and booster turbine 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.
The band gets rid of the turbocharger of tank structure, and preferred embodiment is that the axial direction gets rid of oil groove and radial direction gets rid of oil
The depth of slot is the 5%-20% of rotor shaft diameter, and width is the 5%-30% of rotor shaft diameter.
It can flow into from the lubricating oil being discharged in external series gap in floating bearing and axially get rid of in oil groove, utilize the rotation of turbine rotor
The centrifugal force turned, lubricating oil get rid of oil groove through axial oil groove and the radial direction of getting rid of, are thrown away, splash by centrifugal force from the radial end for getting rid of oil groove
Onto the wall surface of intermediate turbine end separate cavities top half, more heats are taken away, reaches cooling intermediate and protection is floated
The purpose of bearing.
The invention has the benefit that the discharge after the invention adopts the above technical scheme, 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 surface of intermediate turbine end separate cavities top half, takes away the heat that more turbine ends pass 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, thus
The thermal deformation for reducing turbine rotor, improves its reliability, extends the service life of booster.
Detailed description of the invention
Fig. 1 is schematic view of the mounting position of the floating bearing in turbocharger；
Fig. 2 is the operation schematic diagram of existing structure floating bearing position lubricating oil；
Fig. 3 is the structural schematic diagram 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 operation schematic diagram of floating bearing position lubricating oil in the present invention.
Marked in the figure: 1, armature spindle, 101, it is axial get rid of oil groove, 102, it is radial get rid of oil groove, 103, rotor shaft end, 104, close
Seal step；2, turbine wheel, 3, intermediate, 301, intermediate turbine end separate cavities, 4, floating bearing, 5, floating bearing retaining ring.
Specific embodiment
It is further detailed to a kind of turbocharger work that band gets rid of tank structure according to the present invention below against attached drawing
It describes in detail bright.
A kind of band gets rid of the turbocharger of tank structure, including intermediate 3, and the armature spindle 1 in intermediate 3 is arranged in, with
The floating bearing 4 on intermediate 3 is arranged in the turbine wheel 2 that armature spindle 1 is fixedly connected；The rotor shaft end 103 and turbine
The crossover position of 2 back side of impeller connection is uniformly arranged there are six oil groove is got rid of, 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 the axial direction gets rid of oil groove 101 in three-dimensional spiral
Shape, and the direction of rotation of rotation direction and booster turbine is on the contrary, what the axis that the axial direction gets rid of oil groove 101 and armature spindle 1 was constituted
Angle is definite value, and the axial length that the axial direction gets rid of oil groove 101 is less than end face and 2 sealing backside of turbine wheel of floating bearing 4
The distance between step 104；The radial direction is got rid of oil groove 102 and is arranged in the sealed step 104 at 2 back side of turbine wheel, the diameter
Helix shape is dissipated in two dimension to oil groove 102 is got rid of, and the direction of rotation of rotation direction and booster turbine is on the contrary, the radial direction gets rid of oil
The edge of 102 feed-through seal step 104 of slot；The axial direction get rid of oil groove 101 and it is radial get rid of oil groove 102 and correspond to each other one by one be connected to
Together；It is the 10% of 1 diameter of armature spindle that the axial direction, which gets rid of oil groove 101 and gets rid of the depth of oil groove 102 with radial direction, and width is rotor
The 15% of 1 diameter of axis.
When work, the lubricating oil being discharged from 4 gap of floating bearing, which can flow 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 oil groove 102 through axial oil groove 101 and the radial direction of getting rid of, from the radial end for getting rid of oil groove 102
It is thrown away by centrifugal force, is splashed on the wall surface of 301 top half of intermediate turbine end separate cavities, takes away more heats, reach
The purpose of cooling intermediate 1 and protection floating bearing 4.
It is the explanation carried out to the present invention above, present invention specific implementation is not limited to above description；For this field
Interior related personnel can identify 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 gets rid of the turbocharger of tank structure, including intermediate, armature spindle, armature spindle and turbine are equipped in intermediate
Impeller is fixedly connected, and floating bearing, turbine wheel, floating bearing, armature spindle and intermediate are equipped between armature spindle and intermediate
Between formed intermediate turbine end separate cavities, which is characterized in that the crossover position that rotor shaft end is connect with the turbine wheel back side
Be evenly arranged with it is a plurality of get rid of oil groove, it is described get rid of oil groove include it is axial get rid of oil groove and it is radial get rid of oil groove, the axial direction is got rid of oil groove and is set
It sets 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, and the axial direction gets rid of oil groove
Oil groove is got rid of with the radial direction correspond to each other one by one link together；The axial direction gets rid of oil groove in three-dimensional spiral shape, and the axial direction is got rid of
The angle that the axis of oil groove and armature spindle is constituted is definite value, and the axial length that the axial direction gets rid of oil groove is less than the end of floating bearing
The distance between face and turbine wheel sealing backside step；The radial direction gets rid of oil groove in two dimension diverging helix shape, the diameter
To the edge for getting rid of the straight-through turbine wheel sealing backside step of oil groove.
2. the turbocharger that band according to claim 1 gets rid of tank structure, which is characterized in that the axial direction gets rid of oil groove
Helix rotation direction is to extend axially towards turbine wheel, and the axial direction gets rid of the helix rotation direction and the rotation of booster turbine of oil groove
Turn contrary.
3. the turbocharger that band according to claim 1 gets rid of tank structure, which is characterized in that the radial direction gets rid of oil groove
Helix rotation direction is the outer extension radially toward turbine wheel, and the radial direction gets rid of helix rotation direction and the booster whirlpool of oil groove
The direction of rotation of wheel is opposite.
4. the turbocharger that band according to claim 1 gets rid of tank structure, which is characterized 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 CN107288741A (en) | 2017-10-24 |
| CN107288741B true 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)
| Country | Link |
|---|---|
| CN (1) | CN107288741B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 | Thrust structure of turbocharger and turbocharger thereof |
| CN111306185B (en) * | 2019-12-17 | 2025-03-04 | 中船(重庆)装备技术有限公司 | A semi-floating radial bearing structure for an axial-flow 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 |
Family Cites Families (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 |
| JP3607584B2 (en) * | 2000-08-08 | 2005-01-05 | 株式会社日立製作所 | Exhaust turbine supercharger and supercharging system for internal combustion engine |
| GB0108119D0 (en) * | 2001-03-30 | 2001-05-23 | Holset Engineering Co | Oil control device |
| JP5863422B2 (en) * | 2011-11-30 | 2016-02-16 | 三菱重工業株式会社 | Thrust bearing and rotating machine |
| GB201220300D0 (en) * | 2012-11-12 | 2012-12-26 | Cummins Ltd | 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 |
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2017
- 2017-06-24 CN CN201710489437.XA patent/CN107288741B/en active Active
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| Publication number | Publication date |
|---|---|
| CN107288741A (en) | 2017-10-24 |
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