CN206338326U - Turbocharger - Google Patents
Turbocharger Download PDFInfo
- Publication number
- CN206338326U CN206338326U CN201621323683.5U CN201621323683U CN206338326U CN 206338326 U CN206338326 U CN 206338326U CN 201621323683 U CN201621323683 U CN 201621323683U CN 206338326 U CN206338326 U CN 206338326U
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- China
- Prior art keywords
- thrust bearing
- turbocharger
- flow controller
- axial flow
- rotating shaft
- 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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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Abstract
The utility model discloses a kind of turbocharger, the rotating shaft being connected including turbine case, the turbine being arranged in turbine case, with turbine, the radial-thrust bearing and axial thrust bearing and the impeller and impeller housing that are connected to the rotating shaft other end that are sleeved in rotating shaft, the radial-thrust bearing use air hydrodynamic paillon foil radial-thrust bearing；The axial thrust bearing uses static air pressure axial thrust bearing.The utility model supports turbocharger rotor system, the advantages of realizing non lubricant oil, efficiency high, high rotating speed by the combining structure of static air pressure axial thrust bearing and air hydrodynamic paillon foil radial-thrust bearing；Static air pressure axial thrust bearing can bear very big axial load；Static air pressure axial thrust bearing formation high pressure air film can isolate the gas of two kinds of different mediums of turbine end and impeller end；Meanwhile, air hydrodynamic paillon foil radial-thrust bearing is adapted to not need cooling device inside hot environment, turbocharger.
Description
Technical field
The utility model is related to a kind of turbocharger, it is especially a kind of using air hydrodynamic paillon foil radial-thrust bearing and
The turbocharger of static air pressure axial thrust bearing.
Background technology
Turbo-charger bearing generally uses rolling bearing and sliding bearing, and the characteristic of both bearings is in turbocharger
Application in there is problems with：Due to the presence of lubricating oil, inevitably there is oil leakage phenomenon, so as to result in pollution
Problem；Due to the presence of frictional force so that the working speed of rotor can not possibly be too high and less efficient；Cause due to there is abrasion
Bearing life is shorter.In some applied environments, turbine end is two kinds of different gas mediums with impeller end in turbocharger,
It is required that two kinds of gas mediums can not be revealed mutually, it is necessary to increase sealing system.Turbocharger operation is in hot environment, particularly
, it is necessary to increase cooling system when there is the larger temperature difference in turbine end and impeller end.
In existing technology, the support of turbocharger rotor system must include radial support bearing and axial direction
Thrust bearing, if wherein the design speed of rotor-support-foundation system reaches energy in 40000RPM (rev/min), the turbocharger of use
Enough meeting the bearing arrangement of this working speed, to be mainly aerostatic bearing, aero dynamic bearing and hydrodynamic journal liquid polymers (general
Logical mechanical bearing can not meet the demand of this working speed)；Hydrodynamic journal liquid polymers are difficult to solve sealing problem, easily to two ends
Gas medium pollute.There is the problem of bearing capacity is inadequate in the axial thrust bearing of aero dynamic bearing, wherein in turbine
End and impeller end are respectively 10MPa and 3MPa gases at high pressure, due to there is very big pressure differential, therefore rotor-support-foundation system is present
Very big axial force；Aero dynamic bearing is difficult to meet to require as axial thrust bearing.It is proposed to this end that thrust bearing is used
Aerostatic bearing and journal bearing use the technical scheme that aero dynamic bearing is combined.In addition, gas-static axial thrust axle
Hold to form high pressure air film, two kinds of different gas mediums of turbine end and impeller end can be isolated.
Utility model content
A purpose of the present utility model is to solve at least the above and/or defect, and offer at least will be described later
Advantage.Existing roll is replaced the utility model proposes the combination of a kind of aerostatic bearing and air hydrodynamic foil bearing
The technical scheme of bearing and sliding bearing.
In order to realize according to these purposes of the present utility model and further advantage there is provided a kind of turbocharger, including
Turbine case, the turbine being arranged in turbine case, the rotating shaft being connected with turbine, the radial-thrust bearing being sleeved in rotating shaft and axial direction
Thrust bearing and the impeller and impeller housing for being connected to the rotating shaft other end, it is characterised in that the radial-thrust bearing is using empty
Pneumatic pressure paillon foil radial-thrust bearing；The axial thrust bearing uses static air pressure axial thrust bearing.
Preferably, the air hydrodynamic paillon foil radial-thrust bearing includes：
At least one groove is provided with certain intervals and equably on matrix, its inner surface；
At least one the elastic flat paillon foil being sleeved in the rotating shaft, its one end is fixedly connected in groove；
It is clamped at least one elastic wave paillon foil between described matrix and elastic flat paillon foil, its one end is fixedly connected on recessed
In groove.
Preferably, it is provided with annular receiving groove in described matrix；Described matrix is provided with the top of annular receiving groove
First annular gas flow, the second annular gas runner is provided with bottom；The static air pressure axial thrust bearing includes：
Thrust bearing rotating disk, it is placed in the annular receiving groove and is sleeved in the rotating shaft；
The axial axis bearing in the rotating shaft is sleeved on, it is placed in the impeller and is provided with the second annular gas runner
Between matrix；
And, it is provided with the matrix and connects the upper static pressure air inlet of the first annular gas flow and connect institute
State the lower static pressure air inlet of the second annular gas runner；It is provided with the first annular gas flow towards the thrust bearing
The upper axial flow controller of rotating disk；The lower axially section towards the thrust bearing rotating disk is provided with the second annular gas runner
Flow device；
Wherein, by upper static pressure air inlet be passed through gases at high pressure make upper axial flow controller and rotating shaft and thrust bearing rotating disk it
Between the high pressure air film that is formed respectively；Being passed through gases at high pressure by lower static pressure air inlet makes lower axial flow controller and rotating shaft and thrust axis
Forward the high pressure air film formed respectively between disk.
Preferably, the elastic flat paillon foil and elastic wave paillon foil in groove be fixedly connected mode for gluing connection,
One kind in welding and jam connection.
Preferably, the upper axial flow controller and lower axial flow controller are orifice restriction device, slit throttling device and many
One kind in the matter flow controller of hole.
Preferably, annular is provided with the upper axial flow controller of an at least row on the first annular gas flow；Described
Annular is provided with an at least row axial flow controller on second ring gas flow.
Preferably, the upper axial flow controller is along the equally distributed multiple upper axially throttlings of first annular gas flow
Device, its spacing is in 20~30mm；The lower axial flow controller is along the equally distributed multiple lower axial directions of first annular gas flow
Flow controller, its spacing is in 20~30mm.
Preferably, the distance between the puff prot of the upper axial flow controller and thrust bearing rotating disk scope are 10~20
Micron；The distance between the puff prot and thrust bearing rotating disk of lower axial flow controller scope is 10~20 microns.
Preferably, the upper axial flow controller include connected with first annular gas flow first on throttle orifice and with
Throttle orifice on throttle orifice is connected on first second, on described first throttle orifice with diameter greater than second on throttle orifice diameter；
The lower axial flow controller includes connecting with first time throttle orifice of the second annular gas flow passage and with first time throttle orifice
Second time throttle orifice, the diameter with diameter greater than second time throttle orifice of first time throttle orifice.
Preferably, the inner surface of throttle orifice and first time restriction is all evenly arranged with multiple ventilations on described first
Groove.
The utility model at least includes following beneficial effect：Pass through static air pressure axial thrust bearing and air hydrodynamic paillon foil
The combining structure support turbocharger rotor system of radial-thrust bearing, realizes non lubricant oil, efficiency high, rotating speed height etc. excellent
Point；Static air pressure axial thrust bearing can bear very big axial load；Static air pressure axial thrust bearing formation high pressure gas
Film can isolate the gas of two kinds of different mediums of turbine end and impeller end；Meanwhile, air hydrodynamic paillon foil radial-thrust bearing can be with
Adapt to not need cooling device inside hot environment, turbocharger.
Further advantage of the present utility model, target and feature embody part by following explanation, and part will also pass through
Research of the present utility model and practice are understood by the person skilled in the art.
Brief description of the drawings：
Fig. 1 is the overall cross-sectional view of turbocharger described in the utility model；
Fig. 2 is the structural representation of air hydrodynamic paillon foil radial-thrust bearing described in the utility model；
Fig. 3 illustrates for part (static air pressure axial thrust bearing) cross-section structure of turbocharger described in the utility model
Figure；
Fig. 4 is the planar structure of the one side of upper axial flow controller in static air pressure axial thrust bearing described in the utility model
Schematic diagram；
Fig. 5 be Fig. 4 in A-A to planar structure schematic diagram；
Fig. 6 is the planar junction of the another side of upper axial flow controller in static air pressure axial thrust bearing described in the utility model
Structure schematic diagram；
Fig. 7 is the planar structure schematic diagram of B-B direction in Fig. 6；
Fig. 8 is that the part (static air pressure axial thrust bearing) of turbocharger in the utility model another embodiment is cutd open
Face structural representation.
Embodiment：
The utility model is described in further detail below in conjunction with the accompanying drawings, to make those skilled in the art with reference to explanation
Book word can be implemented according to this.
It should be appreciated that such as " having ", "comprising" and " comprising " term used herein do not allot one or many
The presence or addition of individual other elements or its combination.
Fig. 1~3 show a kind of turbocharger of the present utility model, including turbine case 7, are arranged in turbine case 7
Turbine 8, the rotating shaft 10 being connected with turbine 8, the radial-thrust bearing 3 and axial thrust bearing, Yi Jilian being sleeved in rotating shaft 10
The impeller 11 and impeller housing 1 of the other end of rotating shaft 10 are connected on, the radial-thrust bearing 3 uses air hydrodynamic paillon foil radial thrust axle
Hold；The axial thrust bearing uses static air pressure axial thrust bearing.
In the above-mentioned technical solutions, static air pressure axial thrust bearing and air hydrodynamic paillon foil radial-thrust bearing are passed through
Combining structure supports turbocharger rotor system, the advantages of realizing non lubricant oil, efficiency high, high rotating speed；Static air pressure axle
Axial thrust bearing can bear very big axial load；Static air pressure axial thrust bearing formation high pressure air film can isolate turbine
End and the gas of two kinds of different mediums of impeller end.
In the above-mentioned technical solutions, as shown in figure 3, the air hydrodynamic paillon foil radial-thrust bearing includes：Matrix 2, its
At least one groove 23 is provided with certain intervals and equably on inner surface；It is sleeved at least one bullet in the rotating shaft 10
Mild-natured paillon foil 22, its one end is fixedly connected in groove 23；It is clamped at least one between described matrix 2 and elastic flat paillon foil 22
Individual elastic wave paillon foil 21, its one end is fixedly connected in groove 23；In this technical scheme, the rotating shaft 10 adds by accurate
Work, forms high pressure air film supporting radial load between the flat paillon foil 22 of top layer elasticity when rotating at a high speed.
In the above-mentioned technical solutions, it is provided with annular receiving groove 24 in described matrix 2；Described matrix 2 is in annular receiving groove
24 top is provided with first annular gas flow 25, the second annular gas runner 26 is provided with bottom；The static air pressure
Axial thrust bearing includes：
Thrust bearing rotating disk 5, it is placed in the annular receiving groove 24 and is sleeved in the rotating shaft 10；
The axial axis bearing 6 in the rotating shaft 10 is sleeved on, it is placed in the impeller 11 and is provided with the second annular gas
Between the matrix 2 of runner 26, for supporting lower axial flow controller etc. about the installation of structural member；
And, the upper He of static pressure air inlet 901 for connecting the first annular gas flow 25 is provided with described matrix 2
Connect the lower static pressure air inlet 902 of the second annular gas runner 26；Court is provided with the first annular gas flow 25
To the upper axial flow controller 401 of the thrust bearing rotating disk 5；It is provided with and is pushed away described on the second annular gas runner 26
The lower axial flow controller of power bearing rotating disk 5；
Wherein, gases at high pressure are passed through by static pressure air inlet 9 on matrix, gases at high pressure make into upper static pressure air inlet 901
The high pressure air film (31,32) formed respectively between upper axial flow controller 401 and rotating shaft 10 and thrust bearing rotating disk 5；It is quiet under
Being pressed into gas port 902 and being passed through gases at high pressure makes to be formed respectively between lower axial flow controller 402 and rotating shaft 10 and thrust bearing rotating disk 5
High pressure air film (34,33)；These high pressure air films can separate two kinds of different gas mediums of turbine end and impeller end；Axially save
Stream device (401,402) changes the supply gas pressure of feeding pneumatic, it is possible to achieve bigger axial carrying capacity.
In the above-mentioned technical solutions, the elastic flat paillon foil 22 is fixedly connected mode with elastic wave paillon foil 21 in groove
One kind in being connected for gluing connection, welding and jam, can be by elastic flat paillon foil 22 and elastic wave using this connected mode
Paillon foil 21 is stably fixed in neck form air hydrodynamic paillon foil radial-thrust bearing.
In the above-mentioned technical solutions, the upper axial flow controller 401 and lower axial flow controller 402 be orifice restriction device,
One kind in slit throttling device and porous restriction device, can more preferably be realized to supply feeding pneumatic using this flow controller and pressed
The change of power, further makes static air pressure axial thrust bearing realize bigger axial carrying capacity.
In the above-mentioned technical solutions, as also shown in e.g. figs. 4-7, annular is provided with least on the first annular gas flow 25
The upper axial flow controller 401 of one row；Annular is provided with an at least row axial flow controller on the second annular gas runner 26
402；Using this technical scheme, flow controller is more preferably realized the change to feeding pneumatic supply gas pressure, make axial section
The high pressure air film formed between stream device and rotating shaft and thrust bearing rotating disk is more uniform, further makes static air pressure axial thrust axle
Hold and realize bigger axial carrying capacity.
In the above-mentioned technical solutions, the upper axial flow controller 401 is equally distributed many along first annular gas flow
Individual axial flow controller, its spacing is in 20~30mm；The lower axial flow controller 402 is uniformly to divide along first annular gas flow
Multiple lower axial flow controllers of cloth, its spacing is in 20~30mm；Using this technical scheme, make axial flow controller and rotating shaft and push away
The high pressure air film formed between power bearing rotating disk is more uniform and stable, can more preferably realize and feeding pneumatic supply gas pressure is changed
Become, static air pressure axial thrust bearing is realized bigger axial carrying capacity.
In the above-mentioned technical solutions, between the puff prot and thrust bearing rotating disk 5 of the upper axial flow controller 401 away from
It it is 10~20 microns from scope；The distance between the puff prot of the lower axial flow controller 402 and thrust bearing rotating disk 5 scope is
10~20 microns；Using this technical scheme, make the high pressure gas formed between axial flow controller and rotating shaft and thrust bearing rotating disk
Film is more uniform and stable, and static air pressure axial thrust bearing can be made to realize bigger axial carrying capacity.
In another embodiment, as shown in figure 8, the upper axial flow controller 401 includes and first annular gas flow
On the first of connection 25 throttle orifice 403 and connect with throttle orifice on first 403 second on throttle orifice 404, section on described first
Discharge orifice 403 with diameter greater than second on throttle orifice 404 diameter；The lower axial flow controller 402 includes and the second annular gas
First time throttle orifice 405 of the connection of runner 26 and the second time throttle orifice 406 connected with first time throttle orifice 405, described first
The diameter of with diameter greater than second time throttle orifice 406 of lower throttle orifice 405.Using this technical scheme so that pass through first throttle
Pressure-air after the throttling of hole throttle again through the second throttle orifice, makes the flow velocity of pressure-air faster, and restriction effect is more preferable,
The high pressure air film of formation is more uniform and stable.
In the above-mentioned technical solutions, the inner surface of throttle orifice 403 and first time restriction 405 is all uniformly set on described first
Multiple air channel (not shown) are equipped with, the flow velocity of gas can be made faster using the structure of air channel, restriction effect more preferably, is formed
High pressure air film it is more uniform and stable.
Although embodiment of the present utility model is disclosed as above, it is not restricted in specification and embodiment
Listed to use, it can be applied to various suitable fields of the present utility model completely, for those skilled in the art,
Other modification is easily achieved, therefore under the universal limited without departing substantially from claim and equivalency range, this reality
Specific details is not limited to new and shown here as the legend with description.
Claims (10)
1. a kind of turbocharger, including turbine case, be arranged in turbine case turbine, be connected with turbine rotating shaft, be sleeved on
Radial-thrust bearing and axial thrust bearing in rotating shaft and the impeller and impeller housing for being connected to the rotating shaft other end, its feature
It is that the radial-thrust bearing uses air hydrodynamic paillon foil radial-thrust bearing；The axial thrust bearing is quiet using air
Last item axial thrust bearing.
2. turbocharger as claimed in claim 1, it is characterised in that the air hydrodynamic paillon foil radial-thrust bearing bag
Include：
At least one groove is provided with certain intervals and equably on matrix, its inner surface；
At least one the elastic flat paillon foil being sleeved in the rotating shaft, its one end is fixedly connected in groove；
It is clamped at least one elastic wave paillon foil between described matrix and elastic flat paillon foil, its one end is fixedly connected on groove
It is interior.
3. turbocharger as claimed in claim 2, it is characterised in that annular receiving groove is provided with described matrix；It is described
Matrix is provided with first annular gas flow on the top of annular receiving groove, the second annular gas runner is provided with bottom；Institute
Stating static air pressure axial thrust bearing includes：
Thrust bearing rotating disk, it is placed in the annular receiving groove and is sleeved in the rotating shaft；
The axial axis bearing in the rotating shaft is sleeved on, it is placed in the impeller and is provided with the matrix of the second annular gas runner
Between；
And, it is provided with the matrix and connects the upper static pressure air inlet of the first annular gas flow and connect described
The lower static pressure air inlet of second ring gas flow；It is provided with the first annular gas flow towards the thrust bearing rotating disk
Upper axial flow controller；The lower axially throttling towards the thrust bearing rotating disk is provided with the second annular gas runner
Device；
Wherein, being passed through gases at high pressure by upper static pressure air inlet makes to divide between upper axial flow controller and rotating shaft and thrust bearing rotating disk
The high pressure air film not formed；Being passed through gases at high pressure by lower static pressure air inlet makes lower axial flow controller be forwarded with rotating shaft and thrust axis
The high pressure air film formed respectively between disk.
4. turbocharger as claimed in claim 2, it is characterised in that the elastic flat paillon foil and elastic wave paillon foil are in groove
The interior mode that is fixedly connected is one kind in gluing connection, welding and jam connection.
5. turbocharger as claimed in claim 3, it is characterised in that the upper axial flow controller and lower axial flow controller are equal
For one kind in orifice restriction device, slit throttling device and porous restriction device.
6. turbocharger as claimed in claim 3, it is characterised in that annular is provided with the first annular gas flow
The upper axial flow controller of an at least row；Annular is provided with an at least row axial flow controller on the second annular gas runner.
7. turbocharger as claimed in claim 3, it is characterised in that the upper axial flow controller is along first annular gas
Multiple axial flow controllers of uniform flow passage distribution, its spacing is in 20~30mm；The lower axial flow controller is along first annular
The equally distributed multiple lower axial flow controllers of gas flow, its spacing is in 20~30mm.
8. turbocharger as claimed in claim 3, it is characterised in that the puff prot and thrust axis of the upper axial flow controller
The distance between disk scope is forwarded for 10~20 microns；Between the puff prot and thrust bearing rotating disk of the lower axial flow controller
Distance range is 10~20 microns.
9. turbocharger as claimed in claim 3, it is characterised in that the upper axial flow controller includes and first annular gas
On the first of body flow passage throttle orifice and connected with throttle orifice on first second on throttle orifice, throttle orifice on described first
The diameter of throttle orifice on diameter greater than second；The lower axial flow controller include with the first of the second annular gas flow passage
Throttle orifice and the second time throttle orifice connected with first time throttle orifice, with diameter greater than second time throttling of first time throttle orifice
The diameter in hole.
10. turbocharger as claimed in claim 9, it is characterised in that throttle orifice and first time restriction on described first
Inner surface be all evenly arranged with multiple air channels.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621323683.5U CN206338326U (en) | 2016-12-05 | 2016-12-05 | Turbocharger |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621323683.5U CN206338326U (en) | 2016-12-05 | 2016-12-05 | Turbocharger |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206338326U true CN206338326U (en) | 2017-07-18 |
Family
ID=59308657
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621323683.5U Active CN206338326U (en) | 2016-12-05 | 2016-12-05 | Turbocharger |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206338326U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106369056A (en) * | 2016-12-05 | 2017-02-01 | 中国工程物理研究院机械制造工艺研究所 | Turbocharger |
| CN110345160A (en) * | 2018-04-04 | 2019-10-18 | 通用电气公司 | Machine thrust bearing assembly |
| CN112196908A (en) * | 2020-10-13 | 2021-01-08 | 珠海格力电器股份有限公司 | Heat radiation structure of dynamic pressure bearing, dynamic pressure thrust bearing and air compressor |
| CN115030809A (en) * | 2022-06-13 | 2022-09-09 | 康跃科技(山东)有限公司 | Turbocharger of gas dynamic pressure foil bearing |
-
2016
- 2016-12-05 CN CN201621323683.5U patent/CN206338326U/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106369056A (en) * | 2016-12-05 | 2017-02-01 | 中国工程物理研究院机械制造工艺研究所 | Turbocharger |
| CN110345160A (en) * | 2018-04-04 | 2019-10-18 | 通用电气公司 | Machine thrust bearing assembly |
| CN110345160B (en) * | 2018-04-04 | 2021-05-04 | 通用电气公司 | Machine thrust bearing assembly |
| CN112196908A (en) * | 2020-10-13 | 2021-01-08 | 珠海格力电器股份有限公司 | Heat radiation structure of dynamic pressure bearing, dynamic pressure thrust bearing and air compressor |
| CN112196908B (en) * | 2020-10-13 | 2021-09-14 | 珠海格力电器股份有限公司 | Heat radiation structure of dynamic pressure bearing, dynamic pressure thrust bearing and air compressor |
| CN115030809A (en) * | 2022-06-13 | 2022-09-09 | 康跃科技(山东)有限公司 | Turbocharger of gas dynamic pressure foil bearing |
| CN115030809B (en) * | 2022-06-13 | 2024-01-26 | 康跃科技(山东)有限公司 | Turbocharger with pneumatic dynamic pressure foil bearing |
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