CN218522723U - Turbocharger of gas dynamic pressure foil bearing - Google Patents
Turbocharger of gas dynamic pressure foil bearing Download PDFInfo
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- CN218522723U CN218522723U CN202221475263.4U CN202221475263U CN218522723U CN 218522723 U CN218522723 U CN 218522723U CN 202221475263 U CN202221475263 U CN 202221475263U CN 218522723 U CN218522723 U CN 218522723U
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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
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Abstract
The utility model provides a turbo charger of gaseous dynamic pressure foil bearing, relate to booster technical field, shell and whirlpool end middle shell in the middle of the pressure end including mutual butt joint, it is provided with the rotor shaft to run through between shell and the whirlpool end middle shell in the middle of the pressure end, the cover is equipped with whole bearing disc on the rotor shaft, the cover is equipped with whirlpool end thrust disc and the gaseous dynamic pressure foil journal bearing of whirlpool end that set up side by side on the part that whole bearing disc is in the shell in the middle of the whirlpool end, offset between the relative tip of whirlpool end thrust disc and the gaseous dynamic pressure foil journal bearing of whirlpool end, still the cover is equipped with the whirlpool end bearing frame jointly on whirlpool end thrust disc and the gaseous dynamic pressure foil journal bearing of whirlpool end. The utility model solves the problem that the turbocharger in the traditional technology adopts the oil-lubricated sliding bearing, but the structure has lower mechanical efficiency when the turbocharger is at low speed; conventional turbochargers also employ a ball bearing arrangement which solves the problem of low mechanical efficiency, but at high cost and with a lower service life than conventional oil lubricated sliding bearings.
Description
Technical Field
The utility model relates to a booster technical field, concretely relates to turbo charger of gaseous dynamic pressure foil bearing.
Background
The exhaust gas turbocharger has the advantages of improving the power of an engine, reducing fuel consumption, reducing emission and the like, and is widely applied to diesel engines at present. With the advance of the policy of "carbon peak reaching", the requirement on the thermal efficiency of the engine is higher and higher, and the improvement of the efficiency of the turbocharger is very obvious on the improvement of the thermal efficiency of the engine.
The prior device gradually exposes the defects of the technology along with the use, and mainly shows the following aspects:
first, conventional turbochargers use oil-lubricated sliding bearings, but this configuration is mechanically inefficient at low supercharger speeds.
Second, conventional turbochargers also employ a ball bearing arrangement that solves the problem of mechanical inefficiency, but at a higher cost and with a shorter useful life than conventional oil-lubricated sliding bearings.
In view of the above, the prior art is obviously inconvenient and disadvantageous in practical use, and needs to be improved.
SUMMERY OF THE UTILITY MODEL
Aiming at the defects in the prior art, the utility model solves the problem that the turbocharger in the traditional technology adopts the oil-lubricated sliding bearing, but the mechanical efficiency is lower when the turbocharger is at low speed; conventional turbochargers also employ a ball bearing arrangement which solves the problem of mechanical inefficiency, but at a higher cost and with a shorter useful life than conventional oil lubricated sliding bearings.
In order to solve the above problem, the utility model provides a following technical scheme:
a turbocharger of a gas dynamic pressure foil bearing comprises a pressure end middle shell and a vortex end middle shell which are mutually butted, a rotor shaft penetrates through the pressure end middle shell and the vortex end middle shell, an integral bearing disc is sleeved on the rotor shaft, a vortex end thrust disc and a vortex end gas dynamic pressure foil radial bearing which are arranged in parallel are sleeved on the portion, located in the vortex end middle shell, of the integral bearing disc, the vortex end thrust disc and the opposite end portion of the vortex end gas dynamic pressure foil radial bearing are abutted, and a vortex end bearing block is further sleeved on the end thrust disc and the vortex end gas dynamic pressure foil radial bearing together.
As an optimized scheme, a pressure end thrust disc and a pressure end pneumatic dynamic pressure foil radial bearing which are arranged in parallel are sleeved on a part, located in the pressure end middle shell, of the integral bearing disc, the pressure end thrust disc is abutted against the opposite end part of the pressure end pneumatic dynamic pressure foil radial bearing, and a limiting ring section for wrapping the pressure end pneumatic dynamic pressure foil radial bearing is arranged in the pressure end middle shell.
As an optimized scheme, a plurality of matched vortex end pin grooves are circumferentially arranged among the vortex end thrust disc, the vortex end gas dynamic pressure foil radial bearing and the vortex end bearing seat, and a vortex end positioning pin is inserted in each vortex end pin groove.
As an optimized scheme, a plurality of matched pressure end pin grooves are circumferentially arranged among the pressure end thrust disc, the pressure end gas dynamic pressure foil radial bearing and the limiting ring section, and pressure end positioning pins are inserted in the pressure end pin grooves.
As an optimized scheme, a protruding section is arranged on the outer wall of the integral bearing disc, a vortex end thrust bearing and a pressure end thrust bearing are respectively sleeved on two sides of the protruding section, the vortex end thrust bearing abuts against the end face of the vortex end thrust disc, and the pressure end thrust bearing abuts against the pressure end thrust disc.
As an optimized scheme, a pin hole is formed between opposite end parts of the pressure end thrust disc and the vortex end thrust disc along the circumferential direction, and a positioning pin is inserted into the pin hole.
As an optimized scheme, the inner hole of the vortex end bearing seat is in interference fit with the outer ring of the vortex end aerodynamic foil radial bearing.
As an optimized scheme, the inner hole of the limiting ring section is in interference fit with the outer ring of the pressure end gas dynamic pressure foil radial bearing.
As an optimized scheme, the pressure end intermediate shell is connected with the vortex end intermediate shell through a bolt assembly.
Preferably, the inner hole of the integral bearing disc is in interference fit with the shaft neck of the rotor shaft.
Compared with the prior art, the beneficial effects of the utility model are that:
the gas dynamic pressure foil radial bearing has the characteristics of high operating speed, high mechanical efficiency and high reliability, can be used for a supercharger to solve the problems of high efficiency and long service life, and simultaneously has no oil lubrication and oil leakage fault;
the vortex end thrust disc, the vortex end gas dynamic pressure foil radial bearing and the vortex end bearing seat are circumferentially positioned through the vortex end pin groove and the vortex end positioning pin;
the three parts of the pressure end thrust disc, the pressure end gas dynamic pressure foil radial bearing and the limiting ring section are circumferentially positioned through the pressure end pin groove and the pressure end positioning pin;
the pressure end middle shell and the vortex end middle shell axially compress and fix the internal parts through the bolt assembly.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the prior art descriptions will be briefly described below. Throughout the drawings, like elements or portions are generally identified by like reference numerals. In the drawings, elements or portions are not necessarily drawn to scale.
Fig. 1 is a schematic structural diagram of the present invention.
In the figure: 1. pressing the end intermediate shell; 2. a scroll end intermediate shell; 3. a rotor shaft; 4. an integral bearing disc; 5. a vortex end thrust disc; 6. a vortex end aerodynamic foil radial bearing; 7. a scroll end bearing block; 8. pressing end gas dynamic pressure foil radial bearing; 9. a pressure end thrust disc; 10. a limiting ring section; 11. a vortex end locating pin; 12. pressing end positioning pins; 13. positioning pins; 14. a pressure end thrust bearing; 15. a vortex end thrust bearing; 16. a convex section; 17. a bolt assembly; 18. a vortex end seal ring; 19. and (7) shaft sealing.
Detailed Description
Embodiments of the present invention will be described in detail with reference to the accompanying drawings. The following examples are only used to illustrate the technical solutions of the present invention more clearly, and therefore are only used as examples, and the protection scope of the present invention is not limited thereby.
As shown in fig. 1, the turbocharger of the aerodynamic foil bearing includes a pressing end intermediate housing 1 and a vortex end intermediate housing 2 which are butted with each other, a rotor shaft 3 is arranged between the pressing end intermediate housing 1 and the vortex end intermediate housing 2 in a penetrating manner, an integral bearing disc 4 is sleeved on the rotor shaft 3, a vortex end thrust disc 5 and a vortex end aerodynamic foil radial bearing 6 which are arranged in parallel are sleeved on a portion of the integral bearing disc 4 in the vortex end intermediate housing 2, the vortex end thrust disc 5 and the opposite end portion of the vortex end aerodynamic foil radial bearing 6 are abutted against each other, and a vortex end bearing seat 7 is further sleeved on the end thrust disc and the vortex end aerodynamic foil radial bearing 6 together.
The integral bearing disk 4 is sleeved with a pressure end thrust disk 9 and a pressure end pneumatic dynamic pressure foil radial bearing 8 which are arranged in parallel on the part in the pressure end middle shell 1, the opposite end parts of the pressure end thrust disk 9 and the pressure end pneumatic dynamic pressure foil radial bearing 8 are abutted, and a limiting ring section 10 for wrapping the pressure end pneumatic dynamic pressure foil radial bearing 8 is arranged in the pressure end middle shell 1.
A plurality of matched vortex end pin grooves are circumferentially arranged among the vortex end thrust disc 5, the vortex end aerodynamic foil radial bearing 6 and the vortex end bearing seat 7 in an enclosing manner, and a vortex end positioning pin 11 is inserted in each vortex end pin groove.
A plurality of matched pressure end pin grooves are circumferentially arranged among the pressure end thrust disc 9, the pressure end gas dynamic pressure foil radial bearing 8 and the limiting ring section 10, and pressure end positioning pins 12 are inserted in the pressure end pin grooves.
The outer wall of the integral bearing disc 4 is provided with a convex section 16, two sides of the convex section 16 are respectively sleeved with a vortex end thrust bearing 15 and a pressure end thrust bearing 14, the vortex end thrust bearing 15 abuts against the end face of the vortex end thrust disc 5, and the pressure end thrust bearing 14 abuts against the pressure end thrust disc 9.
A pin hole is arranged between the opposite end parts of the pressure end thrust disc 9 and the vortex end thrust disc 5 along the circumferential direction, and a positioning pin 13 is inserted in the pin hole.
The inner hole of the vortex end bearing seat 7 is in interference fit with the outer ring of the vortex end aerodynamic foil radial bearing 6.
And an inner hole of the limiting ring section 10 is in interference fit with an outer ring of the pressure end pneumatic dynamic pressure foil radial bearing 8.
The pressure end intermediate shell 1 and the vortex end intermediate shell 2 are connected through a bolt assembly 17.
The inner bore of the integral bearing disk 4 is in interference fit with the shaft journal of the rotor shaft 3.
The vortex end sealing ring 18 and the turbine rotor sealing ring groove form a vortex end sealing structure, and three vortex end sealing rings 18 are adopted for sealing in order to organize high-temperature waste gas to enter a bearing system;
the inner bore of the shaft seal 19 is fitted with the rotor shaft 3, one end face of which presses against the integral bearing disk 4 and the other end face of which is in close proximity to the impeller.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the embodiments of the present invention, and they should be construed as being included in the scope of the claims and description of the present invention.
Claims (10)
1. A turbocharger for a gas dynamic foil bearing, comprising: the vortex end gas dynamic pressure foil radial bearing comprises a pressure end middle shell (1) and a vortex end middle shell (2) which are mutually butted, a rotor shaft (3) penetrates through the pressure end middle shell (1) and the vortex end middle shell (2), an integral bearing disc (4) is sleeved on the rotor shaft (3), a vortex end thrust disc (5) and a vortex end gas dynamic pressure foil radial bearing (6) which are arranged in parallel are sleeved on the part, located in the vortex end middle shell (2), of the integral bearing disc (4), the vortex end thrust disc (5) and the opposite end part of the vortex end gas dynamic pressure foil radial bearing (6) are abutted, and a vortex end bearing seat (7) is further sleeved on the vortex end thrust disc and the vortex end gas dynamic pressure foil radial bearing (6) together.
2. A turbocharger of a aerodynamic foil bearing according to claim 1, wherein: the integral bearing disc (4) is sleeved with a pressure end thrust disc (9) and a pressure end gas dynamic pressure foil radial bearing (8) which are arranged in parallel, the pressure end thrust disc (9) is abutted against the opposite end part of the pressure end gas dynamic pressure foil radial bearing (8), and a limiting ring section (10) wrapping the pressure end gas dynamic pressure foil radial bearing (8) is arranged in the pressure end intermediate housing (1).
3. A turbocharger of a aerodynamic foil bearing according to claim 2, wherein: the vortex end thrust disc (5), the vortex end gas dynamic pressure foil radial bearing (6) and the vortex end bearing seat (7) are circumferentially provided with a plurality of matched vortex end pin grooves, and vortex end positioning pins (11) are inserted in the vortex end pin grooves.
4. A turbocharger of a aerodynamic foil bearing according to claim 2, wherein: a plurality of matched pressure end pin grooves are circumferentially arranged among the pressure end thrust disc (9), the pressure end gas dynamic pressure foil radial bearing (8) and the limiting ring section (10), and pressure end positioning pins (12) are inserted in the pressure end pin grooves.
5. A turbocharger of a aerodynamic foil bearing according to claim 3, wherein: the outer wall of the integral bearing disc (4) is provided with a protruding section (16), two sides of the protruding section (16) are respectively sleeved with a vortex end thrust bearing (15) and a pressure end thrust bearing (14), the vortex end thrust bearing (15) is abutted to the end face of the vortex end thrust disc (5), and the pressure end thrust bearing (14) is abutted to the pressure end thrust disc (9).
6. A turbocharger of a aerodynamic foil bearing according to claim 2, wherein: a pin hole is formed between the opposite end parts of the pressure end thrust disc (9) and the vortex end thrust disc (5) along the circumferential direction, and a positioning pin (13) is inserted in the pin hole.
7. A turbocharger of a aerodynamic foil bearing according to claim 1, wherein: and an inner hole of the vortex end bearing seat (7) is in interference fit with an outer ring of the vortex end aerodynamic foil radial bearing (6).
8. A turbocharger of a aerodynamic foil bearing according to claim 2, wherein: and the inner hole of the limiting ring section (10) is in interference fit with the outer ring of the pressure end gas dynamic pressure foil radial bearing (8).
9. A turbocharger of a aerodynamic foil bearing according to claim 1, wherein: the pressure end middle shell (1) is connected with the vortex end middle shell (2) through a bolt component (17).
10. A turbocharger of a aerodynamic foil bearing according to claim 1, wherein: and the inner hole of the integral bearing disc (4) is in interference fit with the shaft neck of the rotor shaft (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221475263.4U CN218522723U (en) | 2022-06-13 | 2022-06-13 | Turbocharger of gas dynamic pressure foil bearing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221475263.4U CN218522723U (en) | 2022-06-13 | 2022-06-13 | Turbocharger of gas dynamic pressure foil bearing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218522723U true CN218522723U (en) | 2023-02-24 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221475263.4U Active CN218522723U (en) | 2022-06-13 | 2022-06-13 | Turbocharger of gas dynamic pressure foil bearing |
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| CN (1) | CN218522723U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
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2022
- 2022-06-13 CN CN202221475263.4U patent/CN218522723U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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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