CN108561222B - Turbocharger with electronic quick-start split structure - Google Patents
Turbocharger with electronic quick-start split structure Download PDFInfo
- Publication number
- CN108561222B CN108561222B CN201810298545.3A CN201810298545A CN108561222B CN 108561222 B CN108561222 B CN 108561222B CN 201810298545 A CN201810298545 A CN 201810298545A CN 108561222 B CN108561222 B CN 108561222B
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- Prior art keywords
- shell
- main shaft
- middle shell
- motor
- turbine
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- 238000007789 sealing Methods 0.000 claims abstract description 44
- 238000002347 injection Methods 0.000 claims description 8
- 239000007924 injection Substances 0.000 claims description 8
- 230000004323 axial length Effects 0.000 claims description 2
- 230000001360 synchronised effect Effects 0.000 abstract description 4
- 239000000446 fuel Substances 0.000 description 6
- 239000007789 gas Substances 0.000 description 5
- 238000000034 method Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 1
Classifications
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- 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
- F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
- F02B37/04—Engines with exhaust drive and other drive of pumps, e.g. with exhaust-driven pump and mechanically-driven second pump
-
- 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
- F02B39/02—Drives of pumps; Varying pump drive gear ratio
- F02B39/08—Non-mechanical drives, e.g. fluid drives having variable gear ratio
- F02B39/10—Non-mechanical drives, e.g. fluid drives having variable gear ratio electric
-
- 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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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
Abstract
The invention belongs to the technical field of turbochargers, and relates to a turbocharger with a split structure capable of being started quickly by electrons, which comprises a turbine main shaft and a motor arranged on the turbine main shaft, wherein a first middle shell is arranged on the shaft diameter of one side of the turbine main shaft, extending out of the motor, of the turbine main shaft, a first bearing is arranged between the first middle shell and the turbine main shaft, a second middle shell is arranged on the shaft diameter of the other side of the turbine main shaft, extending out of the motor, of the turbine main shaft, and a second bearing is arranged between the second middle shell and the turbine main shaft; the left end cover of the motor is sealed with the first middle shell, and the right end cover of the motor is sealed with the second middle shell through a multi-step structure; the outer end face of the first middle shell is connected with the diffuser in a sealing manner, the outer end face of the diffuser is connected with the compressor shell in a sealing manner, and one end of the main shaft of the turbine penetrates through the first middle shell and the diffuser and stretches into the shaft diameter in the compressor shell to be provided with the compressor impeller. The turbocharger effectively solves the problem that the natural air suction mode of the turbocharger is adopted, and the pressurized pressure air entering the engine is synchronous with the starting of the engine.
Description
Technical Field
The invention belongs to the technical field of turbochargers, and relates to a turbocharger with a split structure capable of being started quickly by an electronic device.
Background
Turbochargers are actually air compressors that increase the amount of intake air by compressing the air. The turbine drives a coaxial impeller by utilizing the inertial impulse of exhaust gas discharged by the engine, and the impeller presses and sends air sent by an air filter pipeline to be pressurized into a cylinder. When the rotation speed of the engine is increased, the exhaust gas discharge speed and the rotation speed of the turbine are synchronously increased, more air is compressed by the impeller to enter the cylinder, more fuel can be combusted by increasing the pressure and the density of the air, and the output power of the engine can be increased by correspondingly increasing the fuel quantity and adjusting the rotation speed of the engine. The prior turbocharged engine adopts a natural air suction mode at the initial starting stage, so that the air-fuel ratio problem exists at the initial starting stage of the supercharged engine.
Disclosure of Invention
The invention aims at the problems and provides the turbocharger with the electronic quick-start split structure, which effectively solves the problem that the turbocharger naturally inhales, and the pressurized air entering the engine is synchronous with the engine start.
According to the technical scheme of the invention: the utility model provides a turbo charger of electron quick start components of a whole that can function independently structure which characterized in that: the device comprises a turbine main shaft and a motor arranged on the turbine main shaft, wherein a first middle shell is arranged on the shaft diameter of one side of the turbine main shaft, extending out of the motor, a first bearing is arranged between the first middle shell and the turbine main shaft, a second middle shell is arranged on the shaft diameter of the other side, extending out of the motor, of the turbine main shaft, and a second bearing is arranged between the second middle shell and the turbine main shaft; the left end cover of the motor is sealed with the first middle shell, and the right end cover of the motor is sealed with the second middle shell through a multi-step structure; the outer end face of the first middle shell is connected with the diffuser in a sealing manner, the outer end face of the diffuser is connected with the compressor shell in a sealing manner, one end of the main shaft of the turbine penetrates through the first middle shell and the shaft diameter of the diffuser, which extends into the compressor shell, is provided with a compressor impeller, a shaft seal and a distance thrust sleeve are arranged between the compressor impeller and the first bearing, a thrust bearing is arranged on the distance thrust sleeve, and an inner hole of the diffuser is sleeved on the shaft seal; the other end of the turbine main shaft penetrates through the second middle shell and stretches into the shaft diameter in the turbine shell to install a turbine.
As a further improvement of the invention, the diffuser is sealed with the compressor shell through a first rubber sealing ring, the diffuser is sealed with the first middle shell through a second rubber sealing ring, and an air compressor sealing ring is arranged between the inner hole of the diffuser and the shaft seal.
As a further improvement of the invention, the motor comprises a motor shell, a stator core is fixedly arranged on the inner wall of the motor shell, a rotor is arranged on the turbine main shaft corresponding to the inner ring of the stator core, a first photoelectric switch and a second photoelectric switch are respectively arranged on two end faces of the rotor, a motor shell fixing frame is arranged on the motor shell, the motor shell fixing frame is fixedly connected with a left end cover and a right end cover through a first connecting screw and a second connecting screw, a motor cover plate is arranged between the right end cover and the motor shell fixing frame, and a first sealing piece is arranged between an inner hole of the motor cover plate and the turbine main shaft.
As a further improvement of the invention, a first sealing ring seat is arranged in a cavity formed between the first middle shell and the left end cover, a first sealing ring is arranged between the first sealing ring seat and the turbine main shaft, and a second sealing piece is arranged between the stepped hole of the left end cover and the turbine main shaft.
As a further improvement of the invention, a second sealing ring seat is arranged in a cavity formed between the second middle shell and the right end cover, and a second sealing ring is arranged between the second sealing ring seat and the turbine main shaft.
As a further improvement of the invention, the first middle shell and the left end cover and the second middle shell and the right end cover are respectively fastened and connected through nuts, locating pins and screws.
As a further improvement of the invention, the two ends of the second bearing in the axial direction are limited by the first clamp spring and the second clamp spring respectively, and the circumference direction of the second bearing is limited by the first locating pin.
As a further improvement of the invention, the right end cover, the second sealing ring seat and the second middle shell are connected through a second locating pin, and a turbine end sealing ring is arranged between the second middle shell and the turbine.
As a further improvement of the present invention, a VTG assembly is disposed within the turbine housing corresponding to the turbine outer ring.
The invention has the technical effects that: the engine starting device is reasonable and ingenious in structure, and in the working process, the engine starting initial stage does not adopt a natural air suction mode any more, and the supercharging pressure air entering the engine is synchronous with the engine starting, so that the problem of air-fuel ratio supercharging in the traditional supercharging engine starting initial stage is thoroughly solved.
Drawings
Fig. 1 is a schematic structural view of the present invention.
Detailed Description
The following describes the embodiments of the present invention further with reference to the drawings.
In fig. 1, the compressor comprises a lock nut 1, a compressor wheel 2, a diffuser 3, a compressor housing 4, a first rubber seal ring 5, a first intermediate housing 6, a first seal ring 7, a first seal ring seat 8, a left end cover 9, a first connecting screw 10, a motor housing 11, a first photoelectric switch 12, a motor cover 13, a rotor 14, a second photoelectric switch 15, a stator core 16, a second seal ring seat 17, a second seal ring 18, a first clamp spring 19, a second clamp spring 20, a second intermediate housing 21, a VTG (variable geometry turbine blade) assembly 22, a turbine main shaft 23, a turbine housing 24, a turbine 25, a turbine end seal ring 26, a second bearing 27, a first positioning pin 28, a second positioning pin 29, a right end cover 30, a first seal 31, a second connecting screw 32, a second seal 33, a nut 34, a positioning pin 35, a screw 36, a compressor seal ring 37, a first bearing 38, a bearing 39, a second rubber seal ring 40, a shaft seal sleeve 41, 42, and the like.
As shown in fig. 1, the invention relates to a turbocharger with a split structure for electronic quick starting, which comprises a turbine main shaft 23 and a motor arranged on the turbine main shaft 23, wherein a first middle shell 6 is arranged on the shaft diameter of one side of the turbine main shaft 23 extending out of the motor, a first bearing 38 is arranged between the first middle shell 6 and the turbine main shaft 23, a second middle shell 21 is arranged on the shaft diameter of the other side of the turbine main shaft 23 extending out of the motor, and a second bearing 27 is arranged between the second middle shell 21 and the turbine main shaft 23; the left end cover 9 of the motor is sealed with the first middle shell 6 and the right end cover 30 of the motor is sealed with the second middle shell 21 through a multi-step structure; the outer end face of the first intermediate shell 6 is in sealing connection with the diffuser 3, the outer end face of the diffuser 3 is in sealing connection with the compressor shell 4, one end of the turbine main shaft 23 penetrates through the first intermediate shell 6, the shaft diameter of the diffuser 3 extending into the compressor shell 4 is provided with the compressor impeller 2, a shaft seal 42 and a distance thrust sleeve 41 are arranged between the compressor impeller 2 and the first bearing 38, a thrust bearing 39 is arranged on the distance thrust sleeve 41, and an inner hole of the diffuser 3 is sleeved on the shaft seal 42; the turbine 25 is mounted on the shaft diameter of the other end of the turbine main shaft 23 which penetrates through the second intermediate shell 21 and extends into the turbine shell 24. The oil filling hole provided in the housing of the first bearing 38 communicates with the oil filling passage of the first intermediate housing 6.
The diffuser 3 is sealed with the compressor shell 4 through a first rubber sealing ring 5, the diffuser 3 is sealed with the first middle shell 6 through a second rubber sealing ring 40, and an air compressor sealing ring 37 is arranged between an inner hole of the diffuser 3 and a shaft seal 42.
The motor includes motor housing 11, motor housing 11 inner wall fixed stator core 16 that sets up, rotor 14 is installed to the inner circle that corresponds stator core 16 on the turbine main shaft 23, and first photoelectric switch 12, second photoelectric switch 15 are installed respectively to rotor 14 both ends face, installs motor housing mount 37 on the motor housing 11, and motor housing mount 37 passes through first connecting screw 10, second connecting screw 32 and left end cover 9, right-hand member lid 30 fastening connection, is provided with motor cover plate 13 between right-hand member lid 30 and the motor housing mount 37, set up first sealing member 31 between motor cover plate 13 hole and the turbine main shaft 23.
A first sealing ring seat 8 is arranged in a cavity formed between the first middle shell 6 and the left end cover 9, a first sealing ring 7 is arranged between the first sealing ring seat 8 and the turbine main shaft 23, and a second sealing piece 33 is arranged between a stepped hole of the left end cover 9 and the turbine main shaft 23. The multi-step structure between the first middle shell 6 and the left end cover 9 comprises counter bore cavities which are respectively arranged at the center of the first middle shell 6 and the center of the left end cover 9, the two counter bore cavities are combined to form a cavity for placing the first sealing ring seat 8, the multi-step structure further comprises a ring cavity arranged on the first middle shell 6 and a ring-shaped bulge arranged on the left end cover 9, and the ring-shaped bulge is matched in the ring cavity.
A second seal ring seat 17 is arranged in a cavity formed between the second intermediate shell 21 and the right end cover 30, and a second seal ring 18 is arranged between the second seal ring seat 17 and the turbine main shaft 23. The multi-step structure between the second middle shell 21 and the right end cover 30 comprises a countersunk cavity respectively arranged at the center of the second middle shell 21 and the center of the right end cover 30, the two countersunk cavities are combined to form a cavity for placing the second sealing ring seat 17, and the multi-step structure also comprises an annular cavity arranged on the second middle shell 21 and an annular bulge arranged on the right end cover 30, and the annular bulge is matched in the annular cavity.
The first middle shell 6 and the left end cover 9 and the second middle shell 21 and the right end cover 30 are respectively fastened and connected through nuts 34, locating pins 35 and screws 36.
The axial two ends of the second bearing 27 are limited by the first clamp spring 19 and the second clamp spring 20 respectively, and the circumferential direction of the second bearing 27 is limited by the first locating pin 28. The axial length of the second bearing 27 is greater than that of the first bearing 38, radial protrusions extending towards the center of the hole are arranged at two ends of the inner hole of the shell of the second bearing 27, oil injection holes are formed in the shell of the second bearing 27, corresponding to the radial protrusions, oil injection channels formed in the second middle shell 21 are communicated with the two oil injection holes, the oil injection holes are communicated with the inner hole of the second bearing 27, and a positioning groove used for arranging the first positioning pin 28 is formed in the surface of the shell of the second bearing 27.
The right end cover 30, the second seal ring seat 17 and the second intermediate shell 21 are connected through a second positioning pin 29, and a turbine end seal ring 26 is arranged between the second intermediate shell 21 and the turbine 25.
The VTG assembly 22 is disposed within the turbine housing 24 corresponding to an outer ring of the turbine 25.
The working process of the invention is as follows: the conventional starting mode of the turbocharger is that after the engine is started, the energy discharged by the exhaust gas of the engine pushes the turbine 25 of the turbocharger (hot end), and the turbine 25 and the compressor impeller 2 are synchronously rotated (at the same rotation speed) because the turbine main shaft 23 and the compressor impeller 2 (at the cold end) are arranged on the same shaft. The turbine main shaft 23 gradually increases with the increase of the engine exhaust gas discharge amount, and the turbine main shaft 23 also gradually increases in speed.
When the engine is started cold or at low speed, the engine works in a natural air suction state, namely, the air entering the engine is the same as the atmospheric pressure in the area, so that the initial air-fuel ratio work management of the engine is not facilitated, the particulate matters and harmful gases in the exhaust of the engine exhaust cannot meet the integral requirements, and the energy cannot be effectively saved.
The invention solves the problem that the initial stage of the supercharged engine is not in a natural air suction mode any more, and the supercharged pressure air entering the engine is synchronous with the starting and starting, thereby thoroughly solving the problem of air-fuel ratio supercharging in the initial stage of the traditional supercharged engine.
Claims (6)
1. The utility model provides a turbo charger of electron quick start components of a whole that can function independently structure which characterized in that: the device comprises a turbine main shaft (23) and a motor arranged on the turbine main shaft (23), wherein a first middle shell (6) is arranged on the shaft diameter of one side of the turbine main shaft (23) extending out of the motor, a first bearing (38) is arranged between the first middle shell (6) and the turbine main shaft (23), a second middle shell (21) is arranged on the shaft diameter of the other side of the turbine main shaft (23) extending out of the motor, and a second bearing (27) is arranged between the second middle shell (21) and the turbine main shaft (23); the left end cover (9) of the motor and the first middle shell (6) and the right end cover (30) of the motor and the second middle shell (21) are respectively sealed through a multi-step structure; the outer end face of the first middle shell (6) is connected with the diffuser (3) in a sealing manner, the outer end face of the diffuser (3) is connected with the compressor shell (4) in a sealing manner, one end of the turbine main shaft (23) penetrates through the first middle shell (6), the diffuser (3) stretches into the shaft diameter in the compressor shell (4) to be provided with the compressor impeller (2), a shaft seal (42) and a distance thrust sleeve (41) are arranged between the compressor impeller (2) and the first bearing (38), a thrust bearing (39) is arranged on the distance thrust sleeve (41), and an inner hole of the diffuser (3) is sleeved on the shaft seal (42); the other end of the turbine main shaft (23) penetrates through the second middle shell (21) and stretches into the shaft diameter in the turbine shell (24) to install a turbine (25);
The motor comprises a motor shell (11), a stator core (16) is fixedly arranged on the inner wall of the motor shell (11), a rotor (14) is arranged on an inner ring of a turbine main shaft (23) corresponding to the stator core (16), a first photoelectric switch (12) and a second photoelectric switch (15) are respectively arranged on two end faces of the rotor (14), a motor shell fixing frame is arranged on the motor shell (11), the motor shell fixing frame is fixedly connected with a left end cover (9) and a right end cover (30) through a first connecting screw (10) and a second connecting screw (32), a motor cover plate (13) is arranged between the right end cover (30) and the motor shell fixing frame, and a first sealing piece (31) is arranged between an inner hole of the motor cover plate (13) and the turbine main shaft (23);
The axial length of the second bearing (27) is greater than that of the first bearing (38), radial protrusions extending towards the center of the hole are arranged at two ends of the inner hole of the shell of the second bearing (27), oil injection holes are formed in the positions, corresponding to the radial protrusions, of the shell of the second bearing (27), oil injection channels formed in the second middle shell (21) are communicated with the two oil injection holes, the oil injection holes are communicated with the inner hole of the second bearing (27), and positioning grooves used for arranging the first positioning pins (28) are formed in the surface of the shell of the second bearing (27);
A first sealing ring seat (8) is arranged in a cavity formed between the first middle shell (6) and the left end cover (9), a first sealing ring (7) is arranged between the first sealing ring seat (8) and the turbine main shaft (23), and a second sealing piece (33) is arranged between a stepped hole of the left end cover (9) and the turbine main shaft (23);
a second sealing ring seat (17) is arranged in a cavity formed between the second middle shell (21) and the right end cover (30), and a second sealing ring (18) is arranged between the second sealing ring seat (17) and the turbine main shaft (23).
2. The turbocharger with electronic quick start split structure as set forth in claim 1, wherein: the diffuser (3) is sealed with the compressor shell (4) through a first rubber sealing ring (5), the diffuser (3) is sealed with the first middle shell (6) through a second rubber sealing ring (40), and an air compressor sealing ring (37) is arranged between an inner hole of the diffuser (3) and the shaft seal (42).
3. The turbocharger with electronic quick start split structure as set forth in claim 1, wherein: the first middle shell (6) is fixedly connected with the left end cover (9) and the second middle shell (21) is fixedly connected with the right end cover (30) through nuts (34), locating pins (35) and screws (36) respectively.
4. The turbocharger with electronic quick start split structure as set forth in claim 1, wherein: the two axial ends of the second bearing (27) are limited by the first clamp spring (19) and the second clamp spring (20) respectively, and the circumferential direction of the second bearing (27) is limited by the first locating pin (28).
5. The turbocharger with electronic quick start split structure as set forth in claim 1, wherein: the right end cover (30), the second sealing ring seat (17) and the second middle shell (21) are connected through a second locating pin (29), and a turbine end sealing ring (26) is arranged between the second middle shell (21) and the turbine (25).
6. The turbocharger with electronic quick start split structure as set forth in claim 1, wherein: a VTG assembly (22) is disposed within the turbine housing (24) corresponding to an outer race of the turbine (25).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810298545.3A CN108561222B (en) | 2018-04-04 | 2018-04-04 | Turbocharger with electronic quick-start split structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810298545.3A CN108561222B (en) | 2018-04-04 | 2018-04-04 | Turbocharger with electronic quick-start split structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108561222A CN108561222A (en) | 2018-09-21 |
| CN108561222B true CN108561222B (en) | 2024-05-14 |
Family
ID=63534062
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810298545.3A Active CN108561222B (en) | 2018-04-04 | 2018-04-04 | Turbocharger with electronic quick-start split structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108561222B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110206636A (en) * | 2019-04-01 | 2019-09-06 | 中国科学院合肥物质科学研究院 | A kind of novel integrated electronic turbocharger |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006090274A (en) * | 2004-09-27 | 2006-04-06 | Toyota Motor Corp | Turbocharger with electric motor |
| CN101141092A (en) * | 2007-10-19 | 2008-03-12 | 河北工业大学 | Switch reluctance motor used for position control of electric activator |
| CN104196579A (en) * | 2014-08-28 | 2014-12-10 | 施永强 | Exhaust gas turbocharger system with three-level adjustable nozzles |
| CN107407192A (en) * | 2015-02-11 | 2017-11-28 | 博格华纳公司 | Bearing for turbocharger |
| CN208040518U (en) * | 2018-04-04 | 2018-11-02 | 江苏凯迪航控系统股份有限公司 | Having electronic quickly starts the turbocharger of separate structure |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7360361B2 (en) * | 2005-04-09 | 2008-04-22 | Advanced Propulsion Technologies, Inc. | Turbocharger |
-
2018
- 2018-04-04 CN CN201810298545.3A patent/CN108561222B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006090274A (en) * | 2004-09-27 | 2006-04-06 | Toyota Motor Corp | Turbocharger with electric motor |
| CN101141092A (en) * | 2007-10-19 | 2008-03-12 | 河北工业大学 | Switch reluctance motor used for position control of electric activator |
| CN104196579A (en) * | 2014-08-28 | 2014-12-10 | 施永强 | Exhaust gas turbocharger system with three-level adjustable nozzles |
| CN107407192A (en) * | 2015-02-11 | 2017-11-28 | 博格华纳公司 | Bearing for turbocharger |
| CN208040518U (en) * | 2018-04-04 | 2018-11-02 | 江苏凯迪航控系统股份有限公司 | Having electronic quickly starts the turbocharger of separate structure |
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| Publication number | Publication date |
|---|---|
| CN108561222A (en) | 2018-09-21 |
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