CN108317003B - Turbocharger with electronic quick start combined device - Google Patents

Turbocharger with electronic quick start combined device Download PDF

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Publication number
CN108317003B
CN108317003B CN201810300036.XA CN201810300036A CN108317003B CN 108317003 B CN108317003 B CN 108317003B CN 201810300036 A CN201810300036 A CN 201810300036A CN 108317003 B CN108317003 B CN 108317003B
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main shaft
shell
middle shell
motor
turbine main
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CN108317003A (en
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施永强
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Jiangsu Kaidi Aviation Control System Co ltd
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Jiangsu Kaidi Aviation Control System Co ltd
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02BINTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/04Engines with exhaust drive and other drive of pumps, e.g. with exhaust-driven pump and mechanically-driven second pump
    • F02B37/11Engines with exhaust drive and other drive of pumps, e.g. with exhaust-driven pump and mechanically-driven second pump driven by other drive at starting only
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00Road transport of goods or passengers
    • Y02T10/10Internal combustion engine [ICE] based vehicles
    • Y02T10/12Improving 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 electronic quick starting combination device, 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, 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 compressor shell in a sealing mode. 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

Turbocharger with electronic quick start combined device
Technical Field
The invention belongs to the technical field of turbochargers, and relates to a turbocharger with a combined device capable of being started quickly by electrons.
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 combined device, which effectively solves the problem that the natural air suction form of the turbocharger is solved, and the pressurized pressure air entering the engine is synchronous with the engine start.
According to the technical scheme of the invention: a turbocharger with electronic quick start assembly, characterized by: 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 compressor shell in a sealing way, one end of the turbine main shaft penetrates through the first middle shell and stretches into the compressor shell, a compressor impeller is arranged on the shaft diameter of the turbine main shaft, 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, a gas seal plate is sleeved on the shaft seal, and the gas seal plate is axially limited and fixed through a gas seal plate clamp spring; 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 be provided with a turbine, and the outer ring of the turbine is provided with a VTG assembly.
As a further improvement of the invention, the motor comprises a motor shell, a stator core is arranged on the inner wall of the motor shell, a rotor is fixed on the shaft diameter of the turbine main shaft corresponding to the stator core, a first photoelectric switch and a second photoelectric switch are respectively arranged on two end faces of the rotor, and the motor shell is fixedly connected with the left end cover and the right end cover through a motor shell fixing bracket, a first connecting screw and a second connecting screw.
As a further improvement of the invention, a first sealing ring seat is arranged on the joint surface of the first middle shell and the left end cover, a first sealing ring is arranged between an inner hole of the first sealing ring seat and the turbine main shaft, and a second sealing piece is arranged between an inner hole of the left end cover and the turbine main shaft; a second sealing ring seat is arranged 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; a motor cover plate is arranged between the motor shell fixing support and the right end cover, 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 rubber sealing ring is arranged between the compressor housing and the first intermediate housing.
As a further improvement of the invention, a heat shield is arranged on the distance thrust sleeve, a compressor sealing ring is arranged between the air sealing plate and the shaft seal, and a second rubber sealing ring is arranged between the air sealing plate and the first middle shell.
As a further improvement of the invention, the two ends of the second bearing in the axial direction are respectively fixed in a limiting way through the first clamp spring and the second clamp spring, and the circumference direction of the second bearing is fixed in a limiting way through the first locating pin.
As a further improvement of the invention, a turbine end sealing ring is arranged between the inner hole at the outer end of the second intermediate shell and the turbine main shaft.
As a further improvement of the invention, the right end cover, the second sealing ring seat, the second middle shell and the second positioning pin are fastened and connected.
As a further improvement of the invention, the right end cover is fixedly connected with the second middle shell and the left end cover is fixedly connected with the first middle shell through nuts, locating pins and screws respectively.
The invention has the technical effects that: the invention has simple and reasonable structure, solves the problem that the initial stage of starting the supercharged engine does not adopt a natural air suction mode any more in the using process, and the supercharging pressure entering the engine is synchronous with the starting of the engine, thereby thoroughly solving the problem of air-fuel ratio supercharging in the initial stage of starting the traditional supercharged engine.
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, an air sealing plate 3, a compressor housing 4, a first rubber sealing ring 5, a first middle housing 6, a first sealing ring 7, a first sealing 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 plate 13, a rotor 14, a second photoelectric switch 15, a motor housing fixing bracket 16, a second sealing ring seat 17, a second sealing ring 18, a first clamping spring 19, a second clamping spring 20, a second middle housing 21, a VTG (turbine blade) assembly 22, a turbine shaft assembly 23, a turbine housing 24, a turbine 25, a turbine end sealing ring 26, a second bearing 27, a first positioning pin 28, a second positioning pin 29, a right end cover 30, a first sealing member 31, a second connecting screw 32, a second sealing member 33, a nut 34, a positioning pin 35, a screw 36, a heat shield 37, a second bearing 38, a second bearing 39, a second rubber sealing ring 40, a thrust sleeve 41, 42, a clamping spring 43, a stator sealing ring 44, a thrust bearing plate 45, etc.
As shown in fig. 1, the invention relates to a turbocharger with a motor quick-starting combined device, 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 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, taking the joint surface of the first middle shell 6 and the left end cover 9 as an example, the outer ring of the outer end surface of the first middle shell 6 forms an annular bulge, and a groove formed by the annular bulge is matched and connected with a cylindrical bulge formed by the outer end surface of the left end cover 9; the outer end surface of the first intermediate shell 6 is in sealing connection with the compressor shell 4, a compressor impeller 2 is arranged on the shaft diameter of one end of the turbine main shaft 23 penetrating through the first intermediate shell 6 and extending into the compressor shell 4, the compressor impeller 2 is fixed on the turbine main shaft 23 in a limiting manner through a locking nut 1, 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, a gas seal plate 3 is sleeved on the shaft seal 42, and the gas seal plate 3 is fixed in an axial limiting manner through a gas seal plate clamp spring 45; the other end of the main turbine shaft 23 penetrates through the second middle shell 21 and extends into the shaft diameter of the turbine shell 24, a turbine 25 is mounted on the shaft diameter, and a VTG assembly 22 is arranged on the outer ring of the turbine 25. The first bearing 38 is provided with an oil filler hole communicating with an oil filler passage provided in the first intermediate housing 6.
The motor comprises a motor shell 11, a stator core 4 is arranged on the inner wall of the motor shell 11, a rotor 14 is fixed on the shaft diameter of a turbine main shaft 23 corresponding to a stator core 44, a first photoelectric switch 12 and a second photoelectric switch 15 are respectively arranged on two end surfaces of the rotor 14, and the motor shell 11 is fixedly connected with a left end cover 9 and a right end cover 30 through a motor shell fixing bracket 16, a first connecting screw 10 and a second connecting screw 32. The motor is arranged as a kind of quick start between the first intermediate housing 6, the second intermediate housing 21.
The joint surface of the first middle shell 6 and the left end cover 9 is provided with a first sealing ring seat 8, a first sealing ring 7 is arranged between the inner hole of the first sealing ring seat 8 and the turbine main shaft 23, and a second sealing piece 33 is arranged between the inner hole of the left end cover 9 and the turbine main shaft 23; a second sealing ring seat 17 is arranged 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; a motor cover plate 13 is arranged between the motor housing fixing support 16 and the right end cover 30, and a first sealing piece 31 is arranged between an inner hole of the motor cover plate 13 and the turbine main shaft 23.
A first rubber sealing ring 5 is arranged between the compressor housing 4 and the first intermediate housing 6.
The distance thrust sleeve 41 is provided with a heat shield 37, a gas compressor sealing ring 43 is arranged between the gas seal plate 3 and the shaft seal 42, and a second rubber sealing ring 40 is arranged between the gas seal plate 3 and the first intermediate shell 6.
The two axial ends of the second bearing 27 are respectively fixed in a limiting way through the first clamping spring 19 and the second clamping spring 20, and the circumferential direction of the second bearing 27 is fixed in a limiting way through the first positioning 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.
A turbine end sealing ring 26 is arranged between the inner hole at the outer end of the second intermediate shell 21 and the turbine main shaft 23.
The right end cap 30, the second seal ring seat 17, the second intermediate housing 21, and the second positioning pin 29 are fastened and connected.
The right end cover 30 is fixedly connected with the second middle shell 21 and the left end cover 9 is fixedly connected with the first middle shell 6 through nuts 34, locating pins 35 and screws 36.
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 impeller of the turbocharger (hot end), and the turbine main shaft 23 and the compressor impeller (cold end) are arranged on the same shaft, so that the turbine impeller and the compressor impeller rotate synchronously. 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 (7)

1. A turbocharger with electronic quick start assembly, characterized by: 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 compressor shell (4) in a sealing way, one end of the turbine main shaft (23) penetrates through the first middle shell (6) and 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), the distance thrust sleeve (41) is provided with a thrust bearing (39), the shaft seal (42) is sleeved with the air sealing plate (3), and the air sealing plate (3) is axially limited and fixed through an air sealing plate clamp spring (45); 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 (44) is arranged on the inner wall of the motor shell (11), a rotor (14) is fixed on the shaft diameter of a turbine main shaft (23) corresponding to the stator core (44), a first photoelectric switch (12) and a second photoelectric switch (15) are respectively arranged on two end surfaces of the rotor (14), and the motor shell (11) is fixedly connected with a left end cover (9) and a right end cover (30) through a motor shell fixing bracket (16) and a first connecting screw (10) and a second connecting screw (32);
A first sealing ring seat (8) is arranged on the joint surface of the first middle shell (6) and the left end cover (9), a first sealing ring (7) is arranged between the inner hole of the first sealing ring seat (8) and the turbine main shaft (23), and a second sealing piece (33) is arranged between the inner hole of the left end cover (9) and the turbine main shaft (23); a second sealing ring seat (17) is arranged 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); a motor cover plate (13) is arranged between the motor shell fixing support (16) and the right end cover (30), and a first sealing piece (31) is arranged between an inner hole of the motor cover plate (13) and the turbine main shaft (23).
2. The turbocharger with electronic quick start assembly as set forth in claim 1, wherein: a first rubber sealing ring (5) is arranged between the compressor shell (4) and the first middle shell (6).
3. The turbocharger with electronic quick start assembly as set forth in claim 1, wherein: the fixed-distance thrust sleeve (41) is provided with a heat shield (37), an air compressor sealing ring (43) is arranged between the air sealing plate (3) and the shaft seal (42), and a second rubber sealing ring (40) is arranged between the air sealing plate (3) and the first middle shell (6).
4. The turbocharger with electronic quick start assembly as set forth in claim 1, wherein: the two axial ends of the second bearing (27) are respectively limited and fixed through the first clamp spring (19) and the second clamp spring (20), and the circumferential direction of the second bearing (27) is limited and fixed through the first locating pin (28).
5. The turbocharger with electronic quick start assembly as set forth in claim 1, wherein: a turbine end sealing ring (26) is arranged between the inner hole at the outer end of the second intermediate shell (21) and the turbine main shaft (23).
6. The turbocharger with electronic quick start assembly as set forth in claim 1, wherein: the right end cover (30), the second sealing ring seat (17), the second middle shell (21) and the second locating pin (29) are fixedly connected.
7. The turbocharger with electronic quick start assembly as set forth in claim 1, wherein: the right end cover (30) is fixedly connected with the second middle shell (21) and the left end cover (9) and the first middle shell (6) through nuts (34), locating pins (35) and screws (36) respectively.
CN201810300036.XA 2018-04-04 2018-04-04 Turbocharger with electronic quick start combined device Active CN108317003B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201810300036.XA CN108317003B (en) 2018-04-04 2018-04-04 Turbocharger with electronic quick start combined device

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201810300036.XA CN108317003B (en) 2018-04-04 2018-04-04 Turbocharger with electronic quick start combined device

Publications (2)

Publication Number Publication Date
CN108317003A CN108317003A (en) 2018-07-24
CN108317003B true CN108317003B (en) 2024-06-25

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2006090274A (en) * 2004-09-27 2006-04-06 Toyota Motor Corp Turbocharger with electric motor
CN201461073U (en) * 2009-05-14 2010-05-12 黄敏 Air sealing board assembly of turbocharger
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
CN208138040U (en) * 2018-04-04 2018-11-23 江苏凯迪航控***股份有限公司 The turbocharger of having electronic quick start combination unit

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2006090274A (en) * 2004-09-27 2006-04-06 Toyota Motor Corp Turbocharger with electric motor
CN201461073U (en) * 2009-05-14 2010-05-12 黄敏 Air sealing board assembly of turbocharger
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
CN208138040U (en) * 2018-04-04 2018-11-23 江苏凯迪航控***股份有限公司 The turbocharger of having electronic quick start combination unit

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