CN108952949B - Turbocharger with good gas fluidity - Google Patents
Turbocharger with good gas fluidity Download PDFInfo
- Publication number
- CN108952949B CN108952949B CN201810727401.5A CN201810727401A CN108952949B CN 108952949 B CN108952949 B CN 108952949B CN 201810727401 A CN201810727401 A CN 201810727401A CN 108952949 B CN108952949 B CN 108952949B
- Authority
- CN
- China
- Prior art keywords
- turbine
- impeller
- bottom plate
- hub
- turbocharger
- 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.)
- Expired - Fee Related
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- 230000017525 heat dissipation Effects 0.000 abstract description 3
- 238000005265 energy consumption Methods 0.000 abstract description 2
- 230000002349 favourable effect Effects 0.000 abstract description 2
- 230000002035 prolonged effect Effects 0.000 abstract description 2
- 239000002994 raw material Substances 0.000 abstract description 2
- 239000000446 fuel Substances 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- 239000003921 oil Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 239000010687 lubricating oil Substances 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
Images
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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/30—Vanes
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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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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Supercharger (AREA)
Abstract
The invention discloses a turbocharger with good gas fluidity, which comprises a compressor, an intermediate body and a turbine, wherein an impeller in the compressor and a turbine in the turbine both comprise a hub, a bottom plate and blades standing on the bottom plate and arranged around the hub, the back surfaces of the bottom plates of the impeller and the turbine, which are opposite to the blades, are provided with a plurality of air guide grooves around the hub, the edge of the bottom plate is sunken into the hub to form an inclined plane, the blades of the impeller are arranged at intervals in length and are in anticlockwise spiral, and the blades of the turbine are equal in length and are bent in the anticlockwise direction. The structure of the blades and the bottom sheet is favorable for gas flowing, the gas flow generated by high-speed rotation is led out through the arrangement of the gas guide grooves, the structure and the parameter arrangement of the gas guide grooves can lead out the gas brought out by rotation according to different states of the impeller and the turbine, the rotation resistance of the impeller and the turbine is reduced, the working efficiency is improved, the heat dissipation is facilitated, the energy consumption is reduced, the raw materials are saved, the reliability of a turbocharger is improved, and the service life is prolonged.
Description
Technical Field
The invention belongs to the field of turbochargers, and particularly relates to a turbocharger with good gas flowability.
Background
The turbocharger uses the inertia impulse force of the exhaust gas from the engine to push the turbine in the turbine chamber, the turbine drives the coaxial impeller, the impeller presses the air sent by the air filter pipeline, and the air is pressurized and enters the cylinder. When the rotating speed of the engine is increased, the exhaust gas exhaust speed and the rotating speed of the turbine are also increased synchronously, the impeller compresses more air to enter the air cylinder, the pressure and the density of the air are increased, more fuel can be combusted, and the output power of the engine can be increased by correspondingly increasing the fuel quantity and adjusting the rotating speed of the engine.
The turbocharger mainly comprises a compressor, an intermediate body and a turbine. The turbine is the place where the engine exhaust gas pushes the turbine to do work, the compressor is the place where the impeller does work and pressurizes the inlet air, the intermediate body is used for connecting the turbine box body and the compressor, the intermediate body plays a role in fixing and loading the bearing part, and meanwhile, the cooling flow channel of the turbocharger is also arranged in the intermediate body.
The exhaust type turbocharger commonly used at present comprises a turbine shell, a turbine shaft, an intermediate body, a floating bearing, a booster impeller, a pressure wheel shell and a heat retaining ring, wherein the turbine and the booster impeller are respectively arranged at two ends of the turbine shaft, the turbine is positioned in the turbine shell, the booster impeller is positioned in the pressure shell, the turbine shaft is arranged on the intermediate body through two sliding bearings, the turbine shell and the pressure shell are respectively and fixedly arranged at two sides of the intermediate body in a sealing manner, and the two sliding bearings are lubricated and cooled by pressurized lubricating oil. According to the supercharging principle of the turbocharger, in order to improve the supercharging performance of the turbine shaft, the higher the rotating speed, the better, the higher the rotating speed, the larger the air intake quantity, and the fuel oil is reduced.
However, the high-speed rotation easily drives the gas to generate friction, so that large resistance and high heat are formed, and the internal consumption of the supercharger is increased.
Disclosure of Invention
The invention aims to overcome the defects and design the turbocharger with good gas fluidity, good heat dissipation and high working efficiency to reduce the resistance of gas friction.
In order to achieve the purpose, the invention provides a turbocharger with good gas fluidity, which comprises a compressor, an intermediate body and a turbine, wherein an impeller in the compressor and a turbine in the turbine both comprise a hub, a bottom plate and blades standing on the bottom plate and arranged around the hub, a plurality of air guide grooves are arranged on the back surfaces of the bottom plate of the impeller and the turbine around the hub, the edge of the bottom plate is sunken into the hub to form an inclined plane, the blades of the impeller are arranged at intervals in length and are in anticlockwise spiral, and the blades of the turbine are equal in length and are bent towards the anticlockwise direction.
The air guide groove is in a curved knife shape, one end close to the hub is in a circular arc shape, and one end close to the edge of the bottom sheet is in a tip part.
The air guide grooves on the impeller bottom plate are bent in the same direction and are bent clockwise, and the air guide grooves on the turbine bottom plate are bent in the same direction and are bent anticlockwise.
The circular arc of the air guide groove close to one end of the hub is encircled to form a circle, the diameter of the circle encircled by the air guide groove on the impeller bottom piece is 1/3-1/2 of the diameter of the bottom piece, and the diameter of the circle encircled by the air guide groove on the turbine bottom piece is 1/2 which is larger than the diameter of the hub and smaller than the diameter of the bottom piece.
According to the invention, 4-8 air guide grooves are arranged on each bottom sheet, preferably 6 air guide grooves are arranged and uniformly distributed around the wheel hub.
The fall of the inclined plane from the edge of the bottom sheet to the hub is 1.5-2 mm.
The intermediate body comprises a shell of an oil passage, a floating bearing and a supercharger shaft, wherein the floating bearing and the supercharger shaft are arranged in the shell, a turbine and an impeller are respectively arranged at two ends of the supercharger shaft, and the floating bearing is respectively arranged at two sides close to the turbine and the impeller. A pressure expansion plate is further arranged between the impeller and the adjacent floating bearing, and a heat insulation cover is further arranged between the turbine and the adjacent floating bearing. Except for the structural arrangement of the turbine and the impeller, the structures and the connection modes of other parts can be the same as those of the prior art.
Compared with the prior art, the invention has the beneficial effects that: the structure of the blades and the bottom sheet is favorable for gas flowing, the gas flow generated by high-speed rotation is led out through the arrangement of the gas guide grooves, the structure and the parameter arrangement of the gas guide grooves can lead out the gas brought out by rotation according to different states of the impeller and the turbine, the rotation resistance of the impeller and the turbine is reduced, the working efficiency is improved, the heat dissipation is facilitated, the energy consumption is reduced, the raw materials are saved, the reliability of a turbocharger is improved, and the service life is prolonged.
Drawings
Fig. 1 is a schematic view of the operating principle of a turbocharger.
Fig. 2 is a schematic view of the structure of the impeller of the turbocharger according to the present invention.
Fig. 3 is a schematic view of a turbine structure of a turbocharger according to the present invention.
In the figure: 1-hub, 2-bottom plate, 3-blade, 4-air guide groove.
Detailed Description
Preferred embodiments of the present invention will be described in more detail with reference to specific examples.
Example 1
The turbocharger with good gas fluidity shown in fig. 1-3 comprises a compressor, an intermediate body and a turbine, wherein the compressor comprises a compressor shell and an impeller, the turbine comprises a turbine shell and a turbine, the intermediate body comprises a shell of an oil passage, a floating bearing and a supercharger shaft, the floating bearing and the supercharger shaft are arranged in the intermediate body, the turbine and the impeller are respectively arranged at two ends of the supercharger shaft, and the floating bearing is respectively arranged at two sides close to the turbine and the impeller. A pressure expansion plate is further arranged between the impeller and the adjacent floating bearing, and a heat insulation cover is further arranged between the turbine and the adjacent floating bearing.
Impeller in the compressor and turbine in the turbine all include wheel hub 1, film 2 and stand on film 2 around the blade 3 that wheel hub 1 set up, film 2 of impeller and turbine all is equipped with a plurality of air guide grooves 4 around wheel hub 1 on for the back of blade 3, and 2 edges of film sink into an inclined plane to wheel hub 1 department, blade 3 of impeller sets up and blade 3 becomes anticlockwise spiral for the length interval, and the blade 3 length of turbine is equalling and blade 3 is buckled to the anticlockwise.
In this embodiment, the air guide groove 4 is in a curved knife shape, one end close to the hub 1 is an arc, and one end close to the edge of the bottom sheet 2 is a tip. The air guide grooves 4 on the impeller bottom plate 2 are bent in the same direction and are bent clockwise, and the air guide grooves 4 on the turbine bottom plate 2 are bent in the same direction and are bent anticlockwise.
In this embodiment, circular arcs of the air guide grooves 4 close to one end of the hub 1 are encircled to form a circle, the diameter of the circle encircled by the air guide grooves on the impeller bottom plate is 1/2 of the diameter of the bottom plate, and the diameter of the circle encircled by the air guide grooves on the turbine bottom plate is 1/2 which is larger than the diameter of the hub and smaller than the diameter of the bottom plate.
In this embodiment, the number of the air guide grooves 4 is 6 on each bottom plate 2, and the air guide grooves are uniformly distributed around the hub 1.
In the embodiment, the inclined fall from the edge of the bottom plate 2 to the hub 1 is 1.8 mm.
Claims (6)
1. A turbocharger with good gas fluidity comprises a compressor, an intermediate body and a turbine, wherein an impeller in the compressor and the turbine in the turbine both comprise a hub (1), a bottom plate (2) and blades (3) which stand on the bottom plate (2) and are arranged around the hub (1), and the turbocharger is characterized in that the back surfaces of the bottom plates (2) of the impeller and the turbine, which are opposite to the blades (3), are provided with a plurality of air guide grooves (4) around the hub (1), the edge of the bottom plate (2) is sunken into an inclined plane to the hub (1), the blades (3) of the impeller are arranged at intervals, the blades (3) are anticlockwise spiral, the lengths of the blades (3) of the turbine are equal, and the blades (3) are bent anticlockwise; the impeller is characterized in that the air guide grooves (4) are in a bent knife shape, one end close to the hub (1) is an arc, one end close to the edge of the impeller bottom plate (2) is a sharp part, the air guide grooves (4) on the impeller bottom plate (2) are bent in the same direction and are bent clockwise, and the air guide grooves (4) on the turbine bottom plate (2) are bent in the same direction and are bent anticlockwise.
2. The turbocharger with good gas fluidity according to claim 1, wherein the arc of the end of the air guide groove (4) close to the hub (1) is rounded.
3. The turbocharger with good gas fluidity according to claim 2, wherein the circular diameter surrounded by the air guide grooves (4) on the impeller bottom plate (2) is 1/3-1/2 of the diameter of the bottom plate (2).
4. The turbocharger with good gas fluidity according to claim 2, wherein the circular diameter defined by the air guide grooves (4) on the turbine bottom plate (2) is greater than the diameter of the hub (1) and less than 1/2 of the diameter of the bottom plate (2).
5. The turbocharger with good gas fluidity according to claim 1, wherein 4-8 air guide grooves (4) are arranged on each bottom plate and evenly distributed around the hub (1).
6. The turbocharger with good gas fluidity according to claim 1, wherein the slope difference from the edge of the bottom plate (2) to the hub (1) is 1.5-2 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810727401.5A CN108952949B (en) | 2018-07-05 | 2018-07-05 | Turbocharger with good gas fluidity |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810727401.5A CN108952949B (en) | 2018-07-05 | 2018-07-05 | Turbocharger with good gas fluidity |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108952949A CN108952949A (en) | 2018-12-07 |
| CN108952949B true CN108952949B (en) | 2020-12-22 |
Family
ID=64485667
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810727401.5A Expired - Fee Related CN108952949B (en) | 2018-07-05 | 2018-07-05 | Turbocharger with good gas fluidity |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108952949B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111322262B (en) * | 2020-02-18 | 2021-01-12 | 中国科学院工程热物理研究所 | Compact compressed air energy storage system based on compressor and turbine all-in-one machine |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105658930A (en) * | 2013-10-24 | 2016-06-08 | 博格华纳公司 | Axial compressor with a magnetic stepper or servo motor |
| CN107304774A (en) * | 2016-04-19 | 2017-10-31 | 本田技研工业株式会社 | Compressor |
| CN207554415U (en) * | 2017-11-30 | 2018-06-29 | 深圳市华阳新材料科技有限公司 | A kind of compressor impeller for aero-engine |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP5611379B2 (en) * | 2013-01-23 | 2014-10-22 | 株式会社豊田自動織機 | Impeller for turbocharger, method for manufacturing impeller for turbocharger, turbocharger, and turbo unit |
-
2018
- 2018-07-05 CN CN201810727401.5A patent/CN108952949B/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105658930A (en) * | 2013-10-24 | 2016-06-08 | 博格华纳公司 | Axial compressor with a magnetic stepper or servo motor |
| CN107304774A (en) * | 2016-04-19 | 2017-10-31 | 本田技研工业株式会社 | Compressor |
| CN207554415U (en) * | 2017-11-30 | 2018-06-29 | 深圳市华阳新材料科技有限公司 | A kind of compressor impeller for aero-engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108952949A (en) | 2018-12-07 |
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| GR01 | Patent grant | ||
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| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20201222 |