CN114704376B - High-integration turbocharger without independent bearing - Google Patents

High-integration turbocharger without independent bearing Download PDF

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Publication number
CN114704376B
CN114704376B CN202210490365.1A CN202210490365A CN114704376B CN 114704376 B CN114704376 B CN 114704376B CN 202210490365 A CN202210490365 A CN 202210490365A CN 114704376 B CN114704376 B CN 114704376B
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China
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oil
impeller
rotor
sealing
cylindrical surface
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CN114704376A (en
Inventor
李延昭
信效芬
翟彦春
姜卫国
谢凯
司英杰
张金明
宋丽华
于效顺
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Weifang University of Science and Technology
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Weifang University of Science and Technology
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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
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/18—Lubricating arrangements
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • 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
    • 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
    • F04D29/06—Lubrication
    • F04D29/063—Lubrication specially adapted for elastic fluid pumps
    • 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
    • F04D29/08—Sealings
    • F04D29/083—Sealings especially adapted for elastic fluid pumps
    • 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
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • 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
    • F04D29/70—Suction grids; Strainers; Dust separation; Cleaning
    • F04D29/701—Suction grids; Strainers; Dust separation; Cleaning especially adapted for elastic fluid pumps
    • 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)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)

Abstract

The invention discloses a high-integration turbocharger without an independent bearing, which comprises an intermediate body, wherein a compressor impeller and a turbine rotor are assembled in the intermediate body, an impeller central shaft is integrally connected to the compressor impeller, a pressure end sealing assembly is integrally integrated between the impeller central shaft and the intermediate body, a rotor central shaft is integrally connected to the turbine rotor, and a vortex end sealing assembly is integrally integrated between the rotor central shaft and the intermediate body.

Description

High-integration turbocharger without independent bearing
Technical Field
The invention belongs to the technical field of engine turbochargers, and particularly relates to a high-integration turbocharger without an independent bearing.
Background
Turbochargers have been developed and perfected in the last decades as key components for engine power boosting, air intake increasing or controlling, and engine combustion emission control, forming a currently complex and reliable basic form.
Currently, in conventional turbochargers, the axial load is carried by left and right oil wedges on separate thrust bearings provided on the center housing; the radial load is borne by adopting an inner and outer oil film of a single or a plurality of floating bearings which are independently arranged and form constraint with the inner hole of the middle shell and the outer diameter of the turbine rotor; to constrain these two bearing systems, more mating parts need to be employed inside the intermediate shell; the method has the advantages that the requirements on the machining precision and the assembly precision of each part are very high, the reliability of the related connection is predicted, the manufacturing cost of the traditional supercharger is greatly increased, and the breakthrough of related technologies and structures is required to be carried out again under the situation that the rising of raw materials and labor cost is obvious.
The whole structure of the conventional turbocharger is shown in fig. 1, and the main components comprise a compressor shell 1, a lock nut 2, a compressor impeller 3, a sealing ring sleeve seat 4, a sleeve seat fastening screw 5, a pressure end sealing ring 6, an intermediate sealing ring 7, a thrust bearing 8, a thrust bearing fastening screw 9, an intermediate 10, a turbine shell 11, a heat shield 12, a turbine rotor 13, a turbine end sealing ring 14, a floating bearing 15, a bearing retainer ring 16, a thrust sleeve 17, a shaft seal 18, a pressure end sealing ring 19 and other components.
The existing turbocharger structure has the defects that mainly comprises:
1. the shafting parts are various, each part is mutually matched during assembly, the machining precision of each part on the shafting is very high in order to ensure the quality of the assembled product, meanwhile, the requirement on equipment required by assembly is high, the process is complex, and the manufacturing and assembling costs are high.
2. The thrust bearing 8 for bearing the axial load is usually directly fastened or indirectly compressed by a screw 9, the flatness requirements on two end surfaces of the thrust bearing 8 and the flatness requirements on the matched end surfaces of the middle shell 10 are high, and the elements such as the control requirement of the assembly process on the moment of the fastening screw 9 and the like are added, so that the uncertainty elements of the process are more; causing the problem of abnormal wear of the oil wedge surface of the thrust bearing 8 in the short term in the subsequent supercharger use.
3. The floating bearing 15 for bearing radial load mostly adopts a full-floating or semi-floating structure, an oil film bearing gap is formed between the inner cylindrical surface and the outer cylindrical surface of the floating bearing 15 and the inner cylindrical surface of the middle shell 10 and the matched outer cylindrical surface of the turbine rotor 13, and a bearing oil film is formed in the gap by means of lubricating oil with pressure from an engine. The inner cylindrical surface of the intermediate shell 10, the inner and outer cylindrical surfaces of the floating bearing 15 and the matched outer cylindrical surface of the turbine rotor 13 all have very high requirements on the processing quality and the surface roughness so as to ensure that the problem of abnormal abrasion does not occur.
4. In order to establish the axial and radial usual clearances of the supercharger and ensure that the lubricating oil taking part in bearing the load can establish an oil film in time without leakage and other application problems, a plurality of matching parts, such as a shaft seal 18 and a thrust sleeve 17, are arranged inside the intermediate housing 10 of the turbocharger, and the axial oil film clearance size and the matching area are controlled. One or more end-pressing sealing rings 19 are arranged on the shaft seal 18, and a slit is formed between the end-pressing sealing rings and the matching inner hole of the sealing ring sleeve seat 4 to realize the sealing function. On the other side, the turbine rotor 13 is provided with a ring groove matched with the vortex end sealing ring 14, and the sealing function of the vortex end is realized through a matching inner hole of the turbine rotor and the middle shell 10. The combination of a plurality of parts can lead to the increase of the component rings of the size chain, influence the realization of the aerodynamic performance of the compressor impeller 3 and the like, and has high manufacturing cost and reduced reliability.
The above is a few technical problems that are reflected by conventional construction superchargers. At present, the competition of the supercharger industry is more and more severe, and the requirements for cost control and reliability improvement are more and more obvious; in order to improve the above problems, it is necessary to redesign and break through the conventional structure of the conventional turbocharger, and reduce the product cost while improving the product quality.
Disclosure of Invention
The invention aims to solve the main technical problem of providing the high-integration turbocharger without the independent bearing, which does not need to independently arrange the bearing, can simplify the types and the number of parts in the axial direction, effectively reduce the cost of products, simplify the assembly process, improve the assembly precision, improve the quality of products and reduce the occurrence of failure rate.
In order to solve the technical problems, the invention provides the following technical scheme:
the utility model provides a high integration level turbocharger of no independent bearing, includes the midbody, and inside assembly has compressor impeller and the turbine rotor in midbody, is connected with the impeller center pin on the compressor impeller an organic whole, and an organic whole has the pressure end seal assembly between impeller center pin and the midbody, and an organic whole is connected with the rotor center pin on the turbine rotor, and an organic whole has the vortex end seal assembly between rotor center pin and the midbody.
The following is a further optimization of the above technical solution according to the present invention:
the middle part of midbody has been seted up the midbody cooperation hole, and the inside both ends that lie in midbody cooperation hole of midbody have coaxially been seted up vortex end mounting hole and pressure end mounting hole respectively, have seted up pressure end and have got rid of the oil groove and vortex end in the midbody respectively, and the inside of midbody is located the position department that the pressure end got rid of the oil groove and is provided with left side oil wedge face, and the inside of midbody is located the position department that the vortex end got rid of the oil groove and is provided with right side oil wedge face.
Further optimizing: the left oil wedge surface comprises a plurality of left oil wedge inclined surfaces and a plurality of left oil wedge planes; the right side oil wedge surface includes a plurality of right side oil wedge inclined surfaces and a plurality of right side oil wedge flat surfaces.
Further optimizing: the intermediate body is provided with a lubricating oil duct, the lubricating oil duct comprises an oil storage cavity which is arranged in the intermediate body, the oil storage cavity is communicated with an inner matching hole of the intermediate body, and the intermediate body is coaxially provided with an oil inlet hole and a main oil duct which are mutually communicated; the inner surface of the middle body matching inner hole is respectively provided with a plurality of vortex end axial oil delivery grooves and pressure end axial oil delivery grooves, one ends of the vortex end axial oil delivery grooves and the pressure end axial oil delivery grooves are respectively communicated with the oil storage cavity, and the other ends of the vortex end axial oil delivery grooves and the pressure end axial oil delivery grooves are respectively communicated with the corresponding vortex end oil throwing grooves and pressure end oil throwing grooves.
Further optimizing: the pressure end installation hole is internally provided with a pressure end sealing ring matching cylindrical surface, a pressure end gas sealing cylindrical surface and a pressure end gas sealing groove, the diameter of the inner surface of the pressure end gas sealing cylindrical surface is smaller than that of the inner surface of the pressure end sealing ring matching cylindrical surface, and the joint of the pressure end installation hole and the pressure end oil throwing groove on the intermediate body is provided with a pressure end gas sealing end face.
Further optimizing: the vortex end installation hole is internally integrated with a vortex end sealing ring matching cylindrical surface, a vortex end gas sealing cylindrical surface and a vortex end gas sealing groove, the diameter of the inner surface of the vortex end gas sealing cylindrical surface is smaller than that of the inner surface of the vortex end sealing ring matching cylindrical surface, and a vortex end gas sealing end face is arranged at the joint of the vortex end installation hole and the vortex end oil throwing groove on the intermediate body.
Further optimizing: the outer surface of the impeller central shaft is provided with an impeller sealing ring limit cylindrical surface, an impeller air sealing cylindrical surface, an impeller oil throwing groove and an impeller oil wedge matching cylindrical surface, the impeller sealing ring limit cylindrical surface is provided with at least one impeller sealing ring groove, the impeller air sealing cylindrical surface is matched with the pressure end air sealing cylindrical surface, one side of the impeller oil throwing groove is provided with an impeller air sealing end surface, and a distance C1 is formed between the impeller air sealing end surface and the pressure end air sealing end surface; the impeller oil wedge matching end surface at the end part of the impeller central shaft forms a matching gap with the left oil wedge surface, and the middle part of the compressor impeller is provided with an impeller inner hole positioning cylindrical surface and an impeller inner threaded hole.
Further optimizing: the rotor center shaft is sequentially provided with rotor fastening threads, rotor impeller matching cylindrical surfaces, a floating bearing matching cylindrical surface, a rotor air sealing cylindrical surface, a rotor oil throwing groove and a rotor sealing ring limiting cylindrical surface from left to right along the axial direction of the rotor center shaft, a rotor oil wedge matching end surface is arranged at the joint of the rotor air sealing cylindrical surface and the floating bearing matching cylindrical surface, a matching gap is formed between the rotor oil wedge matching end surface and a right side oil wedge surface, a rotor air sealing end surface is arranged on one side of the rotor air throwing groove, and a distance C2 is formed between the rotor air sealing end surface and a vortex end air sealing end surface.
Further optimizing: the pressure end sealing assembly comprises a pressure end sealing ring arranged in the impeller sealing ring groove, and the outer surface of the pressure end sealing ring is matched with the pressure end sealing ring matching cylindrical surface; the vortex end sealing assembly comprises a vortex end sealing ring arranged in a rotor sealing ring groove, and the outer surface of the vortex end sealing ring is matched with a vortex end air sealing column surface.
Further optimizing: the main oil duct is communicated with the oil inlet hole and the oil storage cavity, a main oil duct expansion cylindrical surface is arranged on the main oil duct, a filtering oil plug is arranged at the position of the main oil duct expansion cylindrical surface, and a plurality of oil plug oil passing holes are formed in the outer surface of the filtering oil plug.
The invention adopts the technical scheme and has the following beneficial effects:
1. the invention creatively designs the functions of the floating bearing, the thrust bearing and the sealing ring sleeve seat on the intermediate body, and effectively reduces the number of the parts and related fastening, sealing and auxiliary parts such as fastening screws, intermediate shell sealing rings, bearing retainer rings and the like. During assembly, additional installation of parts such as a floating bearing, a thrust bearing, a sealing ring sleeve seat and the like is not needed, so that the installation and process inspection processes are greatly simplified, and the purchase and process costs are greatly reduced. Because spare part reduces, assembly accuracy promotes more easily, has reduced subsequent inefficacy risk.
2. The invention integrates the functions of the shaft seal, the thrust sleeve, the locking nut and the like on the compressor impeller, and the oil and gas sealing structure is arranged on the compressor impeller, so that the number of parts is reduced, and the oil and gas sealing capacity of the compressor end is improved.
3. According to the invention, the axial positions of the turbine rotor and the compressor impeller are controlled through the impeller axial matching end surface and the rotor oil wedge matching end surface of the turbine rotor, and the oil sealing and gas sealing structure is arranged on the turbine rotor, so that the oil sealing and gas sealing capacity of the turbine end is improved.
4. According to the invention, the porous filtering oil plug is pressed on the main oil duct expansion cylindrical surface of the intermediate body, so that large-size impurities are effectively prevented from entering the intermediate body, and the reliability of a bearing system is improved.
In summary, the turbocharger with high integration level and no independent bearing is related by the invention, the functions of the thrust bearing, the floating bearing and the sealing ring sleeve seat are innovatively integrated on the intermediate body, the functions of the shaft seal, the thrust sleeve and the locking nut are integrated on the impeller of the compressor, and the functions of oil sealing and gas sealing of the shaft system are improved while the design of high integration level is realized. By the aid of the measures, the number of parts is greatly reduced, assembly difficulty and purchase cost of the parts are simplified, and reliability of products is improved.
The invention will be further described with reference to the drawings and examples.
Drawings
FIG. 1 is a schematic diagram of a conventional turbocharger in the background art;
FIG. 2 is a schematic diagram of the overall structure of an embodiment of the present invention;
FIG. 3 is an enlarged view of a portion of FIG. 2 at A;
FIG. 4 is a schematic structural diagram of an intermediate in an embodiment of the present invention;
FIG. 5 is a schematic axial view of the left side oil wedge surface of the intermediate in an embodiment of the present invention;
FIG. 6 is a schematic axial view of the right side oil wedge surface of the intermediate in an embodiment of the present invention;
FIG. 7 is a schematic view of a compressor wheel according to an embodiment of the present invention;
FIG. 8 is a schematic diagram illustrating an axial view of an impeller of a compressor in accordance with an embodiment of the present invention;
FIG. 9 is a schematic view of a turbine rotor according to an embodiment of the present invention;
FIG. 10 is a schematic view of a filter plug according to an embodiment of the present invention;
fig. 11 is a partially enlarged view showing an assembly structure of a filter plug in an intermediate body in an embodiment of the present invention.
In the figure: 1-a compressor housing; 2-locking nuts; 3-compressor impeller; 4-a sealing ring sleeve seat; 5-socket fastening screws; 6-pressing an end sealing ring; 7-an intermediate sealing ring; 8-thrust bearings; 9-thrust bearing fastening screws; 10-intermediates; 11-turbine shell; 12-a heat shield; 13-a turbine rotor; 14-vortex end sealing rings; 15-floating bearings; 16-a bearing retainer ring; 17-a thrust sleeve; 18-shaft seal; 19-pressing an end sealing ring; 20-filtering oil plugs; 1001-the press end sealing ring is matched with a cylindrical surface; 1002-pressing an end sealing air groove; 1003-pressing an end sealing cylinder; 1004-pressing an end face for sealing gas; 1005-pressing an end oil throwing groove; 1006—left side oil wedge; 1007-oil inlet holes; 1008-main oil gallery; 1009—main gallery expansion cylinder; 1010-vortex end gas sealing end face; 1011-vortex end cylinder; 1012-vortex end sealing air groove; 1013-vortex end seal ring mating cylindrical surface; 1014-right side oil wedge convex cylinder; 1015-right side oil wedge surface; 1016-vortex end oil slinger; 1017-vortex end axial oil delivery groove; 1018-oil return chambers; 1019-oil storage chamber; 1020-pressing end axial oil conveying groove; 1021-left side oil wedge convex cylinder; 1022-left side oil wedge ramp; 1023-left side wedge plane; 1024-right side oil wedge bevel; 1025-right side oil wedge plane; 1026-the intermediate mating bore; 1027-vortex end mounting holes; 1028-press end mounting holes; 301-impeller seal ring groove; 302-limiting cylindrical surface of the impeller sealing ring; 303-impeller air sealing cylindrical surface; 304-impeller gas sealing end face; 305-impeller oil slinger; 306-impeller oil wedge mating cylinder; 307-impeller oil wedge mating end face; 308-locating a cylindrical surface in an inner hole of the impeller; 309-an impeller internal threaded bore; 310-impeller assembly hub; 311-impeller central shaft; 1301-rotor impeller matching cylindrical surface; 1302-rotor impeller mating end face; 1303-floating bearing mating cylindrical surfaces; 1304-rotor connection cylinder; 1305-rotor oil wedge mating end face; 1306-rotor air sealing cylinder; 1307-rotor oil slinger; 1308-rotor end face; 1309-rotor seal ring limiting cylinder; 1310-rotor seal ring groove; 1311—rotor fastening threads; 1312—rotor central shaft; 2001-upper end face of oil plug; 2002-oil plug mating cylinder; 2003-oil plug oil hole passing; 2004-lower end face of oil plug.
Detailed Description
Examples: as shown in fig. 2-11, a turbocharger with high integration and no independent bearing comprises an intermediate body 10, wherein a compressor impeller 3 and a turbine rotor 13 are assembled in the intermediate body 10, a pressure end sealing assembly is assembled on the compressor impeller 3, a turbine end sealing assembly is assembled on the turbine rotor 13, an intermediate shell 10 is matched with a compressor shell 1 and a turbine shell 11 through a matched spigot, the application function of the turbocharger is realized, and a lubricating oil duct is formed in the intermediate body 10.
An intermediate matching inner hole 1026 is formed in the middle of the intermediate 10, a vortex end mounting hole 1027 and a press end mounting hole 1028 are formed in two ends of the intermediate matching inner hole 1026 in the intermediate 10, and the vortex end mounting hole 1027 and the press end mounting hole 1028 are respectively arranged coaxially with the intermediate matching inner hole 1026.
The middle body 10 is provided with a pressing end oil throwing groove 1005 at the joint of the pressing end mounting hole 1028 and the middle body matching inner hole 1026.
The middle body 10 is provided with a vortex end oil throwing groove 1016 at the joint of the vortex end mounting hole 1027 and the middle body matching inner hole 1026.
The inside of the intermediate body 10 is provided with a left oil wedge surface 1006 at the position of the oil slinging groove 1005 at the pressing end, and the left oil wedge surface 1006 is integrally connected with the intermediate body 10 through a left oil wedge bulge cylindrical surface 1021.
The right oil wedge surface 1015 is arranged in the middle body 10 at the position of the vortex end oil slinger 1016, and the right oil wedge surface 1015 is integrally connected with the middle body 10 through the right oil wedge bulge cylindrical surface 1014.
By means of the design, the left oil wedge surface 1006 and the right oil wedge surface 1015 can bear the axial load of the turbocharger, and the left oil wedge convex cylindrical surface 1021 and the right oil wedge convex cylindrical surface 1014 can be processed conveniently, and an oil return space is reserved.
The left oil wedge surface 1006 is composed of two parts, and comprises a plurality of left oil wedge inclined surfaces 1022 and left oil wedge planes 1023 which are sequentially and alternately arranged.
The right oil wedge surface 1015 is also formed from two parts, and includes a plurality of right oil wedge inclined surfaces 1024 and right oil wedge plane surfaces 1025 that are sequentially and alternately arranged.
By such design, the left side oil wedge inclined surface 1022 and the right side oil wedge inclined surface 1024 can distribute oil and form backlog oil film, and the left side oil wedge plane 1023 and the right side oil wedge plane 1025 can play a role of parallel support.
By the design, the bearing function of the thrust bearing 8 on the traditional structure is effectively integrated and replaced on the intermediate body 10, parts such as a thrust bearing fastening screw 9 and the like required for fastening the thrust bearing 8 can be effectively reduced, and meanwhile, because the axial spans of the left oil wedge surface 1006 and the right oil wedge surface 1015 are larger, the constraint capacity on a shaft system is stronger, and the machining precision requirement is also reduced.
The lubricating oil duct comprises an oil storage cavity 1019 formed in the middle body 10, and the oil storage cavity 1019 is communicated with a middle body matching inner hole 1026.
An oil inlet hole 1007 and a main oil duct 1008 are coaxially formed in the intermediate body 10, the oil inlet hole 1007 and the main oil duct 1008 are mutually communicated, the outer end of the oil inlet hole 1007 penetrates through the intermediate body 10, and the inner end of the main oil duct 1008 is communicated with the oil storage cavity 1019.
By such design, after entering from the oil inlet hole 1007, the engine lubricating oil enters the oil storage cavity 1019 through the main oil duct 1008 communicated with the oil inlet hole, and at this time, the lubricating oil in the oil storage cavity 1019 flows and distributes oil along the axial direction of the intermediate matching inner hole 1026
The rotation centers of the oil storage cavity 1019 and the middle body matching inner hole 1026 are inconsistent, so that the volume of the oil storage cavity 1019 can be effectively increased, and the oil storage capacity is improved.
The intermediate body matching inner hole 1026 is in clearance fit with the rotor central shaft 1312 of the turbine rotor 13, and lubricating oil in the oil storage cavity 1019 can flow into the clearance, so that radial load is carried, and an oil film clearance function formed by matching the floating bearing 15 and the turbine rotor 13 in a traditional structure is realized.
By the design, the radial bearing function of the floating bearing 15 in the traditional structure is integrated on the intermediate body 10, parts such as the floating bearing 15 and the bearing retainer ring 16 are reduced, 3 bearing retainer rings 16 are omitted on the intermediate body 8, and the processing difficulty and the whole assembly requirement of the intermediate body 8 are simplified.
The inner surface of the intermediate fitting inner hole 1026 is respectively provided with a vortex end axial oil conveying groove 1017 and a press end axial oil conveying groove 1020, and the vortex end axial oil conveying groove 1017 and the press end axial oil conveying groove 1020 are arranged in a plurality along the circumferential direction of the intermediate fitting inner hole 1026.
One ends of the vortex end axial oil delivery groove 1017 and the pressure end axial oil delivery groove 1020, which are close to each other, are respectively communicated with the oil storage cavity 1019.
The ends of the vortex end axial oil delivery groove 1017 and the pressure end axial oil delivery groove 1020, which are far away from each other, are respectively communicated with the corresponding vortex end oil slinging groove 1016 and pressure end oil slinging groove 1005.
In this embodiment, the number of the vortex end axial oil grooves 1017 and the pressure end axial oil grooves 1020 is the same as the number of the left side oil wedge inclined surface 1022 and the right side oil wedge inclined surface 1024, and the vortex end axial oil grooves 1017 and the pressure end axial oil grooves 1020 allow for an even or non-even arrangement.
By means of the design, the radial oil distribution effect of the oil storage cavity 1019 in the middle body matching inner hole 1026 can be improved through the vortex end axial oil conveying groove 1017 and the pressure end axial oil conveying groove 1020, and then the oil conveying effect of the left side oil wedge surface 1006 and the right side oil wedge surface 1015 of the middle body 10 is improved.
And the lubricating oil entering from the main oil duct 1008 can be supplied to the right side oil wedge 1015 and the left side oil wedge 1006 through the vortex end axial oil feed 1017 and the pressure end axial oil feed 1020 respectively, and is not influenced by the radial bearing oil film between the intermediate fitting inner hole 1026 and the rotor central shaft 1312 of the turbine rotor 13.
An oil return cavity 1018 is formed in the intermediate body 10 below the oil storage cavity 1019, and the pressure end oil slinger 1005 and the vortex end oil slinger 1016 are respectively communicated with the oil return cavity 1018.
An oil outlet is formed below the intermediate body 10, and the oil outlet is communicated with an oil return cavity 1018.
So designed, the lubricating oil in the intermediate mating bore 1026 may be delivered to the pressure end slinger 1005 and the vortex end slinger 1016 where it enters the oil return chamber 1018 by gravity to collect and exit the supercharger body from the oil outlet.
The inside of the pressure end mounting hole 1028 is integrally provided with a pressure end sealing ring matching cylindrical surface 1001 and a pressure end sealing air cylindrical surface 1003, and a pressure end sealing air groove 1002 is formed between the pressure end sealing ring matching cylindrical surface 1001 and the pressure end sealing air cylindrical surface 1003.
The inner surface diameter of the press end seal air cylinder 1003 is smaller than the inner surface diameter of the press end seal ring mating cylinder 1001.
In such design, the function of the traditional sealing ring sleeve seat 4 is integrated on the intermediate body 10, the pressing end sealing component is directly matched with the pressing end sealing ring matching cylindrical surface 1001, and meanwhile, parts such as the sleeve seat fastening screw 5 and the like are omitted, so that the assembly process is simplified.
And the diameter of the inner surface of the pressing end sealing air column surface 1003 is smaller than that of the inner surface of the pressing end sealing ring matched column surface 1001, so that the air sealing effect can be improved, meanwhile, the pressing end sealing air column surface 1003 and the pressing end sealing air groove 1002 are increased, and the sealing effect on left side channeling air can be improved.
The middle body 10 is provided with a pressure end sealing end face 1004 at the joint of the pressure end mounting hole 1028 and the pressure end oil slinging groove 1005.
The vortex end mounting hole 1027 is internally integrated with a vortex end sealing ring matching cylindrical surface 1013 and a vortex end gas sealing cylindrical surface 1011, and a vortex end gas sealing groove 1012 is formed between the vortex end sealing ring matching cylindrical surface 1013 and the vortex end gas sealing cylindrical surface 1011.
The diameter of the inner surface of the vortex end gas sealing column 1011 is smaller than that of the inner surface of the vortex end sealing ring matching column 1013 so as to improve the sealing of the gas transmitted from the right side and improve the gas sealing effect.
The middle body 10 is provided with a vortex end gas sealing end surface 1010 at the joint of the vortex end mounting hole 1027 and the vortex end oil slinger 1016.
An impeller central shaft 311 is integrally connected to the compressor impeller 3, and an impeller sealing ring limit cylindrical surface 302, an impeller air sealing cylindrical surface 303 and an impeller oil wedge matching cylindrical surface 306 are sequentially arranged on the outer surface of the impeller central shaft 311.
An impeller oil throwing groove 305 is formed at the joint of the impeller air sealing cylindrical surface 303 and the impeller oil wedge matching cylindrical surface 306.
At least one impeller seal ring groove 301 is formed in the impeller seal ring limiting cylindrical surface 302.
The tip seal assembly includes a tip seal ring 19 mounted within an impeller seal ring groove 301.
After the impeller central shaft 311 is installed in the press end installation hole 1028, the outer surface of the press end sealing ring 19 is matched with the press end sealing ring matching cylindrical surface 1001, so that a labyrinth sealing structure is formed.
The impeller seal air column surface 303 is matched with the press end seal air column surface 1003 to form a slit gap, and the air quantity entering from the left slit is controlled.
An impeller air sealing end face 304 is arranged on one side, close to the impeller air sealing cylindrical face 303, of the impeller oil slinger 305, the impeller air sealing end face 304 is perpendicular to the rotation center of the compressor impeller 3, and the impeller air sealing end face 304 axially falls into an end pressing air sealing cylindrical face 1003.
The impeller seal end face 304 and the press end seal end face 1004 form a distance C1 therebetween.
The design integrates the function of the shaft seal 18 in the traditional structure on the compressor impeller 3, improves the expansibility, designs the gas sealing structure of the compressor end, and improves the sealing effect on gas introduced from the left side while integrating and simplifying the structure through the cooperation of the impeller gas sealing column surface 303 and the impeller oil throwing groove 305.
The diameter of the outer surface of the impeller oil wedge matching cylindrical surface 306 is larger than or equal to that of the outer surface of the left oil wedge protruding cylindrical surface 1021, so that the thrust bearing area can be more effectively established.
An impeller oil wedge matching end surface 307 is arranged on one end part of the impeller central shaft 311 far away from the compressor impeller 3, the impeller oil wedge matching end surface 307 and a left oil wedge surface 1006 on the intermediate body 10 form a matching gap, and the axial force is borne under the support of engine oil.
A blind hole is formed in the middle of the impeller central shaft 311, and an impeller inner hole positioning cylindrical surface 308 and an impeller inner threaded hole 309 are sequentially formed in the blind hole along the axis direction.
The leftmost side of the compressor wheel 3 is provided with an impeller mounting hub 310.
By means of the design, the shaft seal matching effect is achieved through the impeller oil wedge matching cylindrical surface 306 and the impeller oil wedge matching end surface 307, the radial positioning and torque tightening functions of the compressor impeller 3 are achieved through the impeller inner hole positioning cylindrical surface 308 and the impeller inner threads 309, tightening and assembling are conducted through the impeller assembling hub 310 which is integrally designed, the function of a lock nut is achieved integrally, and the assembling structure is simplified.
As shown in fig. 2, 6 and 8, one side of the rotor 13 is integrally connected with a rotor central shaft 1312, and rotor fastening threads 1311, a rotor impeller matching cylindrical surface 1301, a floating bearing matching cylindrical surface 1303, a rotor air sealing cylindrical surface 1306 and a rotor sealing ring limiting cylindrical surface 1309 are sequentially arranged on the rotor central shaft 1312 from left to right along the axial direction.
The diameter of the outer surface of the floating bearing matching cylindrical surface 1303 is larger than that of the outer surface of the rotor impeller matching cylindrical surface 1301, and a rotor impeller matching end surface 1302 is arranged at the joint of the floating bearing matching cylindrical surface 1303 and the rotor impeller matching cylindrical surface 1301.
A rotor connecting cylindrical surface 1304 is provided at the intermediate position of the floating bearing mating cylindrical surface 1303.
The diameter of the outer surface of the rotor air sealing cylindrical surface 1306 is larger than that of the outer surface of the floating bearing matching cylindrical surface 1303, and a rotor oil wedge matching end surface 1305 is arranged at the joint of the rotor air sealing cylindrical surface 1306 and the floating bearing matching cylindrical surface 1303.
The rotor oil slinger 1307 is arranged at the joint of the rotor air sealing cylindrical surface 1306 and the rotor sealing ring limit cylindrical surface 1309.
At least one rotor seal ring groove 1310 is formed in the outer surface of the rotor seal ring limiting cylindrical surface 1309.
As shown in fig. 2, 7, 8 and 9, after the rotor central shaft 1312 of the turbine rotor 13 is assembled into the intermediate mating bore 1026, the impeller inner bore positioning cylindrical surface 308 is tightly matched with the rotor impeller mating cylindrical surface 1301 on the turbine rotor 13, and is radially positioned.
The impeller internal thread 309 is in fastening fit with a rotor fastening thread 1311 on the turbine rotor 13, so that the impeller oil wedge matching end surface 307 and the rotor impeller matching end surface 1302 are fastened together, the axial positioning of the compressor impeller 3 and the turbine rotor 13 is realized, and the two are ensured to coaxially rotate at the same speed.
The rotor oil wedge mating end face 1305 forms a mating clearance with the right side oil wedge face 1015 on the intermediate body 10 to carry the axial load of the supercharger.
The diameter of the outer surface of the rotor seal air cylindrical surface 1306 is larger than or equal to the diameter of the right oil wedge bulge cylindrical surface 1014, so that the thrust bearing area can be more effectively established.
By means of the design, the compressor impeller 3 and the turbine rotor 13 are effectively connected, synchronous rotation of the compressor impeller and the turbine rotor is guaranteed, the function of the thrust sleeve 17 on a traditional structure is achieved by utilizing the matching of the rotor oil wedge matching end face 1305 and the right oil wedge face 1015, the structure is simplified, and the assembly difficulty is reduced.
The rotor oil slinger 1307 is provided with a rotor gas sealing end face 1308 which is perpendicular to the rotation center of the turbine rotor 13 at one side close to the rotor sealing ring limit cylindrical surface 1309, and the rotor gas sealing end face 1308 is sunk into the vortex end gas sealing cylindrical surface 1011 in the axial direction.
The rotor seal face 1308 and the vortex end seal face 1010 form a distance C2 therebetween.
The vortex end sealing assembly comprises a vortex end sealing ring 14 arranged in a rotor sealing ring groove 1310, and the outer surface of the vortex end sealing ring 14 is matched with a vortex end air sealing column surface 1011 to form a labyrinth sealing structure.
By using the inward sinking distance C2 formed between the rotor gas sealing end surface 1308 and the vortex end gas sealing end surface 1010 on the right side of the rotor oil slinger 1307, engine oil can form an oil curtain during high-speed rotation, and gas transmitted from the right side is prevented from entering the intermediate body 8, so that the gas blow-by amount is greatly reduced.
As shown in fig. 2, 10 and 11, the main oil gallery 1008 communicates with the oil inlet hole 1007 and the oil storage cavity 1019, and a main oil gallery expansion cylinder 1009 is disposed on the main oil gallery 1008.
The inner surface diameter of the main oil gallery expansion cylinder 1009 is greater than the inner surface diameter of the main oil gallery 1008.
A filter oil plug 20 is installed at the position of the main oil gallery expansion cylinder 1009.
In this embodiment, the filter oil plug 20 is pressed into the main oil gallery expansion cylinder 1009 from the upper part of the main oil gallery 1008 by press-fitting.
The filter oil plug 20 is provided with an oil plug upper end face 2001, an oil plug lower end face 2004 and an oil plug matching cylindrical face 2002, and the filter oil plug 20 is made of elastic porous materials.
The oil plug matching cylindrical surface 2002 and the oil plug lower end surface 2004 are provided with a plurality of oil plug oil passing holes 2003.
The included angle alpha between the oil plug matching cylindrical surface 2002 and the oil plug lower end surface 2004 is less than or equal to 90 degrees.
The oil plug mating cylindrical surface 2002 is pressed into the main oil gallery expansion cylindrical surface 1009 and forms a tension state.
After the filter oil plug 20 is pressed in, a height H2 is formed between the upper end face 2001 of the oil plug and the lower end face 2004 of the oil plug, and the height H1 is effectively matched with the height H1 of the main oil duct expansion cylindrical surface 1009, so that the filter oil plug is smoothly placed in the main oil duct, and the H1 is more than or equal to the H2.
By the design, the filtering oil plug 20 with the oil plug passing hole 2003 is pressed into the main oil passage expansion cylindrical surface 1009 of the intermediate body 10, and lubricating oil is secondarily filtered through the oil plug 20, so that abrasion to a bearing system of the supercharger when an engine oil filter fails is prevented, and the reliability of the supercharger is improved.
The compressor housing 1 is arranged outside the compressor impeller 3, and the compressor housing 1 is fixedly connected with the intermediate body 10.
The turbine shell 11 is arranged outside the turbine rotor 13, and the turbine shell 11 is fixedly connected with the intermediate body 10.
In summary, the turbocharger with high integration degree and no independent bearing related by the invention is mainly characterized in that the functions of the thrust bearing 8, the floating bearing 15, the sealing ring sleeve seat 4 and the like in the traditional structure are innovatively integrated on the intermediate body 10, the functions of the lock nut 2, the shaft seal 18 and the thrust sleeve 17 are integrated on the compressor impeller 3, and meanwhile, the connecting components of the bearing retainer ring 16, the sleeve seat fastening screw 5, the intermediate body sealing ring 7 and the like are eliminated; on the integrated compressor impeller 3 and turbine rotor 13, an air sealing and oil sealing structure is innovatively designed; the structure of the filter oil plug 20 is innovatively designed, so that the wear resistance of the bearing system is improved.
Through high integration and innovative design for booster device's part kind and quantity reduce by a wide margin, spare part kind and quantity reduce for the assembly degree of difficulty and product spare part cost reduce by a wide margin, and assembly process precision improves, has realized the reduction of product cost and the promotion of reliability in step.
Alterations, modifications, substitutions and variations of the embodiments herein will be apparent to those of ordinary skill in the art in light of the teachings of the present invention without departing from the spirit and principles of the invention.

Claims (3)

1. The utility model provides a high integration level turbocharger of no independent bearing, includes midbody (10), and midbody (10) inside is equipped with compressor wheel (3) and turbine rotor (13), its characterized in that: an impeller central shaft (311) is integrally connected to the air compressor impeller (3), a pressure end sealing assembly is integrally formed between the impeller central shaft (311) and the intermediate body (10), a rotor central shaft (1312) is integrally connected to the turbine rotor (13), and a vortex end sealing assembly is integrally formed between the rotor central shaft (1312) and the intermediate body (10);
an intermediate body matching inner hole (1026) is formed in the middle of the intermediate body (10), vortex end mounting holes (1027) and vortex end mounting holes (1028) are respectively formed in the two ends of the intermediate body (10) and located in the intermediate body matching inner hole (1026) coaxially, a vortex end oil throwing groove (1005) and a vortex end oil throwing groove (1016) are respectively formed in the intermediate body (10), a left oil wedge surface (1006) is arranged at the position, located in the vortex end oil throwing groove (1005), of the inner part of the intermediate body (10), and a right oil wedge surface (1015) is arranged at the position, located in the vortex end oil throwing groove (1016);
the left oil wedge surface (1006) includes a plurality of left oil wedge ramps (1022) and a plurality of left oil wedge planes (1023); the right side oil wedge surface (1015) comprises a plurality of right side oil wedge inclined surfaces (1024) and a plurality of right side oil wedge flat surfaces (1025);
the intermediate body (10) is provided with a lubricating oil duct, the lubricating oil duct comprises an oil storage cavity (1019) arranged in the intermediate body (10), the oil storage cavity (1019) is communicated with an inner hole (1026) matched with the intermediate body, and the intermediate body (10) is coaxially provided with an oil inlet hole (1007) and a main oil duct (1008) which are mutually communicated; a plurality of vortex end axial oil delivery grooves (1017) and pressure end axial oil delivery grooves (1020) are respectively arranged on the inner surface of the middle body matching inner hole (1026), one ends of the vortex end axial oil delivery grooves (1017) and the pressure end axial oil delivery grooves (1020) are respectively communicated with the oil storage cavity (1019), and the other ends of the vortex end axial oil delivery grooves are respectively communicated with the corresponding vortex end oil throwing grooves (1016) and the pressure end oil throwing grooves (1005);
a pressing end sealing ring matching cylindrical surface (1001), a pressing end air sealing cylindrical surface (1003) and a pressing end air sealing groove (1002) are arranged in the pressing end mounting hole (1028), the diameter of the inner surface of the pressing end air sealing cylindrical surface (1003) is smaller than that of the inner surface of the pressing end sealing ring matching cylindrical surface (1001), and a pressing end air sealing end surface (1004) is arranged at the joint of the pressing end mounting hole (1028) and the pressing end oil throwing groove (1005) on the intermediate body (10);
the vortex end mounting hole (1027) is internally integrated with a vortex end sealing ring matching cylindrical surface (1013), a vortex end gas sealing cylindrical surface (1011) and a vortex end gas sealing groove (1012), the diameter of the inner surface of the vortex end gas sealing cylindrical surface (1011) is smaller than that of the inner surface of the vortex end sealing ring matching cylindrical surface (1013), and a vortex end gas sealing end surface (1010) is arranged at the joint of the vortex end mounting hole (1027) and the vortex end oil throwing groove (1016) on the intermediate body (10);
an impeller seal ring limit cylindrical surface (302), an impeller seal gas cylindrical surface (303), an impeller oil throwing groove (305) and an impeller oil wedge matching cylindrical surface (306) are arranged on the outer surface of an impeller central shaft (311), at least one impeller seal ring groove (301) is formed in the impeller seal ring limit cylindrical surface (302), the impeller seal gas cylindrical surface (303) is matched with a pressure end seal gas cylindrical surface (1003), an impeller seal gas end surface (304) is arranged on one side of the impeller oil throwing groove (305), and a distance C1 is formed between the impeller seal gas end surface (304) and the pressure end seal gas end surface (1004); an impeller oil wedge matching end face (307) at the end part of an impeller central shaft (311) and a left oil wedge face (1006) form a matching gap, and an impeller inner hole positioning cylindrical surface (308) and an impeller inner threaded hole (309) are formed in the middle part of the compressor impeller (3);
rotor fastening screw threads (1311), rotor impeller matching cylindrical surfaces (1301), floating bearing matching cylindrical surfaces (1303), rotor sealing cylindrical surfaces (1306), rotor oil slinging grooves (1307) and rotor sealing ring limiting cylindrical surfaces (1309) are sequentially arranged on a rotor central shaft (1312) from left to right along the axial direction of the rotor central shaft, rotor oil wedge matching end faces (1305) are arranged at the connecting positions of the rotor sealing cylindrical surfaces (1306) and the floating bearing matching cylindrical surfaces (1303), matching gaps are formed between the rotor oil wedge matching end faces (1305) and right-side oil wedge faces (1015), rotor sealing end faces (1308) are arranged on one side of the rotor oil slinging grooves (1307), and a distance C2 is formed between the rotor sealing end faces (1308) and vortex end sealing end faces (1010).
2. A high integration turbocharger without independent bearings according to claim 1, wherein: the pressure end sealing assembly comprises a pressure end sealing ring (19) arranged in the impeller sealing ring groove (301), and the outer surface of the pressure end sealing ring (19) is matched with a pressure end sealing ring matching cylindrical surface (1001); the vortex end sealing assembly comprises a vortex end sealing ring (14) arranged in a rotor sealing ring groove (1310), and the outer surface of the vortex end sealing ring (14) is matched with a vortex end gas sealing cylindrical surface (1011).
3. A high integration turbocharger without independent bearings according to claim 2, wherein: the main oil duct (1008) is communicated with the oil inlet hole (1007) and the oil storage cavity (1019), the main oil duct (1008) is provided with a main oil duct expansion cylindrical surface (1009), a filtering oil plug (20) is arranged at the position of the main oil duct expansion cylindrical surface (1009), and a plurality of oil plug oil passing holes (2003) are formed in the outer surface of the filtering oil plug (20).
CN202210490365.1A 2022-05-07 2022-05-07 High-integration turbocharger without independent bearing Active CN114704376B (en)

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CN202970810U (en) * 2012-10-31 2013-06-05 浙江吉利汽车研究院有限公司杭州分公司 Lubrication device in exhaust gas turbocharger for automobile
CN108952950A (en) * 2018-09-03 2018-12-07 康跃科技股份有限公司 A kind of efficient turbocharger of highly integrated shafting
JP6639728B1 (en) * 2018-11-29 2020-02-05 トヨタ自動車株式会社 Turbocharger
CN110410154A (en) * 2019-07-30 2019-11-05 湖南天雁机械有限责任公司 A kind of turbocharger thrust structure and its turbocharger
CN114033717B (en) * 2021-11-02 2023-07-04 潍坊科技学院 High-strength end face positioning compact turbine rotor device of turbocharger

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CN103953431A (en) * 2013-12-30 2014-07-30 常州环能涡轮动力股份有限公司 Small gasoline engine turbosuperchager

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