阅读说明：本技术 一种耐高负压的涡轮增压器压气机端密封结构 (High negative pressure resistant turbocharger compressor end sealing structure ) 是由 赵丕欢 刘毅 田伟 冀翼 史丽媛 梁建伟 于 2020-12-30 设计创作，主要内容包括：本发明公开了一种耐高负压的涡轮增压器压气机端密封结构,其包括中空的轴承体(1)；轴承体(1)的内腔中心位置,具有横向分布的涡轮转轴(8)；涡轮转轴(8)的径向外壁,从左到右分别安装有环绕分布的压气机叶轮(20)、轴封套(6)和止推间隔套(7)；轴封套(6)的左侧与压气机叶轮(20)的右侧相接触；轴封套(6)的右侧,与止推间隔套(7)的左侧相接触；轴封套(6)的径向四周外侧,环绕地安装有封油盖(4)；止推间隔套(7)的径向四周外侧,安装有一个止推轴承板(5)；止推轴承板,安装在轴承体(1)的内侧空腔中。本发明结构设计科学,能够切实提高涡轮增压器压气机端的抗负压能力,保证涡轮增压器的使用可靠性。(The invention discloses a high negative pressure resistant turbocharger compressor end sealing structure, which comprises a hollow bearing body (1); the center of the inner cavity of the bearing body (1) is provided with a turbine rotating shaft (8) which is transversely distributed; a compressor impeller (20), a shaft seal sleeve (6) and a thrust spacer sleeve (7) which are distributed in a surrounding manner are respectively arranged on the radial outer wall of the turbine rotating shaft (8) from left to right; the left side of the shaft sleeve (6) is in contact with the right side of the compressor impeller (20); the right side of the shaft sleeve (6) is contacted with the left side of the thrust spacer sleeve (7); an oil seal cover (4) is circumferentially arranged on the radial outer side of the periphery of the shaft seal sleeve (6); a thrust bearing plate (5) is arranged on the outer side of the radial periphery of the thrust spacer sleeve (7); the thrust bearing plate is installed in the inner side cavity of the bearing body (1). The invention has scientific structural design, can practically improve the negative pressure resistance of the compressor end of the turbocharger and ensure the use reliability of the turbocharger.)

1. A high negative pressure resistant turbocharger compressor end sealing structure is characterized by comprising a hollow bearing body (1);

wherein, the center of the inner cavity of the bearing body (1) is provided with a turbine rotating shaft (8) which is transversely distributed;

a compressor impeller (20), a shaft seal sleeve (6) and a thrust spacer sleeve (7) which are distributed in a surrounding manner are respectively arranged on the radial outer wall of the turbine rotating shaft (8) from left to right;

the left side of the shaft sleeve (6) is in contact with the right side of the compressor impeller (20);

the right side of the shaft sleeve (6) is contacted with the left side of the thrust spacer sleeve (7);

wherein, the radial peripheral outer side of the shaft seal sleeve (6) is provided with an oil seal cover (4) in a surrounding way;

a thrust bearing plate (5) is arranged on the outer side of the radial periphery of the thrust spacer sleeve (7);

and the thrust bearing plate (5) is installed in the inner side cavity of the bearing body (1).

2. The high negative pressure resistant turbocharger compressor end sealing structure according to claim 1, wherein the left end face of the thrust bearing plate (5) is in contact with the right side face of the oil seal cover (4);

the right end face of the thrust bearing plate (5) is in contact with a right reference surface of the cavity on the inner side of the bearing body (1);

the radial outer side surface of the thrust bearing plate (5) is in clearance fit with the inner cavity of the bearing body (1);

the radial outer wall of the turbine rotating shaft (8) is in clearance fit with the shaft seal sleeve (6) and the thrust spacer sleeve (7) respectively;

the radial outer wall of the shaft sleeve (6) is in clearance fit with the right side surface of the oil seal cover (4).

3. The high negative pressure resistant turbocharger compressor end sealing structure according to claim 1, wherein an inner cavity of the bearing body (1) is circumferentially provided with an oil seal cover retainer ring accommodating groove (201);

the radial outer part of the annular oil sealing cover retainer ring (2) is embedded in the oil sealing cover retainer ring accommodating groove (201);

the right side of the radial inner part of the oil seal cover retainer ring (2) is contacted with the left side surface of the oil seal cover (4).

4. The high negative pressure resistant turbocharger compressor end sealing structure according to claim 1, wherein the left end radial outer side surface of the shaft seal sleeve (6) is circumferentially provided with two grooves (6-2) at the matching part with the oil seal cover (4);

and a compressor end sealing ring (9) is respectively arranged in the two grooves (6-2).

5. The high negative pressure resistant turbocharger compressor-end sealing structure according to claim 4, wherein each compressor-end sealing ring (9) has an opening;

two openings, horizontally staggered 180 degrees from each other.

6. The high negative pressure resistant turbocharger compressor end sealing structure according to claim 1, wherein the inner cavity of the bearing body (1) is circumferentially provided with an annular sealing ring groove at the radially inner side surface matched with the oil seal cover (4);

an oil seal cover sealing ring (3) is arranged in the sealing ring groove;

the oil sealing cover sealing ring (3) is an O-shaped ring.

7. The high negative pressure resistant turbocharger compressor-end sealing structure according to claim 1, wherein the shaft seal sleeve (6) comprises a shaft seal sleeve body (60);

the center of the shaft seal sleeve body (60) is provided with a rotating shaft (6-8) which transversely penetrates through;

the left end of the shaft seal sleeve body (60) is a convex part (601), and two sealing grooves (6-2) which are mutually spaced are arranged on the radial outer side surface of the convex part (601) in a surrounding way;

the right end of the shaft seal sleeve body (60) is provided with a supporting part (602);

the left end and the right end of the supporting part (602) are respectively provided with a front plane oil thrower (6-6) and a reverse plane oil thrower (6-7);

twelve positive oil slinging grooves (6-3) are distributed on the left side of the positive plane oil slinging disc (6-6) at equal intervals;

twelve anti-oil slinger grooves (6-4) are distributed on the right side of the anti-plane oil slinger (6-7) at equal intervals.

8. The high negative pressure resistant turbocharger compressor end sealing structure according to claim 1, wherein the oil seal cover (4) is a centrosymmetric structure;

in particular, the oil seal cover (4) comprises an oil seal cover body (40);

the right side of the oil sealing cover body (40) is of a cavity structure;

the oil sealing cover body (40) is internally provided with a shaft seal sleeve matching through hole (4-8) which transversely penetrates through;

the shaft envelope (6) is arranged on the inner side of the shaft envelope matching through hole (4-8);

the oil sealing cover body (40) is provided with an oblique angle boss (4-9) around the position close to the shaft seal sleeve matching through hole (4-8).

9. The high negative pressure resistant turbocharger compressor end sealing structure according to claim 8, wherein the right inner cavity of the oil cap body (40) is provided with a second oil cap oil guide wedge surface (4-6) which is obliquely distributed in a surrounding manner in the radial outer direction of the oblique angle boss (4-9);

a second oil seal cover vertical surface (4-5) is arranged in a right cavity of the oil seal cover body (40) in a surrounding manner;

the second oil seal cover oil guide wedge surface (4-6) on the oblique angle boss (4-9) is connected with the second oil seal cover vertical surface (4-5) through the oil guide grooves (4-7) distributed in a surrounding manner;

a first oil seal cover oil guide wedge surface (4-4) which is distributed in an inclined way and a first oil seal cover vertical surface (4-3) which is distributed vertically are arranged in the right cavity of the oil seal cover body (40) in a surrounding way;

the inner side of the first oil sealing cover vertical surface (4-3) is connected with the outer side of the first oil sealing cover oil guide wedge surface (4-4);

wherein, the right cavity of the oil seal cover body (40) is also provided with an oil seal cover transverse surface (4-2) which is transversely distributed;

the left side of the transverse surface (4-2) of the oil seal cover is connected with the outer side of the vertical surface (4-3) of the first oil seal cover;

wherein, the right end face of the oil seal cover body (40) is an oil seal cover bottom face (4-1) which is distributed in a surrounding way;

the inner side of the bottom surface (4-1) of the oil sealing cover is connected with the right side of the transverse surface (4-2) of the oil sealing cover.

10. The high negative pressure resistant turbocharger compressor end sealing structure according to claim 9, wherein the inner diameters of the first oil seal cover oil guide wedge surface (4-4) and the second oil seal cover oil guide wedge surface (4-6) are gradually increased from left to right;

the right side of the bevel lug boss (4-9) is provided with a bevel lug boss end face (4-10);

the outer side of the end surface (4-10) of the oblique angle boss is closer to the shaft seal sleeve matching through hole (4-8) than the inner side of the vertical surface (4-3) of the first oil seal cover.

Technical Field

The invention relates to the technical field of turbochargers, in particular to a high-negative-pressure-resistant turbocharger compressor end sealing structure.

Background

The function of the turbocharger is to provide more compressed air to the engine, so that the engine can burn more fuel, thereby generating more power, improving the fuel economy of the engine and reducing harmful components of exhaust gas discharged by the engine. The supercharger has the effects of energy conservation and environmental protection, so that the supercharging technology is comprehensively popularized in the field of engines.

For a turbocharger, when an engine runs at idle for a long time and an air filter or an air inlet pipeline is blocked, the oil pressure of engine oil entering the turbocharger is higher than the pressure of the back of an impeller wheel of a compressor for compressing air, and the air compressor end of the engine is in a negative pressure state and is prone to oil leakage.

In addition, when the engine crankcase breather is not smooth, the gas pressure in the supercharger intermediate body is too high, and under the low working condition of the engine, the pressure in the intermediate body is higher than the supercharging pressure, and at this time, the sealing ring of the supercharger piston cannot play a role in sealing, and the oil leakage of the supercharger is easily caused.

Therefore, a high negative pressure resistance is required at the compressor end of the turbocharger to prevent oil leakage from the turbocharger.

However, at present, there is no technology that can actually improve the negative pressure resistance at the compressor end of the turbocharger and ensure the use reliability of the turbocharger.

Disclosure of Invention

The invention aims to provide a high-negative-pressure-resistant turbocharger compressor end sealing structure aiming at the technical defects in the prior art.

Therefore, the invention provides a high negative pressure resistant turbocharger compressor end sealing structure which comprises a hollow bearing body;

wherein, the center of the inner cavity of the bearing body is provided with a turbine rotating shaft which is transversely distributed;

the radial outer wall of the turbine rotating shaft is respectively provided with a compressor impeller, a shaft sleeve and a thrust spacer sleeve which are distributed in a surrounding manner from left to right;

the left side of the shaft sleeve is in contact with the right side of the compressor impeller;

the right side of the shaft sleeve is contacted with the left side of the thrust spacer sleeve;

wherein, the radial peripheral outside of the shaft envelope is provided with an oil seal cover in a surrounding way;

a thrust bearing plate is arranged on the outer side of the radial periphery of the thrust spacer sleeve;

and the thrust bearing plate is installed in the inner side cavity of the bearing body.

Preferably, the left end face of the thrust bearing plate is in contact with the right side face of the oil seal cover;

the right end face of the thrust bearing plate is in contact with the right side reference face of the cavity on the inner side of the bearing body;

the radial outer side surface of the thrust bearing plate is in clearance fit with the inner cavity of the bearing body;

the radial outer wall of the turbine rotating shaft is in clearance fit with the shaft sleeve and the thrust spacer sleeve respectively;

the radial outer wall of the shaft sealing sleeve is in clearance fit with the right side face of the oil sealing cover.

Preferably, an oil seal cover retainer ring accommodating groove is circumferentially arranged in the inner cavity of the bearing body;

the radial outer part of the annular oil sealing cover retainer ring is embedded in the oil sealing cover retainer ring accommodating groove;

the right side of the radial inner part of the oil seal cover retainer ring is in contact with the left side surface of the oil seal cover.

Preferably, two grooves are circumferentially arranged on the radial outer side face of the left end of the shaft sleeve at the matching part of the shaft sleeve and the oil sealing cover;

and a compressor end sealing ring is respectively arranged in the two grooves.

Preferably, each compressor end sealing ring has an opening therein;

two openings, horizontally staggered 180 degrees from each other.

Preferably, an annular sealing ring groove is circumferentially arranged on the inner cavity of the bearing body at the radial inner side surface matched with the oil sealing cover;

an oil seal cover sealing ring is arranged in the sealing ring groove;

the sealing ring of the oil sealing cover is an O-shaped ring.

Preferably, the shaft seal cartridge comprises a shaft seal cartridge body;

the center of the shaft sleeve body is provided with a rotating shaft which transversely penetrates through the shaft sleeve body;

the left end of the shaft seal sleeve body is a convex part, and two sealing grooves which are mutually spaced are arranged on the radial outer side surface of the convex part in a surrounding manner;

the right end of the shaft sleeve body is a supporting part;

the left end and the right end of the supporting part are respectively provided with a front plane oil thrower and a back plane oil thrower;

twelve positive oil slinging grooves are distributed on the left side of the positive plane oil slinging disc at equal intervals;

twelve anti-oil slinging grooves are distributed on the right side of the anti-plane oil slinging disc at equal intervals.

Preferably, the oil seal cover is of a central symmetrical structure;

in particular, the oil seal cover comprises an oil seal cover body;

the right side of the oil seal cover body is of a cavity structure;

the oil seal cover body is internally provided with a shaft seal sleeve matching through hole which transversely penetrates through;

the shaft seal sleeve is matched with the inner side of the through hole and is provided with a shaft seal sleeve;

the oil sealing cover body is provided with an oblique angle boss around the shaft seal sleeve matching through hole.

Preferably, the right inner cavity of the oil seal cover body is provided with a second oil seal cover oil guide wedge surface which is distributed in an inclined manner in a surrounding manner in the radial outer side direction of the oblique angle boss;

a second oil seal cover vertical surface is arranged in the right cavity of the oil seal cover body in a surrounding manner;

the oil guide wedge surface of the second oil sealing cover on the oblique angle boss is connected with the vertical surface of the second oil sealing cover through the oil guide grooves distributed in a surrounding manner;

a first oil seal cover oil guide wedge surface which is distributed in an inclined way and a first oil seal cover vertical surface which is distributed vertically are arranged in the right cavity of the oil seal cover body in a surrounding way;

the inner side of the vertical surface of the first oil sealing cover is connected with the outer side of the oil guide wedge surface of the first oil sealing cover;

the right cavity of the oil seal cover body is also provided with a transverse surface of the oil seal cover which is transversely distributed;

the left side of the transverse surface of the oil sealing cover is connected with the outer side of the vertical surface of the first oil sealing cover;

the right end face of the oil seal cover body is the bottom face of the oil seal cover which is distributed in a surrounding mode;

the inner side of the bottom surface of the oil sealing cover is connected with the right side of the transverse surface of the oil sealing cover.

Preferably, the inner diameters of the oil guide wedge surfaces of the first oil seal cover and the second oil seal cover gradually increase from left to right;

the right side of the oblique angle boss is provided with an oblique angle boss end surface;

the outer side of the end face of the oblique angle boss is closer to the shaft seal sleeve matching through hole than the inner side of the vertical face of the first oil seal cover.

Compared with the prior art, the technical scheme provided by the invention has the advantages that the high-negative-pressure-resistant turbocharger compressor end sealing structure is scientific in structural design, the negative-pressure-resistant capacity of the turbocharger compressor end can be practically improved, the use reliability of the turbocharger is ensured, and the high-negative-pressure-resistant turbocharger compressor end sealing structure has great production practice significance.

The invention can improve the negative pressure resistance of the compressor end of the turbocharger on the premise of not changing the length of small parts of the turbocharger shaft system, not obviously increasing the manufacturing cost of the turbocharger and not influencing the reliability of the turbocharger, and is a compressor end sealing structure with easy processing of parts of a sealing shaft system and high negative pressure resistance.

Drawings

Fig. 1 is an overall sectional schematic view of a high negative pressure resistant turbocharger compressor end sealing structure provided by the present invention, located in a bearing body (i.e., an intermediate body) of a turbocharger;

FIG. 2 is an enlarged view of section A of FIG. 1 showing a high negative pressure resistant turbocharger compressor end seal configuration in accordance with the present invention;

fig. 3a is a schematic axial cross-sectional view of a shaft seal sleeve in the high negative pressure resistant turbocharger compressor end sealing structure provided by the invention;

FIG. 3b is a schematic view of the left side of the shaft sleeve in the high negative pressure resistant turbocharger compressor end seal configuration provided by the present invention;

FIG. 3c is a schematic view of the right side of the shaft sleeve in the high negative pressure resistant turbocharger compressor end seal structure of the present invention

Fig. 4 is a schematic view of an oil seal cover in the high negative pressure resistant turbocharger compressor end sealing structure provided by the invention.

Detailed Description

In order to make the technical means for realizing the invention easier to understand, the following detailed description of the present application is made in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant application and are not limiting of the application. It should be noted that, for convenience of description, only the portions related to the present application are shown in the drawings.

It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.

It should be noted that in the description of the present application, the terms of direction or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, which are merely for convenience of description, and do not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present application.

In addition, it should be noted that, in the description of the present application, unless otherwise explicitly specified and limited, the term "mounted" and the like should be interpreted broadly, and may be, for example, either fixedly mounted or detachably mounted.

The specific meaning of the above terms in the present application can be understood by those skilled in the art as the case may be.

Referring to fig. 1 to 4, the present invention provides a high negative pressure resistant turbocharger compressor end sealing structure, including a hollow bearing body 1;

wherein, the center of the inner cavity of the bearing body 1 is provided with a turbine rotating shaft 8 which is transversely distributed;

the radial outer wall of the turbine rotating shaft 8 is respectively provided with a compressor impeller 20, a shaft seal sleeve 6 and a thrust spacer sleeve 7 which are distributed in a surrounding manner from left to right;

the compressor wheel 20 is provided with a plurality of turbine blades.

The left side of the shaft envelope 6 is in contact with the right side of the compressor wheel 20;

the right side of the shaft envelope 6 is in contact with the left side of the thrust spacer 7;

wherein, the radial periphery outside of the shaft seal sleeve 6 is provided with an oil seal cover 4 in a surrounding way;

a thrust bearing plate 5 is arranged on the outer side of the radial periphery of the thrust spacer sleeve 7;

and the thrust bearing plate 5 is installed in the inner side cavity of the bearing body 1.

In the invention, in the concrete implementation, the left end surface of the thrust bearing plate 5 is contacted with the right side surface of the oil seal cover 4;

in the invention, in the concrete implementation, the right end face of the thrust bearing plate 5 is in contact with the right reference surface (namely the right side wall) of the cavity on the inner side of the bearing body 1;

in the concrete implementation, the radial outer side surface of the thrust bearing plate 5 is in clearance fit with the inner cavity of the bearing body 1.

In the invention, in a concrete implementation, an inner cavity of the bearing body 1 is circumferentially provided with an oil seal cover retainer ring accommodating groove 201;

the radial outer part of the annular oil seal cover retainer ring 2 is embedded in the oil seal cover retainer ring accommodating groove 201;

the right side of the radial inner part of the oil seal cover retainer ring 2 is contacted with the left side surface of the oil seal cover 4.

Therefore, with the present invention, the left end of the oil seal cover 4 can tightly press the oil seal cover 4 and the thrust bearing plate 5 against the right reference surface (i.e., the right sidewall) of the cavity inside the bearing body 1 via the oil seal cover retainer 2 (which is a resilient retainer).

In the invention, the radial outer wall of the turbine rotating shaft 8 is in clearance fit with the shaft seal sleeve 6 and the thrust spacer sleeve 7 respectively.

The radially outer wall of the shaft sleeve 6 (specifically, the outer wall of the support portion 602) is in clearance fit with the right side surface of the oil seal cover 4, with a second clearance 11 therebetween.

In the invention, in the concrete implementation, two grooves 6-2 are circumferentially arranged on the radial outer side surface of the left end of the shaft seal sleeve 6 at the matching part of the shaft seal sleeve and the oil seal cover 4;

a compressor end sealing ring 9 is respectively arranged in the two grooves 6-2;

in the concrete implementation, the compressor end sealing rings 9 are piston rings, the number of the compressor end sealing rings is two, and the material is W6Mo5Cr4V2, when the two compressor end sealing rings 9 are assembled, the openings on the two compressor end sealing rings 9 (one opening is arranged on one compressor end sealing ring 9) are preferably staggered by 180 degrees horizontally (namely, the two openings are staggered by 180 degrees, and the included angle between the central points of the two openings and the central point of the compressor end sealing ring 9 is 180 degrees), so that the lubricating oil can be further effectively prevented from entering the wheel back of the compressor impeller 20 under the condition that the air intake of the compressor is negative pressure.

In the present invention, in a specific implementation, the radially outer side surface of the thrust spacer 7 is in clearance fit with the inner side surface of the thrust bearing plate 5, and a first clearance 10 is provided between the two.

In the invention, in the concrete implementation, an annular sealing ring groove (specifically an O-shaped ring groove) is circumferentially arranged on the inner side surface of the inner cavity of the bearing body (namely the intermediate body) 1 in the radial direction matched with the oil sealing cover 4;

in the sealing ring groove, an oil seal cover sealing ring 3 is arranged.

It should be noted that, compared with the prior art in which the O-ring groove is disposed on the outer diameter surface of the oil seal cover, the oil storage space of the oil seal cover is increased, so that the lubricating oil can be effectively prevented from entering the second gap 11 (the gap between the oil seal cover 4 and the shaft seal sleeve 6) and oil leakage can be prevented.

In the concrete implementation, the oil seal cover sealing ring 3 is an O-shaped ring.

In particular, the second gap 11 is not easily too large, controlled by component tolerances, and the minimum tolerance is slightly larger than the axial gap, in this example, the transverse width of the second gap 11 is in the range of 0.17mm to 0.3 mm.

It should be noted that, for the specific implementation of the present invention, the small shafting parts are all assembled on the bearing body 1, the bearing body 1 is a support body of the supercharger component and is matched with the oil seal cover sealing ring 3 to prevent the lubricating oil from leaking to the compressor end from the gap between the oil seal cover 4 and the bearing body 1, and the bearing body 1 bears the mechanical load of the rotor component and also bears the thermal load transmitted from the turbine end.

In the invention, the thrust bearing plate 5 is used for limiting the axial movement of the turbine rotating shaft 8, and preventing the impeller of the compressor from rubbing against the volute and the impeller of the turbine from rubbing against the turbine box.

For the invention, the thrust spacer 7 rotates along with the turbine rotating shaft 8, and is used for throwing part of lubricating oil flowing out of the thrust bearing plate 5 into the oil return cavity of the bearing body 1.

For the invention, in concrete realization, the turbine rotating shaft 8 drives the thrust spacer sleeve 7, the shaft seal sleeve 6 and the compressor impeller 20 which are arranged on the turbine rotating shaft 8 in a penetrating way to rotate, and also bears various loads and vibration loads when the rotor works, so that alternating stress generated by bending and torsion is borne.

Specifically, the compressor impeller 20 rotates along with the turbine rotating shaft 8 at a circumferential speed, and the gas pressure generated by the compressor impeller 20 acting on air can prevent lubricating oil from leaking from the sealing ring 9 to the compressor end and also bear loads such as centrifugal force, blade vibration, gas pressure and the like generated by the rotation of the impeller.

In particular, the compressor end sealing ring 9 is used for preventing lubricating oil of the bearing from entering a through flow part at the compressor end of the supercharger, preventing air of the compressor from entering a lubricating oil cavity of the supercharger and ensuring the normal work of the supercharger.

In the present invention, in a specific implementation, the shaft seal sleeve 6 includes a shaft seal sleeve body 60;

it should be noted that, for the present invention, the middle section of the shaft seal sleeve body 60 is a convex structure;

the center of the shaft sleeve body 60 is provided with a rotating shaft 6-8 transversely penetrating;

the left end of the shaft seal sleeve body 60 is a convex part 601, and two sealing grooves 6-2 which are mutually spaced are arranged on the radial outer side surface of the convex part 601 in a surrounding manner;

the right end of the shaft sleeve body 60 is a support part 602;

the left end and the right end of the supporting part 602 are respectively provided with a front plane oil thrower 6-6 and a reverse plane oil thrower 6-7;

twelve positive oil slinger grooves 6-3 are distributed on the left side of the positive plane oil slinger 6-6 at equal intervals;

twelve anti-oil slinger grooves 6-4 are distributed on the right side of the anti-plane oil slinger 6-7 at equal intervals;

in concrete implementation, the forward oil throwing groove 6-3 and the reverse oil throwing groove 6-4 are both arc-shaped oil throwing grooves, the radial outer sides of the arc-shaped oil throwing grooves are opened (namely normally opened), the right side of the reverse oil throwing groove 6-4 is opened (unsealed), and the left side of the forward oil throwing groove 6-3 is opened (unsealed).

It should be noted that, in the present invention, due to the oil slinger grooves, a convex tooth is formed between any two adjacent oil slinger grooves, so that the front plane oil slinger 6-6 and the back plane oil slinger 6-7 are tooth-shaped planes with twelve teeth.

It should be noted that the shape and structure of the forward oil slinger 6-3 and the reverse oil slinger 6-4 are the same, but are respectively located on the forward plane oil slinger 6-6 and the reverse plane oil slinger 6-7 which are oppositely arranged.

In the concrete implementation, the left side and the right side of the shaft seal sleeve body 60 are respectively provided with a shaft seal sleeve and impeller contact end surface 6-1 and a shaft seal sleeve and thrust bearing plate contact end surface 6-5.

It should be noted that, based on the above statements, for the present invention, the shaft seal sleeve 6 includes a shaft seal sleeve body 60, a shaft seal sleeve and impeller contact end face 6-1, two seal grooves 6-2, a forward oil slinger groove 6-3, a reverse oil slinger groove 6-4, a shaft seal sleeve and thrust bearing plate contact end face 6-5, a forward plane oil slinger 6-6 and a reverse plane oil slinger 6-7.

It should be noted that, for the present invention, the front plane oil thrower 6-6 and the reverse plane oil thrower 6-7 can throw out part of the lubricating oil; the positive oil throwing groove 6-3 and the negative oil throwing groove 6-4 do work on the lubricating oil entering the oil throwing grooves through the rotation effect, the lubricating oil is well thrown out, and the oil quantity entering the position of the end sealing ring 9 of the compressor is effectively reduced.

In the invention, the oil seal cover 4 is a centrosymmetric structure;

in particular, the oil seal cover 4 comprises an oil seal cover body 40;

the right side of the oil seal cover body 40 is of a cavity structure;

the oil sealing cover body 40 is internally provided with a shaft seal sleeve matching through hole 4-8 which transversely penetrates through;

the shaft envelope is matched with the inner sides of the through holes 4-8 and is provided with a shaft envelope 6;

the oil sealing cover body 40 is provided with an oblique angle boss 4-9 around the shaft seal sleeve matching through hole 4-8.

In the concrete implementation, a second oil sealing cover oil guide wedge surface 4-6 which is distributed in an inclined manner is arranged in the right inner cavity of the oil sealing cover body 40 in the radial outer side direction of the oblique angle boss 4-9 in a surrounding manner;

a second oil seal cover vertical surface 4-5 is arranged in the right cavity of the oil seal cover body 40 in a surrounding manner;

the second oil seal cover oil guide wedge surface 4-6 on the oblique angle boss 4-9 is connected with the second oil seal cover vertical surface 4-5 through the oil guide grooves 4-7 distributed in a surrounding manner;

wherein, the oil guide grooves 4-7 are grooves with arc-shaped axial cross sections, in particular to oil guide grooves in a fillet form.

In the concrete implementation, a first oil seal cover oil guide wedge surface 4-4 which is distributed in an inclined manner and a first oil seal cover vertical surface 4-3 which is distributed vertically are arranged in a right cavity of the oil seal cover body 40 in a surrounding manner;

the inner side (namely the lower side) of the first oil sealing cover vertical surface 4-3 is connected with the outer side of the first oil sealing cover oil guide wedge surface 4-4;

wherein, the right cavity of the oil seal cover body 40 is also provided with an oil seal cover transverse surface 4-2 which is transversely distributed;

the left side of the transverse surface 4-2 of the oil seal cover is connected with the outer side (namely the upper side) of the vertical surface 4-3 of the first oil seal cover;

wherein, the right end face of the oil seal cover body 40 is the oil seal cover bottom face 4-1 which is distributed in a surrounding way;

the inner side (i.e., the lower side) of the oil cap bottom surface 4-1 is connected with the right side of the oil cap cross surface 4-2.

In the concrete implementation, the inner diameters of the first oil seal cover oil guide wedge surface 4-4 and the second oil seal cover oil guide wedge surface 4-6 are gradually increased from left to right.

In the concrete implementation, the right side of the oblique angle boss 4-9 is provided with an oblique angle boss end face 4-10;

the outer side of the end surface 4-10 of the oblique angle boss is closer to the shaft sleeve matching through hole 4-8 (i.e. lower position) than the inner side of the first oil sealing cover vertical surface 4-3, so as to ensure that the shaft sleeve 6 can throw oil onto the oil sealing cover transverse surface 4-2 which is farther away, so that the lubricating oil can be prevented from splashing into the second gap 11, and a part of the lubricating oil left on the oil sealing cover transverse surface 4-2 flows to the bottom (i.e. right end) of the oil sealing cover 4, and a part of the lubricating oil which splashes to the second oil sealing cover oil guide wedge surface 4-6 flows into the oil guide groove 4-7 along the first oil sealing cover vertical surface 4-3, the first oil sealing cover oil guide wedge surface 4-4 and the second oil sealing cover vertical surface 4-5, so that the lubricating oil which enters the oil guide groove 4-7 can smoothly flow to the bottom (i.e. right end) of the oil sealing cover, the lubricating oil can be prevented from flowing into the second gap 11, and can be well prevented from flowing into a compressor end (located at the compressor end in the left side direction of the turbine rotating shaft, namely, at the compressor end in the direction of the compressor impeller 20) from the gap between the two sealing rings 9 under the condition that the engine is in a low working condition or is in idle running for a long time to cause negative pressure of air inlet of the engine, so that oil leakage is prevented.

Based on the above discussion, the oil sealing cover 4 integrally includes an oil sealing cover body 40, an oil sealing cover bottom surface 4-1, an oil sealing cover transverse surface 4-2, a first oil sealing cover vertical surface 4-3, a first oil sealing cover oil guide wedge surface 4-4, a second oil sealing cover vertical surface 4-5, a second oil sealing cover oil guide wedge surface 4-6, an oil guide groove 4-7, a shaft seal sleeve matching through hole 4-8, an oblique angle boss 4-9, and an oblique angle boss end surface 4-10.

Compared with the prior art, the high negative pressure resistant turbocharger air compressor end sealing structure provided by the invention has the following beneficial effects:

1. for the invention, the positive and negative surfaces (namely the left and right sides) of the shaft seal sleeve 6 are respectively provided with an oil slinger structure (namely a positive plane oil slinger 6-6 and a reverse plane oil slinger 6-7) which are uniformly provided with twelve arc-shaped oil slingers and a tooth-shaped plane with twelve teeth, waste gas drives the supercharger to operate in the process of idling or high-speed operation of a diesel engine, lubricating oil entering the oil slinger grooves can be thrown out by the shaft seal sleeve 6 arranged on the turbine rotating shaft 8 through the rotating action, the oil quantity entering the sealing ring 9 at the end of the compressor is effectively reduced, and the lubricating oil thrown out by the shaft seal sleeve 6 can be guided back to an oil return cavity of the bearing body 1 (namely a cavity formed between the right side of the oil seal cover 4 and the left side inside the bearing body 1) through two oil guide wedge surfaces, so as to improve the negative pressure resistance of the compressor.

2. According to the invention, on the premise of not changing the length of shafting parts, the shaft seal sleeve can be provided with two separated piston sealing ring grooves (namely two grooves 6-2 for installing the compressor end sealing ring 9), when the two piston sealing rings (namely two compressor end sealing rings 9) are assembled, the openings on the two compressor end sealing rings 9 are horizontally staggered by 180 degrees, under the condition that the air inlet of the compressor is negative pressure, lubricating oil can be further effectively prevented from entering the wheel back of the compressor impeller 20, and the processing is convenient.

3. For the invention, twelve arc oil throwing grooves which are uniformly distributed on the front surface and the back surface of the shaft seal sleeve 6 can be molded by die sinking and casting, the structure is simple, the processing is convenient, and the manufacturing cost of the supercharger is greatly reduced.

Compared with the prior art, the high-negative-pressure-resistant turbocharger compressor end sealing structure provided by the invention is scientific in structural design, can practically improve the negative-pressure-resistant capability of the turbocharger compressor end, ensures the use reliability of the turbocharger, and has great production practice significance.

The invention can improve the negative pressure resistance of the compressor end of the turbocharger on the premise of not changing the length of small parts of the turbocharger shaft system, not obviously increasing the manufacturing cost of the turbocharger and not influencing the reliability of the turbocharger, and is a compressor end sealing structure with easy processing of parts of a sealing shaft system and high negative pressure resistance.

The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, various modifications and decorations can be made without departing from the principle of the present invention, and these modifications and decorations should also be regarded as the protection scope of the present invention.