A double-sided blade guide vane seal structure for a compressor

Abstract

The application discloses a double-end blade drainage type compressor sealing structure, which comprises a hollow bearing body; the inner cavity center position of the bearing body is provided with a transversely distributed rotor shaft; the radial outer wall of the rotor shaft is respectively provided with a circumferentially distributed compressor impeller, a double-end blade drainage type shaft sealing sleeve and a drainage type thrust bearing from left to right; the radial outer side of the four sides of the double-end blade drainage type shaft sealing sleeve is circumferentially provided with a drainage type oil sealing cover; the left end radial outer side surface of the double-end blade drainage type shaft sealing sleeve is circumferentially provided with a plurality of sealing ring grooves at the matching position of the drainage type oil sealing cover; the right end radial outer side surface of the double-end blade drainage type shaft sealing sleeve is circumferentially provided with a drainage type boss; the drainage type boss is circumferentially provided with a first drainage type groove, an inclined oil guide groove and an oil guide ring groove. The double-end blade drainage type compressor sealing structure can effectively improve the sealing performance of the turbocharger compressor.

Description

Technical Field

[0001] This invention relates to the field of turbocharger technology, and in particular to a sealing structure for a double-ended blade induced draft compressor. Background Technology

[0002] The function of a turbocharger is to provide more compressed air to the engine, enabling it to burn more fuel, thereby generating more power, improving fuel economy, and reducing harmful components in engine exhaust emissions. It is precisely because of the energy-saving and environmentally friendly effects of turbochargers that turbocharging technology has been widely adopted in the engine industry.

[0003] For turbochargers, when the engine is idling for a long time or operating at low speed, the boost pressure is low, or even the compressor is under negative pressure, which can cause oil leakage. This raises the question of how to improve the compressor's resistance to negative pressure.

[0004] Currently, existing technologies improve compressor sealing performance by optimizing the structure, quantity, and materials of compressor-end components, increasing the number of sealing rings, or adjusting the materials and specifications of the sealing rings. However, for small turbochargers, the sealing structure at the compressor end is extremely compact, so existing technical solutions can no longer meet the needs of further improving compressor sealing performance.

[0005] Figure 1 , Figure 2 The diagram shows a typical existing turbocharger. The turbocharger shown in the figure mainly includes a compressor volute 1, a bearing housing 2, a turbine housing 3, a shaft seal sleeve 4, a sealing ring 5, an oil seal cap 6, a thrust bearing 7, a shaft end nut 8, a compressor impeller 9, a thrust plate 10, a rotor shaft 11, and a turbine impeller 12.

[0006] The compressor end seal is ensured by the pressure balance on both sides of the compressor sealing ring 5, which further reduces the accumulation of lubricating oil at the compressor end and is crucial for improving the compressor's sealing performance.

[0007] Currently, there are generally two situations that can lead to oil leakage at the compressor end. One is when the compressor end is under negative pressure. That is, air enters from the compressor volute inlet 101 through the rotation of the compressor impeller 9, passes through the compressor volute diffuser section 102, and enters the compressor volute cavity 103. When the compressor impeller 9 is in a low-speed condition for a long time, due to the low boost pressure, or even the compressor under negative pressure, the lubricating oil inside the bearing housing 2, which is under positive pressure, leaks into the compressor volute cavity 103 through the sealing ring 5, causing compressor oil leakage. The more lubricating oil accumulates at the compressor end, the more serious the oil leakage will be.

[0008] Secondly, excessively high internal lubricating oil pressure in bearing housing 2 leads to excessive lubricating oil entering the turbocharger, causing oil leakage. Lubricating oil enters bearing housing 2 through inlet 201, then passes through oil distribution channel 2021 into bearing distribution channel 2031 and thrust bearing inlet channel 701, before entering the oil chamber 204 within the bearing housing and exiting the turbocharger through return port 205. When the oil level in the oil chamber 204 exceeds the discharge capacity of return port 205, lubricating oil rapidly accumulates within bearing housing 2. When the oil level exceeds the maximum load-bearing capacity of the oil chamber 204, compressor oil leakage occurs.

[0009] Therefore, there is an urgent need to develop a technology that can solve the above-mentioned technical problems. Summary of the Invention

[0010] The purpose of this invention is to address the technical deficiencies of existing technologies by providing a sealing structure for a double-ended blade induced flow compressor.

[0011] Therefore, the present invention provides a double-bladed induced flow compressor sealing structure, including a hollow bearing body, a double-bladed induced flow shaft seal sleeve, a sealing ring, an induced flow oil seal cap, and an induced flow thrust bearing;

[0012] At the center of the inner cavity of the bearing housing, there is a laterally distributed rotor shaft;

[0013] The radial outer wall of the rotor shaft is equipped with a compressor impeller, a double-ended blade induced flow shaft seal, and an induced flow thrust bearing, which are arranged in a ring from left to right.

[0014] Among them, a drain-type oil cap is installed around the radial periphery of the double-ended blade drain-type shaft seal sleeve;

[0015] On the radially outer side of the left end of the double-ended blade drainage shaft seal sleeve, multiple sealing ring grooves are arranged around the mating point with the drainage oil seal cap.

[0016] Each sealing ring groove contains a sealing ring.

[0017] The center of the double-ended blade drainage shaft seal sleeve is provided with a transverse through shaft seal sleeve mounting hole;

[0018] The outer wall of the right end of the double-ended blade drainage shaft seal is provided with an outwardly protruding drainage boss.

[0019] The inner side of the left end of the drainage boss is provided with a first drainage groove around the double-ended blade drainage shaft seal.

[0020] The radial perimeter of the drainage boss is surrounded by a concave, sloping oil guide groove.

[0021] The right end of the drainage boss has an oil guide ring groove arranged around its radial perimeter in a circular direction.

[0022] As can be seen from the technical solution provided by the present invention above, compared with the prior art, the present invention provides a double-ended blade induced flow compressor sealing structure. Its structural design is scientific and can effectively improve the sealing performance of turbocharger compressors. It is especially suitable for compact turbocharger structures with limited space. The technical solution of the present invention can better play its role in improving the sealing performance of compressors and has significant practical significance.

[0023] The technical solution of this invention, through the cooperation of multiple components including a double-ended blade flow-draining shaft seal sleeve, a sealing ring, a flow-draining oil seal cap, and a flow-draining thrust bearing, can effectively reduce the degree of lubricating oil accumulation at the compressor end and improve the sealing performance of the turbocharger compressor, which has significant practical significance and application value. Attached Figure Description

[0024] Figure 1 A schematic diagram of the structure of a typical existing turbocharger. Figure 1 ;

[0025] Figure 2 A schematic diagram of the structure of a typical existing turbocharger. Figure 2 ,yes Figure 1 A magnified view of a portion of the image;

[0026] Figure 3 A schematic diagram of a double-ended blade induced flow compressor sealing structure provided by the present invention, as shown in Embodiment 1;

[0027] Figure 4a A three-dimensional structural diagram of the double-ended blade induced-flow shaft seal sleeve used in the double-ended blade induced-flow compressor sealing structure provided by the present invention. Figure 1 ;

[0028] Figure 4b A three-dimensional structural diagram of the double-ended blade induced-flow shaft seal sleeve used in the double-ended blade induced-flow compressor sealing structure provided by the present invention. Figure 2 ;

[0029] Figure 4c A schematic diagram of the planar structure design of the double-ended blade induced-flow shaft seal sleeve used in an embodiment of the double-ended blade induced-flow compressor sealing structure provided by the present invention. Figure 1 This diagram is a schematic representation of looking up from below.

[0030] Figure 4d A schematic diagram of the planar structure design of the double-ended blade induced-flow shaft seal sleeve used in an embodiment of the double-ended blade induced-flow compressor sealing structure provided by the present invention. Figure 2 ;

[0031] Figure 4e A schematic diagram of the planar structure design of the double-ended blade induced-flow shaft seal sleeve used in an embodiment of the double-ended blade induced-flow compressor sealing structure provided by the present invention. Figure 3 This diagram is a top-down view.

[0032] Figure 5 A schematic diagram of the structure of the drain-type oil sealing cap in a double-ended blade drain-type compressor sealing structure provided by the present invention;

[0033] Figure 6 A schematic diagram of the structure of the flow-guiding thrust bearing in a double-ended blade flow-guiding compressor sealing structure provided by the present invention;

[0034] Figure 7 A schematic diagram of Embodiment 2 of a double-ended blade induced flow compressor sealing structure provided by the present invention;

[0035] Figure 8 A schematic diagram of the second embodiment of the drain-type oil sealing cap in a double-ended blade drain-type compressor sealing structure provided by the present invention;

[0036] In the diagram, 1 is the compressor volute, 2 is the bearing housing, 3 is the turbine housing, 4 is the shaft seal sleeve, 5 is the sealing ring, 6 is the oil seal cap, 7 is the thrust bearing, 8 is the shaft end nut, 9 is the compressor impeller, 10 is the thrust vane, 11 is the rotor shaft, and 12 is the turbine impeller.

[0037] Among them, 101 is the compressor volute inlet, 102 is the compressor volute diffuser section, 103 is the compressor volute cavity, 104 is the compressor impeller back clearance, 105 is the shaft seal sleeve installation fit clearance, and 106 is the labyrinth seal clearance.

[0038] 201 is the lubricating oil inlet, 2021 is the bearing housing oil distribution channel, 2031 is the bearing housing oil distribution channel, 204 is the bearing housing oil cavity, and 205 is the bearing housing oil return port.

[0039] 41 is a double-ended blade drainage shaft seal sleeve, 4101 is a variable width inclined blade, 4102 is a variable width full-through oil drainage groove, 4103 is a sloped oil drainage groove, 4104 is a constant width inclined blade, 4105 is a constant width full-through oil drainage groove, 4106 is a sealing ring groove, 4107 is a thrust bearing mating surface, and 4108 is an oil drainage ring groove.

[0040] 61 is a drain-type oil cap, 6102 is an oil collection chamber, 6101 is an oil guide flange, and 6103 is an oil guide slope;

[0041] 71 is a flow-through type thrust bearing, 701 is the thrust bearing oil inlet passage, 7101 is the oil guide chamber, 7102 is the oil reservoir chamber, and 7103 is the oil drain ring groove. Detailed Implementation

[0042] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0043] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0044] In the description of this patent, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "setting" should be interpreted broadly. For example, they can refer to a fixed connection or setting, a detachable connection or setting, or an integral connection or setting. Those skilled in the art can understand the specific meaning of the above terms in this patent according to the specific circumstances.

[0045] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0046] Example 1.

[0047] See Figure 1 , Figure 3 , Figures 4a to 4e , Figure 5 and Figure 6 The present invention provides a sealing structure for a double-bladed induced flow compressor, including a hollow bearing body 2, a double-bladed induced flow shaft seal sleeve 41, a sealing ring 5, an induced flow oil seal cap 61, and an induced flow thrust bearing 71.

[0048] It should be noted that this invention is applied to Figure 1 The turbocharger shown has been further optimized and improved in terms of its shaft seal, oil cover and thrust bearing, resulting in a double-ended blade induced flow shaft seal 41, an induced flow oil cover 61 and an induced flow thrust bearing 71.

[0049] At the center of the inner cavity of the bearing body 2, there is a laterally distributed rotor shaft 11;

[0050] The radial outer wall of the rotor shaft 11 is equipped with a compressor impeller 9, a double-ended blade induced flow shaft seal sleeve 41 and an induced flow thrust bearing 71, which are arranged in a ring from left to right.

[0051] Among them, a drainage-type oil cap 61 is installed around the radial periphery of the double-ended blade drainage-type shaft seal sleeve 41.

[0052] On the radially outer side of the left end of the double-ended blade drainage shaft seal sleeve 41, at the point of mating with the drainage oil seal cap 61, a plurality of sealing ring grooves 4106 (not limited to two) are arranged around it.

[0053] Each sealing ring groove 4106 contains a sealing ring 5.

[0054] In this invention, specifically, a transversely penetrating shaft seal mounting hole 4100 is provided at the center of the double-ended blade drainage shaft seal sleeve 41.

[0055] It should be noted that the shaft seal mounting hole 4100 is used to install the rotor shaft 11 (i.e., turbine shaft) at the compressor end of the turbocharger.

[0056] The outer wall of the left end of the double-ended blade drainage shaft seal 41 is provided with two sealing ring grooves 2 spaced vertically around it.

[0057] The outer wall of the right end of the double-ended blade drainage shaft seal 41 is provided with an outwardly protruding drainage boss 400.

[0058] The inner side of the left end of the drainage boss 400 is provided with a first drainage groove 401 around the double-ended blade drainage shaft seal 41.

[0059] The radial periphery of the drainage boss 400 is surrounded by a concave sloping oil guide groove 4103.

[0060] The right end of the drainage boss 400 has an oil guide ring groove 4108 arranged around its radial perimeter along the circumferential direction.

[0061] In this invention, specifically, the right side of the center of the drainage boss 400 is the thrust bearing mating surface 4107.

[0062] In this invention, specifically, the left end of the drainage boss 400 has multiple variable-width oblique blades 4101 that protrude to the left evenly along the circumferential direction around its four edges.

[0063] Between any two adjacent variable width inclined blades 4101, there is a blade variable width full-through oil guiding groove 4102;

[0064] The variable width full-through oil guide groove 4102 of the blade is a groove with the same width at the inlet and outlet;

[0065] The blade has a variable width, fully-through oil guide groove 4102, which is connected to the first guide groove 401.

[0066] In practice, the variable width full-through oil guide groove 4102 of the blade is a groove with different widths at the inlet and outlet (i.e., the openings on the inner and outer sides).

[0067] In practice, the inlet width of the variable width full-through oil guide channel 4102 is smaller than its outlet width.

[0068] In practice, the blade variable width full-through oil guide groove 4102 has openings on both the inner and outer sides (i.e., it is not sealed).

[0069] It should be noted that, for the present invention, the purpose of setting the variable width inclined blade 4101 is to create a pressure difference at both ends of the variable width full-through oil guide groove 4102 where the widths of the inlet and outlet (i.e., the openings on the inner and outer sides) are different. This causes the lubricating oil to flow through the self-priming channel (i.e., the inner end opening of the variable width full-through oil guide groove 4102) and the oil discharge channel (i.e., the outer end opening of the variable width full-through oil guide groove 4102), so that the lubricating oil near the sealing ring groove 4106 and the sealing ring mounted thereon is drawn out of the shaft seal sleeve, thereby improving the sealing performance of the shaft seal sleeve.

[0070] In specific implementation, the tilting direction of the variable width inclined blade 4101 is backward tilting along the rotation direction X of the shaft sleeve;

[0071] In specific implementation, the tilt angle of each variable width inclined blade 4101 is α;

[0072] The value of α satisfies the condition: 0°≤α≤65°;

[0073] In practice, the maximum diameter end face (i.e. the outermost end face with the largest width) of the variable width inclined blade 4101 is provided with a sloping oil guide ring groove 4103, which is conducive to guiding the lubricating oil out of the shaft seal sleeve.

[0074] In specific implementation, the slope angle of the inclined oil guide ring groove 4103 is 15° to 45°;

[0075] In this invention, specifically, the right periphery of the drainage boss 400 is uniformly distributed with a plurality of downwardly protruding oblique blades 4104 of equal width along the circumferential direction.

[0076] Between any two adjacent equal-width inclined blades 4104, there is a blade equal-width full-through oil guiding groove 4105;

[0077] The blade has a full-width, continuous oil guide groove 4105 that is connected to the oil guide ring groove 4108.

[0078] In practice, the blade's equal-width, fully-through oil guiding groove 4105 is a groove with the same width at both the inlet and outlet (i.e., the openings on both the inner and outer sides).

[0079] In practice, the inner and outer sides of the blade-width, fully-through oil guiding groove 4105 are open (i.e., not sealed).

[0080] It should be noted that, for the present invention, the purpose of setting the equal-width inclined blade 4104 is to throw the lubricating oil in the oil guide ring groove 4108 out of the shaft seal sleeve through the equal-width full-through oil guide groove 4105 of the blade, thereby reducing the accumulation of lubricating oil in the shaft seal sleeve and improving the sealing performance of the shaft seal sleeve.

[0081] In this invention, specifically, the width of the oil guide ring groove 4108 is not greater than one-fifth of the width of the equal-width full-through oil guide channel 4105.

[0082] In this invention, specifically, the blade type of the variable width inclined blade 4101 includes any one of the following: arc shape, triangle, trapezoid, and parabola. The purpose is to make the pressure difference between the two ends of the variable width full-through oil guide groove 4102 more diverse and stable by using blades composed of different blade types.

[0083] It should be noted that the sealing ring 5 is a separate double-ring structure. Based on the structural dimensions of the double-ended blade drainage shaft seal sleeve 41 and the drainage oil seal cap 61, multiple sealing rings can be set to improve the sealing performance of the mechanism.

[0084] In specific implementation, the side clearance of the axial fit between the sealing ring 5 and the sealing ring groove 4106 of the double-ended blade drainage shaft seal sleeve 41 is no more than 0.05mm, and the material hardness of the sealing ring 5 is greater than that of the drainage oil seal cap 61.

[0085] In specific implementation, the shaft seal sleeve installation clearance 105 between the double-ended blade drainage shaft seal sleeve 41 and the drainage oil seal cover 61 is no greater than 0.20mm, and the labyrinth seal clearance 106 formed by the two is controlled to be no greater than one-fifth of the minimum width of the blade variable width full-through oil guiding drainage groove 4102;

[0086] In this invention, specifically, the drain-type oil sealing cap 61 includes an oil collecting chamber 6102, an oil guiding flange 6101, and an oil guiding ramp 6103;

[0087] On the radially inner side of the right end of the drain-type oil sealing cap 61, there is an oil collection cavity 6102 arranged in a ring.

[0088] An arc-shaped oil guide flange 6101 and an oil guide ramp 6103 are provided on the left side of the oil collecting cavity 6102;

[0089] In practice, the oil guide ramp 6103 is connected to the lower end of the oil guide flange 6101.

[0090] In practice, the center of the oil guide flange 6101 of the flow-draining oil cover 61 is within the area covered by the inclined oil guide groove 4103 of the double-ended blade flow-draining shaft seal sleeve. It is used to guide the lubricating oil thrown out by the equal-width inclined blades 4104 into the inclined oil guide groove 4103, and finally guide the lubricating oil along the oil guide ramp to the oil cavity 204 in the bearing body, thereby reducing the degree of lubricating oil accumulation at the compressor end.

[0091] In this invention, specifically, the flow-guiding thrust bearing 71 includes an oil guiding chamber 7101, an oil storage chamber 7102, and an oil drain ring groove 7103.

[0092] An oil reservoir 7102 is provided at the radial center position of the right end of the flow-type thrust bearing 71;

[0093] The upper part of the oil storage chamber 7102 is provided with three oil guide chambers 7101 that are spaced apart;

[0094] The oil guiding cavity 7101 and the oil storage cavity 7102 are interconnected;

[0095] An arc-shaped oil drain ring groove 7103 is provided on the outer edge of the right side of the oil storage chamber 7102.

[0096] In practice, the maximum diameter of the oil drain ring groove 7103 is not less than the maximum diameter of the thrust bearing mating surface 4107 of the double-ended blade drainage shaft seal sleeve 41.

[0097] In a specific implementation, an annular thrust plate 10 is also provided on the radial outer wall of the rotor shaft 11, on the right side of the flow-draining thrust bearing 71.

[0098] In practice, the maximum diameter of the oil drain ring groove 7103 of the flow-type thrust bearing 71 is not less than the maximum diameter of the thrust plate 10.

[0099] In this invention, specifically, the right end of the rotor shaft 11 is fixedly connected to the center position of the turbine impeller 12 in the turbocharger.

[0100] In this invention, specifically, multiple turbine blades are installed on the compressor impeller 9.

[0101] In practice, the compressor impeller 9 is fixed to the left end of the rotor shaft 11 by the shaft end nut 8.

[0102] In this invention, specifically, the left side of the double-ended blade flow-guiding shaft seal sleeve 41 is in contact with the right side of the compressor impeller 9;

[0103] The right side of the double-ended blade drainage shaft seal 41 is in contact with the left side of the drainage thrust bearing 71.

[0104] It should be noted that, in this invention, a labyrinth seal and lubricating oil drainage path are constructed by combining components such as a double-ended blade drainage shaft seal sleeve, a drainage oil sealing cap and sealing ring, and a drainage thrust bearing. This allows the lubricating oil flowing through the compressor end to be quickly carried away from the compressor end, reducing the degree of lubricating oil accumulation in the compressor shaft seal sleeve area, thereby improving the compressor's sealing performance.

[0105] See Figure 3 The present invention uses a compressor sealing structure composed of a double-ended blade flow-draining shaft seal sleeve 41, a sealing ring 5, a flow-draining oil seal cap 61, and a flow-draining thrust bearing 71 to significantly reduce the accumulation of lubricating oil at the compressor end, thereby improving the compressor's sealing performance. Figures 4a to 4e The diagram shows the structure of a double-ended blade drainage-type shaft seal. Figure 5 The diagram shows the structure of a drain-type oil seal cap. Figure 6 The diagram shows the structure of a flow-driven thrust bearing.

[0106] In this invention, specifically, the number of variable-width inclined blades 4101 and the number of equal-width inclined blades 4104 in the double-ended blade drainage shaft seal 41 are the same, and the number of blades is not less than 10.

[0107] In this invention, specifically, the variable width inclined blade 4101 of the double-ended blade drainage shaft seal 41 is tilted in the direction of backward tilt along the rotation direction X of the double-ended blade drainage shaft seal 41.

[0108] The inclined direction of the equal-width oblique blade 4104 is forward along the rotation direction of the double-ended blade drainage shaft seal 41.

[0109] It should be noted that, for the present invention, for multiple variable-width oblique blades, an oil guide ring groove is provided on the end face of the blade with the largest diameter; for multiple equal-width oblique blades, an oil guide ring groove is provided on the end face of the blade with the smallest diameter.

[0110] Example 2.

[0111] For the present invention, see Embodiment 2, see Figure 7 , Figure 8 As shown, the shape of the oil guide flange 6101 has been further optimized and improved. The structural design requirements of other parts are the same as those in Embodiment 1 above.

[0112] Specifically, the oil guide flange 6101 has two or more pointed bosses, and the center of all its flanges is within the range covered by the inclined oil guide groove 4103 of the double-ended blade flow-type shaft seal 41. This is used to guide the lubricating oil thrown out by the equal-width inclined blades 4104 into the inclined oil guide groove 4103, and finally guide the lubricating oil along the oil guide ramp 6103 to the oil cavity 204 in the bearing body.

[0113] It should be noted that, in this invention, a labyrinth seal and lubricating oil drainage path are constructed by combining components such as a double-ended blade drainage shaft seal sleeve, a drainage oil sealing cap and sealing ring, and a drainage thrust bearing. This allows the lubricating oil flowing through the compressor end to be quickly carried away from the compressor end, reducing the degree of lubricating oil accumulation in the compressor shaft seal sleeve area, thereby improving the compressor's sealing performance.

[0114] In summary, compared with the prior art, the double-ended blade induced flow compressor sealing structure provided by the present invention has a scientific structural design and can effectively improve the sealing performance of turbocharger compressors. It is especially suitable for compact turbocharger structures with limited space. The technical solution of the present invention can better play its role in improving the sealing performance of compressors and has significant practical significance.

[0115] The technical solution of this invention, through the cooperation of multiple components including a double-ended blade flow-draining shaft seal sleeve, a sealing ring, a flow-draining oil seal cap, and a flow-draining thrust bearing, can effectively reduce the degree of lubricating oil accumulation at the compressor end and improve the sealing performance of the turbocharger compressor, which has significant practical significance and application value.

[0116] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A sealing structure for a double-ended blade induced-flow compressor, characterized in that, It includes a hollow bearing body (2), a double-ended blade drain-type shaft seal sleeve (41), a sealing ring (5), a drain-type oil seal cap (61), and a drain-type thrust bearing (71). The bearing body (2) has a transversely distributed rotor shaft (11) at the center of its inner cavity. The radial outer wall of the rotor shaft (11) is equipped with compressor impellers (9), double-ended blade induced flow shaft seal (41) and induced flow thrust bearing (71) arranged in a ring from left to right. Among them, a drainage-type oil cap (61) is installed around the radial periphery of the double-ended blade drainage-type shaft seal sleeve (41). On the radially outer side of the left end of the double-ended blade drainage shaft seal sleeve (41), multiple sealing ring grooves (4106) are arranged around the mating point with the drainage oil seal cap (61). Each sealing ring groove (4106) is equipped with a sealing ring (5); The center of the double-ended blade drainage shaft seal sleeve (41) is provided with a transverse through shaft seal sleeve mounting hole (4100). The outer wall of the right end of the double-ended blade drainage shaft seal (41) is provided with an outwardly protruding drainage boss (400). The inner side of the left end of the drainage boss (400) is provided with a first drainage groove (401) around the double-ended blade drainage shaft seal (41). The radial periphery of the drainage boss (400) is surrounded by a concave, sloping oil guide ring groove (4103). The right end of the drainage boss (400) has an oil guide ring groove (4108) arranged around its radial perimeter in the circumferential direction. The left end of the drainage boss (400) has multiple variable-width oblique blades (4101) that protrude to the left evenly along the circumferential direction. Between any two adjacent variable width inclined blades (4101), there is a blade variable width full-through oil guide groove (4102). The variable width full-through oil guide groove (4102) of the blade is a groove with the same width at the inlet and outlet; The blade has a variable width full-through oil guide groove (4102), which is connected to the first guide groove (401); The right side of the drainage boss (400) has multiple downward-protruding oblique blades (4104) of equal width evenly distributed along the circumferential direction. Between any two adjacent equal-width oblique blades (4104), there is a blade equal-width full-through oil guiding groove (4105). The blade-width, full-through oil guide groove (4105) is connected to the oil guide ring groove (4108).

2. The sealing structure of the double-ended blade induced-flow compressor as described in claim 1, characterized in that, The variable width full-through oil guide groove (4102) of the blade is a groove with different widths at the inlet and outlet.

3. The sealing structure of the double-ended blade induced-flow compressor as described in claim 1, characterized in that, The tilting direction of the variable width inclined blade (4101) is backward tilting along the rotation direction X of the shaft sleeve; The tilt angle of each variable-width oblique blade (4101) is α; The value of α satisfies the condition: 0°≤α≤65°.

4. The sealing structure of the double-ended blade induced-flow compressor as described in claim 1, characterized in that, The slope angle of the inclined oil guide ring groove (4103) is 15°~45°.

5. The sealing structure of the double-ended blade induced-flow compressor as described in claim 1, characterized in that, The blade has a full-width oil guide groove (4105), which is a groove with the same width at the inlet and outlet. The width of the oil guide ring groove (4108) is not greater than one-fifth of the width of the blade-equal-width full-through oil guide channel (4105).

6. The sealing structure of the double-ended blade induced-flow compressor as described in claim 1, characterized in that, The drain-type oil cap (61) includes an oil collection chamber (6102), an oil guide flange (6101), and an oil guide ramp (6103). On the radial inner side of the right end of the drain-type oil sealing cap (61), there is an oil collection cavity (6102) distributed around it. The left side of the oil collecting cavity (6102) is provided with an arc-shaped oil guiding flange (6101) and an oil guiding ramp (6103).

7. The sealing structure of the double-ended blade induced-flow compressor as described in claim 1, characterized in that, The flow-through type thrust bearing (71) includes an oil guide chamber (7101), an oil reservoir (7102), and an oil drain ring groove (7103). An oil reservoir (7102) is provided at the radial center position of the right end of the flow-type thrust bearing (71). The upper part of the oil storage chamber (7102) is provided with three oil guide chambers (7101) spaced apart. The oil guiding chamber (7101) and the oil storage chamber (7102) are interconnected; An arc-shaped oil drain ring groove (7103) is provided on the outer edge of the right side of the oil storage chamber (7102).

8. The sealing structure of the double-ended blade induced-flow compressor as described in claim 7, characterized in that, The maximum diameter of the drain ring groove (7103) is not less than the maximum diameter of the thrust bearing mating surface (4107) of the double-ended blade drainage shaft seal sleeve (41); On the radial outer wall of the rotor shaft (11), at the right side of the flow-type thrust bearing (71), there is also an annular thrust plate (10). The maximum diameter of the drain ring groove (7103) of the drain type thrust bearing (71) is not less than the maximum diameter of the thrust plate (10).

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