All-working-condition supercharging structure of turbocharger

Abstract

The invention relates to the field of turbochargers, in particular to a turbocharger all-working-condition supercharging structure which comprises a gas guide shell, a connecting shell, a second volute, a middle shell and a first volute which are fixedly connected in sequence, and a turbine shaft is installed in the middle shell; a turbine impeller is fixedly installed at the first end of the turbine shaft, a gas compressor impeller is fixedly installed at the second end of the turbine shaft, the turbine impeller is located in the first volute, and the gas compressor impeller is located in the second volute. The second end of the turbine shaft penetrates through the compressor impeller and is fixedly connected with the movable impeller; the air compressor further comprises a static impeller, and the static impeller is fixed to the connecting position of the air guide shell and the connecting shell and located between the movable impeller and the air compressor impeller. According to the invention, gas can be compressed twice, and enough gas can be fed into the engine at a low speed, so that hysteresis is avoided.

Description

Technical Field

[0001] The invention relates to the field of turbochargers, and in particular to a turbocharger full-operating-condition supercharging structure. Background Art

[0002] The turbocharger uses the inertial force of the exhaust gas discharged by the engine to drive the turbine in the turbine chamber, and the turbine drives the coaxial impeller, which presses the air sent from the air filter pipe to enter the cylinder with pressure. With the continuous development and popularization of the engine industry, matching the engine with a turbocharger is conducive to energy conservation and emission reduction, and improving power performance. This technology is also the general trend. However, the turbocharger has hysteresis at low speed and poor low-speed responsiveness.

[0003] The Chinese invention patent with application number CN202120123996.0 discloses an electronically assisted turbocharger, including a base plate, on which a power drive device is provided; the power drive device includes a power structure and a power drive structure connected to the power structure, and the power drive structure is connected to a turbocharger; the turbocharger includes a turbine structure and an air compression structure matched with the turbine structure; the air compression structure includes a first housing, in which a compressor wheel is provided, the compressor wheel is fixedly connected to a transmission shaft connected to the power drive structure, and the transmission shaft is connected to the turbine structure; the turbine structure includes a second housing, in which a turbine is fixedly connected to the transmission shaft. Although this structure can solve the low-speed hysteresis phenomenon to a certain extent, this structure requires the addition of a motor, a gear set and a corresponding electronic control system, and the structure is complex and the cost is high. Summary of the invention

[0004] In order to solve the defects in the prior art, the present invention provides a turbocharger full-operation condition supercharging structure, which is specifically achieved through the following technical solutions: A turbocharger full-operating-condition boosting structure comprises an air guide casing, a connecting casing, a second volute casing, an intermediate casing and a first volute casing which are fixedly connected in sequence, wherein a turbine shaft is installed in the intermediate casing; a turbine impeller is fixedly installed on the first end of the turbine shaft, and a compressor impeller is fixedly installed on the second end, the turbine impeller is located in the first volute casing, and the compressor impeller is located in the second volute casing; the second end of the turbine shaft passes through the compressor impeller and is fixedly connected to the moving impeller; and further comprises a stationary impeller, which is fixed at the connection between the air guide casing and the connecting casing, and is located between the moving impeller and the compressor impeller.

[0005] The impeller comprises an impeller shaft, a connecting section is fixed to the first end of the impeller shaft, a plurality of first blades are fixedly mounted on the outer wall of the impeller shaft in a circumferential array, and the connecting section is fixedly connected to the turbine shaft.

[0006] The stationary impeller comprises an outer ring and an inner ring, and a plurality of second blades are fixedly mounted in a circular array between the outer ring and the inner ring.

[0007] The outer ring is installed between the air guide shell and the connecting shell, and the inner ring is located between the impeller shaft and the turbine shaft.

[0008] The connecting section is provided with a first mounting hole, the first mounting hole is provided with an internal thread, the second end of the turbine shaft is provided with an external thread, and the external thread is meshed with the internal thread in the first mounting hole.

[0009] A connecting pin is also installed between the stationary impeller and the connecting shell.

[0010] The connecting section is located on the inner ring and is provided with a plurality of first convex rings.

[0011] A sealing bushing and a fixed-distance thrust sleeve are also installed on the turbine shaft between the compressor impeller and the intermediate housing, and the sealing bushing is located between the fixed-distance thrust sleeve and the compressor impeller.

[0012] A thrust bearing is sleeved on the fixed-distance thrust sleeve, a sealing member is sleeved on the sealing bushing, and an elastic retaining ring is installed on the side of the sealing member facing the compressor impeller.

[0013] The technical solution of the present invention has the following advantages: The turbine shaft drives the compressor impeller to rotate, and also drives the moving impeller to rotate together. The airflow is compressed by the moving impeller, then compressed by the stationary impeller, and finally compressed by the compressor impeller. This can achieve good low-speed performance of the turbocharger and can be applied in batches.

[0014] This turbocharger structure can provide three-stage compression, which is much more efficient than the previous one-stage compression. The number of moving and stationary impellers can also be appropriately increased according to demand.

[0015] The overall cost is saved, the structure is reliable, the integration is high, and the defect of poor low-speed responsiveness of the turbocharger can be greatly improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0017] Figure 1 It is a structural schematic diagram of the present invention; Figure 2 It is a schematic diagram of the matching relationship between the impeller assembly and the turbine shaft; Figure 3 The structure of the impeller is shown in Figure 1. Figure 1 ; Figure 4 The structure of the impeller is shown in Figure 1. Figure 2 ; Figure 5 The structure of the stationary impeller Figure 1 ; Figure 6 The structure of the stationary impeller Figure 2 ; Figure 7 For attachment Figure 1 The structural diagram at A in the middle; Figure 8 For attachment Figure 1 The structural diagram at B in the middle; Fig. 9 For attachment Figure 1 Schematic diagram of the structure at C in the middle; In the figure, 1-moving impeller, 101-impeller shaft, 102-first blade, 103-locking hole, 104-connecting section, 105-first convex ring; 2-static impeller, 201-outer ring, 2011-first step portion, 2012-second step portion, 202-second blade, 203-inner ring; 3- compressor impeller, 4- turbine shaft; 5-intermediate housing, 501-oil inlet passage, 502-seal, 503-sealing bushing, 504-elastic retaining ring, 505-thrust bearing, 506-fixed distance thrust sleeve; 6-first volute, 7-turbine impeller, 8-oil return chamber; 9-second volute, 91-connecting shell, 9101-third step portion, 9102-fourth step portion, 9103-fifth step portion, 9104-connecting pin; 10- Gas guide shell. DETAILED DESCRIPTION

[0018] The technical solution of the present invention will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0019] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance.

[0020] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0021] In addition, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0022] As attached Figure 1 To Attachment Fig. 9 As shown, the present invention provides a turbocharger full-operating-condition boosting structure, comprising an intermediate casing 5, with a first volute 6 and a second volute 9 fixedly mounted at both ends of the intermediate casing 5; a turbine shaft 4 is mounted in the intermediate casing 5, with a first end of the turbine shaft 4 extending into the first volute 6 and fixedly mounted with a turbine impeller 7, and a second end of the turbine shaft 4 extending into the second volute 9 and fixedly mounted with a compressor impeller 3.

[0023] The second end of the turbine shaft 4 passes through the compressor impeller 3 and is fixedly connected to the moving impeller 1 .

[0024] The structure of the impeller 1 is shown in the attached figure. Figure 3 and attached Figure 4 The structure shown in the figure includes a bullet-shaped impeller shaft 101 , and a connecting section 104 is fixedly connected to the first end of the impeller shaft 101 .

[0025] A plurality of first blades 102 are fixedly mounted on the outer wall of the impeller shaft 101 in a circumferential array.

[0026] The connecting section 104 is provided with a first mounting hole, the first mounting hole is provided with an internal thread, and the second end of the turbine shaft 4 is provided with an external thread, which meshes with the internal thread in the first mounting hole to achieve fixed installation of the impeller 1.

[0027] A locking hole 103 is provided at one end of the impeller shaft 101 away from the connecting section 104, i.e., the second end. The locking hole 103 is a hexagonal blind hole, which is used to tighten the impeller 1 and the turbine shaft 4 using a hexagonal wrench when installing the impeller 1, so as to achieve a stable connection between the turbine shaft 4 and the impeller 1.

[0028] It also includes an air guide housing 10 and a connecting housing 91. The connecting housing 91 is located between the air guide housing 10 and the second volute housing 9, that is, the first end and the second end of the connecting housing 91 are fixedly connected to the air guide housing 10 and the second volute housing 9 respectively.

[0029] A stationary impeller 2 is also fixedly mounted at the connection between the air guide housing 10 and the connection housing 91, and the stationary impeller 2 is located between the compressor impeller 3 and the impeller shaft 101. The connecting section 104 passes through the stationary impeller 2 and abuts against the compressor impeller 3.

[0030] The first end of the connecting shell 91 is provided with a third step portion 9101, a fifth step portion 9103, and a fourth step portion 9102 from the inside to the outside; wherein, the fourth step portion 9102 abuts against the end of the air guide shell 10, the third step portion 9101 abuts against the second end of the static impeller 2, and the first end of the static impeller 2 abuts against the sixth step portion of the air guide shell 10, thereby realizing the connection of the static impeller 2.

[0031] In order to install the stationary impeller 2 more firmly, a connecting pin 9104 is installed between the stationary impeller 2 and the connecting shell 91 .

[0032] A seventh step portion is provided at the second end of the connecting shell 91 , and the seventh step portion matches the eighth step portion on the second volute shell 9 .

[0033] The structure of the stationary impeller 2 is shown in the attached figure. Figure 5 To Attachment Figure 6 As shown, it includes an outer ring 201 and an inner ring 203 , and a plurality of second blades 202 are fixedly installed in a circular array between the outer ring 201 and the inner ring 203 .

[0034] The first end of the inner ring 203 is in clearance fit with the connecting section 104, and the second end is in clearance fit with the compressor impeller 3. Figure 7 As shown, the outer wall of the inner ring 203 realizes a smooth transition from the outer wall of the impeller shaft 101 to the compressor impeller 3 .

[0035] The first end of the outer ring 201 abuts against the sixth step portion, the second end abuts against the third step portion 9101 , and the inner diameter of the first end is greater than the inner diameter of the second end.

[0036] Since the inner ring 203 and the impeller 1 and the compressor impeller 3 are all clearance fits, in order to reduce the airflow passing through the gaps between the inner ring 203 and the impeller 1 and the compressor impeller 3, a plurality of first convex rings 105 are provided on the connecting section 104, and a gap is left between two adjacent first convex rings 105.

[0037] The first end of the outer wall of the outer ring 201 is provided with a first step portion 2011, and the second end is provided with a second step portion 2012, and the diameter of the second step portion 2012 is smaller than the diameter of the first step portion 2011. The first step portion 2011 is against the sixth step portion on the side facing the air guide housing 10, and is against the fifth step portion 9103 on the side facing the stator wheel 2; the second step portion 2012 is against the third step portion 9101. Figure 8 As shown, the fifth step portion 9103 is located between the second step portion 2012 and the air guide housing 10 .

[0038] The impeller 1 is located in the air guide casing 10 .

[0039] In order to install the connecting pin 9104, a first plugging hole is provided on the second step portion 2012, and a second plugging hole is provided on the third step portion 9101. Both ends of the connecting pin 9104 are respectively plugged into the first plugging hole and the second plugging hole.

[0040] The intermediate housing 5 is provided with an oil inlet passage 501 and an oil return chamber 8 for introducing lubricating oil.

[0041] A sealing bushing 503 and a fixed-distance thrust sleeve 506 are also installed on the turbine shaft 4 located between the compressor impeller 3 and the intermediate casing 5 , wherein the sealing bushing 503 is located between the fixed-distance thrust sleeve 506 and the compressor impeller 3 .

[0042] A thrust bearing 505 is sleeved on the fixed-distance thrust sleeve 506 , a sealing member 502 is sleeved on the sealing bushing 503 , and an elastic retaining ring 504 is installed on the side of the sealing member 502 facing the compressor impeller 3 .

[0043] When the present invention is in use, the engine exhaust drives the turbine impeller 7 to rotate, the turbine impeller 7 drives the turbine shaft 4 to rotate, and the turbine shaft 4 drives the compressor impeller 3 and the moving impeller 1 to rotate; the gas is first compressed by the moving impeller 1 from the air guide casing 10, then compressed by the stationary impeller 2 for the second time, and then compressed by the compressor impeller 3 for the third time. Therefore, even at a low speed, the present invention can compress the gas three times, and at a low speed, there will be enough gas to be sent to the engine, so no hysteresis will occur.

[0044] Obviously, the above embodiments are merely examples for the purpose of clear explanation, and are not intended to limit the implementation methods. For those skilled in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the implementation methods here. The obvious changes or modifications derived therefrom are still within the scope of protection of the invention.

Claims

1. A turbocharger full-operation condition supercharging structure, characterized in that: The invention comprises an air guide casing (10), a connecting casing (91), a second volute casing (9), an intermediate casing (5), and a first volute casing (6) which are fixedly connected in sequence, wherein a turbine shaft (4) is mounted in the intermediate casing (5); a turbine impeller (7) is fixedly mounted on the first end of the turbine shaft (4), and a compressor impeller (3) is fixedly mounted on the second end; the turbine impeller (7) is located in the first volute casing (6), and the compressor impeller (3) is located in the second volute casing (9); the second end of the turbine shaft (4) passes through the compressor impeller (3) and is fixedly connected to the moving impeller (1); and the invention also comprises a stationary impeller (2), wherein the stationary impeller (2) is fixed at the connection between the air guide casing (10) and the connecting casing (91), and the stationary impeller (2) is located between the moving impeller (1) and the compressor impeller (3).

2. The turbocharger full-operation condition supercharging structure according to claim 1, characterized in that: The impeller (1) comprises an impeller shaft (101), a connecting section (104) being fixed to the first end of the impeller shaft (101), a plurality of first blades (102) being fixedly mounted in a circumferential array on the outer wall of the impeller shaft (101), and the connecting section (104) being fixedly connected to the turbine shaft (4).

3. The turbocharger full-operation condition supercharging structure according to claim 2 is characterized in that: The stationary impeller (2) comprises an outer ring (201) and an inner ring (203), and a plurality of second blades (202) are fixedly mounted in a circular array between the outer ring (201) and the inner ring (203).

4. The turbocharger full-operation condition supercharging structure according to claim 3, characterized in that: The outer ring (201) is installed between the air guide shell (10) and the connecting shell (91), and the inner ring (203) is located between the impeller shaft (101) and the turbine shaft (4).

5. The turbocharger full-operation condition supercharging structure according to claim 4, characterized in that: The connecting section (104) is provided with a first mounting hole, the first mounting hole is provided with an internal thread, and the second end of the turbine shaft (4) is provided with an external thread, the external thread meshing with the internal thread in the first mounting hole.

6. The turbocharger full-operation condition supercharging structure according to claim 3, characterized in that: A connecting pin (9104) is also installed between the stationary impeller (2) and the connecting shell (91).

7. The turbocharger full-operation condition supercharging structure according to claim 3, characterized in that: The connecting section (104) is located on the inner ring (203) and is provided with a plurality of first convex rings (105).

8. The turbocharger full-operation condition supercharging structure according to claim 1, characterized in that: A sealing bushing (503) and a fixed-distance thrust sleeve (506) are also installed on the turbine shaft (4) between the compressor impeller (3) and the intermediate casing (5); the sealing bushing (503) is located between the fixed-distance thrust sleeve (506) and the compressor impeller (3).

9. The turbocharger full-operation condition supercharging structure according to claim 8, characterized in that: A thrust bearing (505) is sleeved on the fixed-distance thrust sleeve (506), a sealing member (502) is sleeved on the sealing sleeve (503), and an elastic retaining ring (504) is installed on the side of the sealing member (502) facing the compressor impeller (3).

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