CN213510762U

CN213510762U - A turbine subassembly for turbo charger

Info

Publication number: CN213510762U
Application number: CN202022076004.1U
Authority: CN
Inventors: 蔡赫
Original assignee: Auto Industry Tianjin Environmental Protection Technology Development Co ltd
Current assignee: Auto Industry Tianjin Environmental Protection Technology Development Co ltd
Priority date: 2020-09-21
Filing date: 2020-09-21
Publication date: 2021-06-22
Anticipated expiration: 2030-09-21

Abstract

The utility model belongs to the field of turbocharger components, in particular to a turbine end component for a turbocharger, which comprises a turbine end bearing shell, wherein a bearing body is fixedly sleeved on an inner ring of the turbine end bearing shell, a horizontal turbine shaft is fixedly sleeved on the inner ring of the bearing body, two semicircular hoops which form a circular shape are sleeved on an outer ring of the turbine shaft positioned outside the turbine end bearing shell, a first mounting plate is fixed on an outer ring of a front side end, which is close to each other, of the two semicircular hoops, the two first mounting plates are fixedly connected through bolts, a second mounting plate is fixed on an outer ring, which is far away from each other, of the two semicircular hoops, the second mounting plate is fixed on an outer side wall of the turbine end bearing shell through bolts, the inner ring, which is close to the bearing body, of the semicircular hoops is provided with an arc-shaped first mounting groove, the utility, the service life of the bearing is prolonged, the sealing assembly is convenient to disassemble and assemble, the sealing assembly is convenient to replace, and the practicability is high.

Description

A turbine subassembly for turbo charger

Technical Field

The utility model relates to a turbo charger subassembly technical field especially relates to a turbine subassembly for turbo charger.

Background

The turbocharger is actually an air compressor that increases the intake air amount by compressing air. The engine uses the inertia impulse force of the exhaust gas from the engine to push the turbine in the turbine chamber, the turbine drives the coaxial impeller, the impeller presses the air sent by the air filter pipeline, and the air is pressurized and enters the cylinder. When the rotating speed of the engine is increased, the exhaust gas exhaust speed and the rotating speed of the turbine are also increased synchronously, the impeller compresses more air to enter the air cylinder, the pressure and the density of the air are increased, more fuel can be combusted, and the output power of the engine can be increased by correspondingly increasing the fuel quantity and adjusting the rotating speed of the engine.

However, the sealing performance of the scroll end of the existing turbocharger is poor, so that the bearing of the scroll end is easily damaged due to entering of sundries, and the service life is influenced.

SUMMERY OF THE UTILITY MODEL

The utility model provides a vortex subassembly for turbo charger, it is relatively poor to have solved the leakproofness of current turbo charger's vortex end, leads to the bearing of vortex end to damage because of getting into debris easily, influences life's problem.

In order to achieve the above purpose, the utility model adopts the following technical scheme:

a turbine end component for a turbocharger comprises a turbine end bearing shell, wherein a bearing body is fixedly sleeved on an inner ring of the turbine end bearing shell, a horizontal turbine shaft is fixedly sleeved on an inner ring of the bearing body, an outer ring of the turbine shaft, which is positioned outside the turbine end bearing shell, is sleeved with two semicircular hoops forming a circle, the two semicircular hoops are fixed on a front side end outer ring close to each other and are connected with each other through bolts, a second mounting plate is fixed on an outer ring, which is far away from each other, of the two semicircular hoops, the second mounting plate is fixed on an outer side wall of the turbine end bearing shell through bolts, the semicircular hoops are close to an inner ring of the bearing body and are provided with arc-shaped first mounting grooves, the inner sleeves of the two first mounting grooves are provided with annular first sealing rings, the outer ring of the turbine shaft, which is positioned outside the turbine end bearing shell, is sequentially provided with a first annular groove, the inner ring of first sealing washer is equipped with annular clamping ring, the clamping ring cover is located the inside of first ring channel, the inner ring that bearing body was kept away from to semicircle hoop has seted up curved second mounting groove, and the inside cover of two second mounting grooves is equipped with annular second sealing washer, second sealing washer cover is located the inside of second ring channel.

Preferably, a side end of the first seal ring is in contact with a side end of the bearing body.

Preferably, the first sealing ring, the connecting ring and the second sealing ring are all made of rubber materials.

Preferably, the first sealing ring and the connecting ring are of an integrally formed structure.

Preferably, the size of the first annular groove is matched with the size of the connecting ring.

Preferably, the size of the second annular groove is matched with the size of the inner ring of the second sealing ring.

The utility model has the advantages that:

1. through the cooperation effect of vortex end bearing housing, bearing, turbine shaft, semicircle hoop, first sealing washer, clamping ring, second sealing washer, first ring channel and second ring channel, can effectually promote the leakproofness of turbo charger's vortex end through seal assembly, can effectually prevent that the bearing of vortex end from damaging because of getting into debris, can effectual extension bearing's life.

2. Through the cooperation of vortex end bearing shell, semicircle hoop, first mounting panel and second mounting panel, can make things convenient for dismouting seal assembly, conveniently change seal assembly, the practicality is higher.

The utility model relates to a novelty, the leakproofness is good, can avoid the bearing of whirlpool end to damage because of getting into debris, is favorable to promoting the life of bearing, makes things convenient for dismouting seal assembly, conveniently changes seal assembly, and the practicality is higher.

Drawings

Fig. 1 is a schematic structural diagram of a turbine end assembly for a turbocharger according to the present invention;

fig. 2 is a cross-sectional view of a turbine end assembly for a turbocharger in accordance with the present invention;

FIG. 3 is an enlarged view of a portion A of FIG. 2;

fig. 4 is a side view of a semicircular band for a turbine end assembly of a turbocharger according to the present invention.

Reference numbers in the figures: 1. a scroll end bearing housing; 2. a turbine shaft; 3. a first mounting plate; 4. a semi-circular hoop; 5. a second mounting plate; 6. a bearing body; 7. a first annular groove; 8. a second annular groove; 9. a first seal ring; 10. a connecting ring; 11. and a second seal ring.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments.

Referring to fig. 1-4, a turbine end assembly for a turbocharger, including a turbine end bearing housing 1, an inner ring of the turbine end bearing housing 1 is fixedly sleeved with a bearing body 6, an inner ring of the bearing body 6 is fixedly sleeved with a horizontal turbine shaft 2, an outer ring of the turbine shaft 2 located outside the turbine end bearing housing 1 is sleeved with two semicircular hoops 4 forming a circular shape, front side end outer rings of the two semicircular hoops 4 close to each other are respectively fixed with a first mounting plate 3, the two first mounting plates 3 are fixedly connected through bolts, outer rings of the two semicircular hoops 4 far away from each other are respectively fixed with a second mounting plate 5, the second mounting plate 5 is fixed on an outer side wall of the turbine end bearing housing 1 through bolts, the inner rings of the semicircular hoops 4 close to the bearing body 6 are provided with arc-shaped first mounting grooves, inner sleeves of the two first mounting grooves are provided with annular first sealing rings 9, an outer ring of the turbine shaft 2 located outside the turbine end bearing housing 1 is 8, the inner circle of first sealing washer 9 is equipped with annular clamping ring 10, and the inside of first ring channel 7 is located to the clamping ring 10 cover, and curved second mounting groove has been seted up to the inner circle that bearing body 6 was kept away from to semicircle hoop 4, and the inside cover of two second mounting grooves is equipped with annular second sealing washer 11, and the inside of second ring channel 8 is located to second sealing washer 11 cover.

The side end of the first seal ring 9 contacts with the side end of the bearing body 6, so that the sealing performance of the bearing body 6 can be effectively improved.

The first sealing ring 9, the connecting ring 10 and the second sealing ring 11 are made of rubber materials, the first sealing ring 9 can be attached to the bearing body 6, the connecting ring 10 can be attached to the groove wall of the first annular groove 7, the second sealing ring 11 can be attached to the groove wall of the second annular groove 8, the first sealing ring 9 and the connecting ring 10 are of an integrally formed structure, and the sealing performance of the first sealing ring 9 connected with the turbine shaft 2 can be guaranteed.

The dimensions of the first annular groove 7 are adapted to the dimensions of the connecting ring 10, ensuring the tightness of the connection of the connecting ring 10 to the turbine shaft 2.

The size of the second annular groove 8 is matched with the size of the inner ring of the second sealing ring 11, so that the sealing performance of the connection between the second sealing ring 11 and the turbine shaft 2 can be ensured.

Example (b): the sealing performance of the semicircular hoop 4 connected with the turbine shaft 2 can be improved primarily through the arrangement of the second sealing ring 11, namely, the sealing performance of the vortex end can be improved primarily, sundries can be prevented from entering the bearing body 6 primarily, the sealing performance of the semicircular hoop 4 connected with the turbine shaft 2 can be further improved through the arrangement of the first sealing ring 9 and the connecting ring 10, namely, the sealing performance of the vortex end can be further improved, the sundries can be further prevented from entering the bearing body 6, therefore, the bearing of the vortex end is prevented from being damaged due to the sundries entering, and the service life of the bearing can be effectively prolonged; seal assembly is formed by the semicircular hoop 4, the first seal ring 9, the connecting ring 10 and the second seal ring 11, when the seal assembly needs to be disassembled and assembled, the bolt for connecting the two first mounting plates 3 and the bolt for fixing the second mounting plate 5 are disassembled and assembled, so that the seal assembly can be disassembled and assembled conveniently.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and to simplify the description, but do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be construed as limiting the present invention.

Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating 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 the present invention, "a plurality" means two or more unless specifically limited otherwise.

The above, only be the concrete implementation of the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the utility model, the concept of which is equivalent to replace or change, should be covered within the protection scope of the present invention.

Claims

1. The utility model provides a turbine end subassembly for turbo charger, includes turbine end bearing housing (1), its characterized in that, the fixed bearing body (6) that has cup jointed of inner circle of turbine end bearing housing (1), the fixed horizontal turbine shaft (2) that has cup jointed of inner circle of bearing body (6), be located turbine end bearing housing (1) outside the outer lane cover of turbine shaft (2) is equipped with two and constitutes circular shape semicircle hoops (4), two the preceding side outer lane that semicircle hoop (4) are close to each other all is fixed with first mounting panel (3), two first mounting panel (3) pass through bolt fixed connection, two the outer lane that semicircle hoop (4) kept away from each other all is fixed with second mounting panel (5), second mounting panel (5) pass through the bolt fastening on the lateral wall of turbine end bearing housing (1), arc first mounting groove has been seted up to semicircle hoop (4) inner circle near bearing body (6), the inside cover of two first mounting grooves is equipped with annular first sealing washer (9), is located vortex end bearing housing (1) outside first ring channel (7) and second ring channel (8) have been seted up in proper order to the outer lane of turbine shaft (2), the inner circle of first sealing washer (9) is equipped with annular clamping ring (10), clamping ring (10) cover is located the inside of first ring channel (7), the inner circle that bearing body (6) was kept away from in semicircle hoop (4) has seted up curved second mounting groove, and the inside cover of two second mounting grooves is equipped with annular second sealing washer (11), second sealing washer (11) cover is located the inside of second ring channel (8).

2. A turbine end assembly for a turbocharger according to claim 1, characterized in that the lateral end of the first seal ring (9) is in contact with the lateral end of the bearing body (6).

3. A turbine end assembly for a turbocharger according to claim 1, wherein the first seal ring (9), the connecting ring (10) and the second seal ring (11) are all of rubber.

4. A turbine end assembly for a turbocharger according to claim 1, wherein the first sealing ring (9) is of integral construction with the connecting ring (10).

5. A turbine end assembly for a turbocharger according to claim 1, characterized in that the dimensions of the first annular groove (7) are adapted to the dimensions of the connecting ring (10).

6. A turbine end assembly for a turbocharger according to claim 1, wherein the dimensions of the second annular groove (8) are adapted to the dimensions of the inner ring of the second sealing ring (11).