A turbine end seal structure

Abstract

This invention relates to the field of engine turbocharger technology and provides a turbine end sealing structure, including an intermediate shell on which a turbine shaft and a turbine housing are mounted; a turbine is mounted on the turbine shaft; a nozzle ring is mounted on the turbine housing; a turbine housing insert is installed inside the turbine housing; and a sealing plate is mounted on the nozzle ring, which mates with the turbine housing insert. The sealing plate is embedded in the nozzle ring to reduce the installation gap between the nozzle ring and the turbine housing, and to reduce the gap between the nozzle ring and the turbine housing insert, thereby ensuring that engine exhaust gas does not easily leak from the turbine end of the turbocharger.

Description

Technical Field

[0001] This invention relates to the field of engine turbocharger technology and provides a turbine end sealing structure. Background Technology

[0002] With the continuous development and popularization of the engine industry, matching engines with turbochargers is beneficial for energy conservation, emission reduction, and improved power performance, and this technology is an inevitable trend.

[0003] The turbine end of the existing turbocharger is connected to the engine exhaust pipe. The engine exhaust gas has a high temperature and pressure, and there are often air leaks at the turbine end of the turbocharger. Summary of the Invention

[0004] To address the aforementioned deficiencies, the present invention aims to provide a turbine end sealing structure to solve the problems mentioned in the background art. The device includes an intermediate shell, on which a turbine shaft and a turbine housing are mounted; a turbine is mounted on the turbine shaft; a nozzle ring is mounted on the turbine housing; a turbine housing insert is installed inside the turbine housing; and a sealing plate that mates with the turbine housing insert is mounted on the nozzle ring.

[0005] Furthermore, sealing plates are installed on both the inner and outer walls of the nozzle ring; the sealing plate on the inner wall of the nozzle ring abuts against the turbine housing insert, and the sealing plate on the outer wall of the nozzle ring abuts against the turbine housing.

[0006] Furthermore, the sealing disc is a double-layered spiral structure, and the projections of the first and last ends of the spiral in the axial direction do not coincide.

[0007] Furthermore, a sealing ring is provided on the turbine housing insert, and the sealing ring is located at the end face where the turbine housing and the turbine housing insert abut.

[0008] Furthermore, an explosion-proof sleeve is installed between the turbine housing and the turbine housing bushing.

[0009] Furthermore, a heat insulation cover is installed on the intermediate shell, with one end of the heat insulation cover abutting against the intermediate shell and the other end abutting against the nozzle ring.

[0010] Furthermore, the heat shield is installed between the turbine housing and the intermediate housing.

[0011] Furthermore, the end of the turbine housing furthest from the intermediate housing is bolted to the turbine housing insert.

[0012] In summary, during actual use, the turbine housing connects to the engine's exhaust end. The nozzle ring has blades, and the combustion exhaust gas blows through the nozzle ring, causing the turbine to rotate. The turbine then transmits the rotational force to the turbine shaft. The inner ring of the turbine housing bushing engages with the turbine to form an airflow channel, through which the exhaust gas driving the turbine's rotation is discharged. The sealing disc is a spiral stacked sealing structure made of high-temperature resistant material. The sealing disc is embedded in the nozzle ring to reduce the installation gap between the nozzle ring and the turbine housing, and to reduce the gap between the nozzle ring and the turbine housing bushing, ensuring that engine exhaust gas does not easily leak from the turbine end of the turbocharger. Attached Figure Description

[0013] Figure 1 This is a cross-sectional view of a turbocharger;

[0014] Figure 2 for Figure 1 Enlarged view of the A-section structure;

[0015] Figure 3 for Figure 1 Enlarged view of the structure of section B;

[0016] Figure 4 This is a schematic diagram of the sealing laminate structure;

[0017] Figure 5 for Figure 4 Enlarged view of the C-section structure;

[0018] Figure 6 for Figure 1 A partial view;

[0019] In the diagram: 1-Nozzle ring; 2-Sealing plate; 3-Turbine housing; 4-Explosion-proof sleeve; 5-Turbine housing insert; 51-Sealing ring band; 6-Turbine shaft; 61-Turbine; 7-Heat insulation cover; 8-Intermediate shell. Detailed Implementation

[0020] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention.

[0021] See Figure 1-6The purpose of this invention is to provide a turbine end sealing structure, including an intermediate shell 8, which is the core of a turbocharger and serves as a mounting housing. The intermediate shell 8 contains a turbine shaft 6 disposed within it and a bearing positioned between the intermediate shell 8 and the turbine shaft 6. The intermediate shell 8 also includes lubrication structures such as oil holes to ensure lubrication of the internal structure. The intermediate shell 8 primarily provides support for the bearing within the turbocharger. The turbine shaft 6 and turbine housing 3 are mounted on the intermediate shell 8. The turbine shaft 6 is mounted on the bearing inside the intermediate shell 8. The turbine housing 3 is helical in shape and includes an annular flow channel, providing the necessary conditions for the rotation of the turbocharger's turbine 61. A turbine 61 is mounted on the turbine shaft 6, located at one end of the turbine shaft 6 and within the turbine housing 3. Exhaust gas drives the turbine 61 to rotate, providing power to the compressor. A nozzle ring 1 is mounted on the turbine housing 3, positioned between the turbine housing 3 and the intermediate shell 8. During installation, the nozzle ring 1 is first installed on the intermediate shell 8, and then the turbine housing 3 is installed. The turbine housing 3 and the intermediate shell 8 cooperate to secure the nozzle ring 1. The nozzle ring 1 has blades that change the angle at which the airflow enters the turbine housing 3, guiding the combustion exhaust gas to the turbine 61 and causing it to rotate. The bladed nozzle ring 1 is existing technology and will not be described in detail here. A turbine housing sleeve 5 is installed inside the turbine housing 3. Specifically, part of the turbine housing sleeve 5 fits inside the turbine housing 3, and another part wraps around the end of the turbine housing 3 away from the intermediate housing 8. The end of the turbine housing sleeve 5 that wraps around the turbine housing 3 is fixedly connected to the turbine housing 3 by bolts. The inner ring of the turbine housing sleeve 5 cooperates with the turbine 61 to form an airflow channel, through which the exhaust gas driving the turbine 61 to rotate is discharged. A sealing plate 2 is installed on the nozzle ring 1; the sealing plate 2 is a spiral stacked sealing structure made of high-temperature resistant material.

[0022] The working principle of the device is as follows: the turbine housing 3 is connected to the exhaust end of the engine. The exhaust gas after combustion will enter the annular flow channel of the turbine housing 3. The gas in the annular flow channel is changed by the blades on the nozzle ring 1 to change the angle of the airflow into the turbine housing 3, which guides the exhaust gas to the turbine 61, blows the turbine 61 to rotate, and the turbine 61 then transmits the rotational force to the turbine shaft 6.

[0023] However, the exhaust gas from the engine is hot and has high pressure. During the operation of the device, the exhaust gas will leak out through the gaps. Specifically, part of the exhaust gas enters the nozzle ring 1 through the annular flow channel, enters the installation gap between the nozzle ring 1 and the turbine housing 3, and then leaks to the outside along the gap between the turbine housing sleeve 5 and the turbine housing 3; another part of the exhaust gas will enter the gap between the turbine housing sleeve 5 and the nozzle ring 1, and then leak to the outside along the gap between the turbine housing sleeve 5 and the turbine housing 3.

[0024] The sealing disc 2 is installed on the nozzle ring 1. Specifically, the sealing disc 2 is embedded in the nozzle ring 1 to reduce the installation gap between the nozzle ring 1 and the turbine housing 3, and to reduce the gap between the nozzle ring 1 and the turbine housing bushing 5. At this time, as the gap is reduced, the exhaust gas requires greater pressure to enter the gap, ensuring that the exhaust gas does not easily leak.

[0025] Preferably, sealing plates 2 are installed on both the inner and outer walls of the nozzle ring 1; that is, two sealing plates 2 are provided on the nozzle ring 1. The sealing plate 2 on the inner wall of the nozzle ring 1 abuts against the turbine housing insert 5, and the sealing plate 2 on the outer wall of the nozzle ring 1 abuts against the turbine housing 3. Specifically, annular grooves are provided on both the inner and outer walls of the nozzle ring 1, and the two sealing plates 2 are respectively installed in the two annular grooves, with the ring width of the sealing plate 2 (i.e., the difference between the inner and outer radii) slightly larger than the ring width of the annular groove. The sealing plate 2 protrudes slightly from the nozzle ring 1, and the protruding part can achieve the function of sealing gaps. This arrangement can completely seal the gaps formed by the inner and outer rings of the nozzle ring 1, ensuring the sealing performance of the nozzle ring 1 end face and ensuring good sealing of the turbocharger.

[0026] Preferably, the sealing disc 2 is a double-layered helical structure, and the beginning and end of the helix of the sealing disc 2 do not coincide in the thickness direction of the helix. The double-layered sealing disc 2 can increase the thickness, increase the contact area with the turbine housing bushing 5 or turbine housing 3, and enhance the sealing effect; while the helical structure of the sealing disc 2 can facilitate the enlargement or reduction of the inner diameter of the sealing disc 2 during installation. Reducing the inner diameter during installation makes it easier to install on the inner ring side of the nozzle ring 1, and increasing the inner diameter makes it easier to install on the outer ring side of the nozzle ring 1.

[0027] See Figure 3 Preferably, the turbine housing insert 5 is provided with a sealing ring 51, which is located at the contact point between the turbine housing 3 and the turbine housing insert 5. Specifically, the sealing ring 51 is a ring-shaped protrusion of the turbine housing insert 5, located at the contact surface where the turbine housing insert 5 wraps around the turbine housing 3. When the turbine housing insert 5 and the turbine housing 3 are fastened with bolts, the sealing ring 51 will firmly abut against the turbine housing 3 and produce a certain elastic deformation, so that it can block the gap between the turbine housing insert 5 and the turbine housing 3, thus playing a sealing role.

[0028] See Figure 6 Preferably, an explosion-proof sleeve 4 is installed between the turbine housing 3 and the turbine housing bushing 5. Specifically, one end face of the explosion-proof sleeve 4 abuts against the nozzle ring 1, and the other end face abuts against both the turbine housing bushing 5 and the turbine housing 3; the inner ring side of the explosion-proof sleeve 4 abuts against the turbine housing bushing 5, and the outer ring side abuts against the turbine housing 3. The installation of the explosion-proof sleeve 4 between the turbine housing 3 and the turbine housing bushing 5 improves the turbocharger's containment.

[0029] Preferably, a heat insulation cover 7 is installed on the intermediate shell 8, with one end of the heat insulation cover 7 abutting against the intermediate shell 8 and the other end abutting against the nozzle ring 1. Since the exhaust gas is a high-temperature and high-pressure gas, its high temperature will affect the life and operating status of the mechanical parts inside the intermediate shell 8. The heat insulation cover 7 serves to insulate the intermediate shell 8 from heat.

[0030] Preferably, the heat shield 7 is installed between the turbine housing 3 and the intermediate housing 8. The two end faces of the heat shield 7 abut against the intermediate housing 8 and the nozzle ring 1 respectively, so that the exhaust gas does not come into contact with the intermediate housing 8 after entering the turbine housing 3, thus achieving the purpose of heat insulation.

[0031] Preferably, the end of the turbine housing 3 furthest from the intermediate housing 8 is bolted to the turbine housing insert 5. This connection method makes the connection between the two more secure.

[0032] In summary, during actual use, the turbine housing 3 connects to the engine's exhaust end, and the nozzle ring 1 has blades. Combustion exhaust gases pass through the nozzle ring 1, driving the turbine 61 to rotate. The turbine 61 then transmits the rotational force to the turbine shaft 6. The inner ring of the turbine housing insert 5 engages with the turbine 61 to form an airflow channel, through which the exhaust gases driving the turbine 61 are discharged. The sealing plate 2 is a spiral stacked sealing structure made of high-temperature resistant material. The sealing plate 2 is embedded in the nozzle ring 1 to reduce the installation gap between the nozzle ring 1 and the turbine housing 3, and to reduce the gap between the nozzle ring 1 and the turbine housing insert 5, ensuring that engine exhaust gases do not easily leak from the turbine end of the turbocharger.

[0033] Of course, the present invention may have other various embodiments. Without departing from the spirit and essence of the present invention, those skilled in the art can make various corresponding changes and modifications according to the present invention, but these corresponding changes and modifications should all fall within the protection scope of the appended claims.

Claims

1. A turbine end sealing structure, characterized in that, Includes an intermediate shell (8), on which a turbine shaft (6) and a turbine housing (3) are mounted; a turbine (61) is mounted on the turbine shaft (6), a nozzle ring (1) is mounted on the turbine housing (3), and a turbine housing insert (5) is installed inside the turbine housing (3); a sealing plate (2) that mates with the turbine housing insert (5) is mounted on the nozzle ring (1). The inner and outer walls of the nozzle ring (1) are both fitted with sealing plates (2); the sealing plates (2) on the inner wall of the nozzle ring (1) abut against the turbine housing insert (5), and the sealing plates (2) on the outer wall of the nozzle ring (1) abut against the turbine housing (3). The sealing plate (2) is a double-layered spiral structure, and the projections of the first and last ends of the spiral in the axial direction do not coincide.

2. The turbine end sealing structure according to claim 1, characterized in that, The turbine housing insert (5) is provided with a sealing ring (51), which is located at the end face where the turbine housing (3) and the turbine housing insert (5) abut.

3. The turbine end sealing structure according to claim 1, characterized in that, An explosion-proof sleeve (4) is installed between the turbine housing (3) and the turbine housing bushing (5).

4. The turbine end sealing structure according to claim 1, characterized in that, A heat shield (7) is installed on the intermediate shell (8). One end of the heat shield (7) abuts against the intermediate shell (8), and the other end abuts against the nozzle ring (1).

5. The turbine end sealing structure according to claim 4, characterized in that, The heat shield (7) is installed between the turbine housing (3) and the intermediate housing (8).

6. The turbine end sealing structure according to claim 1, characterized in that, The end of the turbine housing (3) away from the intermediate housing (8) is bolted to the turbine housing bushing (5).

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