CN219061773U

CN219061773U - Variable geometry turbocharger

Info

Publication number: CN219061773U
Application number: CN202223250455.8U
Authority: CN
Inventors: 王九胜; 黄建军; 陈展浩
Original assignee: Jiangsu Easyland Automotive Science & Technology Co ltd
Current assignee: Jiangsu Easyland Automotive Science & Technology Co ltd
Priority date: 2022-12-05
Filing date: 2022-12-05
Publication date: 2023-05-23
Anticipated expiration: 2032-12-05

Abstract

The utility model relates to the technical field of turbochargers, in particular to a variable geometry turbocharger, which comprises a turbine housing, an intermediate housing and a compressor housing which are sequentially connected, wherein a rotor assembly is arranged in the intermediate housing, an exhaust gas outlet channel and an exhaust gas inlet channel are formed in the turbine housing, the exhaust gas inlet channel is communicated with the exhaust gas outlet channel through a first flow channel, a nozzle ring is arranged between the intermediate housing and the rotor assembly, the first flow channel is positioned at one side of the nozzle ring, an annular cavity is formed at one side of the nozzle ring, far from the first flow channel, a plurality of first air channels are axially formed in the intermediate housing, a plurality of gaps are formed at the end part, far from the turbine housing, of the nozzle ring, a plurality of second air channels are axially formed in the turbine housing, and the first flow channels are sequentially communicated with the annular cavity through the second air channels, the first air channels and the gaps; the utility model has simple structural design, the strength of the nozzle ring can be ensured, and the nozzle ring and the guide post cannot rigidly collide.

Description

Variable geometry turbocharger

Technical Field

The utility model relates to the technical field of turbochargers, in particular to a variable geometry turbocharger.

Background

Turbochargers are devices for supplying air to the inlet of an internal combustion engine at a pressure above atmospheric pressure (boost pressure), in fact an air compressor, and are widely used in the automotive industry. The turbocharger includes a turbine assembly, an intermediate body, and a compressor assembly connected therebetween, the turbine assembly providing an exhaust gas driven turbine wheel mounted on a rotatable shaft connected downstream of an engine outlet manifold, rotation of the turbine wheel causing rotation of a compressor wheel mounted on the other end of the shaft, the compressor wheel carrying compressed air to the engine inlet manifold. In order to ensure the balance of the pressure at the two sides of the nozzle ring, the nozzle ring is provided with balance holes.

At present, balance holes in the traditional turbocharger are formed in the nozzle ring and are positioned beside the blades, and because the nozzle ring is in a high-temperature and high-pressure environment, the strength of the nozzle ring can be influenced by the balance holes formed in the nozzle ring, so that the service lives of the nozzle ring and the turbocharger are influenced. In addition, the nozzle ring and the guide pillar are movably connected through the guide pin, an axial gap exists between the nozzle ring and the guide pillar, the guide pillar can axially float before and after starting, and then the nozzle ring and the guide pillar can generate rigid collision, so that the service lives of the nozzle ring and the turbocharger are influenced.

Disclosure of Invention

The utility model aims to overcome the defects and the shortcomings of the prior art and provide the variable geometry turbocharger which is simple in structural design, ensures the strength of a nozzle ring and does not rigidly collide with a guide post.

The technical scheme for realizing the aim of the utility model is as follows: the utility model provides a variable geometry turbocharger, includes turbine shell, midbody shell and the compressor shell that connects gradually, be equipped with rotor subassembly in the midbody shell, the middle part axial of turbine shell has been seted up the waste gas passageway of giving vent to anger, the circumference of turbine shell is equipped with annular waste gas inlet channel, waste gas inlet channel passes through first runner and waste gas passageway intercommunication of giving vent to anger, be equipped with turbine wheel in the waste gas passageway of giving vent to anger, the midbody shell is close to being equipped with the nozzle ring between tip and the rotor subassembly of turbine shell, first runner is located one side of nozzle ring, one side that the nozzle ring kept away from first runner has annular cavity, the midbody shell is close to the tip axial of turbine shell and has been seted up a plurality of first air vent, the tip that the turbine shell kept away from turbine shell has a plurality of breach, the turbine shell is close to the tip axial of midbody shell has been seted up a plurality of second air vent, the one end of first air vent communicates with first air vent through the second air vent, the other end passes through breach and annular cavity intercommunication.

Further, the nozzle ring includes mounting plate and a plurality of blade, the mounting plate includes annular baffle, the annular internal support portion of being connected with the baffle internal periphery and the annular external support portion of being connected with the baffle external periphery, annular cavity is by baffle, internal support portion and external support portion formation, the even terminal surface that is close to turbine housing at the baffle of installing of blade, the tip support of baffle is kept away from to internal support portion is on rotor assembly's annular first step face, the tip support of baffle is kept away from to external support portion is on the annular second step face of midbody shell, the breach is located the tip of baffle is kept away from to external support portion.

Further, an air inlet channel is axially formed in the middle of the compressor shell, an annular air outlet channel is formed in the circumference of the compressor shell, the air inlet channel is communicated with the air outlet channel through a second flow channel, and a compressor impeller is arranged in the air inlet channel.

Further, the rotor assembly comprises a rotor shaft and a bearing member sleeved on the rotor shaft, the rotor shaft is in running fit with the bearing member, two ends of the rotor shaft extend into the turbine housing and the compressor housing respectively and are connected with the turbine impeller and the compressor impeller respectively, and the nozzle ring is arranged between the intermediate housing and the bearing member.

Further, an inner piston ring is arranged between the bearing piece and the inner supporting part, an outer piston ring is arranged between the intermediate shell and the outer supporting part, and the inner piston ring and the outer piston ring are in contact with the nozzle ring.

Further, a guide pillar is arranged between the intermediate shell and the bearing piece, the end part of the guide pillar, which is close to the turbine shell, stretches into the annular cavity and is connected with the partition board, and the end part of the guide pillar, which is close to the compressor shell, is connected with the adjusting block.

Further, the guide pillar comprises a guide part and a mounting part, wherein the end part of the guide part, which is close to the turbine shell, is integrally connected with the middle part of the mounting part, the two ends of the mounting part are respectively connected with the partition board through guide pins, an elastic gasket is arranged between the mounting part and the guide pins, and the elastic gasket is sleeved outside the guide pins.

Further, the mounting holes are respectively formed in the two ends of the mounting portion, and the guide pins penetrate through the mounting holes and are in clearance fit with the mounting holes.

Further, the guide post is T-shaped.

Further, the mounting portion is arc-shaped.

After the technical scheme is adopted, the utility model has the following positive effects:

(1) According to the utility model, through the arrangement of the first air passage, the notch and the second air passage, the first flow passage and the annular cavity are communicated, so that the balance of air pressure at two sides of the nozzle ring is realized, and compared with the balance holes formed in the nozzle ring, the integrity of the nozzle ring is ensured, the strength of the nozzle ring is further ensured, and the service lives of the nozzle ring and the turbocharger are prolonged;

(2) According to the utility model, the elastic washer is arranged between the guide post and the guide pin, so that the axial gap between the guide post and the partition plate is eliminated, and further, the axial movement of the guide post and the rigid collision of the partition plate of the nozzle ring before and after starting is avoided, and the service lives of the nozzle ring and the turbocharger are further prolonged.

Drawings

In order that the utility model may be more readily and clearly understood, a further detailed description of the utility model will be rendered by reference to specific embodiments that are illustrated in the appended drawings, in which:

FIG. 1 is a schematic diagram of the structure of the present utility model;

FIG. 2 is a cross-sectional view taken along the direction A-A in FIG. 1;

FIG. 3 is an enlarged view of portion B of FIG. 3;

FIG. 4 is a schematic view of the present utility model with the turbine casing removed;

FIG. 5 is a schematic illustration of the structure of the utility model with the housing removed;

FIG. 6 is a schematic view of a mounting plate of the present utility model;

FIG. 7 is an elevation view of a guide post of the present utility model;

FIG. 8 is a schematic view of an elastomeric gasket of the present utility model;

FIG. 9 is a schematic view of a mounting hole of the present utility model.

In the figure: 1. a turbine housing; 2. an intermediate housing; 3. a compressor housing; 4. a rotor assembly; 4a, a rotor shaft; 4b, bearing members; 5. an exhaust gas outlet passage; 6. an exhaust gas intake passage; 7. a first flow passage; 8. a turbine wheel; 9. a nozzle ring; 9a, mounting plate; 9a1, a separator; 9a2, an inner support; 9a3, an outer support; 9b, blades; 10. an annular cavity; 11. a first air duct; 12. a notch; 13. a second ventilation channel; 14. a first step surface; 15. a second step surface; 16. an air intake passage; 17. an air outlet channel; 18. a second flow passage; 19. a compressor wheel; 20a, an inner piston ring; 20b, an outer piston ring; 21. a guide post; 21a, a guide part; 21b, a mounting part; 22. an adjusting block; 23. a guide pin; 24. an elastic washer; 25. a mounting hole; 26. adjusting the connecting rod; 27. and (3) a rocker arm.

Detailed Description

As shown in fig. 1-4, a variable geometry turbocharger comprises a turbine housing 1, an intermediate housing 2 and a compressor housing 3 which are sequentially connected, wherein a rotor assembly 4 is arranged in the intermediate housing 2, an exhaust gas outlet channel 5 is axially formed in the middle of the turbine housing 1, an annular exhaust gas inlet channel 6 is circumferentially arranged on the turbine housing 1, the exhaust gas inlet channel 6 is communicated with the exhaust gas outlet channel 5 through a first flow channel 7, a turbine wheel 8 is arranged in the exhaust gas outlet channel 5, a nozzle ring 9 is arranged between the end, close to the turbine housing 1, of the intermediate housing 2 and the rotor assembly 4, the first flow channel 7 is positioned on one side of the nozzle ring 9, an annular cavity 10 is formed in one side, far from the first flow channel 7, of the intermediate housing 2, a plurality of first air channels 11 are axially formed in the end, close to the turbine housing 1, of the nozzle ring 9, a plurality of gaps 12 are axially formed in the end, close to the intermediate housing 2, of the turbine housing 1, a plurality of second air channels 13 are axially formed in the end, one end of the first air channels 11 is communicated with the first air channels 7 through the second air channels 13, and the other end is communicated with the annular cavity 10 through the gaps 12. Through the setting of first air vent 11, breach 12 and second air vent 13, intercommunication first fluid passage 7 and annular cavity 10 realize the balance of nozzle ring 9 both sides atmospheric pressure, compare on nozzle ring 9 with the balancing hole seting up, guarantee the wholeness of nozzle ring 9, and then guarantee the intensity of nozzle ring 9 to promote nozzle ring 9 and turbo charger's life. Specifically, the first air passage 11, the notch 12 and the second air passage 13 are all uniformly arranged; an air inlet channel 16 is axially formed in the middle of the compressor shell 3, an annular air outlet channel 17 is circumferentially formed in the compressor shell 3, the air inlet channel 16 is communicated with the air outlet channel 17 through a second flow channel 18, and a compressor impeller 19 is arranged in the air inlet channel 16; the rotor assembly 4 comprises a rotor shaft 4a and a bearing piece 4b sleeved on the rotor shaft 4a, the rotor shaft 4a is in running fit with the bearing piece 4b, two ends of the rotor shaft 4a extend into the turbine shell 1 and the compressor shell 3 respectively and are connected with the turbine impeller 8 and the compressor impeller 19 respectively, and the nozzle ring 9 is arranged between the intermediate shell 2 and the bearing piece 4 b; an inner piston ring 20a is provided between the bearing member 4b and the inner support portion 9a2, an outer piston ring 20b is provided between the intermediate body housing 2 and the outer support portion 9a3, and both the piston ring 20a and the outer piston ring 20b collide with the nozzle ring 9.

As shown in fig. 3 to 6, the nozzle ring 9 includes a mounting plate 9a and a plurality of vanes 9b, the mounting plate 9a includes an annular diaphragm 9a1, an annular inner support portion 9a2 connected to an inner peripheral edge of the diaphragm 9a1, and an annular outer support portion 9a3 connected to an outer peripheral edge of the diaphragm 9a1, the annular cavity 10 is formed by the diaphragm 9a1, the inner support portion 9a2, and the outer support portion 9a3, the vanes 9b are uniformly mounted on an end face of the diaphragm 9a1 near the turbine housing 1, an end of the inner support portion 9a2 away from the diaphragm 9a1 is supported on an annular first step face 14 of the rotor assembly 4, an end of the outer support portion 9a3 away from the diaphragm 9a1 is supported on an annular second step face 15 of the intermediate housing 2, and the notch 12 is located at an end of the outer support portion 9a3 away from the diaphragm 9a 1. In particular, the vane 9b protrudes into the first flow channel 7.

As shown in fig. 2 to 6, a guide post 21 is provided between the intermediate body casing 2 and the bearing member 4b, the end of the guide post 21 near the turbine casing 1 extends into the annular cavity 10 and is connected with the partition 9a1, and the end of the guide post 21 near the compressor casing 3 is connected with an adjusting block 22. In particular, the adjusting block 22 is connected to a rocker arm 27 via an adjusting link 26, which is not described here too much for the prior art.

As shown in fig. 7 and 8, the guide post 21 includes a guide portion 21a and an installation portion 21b, the end portion of the guide portion 21a, which is close to the turbine housing 1, is integrally connected with the middle portion of the installation portion 21b, both ends of the installation portion 21b are respectively connected with the partition 9a1 through guide pins 23, an elastic washer 24 is provided between the installation portion 21b and the guide pins 23, and the elastic washer 24 is sleeved on the guide pins 24. By arranging the elastic washer 24 between the guide post 21 and the guide pin 23, the axial gap between the guide post 21 and the partition plate 9a1 is eliminated, and further, the axial movement of the guide post 21 before and after starting and the rigid collision of the partition plate 9a1 of the nozzle ring 9 are avoided, so that the service lives of the nozzle ring 9 and the turbocharger are further prolonged. Specifically, the guide post 21 is T-shaped, the mounting portion 21b is arc-shaped, and the elastic washer 24 is high-temperature resistant and high-elasticity.

As shown in fig. 9, the mounting portion 21b has mounting holes 25 formed at both ends thereof, and the guide pins 23 are disposed through the mounting holes 25 and are in clearance fit with the mounting holes 25, so that the guide posts 21 can shake radially when assembled. Specifically, the clearance between the mounting hole 25 at one end of the mounting portion 21b and the guide pin 23 is larger than the clearance between the mounting hole 25 at the other end of the mounting portion 21b and the guide pin 23.

In operation, gas from an internal combustion engine (not shown) is delivered to the exhaust gas inlet channel 6, through the first flow channel 7 and the turbine wheel 8 to the exhaust gas outlet channel 5, and gas delivered from the exhaust gas inlet channel 6 to the exhaust gas outlet channel 5 drives the turbine wheel 8 to rotate, and further drives the compressor wheel 19 to rotate through the rotor shaft 4a, and the rotation of the compressor wheel 19 pressurizes and delivers ambient air to the internal combustion engine through the air inlet channel 16. Proved by experiments, the sum of the sectional areas of the balance holes on the traditional nozzle ring is 221.056mm ² The sum of the sectional areas of the notches in the utility model is 241.4032mm ² 。

While the foregoing is directed to embodiments of the present utility model, other and further details of the utility model may be had by the present utility model, it should be understood that the foregoing description is merely illustrative of the present utility model and that no limitations are intended to the scope of the utility model, except insofar as modifications, equivalents, and improvements may be made within the spirit and principles of the utility model.

Claims

1. The utility model provides a variable geometry turbocharger, includes turbine shell (1), midbody shell (2) and compressor shell (3) that connect gradually, be equipped with rotor subassembly (4) in midbody shell (2), waste gas passageway (5) have been seted up to the middle part axial of turbine shell (1), the circumference of turbine shell (1) is equipped with annular waste gas inlet channel (6), waste gas inlet channel (6) are through first runner (7) and waste gas passageway (5) intercommunication, be equipped with turbine impeller (8) in waste gas passageway (5), be equipped with nozzle ring (9) between the tip that midbody shell (2) are close to turbine shell (1) and rotor subassembly (4), first runner (7) are located one side of nozzle ring (9), one side that first runner (7) were kept away from to nozzle ring (9) has annular cavity (10), its characterized in that: the turbine shell is characterized in that a plurality of first air passages (11) are axially formed in the end portion, close to the turbine shell (1), of the intermediate shell (2), a plurality of gaps (12) are formed in the end portion, far away from the turbine shell (1), of the nozzle ring (9), a plurality of second air passages (13) are axially formed in the end portion, close to the intermediate shell (2), of the turbine shell (1), one end of each first air passage (11) is communicated with the first air passage (7) through the second air passages (13), and the other end of each first air passage is communicated with the annular cavity (10) through the corresponding gap (12).

2. A variable geometry turbocharger according to claim 1, wherein: the nozzle ring (9) comprises a mounting disc (9 a) and a plurality of blades (9 b), the mounting disc (9 a) comprises an annular partition plate (9 a 1), an annular inner supporting portion (9 a 2) connected with the inner periphery of the partition plate (9 a 1) and an annular outer supporting portion (9 a 3) connected with the outer periphery of the partition plate (9 a 1), an annular cavity (10) is formed by the partition plate (9 a 1), the inner supporting portion (9 a 2) and the outer supporting portion (9 a 3), the blades (9 b) are uniformly mounted on the end face, close to the turbine housing (1), of the partition plate (9 a 1), the end portion, far away from the partition plate (9 a 1), of the inner supporting portion (9 a 2) is supported on an annular first step surface (14) of the rotor assembly (4), the end portion, far away from the partition plate (9 a 1), of the outer supporting portion (9 a 3) is supported on an annular second step surface (15) of the intermediate housing (2), and the notch (12) is located at the end portion, far away from the partition plate (9 a 1).

3. A variable geometry turbocharger according to claim 1, wherein: the middle part axial of compressor shell (3) has seted up air inlet channel (16), the circumference of compressor shell (3) is equipped with annular air outlet channel (17), air inlet channel (16) are through second flow path (18) and air outlet channel (17) intercommunication, be equipped with compressor impeller (19) in air inlet channel (16).

4. A variable geometry turbocharger according to claim 3, wherein: the rotor assembly (4) comprises a rotor shaft (4 a) and a bearing piece (4 b) sleeved on the rotor shaft (4 a), the rotor shaft (4 a) is in running fit with the bearing piece (4 b), two ends of the rotor shaft (4 a) extend into the turbine shell (1) and the compressor shell (3) respectively and are connected with the turbine impeller (8) and the compressor impeller (19) respectively, and the nozzle ring (9) is arranged between the intermediate shell (2) and the bearing piece (4 b).

5. A variable geometry turbocharger according to claim 4, wherein: an inner piston ring (20 a) is arranged between the bearing piece (4 b) and the inner supporting part (9 a 2), an outer piston ring (20 b) is arranged between the intermediate body shell (2) and the outer supporting part (9 a 3), and the inner piston ring (20 a) and the outer piston ring (20 b) are in contact with the nozzle ring (9).

6. A variable geometry turbocharger according to claim 4 or 5, wherein: a guide post (21) is arranged between the intermediate shell (2) and the bearing piece (4 b), the end part of the guide post (21) close to the turbine shell (1) stretches into the annular cavity (10) and is connected with the partition plate (9 a 1), and the end part of the guide post (21) close to the compressor shell (3) is connected with the adjusting block (22).

7. A variable geometry turbocharger according to claim 6, wherein: the guide post (21) comprises a guide part (21 a) and a mounting part (21 b), wherein the end part, close to the turbine shell (1), of the guide part (21 a) is connected with the middle part of the mounting part (21 b) in an integrated manner, two ends of the mounting part (21 b) are respectively connected with the partition plate (9 a 1) through guide pins (23), an elastic washer (24) is arranged between the mounting part (21 b) and the guide pins (23), and the elastic washer (24) is sleeved on the guide pins (23).

8. A variable geometry turbocharger according to claim 7, wherein: mounting holes (25) are respectively formed in two ends of the mounting portion (21 b), and the guide pins (23) penetrate through the mounting holes (25) and are in clearance fit with the mounting holes (25).

9. A variable geometry turbocharger according to claim 6, wherein: the guide post (21) is T-shaped.

10. A variable geometry turbocharger according to claim 7, wherein: the mounting part (21 b) is arc-shaped.