CN113123857B

CN113123857B - Turbine box exhaust gas bypass device

Info

Publication number: CN113123857B
Application number: CN201911395865.1A
Authority: CN
Inventors: 谢正海; 赵肖龙; 刘红美
Original assignee: SAIC Motor Corp Ltd
Current assignee: SAIC Motor Corp Ltd
Priority date: 2019-12-30
Filing date: 2019-12-30
Publication date: 2022-08-09
Anticipated expiration: 2039-12-30
Also published as: CN113123857A

Abstract

The application discloses turbine case exhaust gas bypass device, including valve body, connecting rod, packing ring and bush, wherein: the bush is embedded in a valve seat of the turbine case, the inner center of the bush includes an exhaust gas passage, and the exhaust gas passage of the bush is communicated with the exhaust gas passage of the turbine case; the valve body is arranged on a valve seat of the turbine box, and the end surface of the lower end of the valve body is in contact fit with the end surface of the upper end of the bushing; the connecting rod is installed on the valve body through the gasket and drives the valve body to rotate axially. Therefore, the spiral flow characteristic is given to the bypass exhaust gas flowing through the liner, the exhaust gas bypass capacity of the turbocharger is improved, the vibration noise caused by the impact of the bypass exhaust gas on the valve body is reduced, and the turbine efficiency of the exhaust gas turbocharger is effectively improved.

Description

Turbine box exhaust gas bypass device

Technical Field

The embodiment of the application relates to the field of turbochargers, in particular to a turbine box waste gas bypass device.

Background

At present, a turbocharger is generally installed on an automobile to improve the performance of an automobile engine, such as improving the power density of the engine, reducing exhaust emission and solving the problem of insufficient power of the automobile. An exhaust gas turbocharger is one type of turbocharger that uses high-temperature, high-speed exhaust gas discharged from a vehicle engine to drive a turbine of the turbocharger to operate, and supplies a sufficient amount of air to the engine. The greater the flow rate of exhaust gas through the exhaust gas turbocharger, the faster the speed of the turbine in the exhaust gas turbocharger. The exhaust gas bypass structure is added to the exhaust gas turbocharger, so that the exhaust gas of the engine can be discharged from the exhaust gas bypass structure without passing through the turbine structure of the exhaust gas turbocharger, and the overspeed of the exhaust gas turbocharger is avoided.

In the prior art, when exhaust gas discharged by an engine enters a turbine box exhaust gas bypass structure to be exhausted, a valve body is impacted by high-temperature and high-pressure exhaust gas, and vibration knocking among parts in the turbine box is further caused; the valve seat of the turbine box is subjected to frequent impact of the exhaust valve body and scouring of high-temperature exhaust gas, so that the sealing surface is excessively abraded, and the problems of hot cracks of the valve seat and the like are caused. Therefore, when the wastegate valve enters the turbine case, the wastegate valve will suffer from the problems of aged wear of the structure, generation of noise and vibration, and further, the bypass exhaust gas flow characteristics of the wastegate valve.

Disclosure of Invention

Based on the above problem, the present application provides a turbine box exhaust gas bypass device to improve the bypass exhaust gas flow characteristics of the exhaust gas bypass structure.

The embodiment of the application provides a turbine case exhaust gas bypass device, including valve body, connecting rod, packing ring and bush, wherein: the bush is embedded in a valve seat of the turbine case, the inner center of the bush includes an exhaust gas passage, and the exhaust gas passage of the bush is communicated with the exhaust gas passage of the turbine case; the valve body is arranged on a valve seat of the turbine box, and the end surface of the lower end of the valve body is in contact fit with the end surface of the upper end of the bushing; the connecting rod is installed on the valve body through the gasket and drives the valve body to rotate axially.

Optionally, in any embodiment of the present application, the liner includes a first connection portion, a second connection portion, and a third connection portion located outside an exhaust gas passage of the liner, and the first connection portion, the second connection portion, and the third connection portion are sequentially arranged in an exhaust gas passage axis direction of the liner; the outer sides of the first connecting part and the second connecting part are embedded in a valve seat of the turbine box, and the end surface of the upper end of the first connecting part is in contact fit with the end surface of the lower end of the valve body; the outer side face of the third connecting portion and the inner wall of the exhaust gas channel of the turbine box form a circular cavity, and at least two rotary air passages are arranged between the outer side face and the inner side face of the third connecting portion.

Optionally, in any embodiment of the present application, all the rotating air ducts are uniformly distributed on the third connecting portion, and a side surface of the rotating air duct is tangentially connected with an inner side surface of the third connecting portion.

Optionally, in any embodiment of the present application, the outer side surface of the second connecting portion includes at least one ring groove.

Optionally, in any embodiment of the present application, the second connecting portion includes at least one anti-rotation plane on an outer side surface thereof.

Optionally, in any embodiment of the present application, the anti-rotation plane is provided with at least one groove.

Optionally, in any embodiment of the present application, a flow area of the rotary air duct on an outer side surface of the third connection portion is larger than a flow area on an inner side surface of the third connection portion.

Optionally, in any embodiment of the present application, the bushing is cast integrally with the turbine case.

Optionally, in any embodiment of the present application, an end surface of the lower end of the valve body is a spherical surface, and an end surface of the upper end of the bushing is a conical surface.

Optionally, in any embodiment of the present application, a spring washer is further included, which is mounted between the connecting rod and the washer.

Among the technical scheme of this application embodiment, turbine case exhaust gas bypass device, including valve body, connecting rod, packing ring and bush, wherein: the bush is embedded in a valve seat of the turbine case, the inner center of the bush includes an exhaust gas passage, and the exhaust gas passage of the bush is communicated with the exhaust gas passage of the turbine case; the valve body is arranged on a valve seat of the turbine box, and the end surface of the lower end of the valve body is in contact fit with the end surface of the upper end of the bushing; the connecting rod is installed on the valve body through the gasket and drives the valve body to axially rotate. Therefore, the spiral flow characteristic is given to the bypass exhaust gas flowing through the liner, the exhaust gas bypass capacity of the turbocharger is improved, the vibration noise caused by the impact of the bypass exhaust gas on the valve body is reduced, and the turbine efficiency of the exhaust gas turbocharger is effectively improved.

Drawings

In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without inventive exercise.

FIG. 1 is a schematic view of a turbine case exhaust gas bypass device according to an embodiment of the present application;

FIG. 2 is a schematic view of a liner of a turbine case exhaust gas bypass device according to an embodiment of the present application;

FIG. 3 is a cross-sectional view of a liner of the exhaust gas bypass device of the turbine case according to the first embodiment of the present application;

FIG. 4 is a cross-sectional view taken along line A-A of the bushing shown in FIG. 3 according to one embodiment of the present application;

fig. 5 is a schematic flow diagram of an exhaust gas flow of the turbine box exhaust gas bypass device according to the first embodiment of the present application.

Detailed Description

It is not necessary for any particular embodiment of the invention to achieve all of the above advantages at the same time.

In order to make the technical solutions of the present invention better understood, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

Example one

Referring to fig. 1, a schematic diagram of a turbine box exhaust gas bypass device according to an embodiment of the present invention is shown.

As shown in fig. 1, the present embodiment provides a turbine box exhaust gas bypass device including a valve body 200, a connecting rod 300, a gasket 400, and a bush 500, wherein: the bushing 500 is embedded in the valve seat 101 of the turbine case 100, the inner center of the bushing includes an exhaust gas passage 504, and the exhaust gas passage 504 of the bushing 500 communicates with the exhaust gas passage 102 of the turbine case 100; the valve body 200 is installed on the valve seat 101 of the turbine box 100, and the end surface 201 at the lower end of the valve body is in contact fit with the end surface 511 at the upper end of the bushing; the connecting rod 300 is mounted on the valve body 200 through the washer 400, and the valve body 200 is driven to axially rotate by the connecting rod 300.

In this embodiment, the turbine case 100 includes an exhaust gas passage 102 and a valve seat 101, and an outlet of the exhaust gas passage 102 of the turbine case 100 is located on the valve seat 101. The bush 500 is embedded in the valve seat 101 of the turbine case 100, and the inner center of the bush 500 includes an exhaust gas passage 504, and the exhaust gas passage 504 of the bush 500 communicates with the exhaust gas passage 102 of the turbine case 100. The end surface 201 at the lower end of the valve body is in sealing fit with the end surface 511 at the upper end of the bushing so as to seal the exhaust gas channel 504 at the center of the interior of the bushing. The connecting rod 300 is installed on the valve body 200 through a gasket 400, and the valve body 200 can be driven to rotate axially through the connecting rod 300, so that the end surface of the lower end of the valve body 200 is separated from the end surface 511 of the upper end of the bushing to control the opening of the exhaust gas channel 504 of the bushing 500; or the end surface 201 of the lower end of the valve body 200 is in sealing fit with the end surface 511 of the upper end of the bushing to control the closing of the exhaust gas channel 504 of the bushing 500. When the exhaust gas passage 504 of the liner 500 is opened, the bypass exhaust gas flows through the exhaust gas passage 102 of the turbine case 100 and then enters the exhaust gas passage 504 of the liner 500, and the bypass exhaust gas is given a spiral flow characteristic in the exhaust gas passage 504 of the liner 500, thereby improving the flow characteristic of the bypass exhaust gas, reducing the impact of the high-temperature and high-pressure airflow on the valve body 200, and reducing noise.

Referring to fig. 2, the figure is a schematic view of a liner of a turbine case exhaust gas bypass device according to an embodiment of the present application; referring to fig. 3, a sectional view of a liner of a turbine case exhaust gas bypass device according to a first embodiment of the present application is shown.

Alternatively, as shown in fig. 2 and 3, the liner 500 includes a first connecting portion 501, a second connecting portion 502, and a third connecting portion 503 located outside the exhaust gas channel 504 of the liner 500, and the first connecting portion 501, the second connecting portion 502, and the third connecting portion 503 are sequentially arranged along the axial direction of the exhaust gas channel 504 of the liner 500; the outer sides of the first connecting part 501 and the second connecting part 502 are embedded in the valve seat 101 of the turbine box 100, and the end surface of the upper end of the first connecting part 501 is in contact with the end surface 201 of the lower end of the valve body; the outer side surface of the third connecting portion 503 and the inner wall of the exhaust gas passage 102 of the turbine box 100 form a circular ring-shaped cavity, and at least two rotary gas passages 513 are included between the outer side surface and the inner side surface of the third connecting portion 503.

The bushing 500 may be a hollow cylinder of a three-step type, that is, the first connection portion 501, the second connection portion 502, and the third connection portion 503 are sequentially disposed in the bushing 500 along the axial direction of the exhaust gas channel 504 of the bushing 500, and when the bypass exhaust gas passes through the exhaust gas channel 504 at the center of the inside of the bushing, the bypass exhaust gas sequentially passes through the third connection portion 503, the second connection portion 502, and the first connection portion 501. And the diameter of the cross section of the first connecting part 501 is larger than that of the cross section of the second connecting part 502, and the cross section of the second connecting part 502 is directly connected with that of the third connecting part 503. The first connection portion 501 and the outer side of the second connection portion 502 are embedded in the valve seat 101 of the turbine case 100, so that the bushing 500 is tightly combined with the valve seat 101 of the turbine case 100, thereby improving the sealing effect between the bushing 500 and the valve seat 101 of the turbine case 100. The area of the end surface 511 at the upper end of the bush is not smaller than the area of the end surface 201 at the lower end of the valve body to improve the sealing effect. The circular ring-shaped cavity is used for splitting the exhaust gas flow in the exhaust gas passage 102 of the turbine case 100, and the rotating air passage 513 is used for rotating the split exhaust gas flow.

For example, refer to FIG. 4, which is a sectional view taken along A-A of the bushing shown in FIG. 3 according to one embodiment of the present application; referring to fig. 5, the flow of the exhaust gas bypass device of the turbine box according to the first embodiment of the present application is schematically shown.

As shown in fig. 4 and 5, when the exhaust gas passage 504 of the liner 500 is opened, the bypass exhaust gas flows through the exhaust gas passage 102 of the turbine case 100 and then enters the exhaust gas passage 504 of the liner 500. When entering the liner 500, the flow of bypass exhaust gas is split into a first exhaust gas flow and a second exhaust gas flow, the first exhaust gas flow flowing directly into the exhaust gas channel 504 in the center of the liner interior; the second exhaust gas flow flows into the annular cavity and then enters the rotary air passage 513, and the second exhaust gas flow changes the flow direction and flows tangentially along the circumference of the inner wall of the liner 500 into the exhaust gas channel 504 at the center of the inner part of the liner under the guidance of the rotary air passage 513. When the first and second exhaust gas flows merge at the exhaust passage 504 at the center of the liner interior, the bypass exhaust gas at the center of the liner 500 is caused to impart a helical flow characteristic, resulting in a helical exhaust gas flow. Further, the spiral exhaust gas flows toward the inner side surface of the liner 500 by the centrifugal force, so that a low pressure region is formed at the axial portion of the exhaust gas passage 504 at the center of the inside of the liner, that is, at the center of the exhaust gas passage of the first connection portion 501, at a position corresponding to the middle position of the valve body 200, to reduce the impact of the gas flow on the valve body 200. Therefore, the problems of ageing and abrasion, noise generation and vibration of the waste gas bypass structure are solved, and the bypass waste gas flow characteristic of the waste gas bypass valve is improved.

Wherein all the rotary air passages 513 are uniformly distributed on the third connecting portion 503, and the side surfaces of the rotary air passages 513 are tangentially connected with the inner side surface of the third connecting portion 503. The shape, size, distribution number, etc. of the rotary air passage 513 all have a significant influence on the form of the spiral air flow, and the spiral waste gas achieves an optimal swirl ratio through the design of the rotary air passage 513, so that the bypass waste gas generates a strong rotary air flow after flowing through the rotary air passage 513.

Wherein a flow area of the rotary air duct 513 on an outer side surface of the third connection portion 503 is larger than a flow area on an inner side surface of the third connection portion 503. And the exhaust gas flow enters the rotating air duct 513 from the outer side surface of the third connecting part 503 and flows out from the inner side surface of the third connecting part 503, and the gas volume entering the passage is equal to the gas volume flowing out of the passage in the same time, so that the exhaust gas flow flowing out from the inner side surface of the third connecting part 503 has a higher flow velocity, thereby generating a strong rotating gas flow.

For example, the third connecting portion 503 may be provided with four rotary air passages 513, and the rotary air passages 513 are uniformly distributed on the ground third connecting portion and penetrate through the side wall of the third connecting portion 503. Both side surfaces of the rotary air duct 513 are tangentially connected to the inner side surface of the third connecting portion 503. The flow area of the rotary air duct 513 on the outer side surface of the third connecting portion 503 is made larger than the flow area on the inner side surface of the third connecting portion 503. The sides of the swirling air path 513 direct the exhaust gas flow to generate a swirling air flow.

The outer side surface of the second connecting portion 502 includes at least one ring groove 512. When the bush 500 is fitted in the valve seat 101 of the turbine case 100, the ring groove 512 is engaged with the valve seat 101 of the turbine case 100 to prevent the bush 500 from sliding in the axial direction of the bush 500 with respect to the valve seat 101 of the turbine case 100.

Wherein, the outer side surface of the second connecting part 502 comprises at least one anti-rotation plane 522. When the bushing 500 is embedded in the valve seat 101 of the turbine case 100, the square rotation plane prevents the bushing 500 from rotating relative to the valve seat 101 of the turbine case 100 by the fitting structure with the upper plane of the base.

Wherein the anti-rotation plane 522 is provided with at least one groove 532. The groove 532 allows the turbine case material to be poured and embedded therein, forming a structure corresponding to the groove. This groove 532 may cooperate with the base of the turbine case 100 to secure when the liner 500 is embedded in the valve seat 101 of the turbine case 100, thereby further preventing the liner 500 from rotating or sliding relative to the base of the turbine case 100. In addition, the grooves 532 do not extend through the exhaust passage into the center of the interior of the hair sleeve.

Alternatively, the bushing 500 is integrally molded with the turbine case 100. Wherein the liner 500 is embedded in the volute material to ensure that the liner 500 is integrated with the turbine case 100 casting. The bushing 500 material needs to have high temperature, oxidation, and wear resistance to improve turbocharger service life. It can be sintered and formed by alloy powder formula, and the formed bushing 500 is integrally cast with the valve seat 101 of the turbine box 100. For example, when the turbine case 100 is made of cast iron, it is oxidized at a high temperature to form scale, thereby generating internal blowby gas. Therefore, the material of the bushing 500 can be a stainless steel material mainly containing chromium and molybdenum phases, so that the sealing performance of the waste bypass structure is improved; or the material of the bushing 500 may be nickel, tungsten, vanadium, or other alloy components, so that the bushing 500 has a self-lubricating function after sintering and forming.

Optionally, the end surface 201 of the lower end of the valve body is a spherical surface, and the end surface 511 of the upper end of the bushing is a conical surface. The end surface 511 at the upper end of the bushing is the upper end surface of the first connecting portion 501, when the end surface 201 at the lower end of the valve body 200 is attached to the end surface 511 at the upper end of the bushing, the spherical surface is in contact with the conical surface, the tangential contact concept of the conical surface and the spherical surface is applied, the sealing specific pressure between the valve body 200 and the bushing 500 tends to be uniformly distributed, and the resultant force of the sealing force passes through the center of the valve body 200, so that the sealing efficiency is greatly improved, the low-speed torque of the engine is improved, and the exhaust noise is reduced. When the end face 201 of the lower end of the valve body 200 is separated from the end face 511 of the upper end of the bush, the spherical end face can better split the exhaust gas flow than a planar end face, and the valve body 200 is uniformly stressed to reduce the exhaust gas noise. The conical surface of the upper end of the bush 500 may be machined together with the turbine case 100 to secure the sealing accuracy.

Optionally, a spring washer 600 is further included and mounted between the connecting rod 300 and the washer 400. The spring pad 600 has a certain pre-tightening force in an installation state, so that the connecting rod 300 and the washer 400 are flexibly connected to eliminate noise generated by knocking vibration.

Wherein, the spring washer 600 may be a bowl-shaped spring washer 600 to better eliminate the gap between the washer 400 and the connecting rod 300 of the valve body 200,

as can be seen from the above embodiments of the present invention, the turbine box exhaust gas bypass device adds the embedded bushing 500 to the exhaust gas turbine box 100 to provide a spiral flow characteristic to the bypass exhaust gas flowing through the bushing 500, so as to improve the exhaust gas bypass capability of the turbocharger and reduce the vibration noise of the exhaust gas bypass device caused by the impact of the bypass exhaust gas on the valve body 200. And the contact sealing of the spherical surface of the valve body 200 and the conical surface of the valve seat 101 of the bushing 500 is used for replacing the plane sealing, and the integral casting process of the valve seat 101 and the bushing 500 is adopted, so that the strength and the sealing performance of the waste gas valve seat 101 are improved. Thereby effectively improving the turbine efficiency of the exhaust gas turbocharger.

It should be noted that, in the present specification, all the embodiments are described in a progressive manner, and the same and similar parts among the embodiments may be referred to each other, and each embodiment focuses on the differences from the other embodiments. The above-described embodiments of the apparatus and system are merely illustrative, and the modules illustrated as separate components may or may not be physically separate, and the components suggested as modules may or may not be physical modules, may be located in one place, or may be distributed on a plurality of network modules. Some or all of the modules may be selected according to actual needs to achieve the purpose of the solution of the present embodiment. One of ordinary skill in the art can understand and implement it without inventive effort.

The above description is only one specific embodiment of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered by the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. The utility model provides a turbine case exhaust gas bypass device which characterized in that, includes valve body, connecting rod, packing ring and bush, wherein:

the bush is embedded in a valve seat of the turbine case, the inner center of the bush includes an exhaust gas passage, and the exhaust gas passage of the bush is communicated with the exhaust gas passage of the turbine case;

the valve body is arranged on a valve seat of the turbine box, and the end surface of the lower end of the valve body is in contact fit with the end surface of the upper end of the bushing;

the connecting rod is installed on the valve body through the gasket and drives the valve body to rotate axially;

the bushing comprises a first connecting part, a second connecting part and a third connecting part which are positioned on the outer side of the exhaust gas channel of the bushing, and the first connecting part, the second connecting part and the third connecting part are sequentially arranged along the axial direction of the exhaust gas channel of the bushing;

the outer sides of the first connecting part and the second connecting part are embedded in a valve seat of the turbine box, and the end surface of the upper end of the first connecting part is in contact fit with the end surface of the lower end of the valve body;

the outer side face of the third connecting portion and the inner wall of the exhaust gas channel of the turbine box form a circular cavity, and at least two rotary air passages are arranged between the outer side face and the inner side face of the third connecting portion.

2. The turbine box exhaust gas bypass device according to claim 1, wherein all the rotating gas passages are uniformly distributed on the third connecting portion, and the side surfaces of the rotating gas passages are tangentially connected to the inner side surface of the third connecting portion.

3. The turbine case exhaust gas bypass device according to claim 1, wherein the second connection portion includes at least one ring groove on an outer side surface thereof.

4. The turbine case exhaust gas bypass device according to claim 1, wherein the second connecting portion includes at least one rotation-preventing flat on an outer side surface thereof.

5. The turbine case exhaust gas bypass device according to claim 4, wherein at least one groove is provided on the rotation-preventing plane.

6. The turbine case exhaust gas bypass device according to claim 1, wherein a flow area of the rotation gas passage is larger at an outer side surface of the third connection portion than at an inner side surface of the third connection portion.

7. The turbine case exhaust gas bypass arrangement of claim 1, wherein the bushing is cast integral with the turbine case.

8. The turbine box exhaust gas bypass device according to claim 1, wherein an end surface of the lower end of the valve body is a spherical surface, and an end surface of the upper end of the bushing is a conical surface.

9. The turbine case exhaust gas bypass arrangement of claim 1, further comprising a spring washer mounted between the connecting rod and the washer.