CN115075899A - Integrated serial two-stage supercharging structure for realizing high-low pressure stage pressure ratio distribution - Google Patents

Abstract

The invention discloses an integrated tandem type two-stage supercharging structure for realizing high-low pressure stage pressure ratio distribution, which comprises a low-pressure stage compressor, a low-pressure stage turbine, a high-pressure stage compressor and a high-pressure stage turbine; the waste gas outlet on the high-pressure stage worm gear box, namely the outlet of the high-pressure stage worm gear box, is directly butted with the waste gas inlet on the low-pressure stage worm gear box of the low-pressure stage turbine, namely the inlet of the low-pressure stage worm gear box. Compared with the prior art, the waste gas discharged after the expansion work of the high-pressure stage turbine is not required to be introduced into the low-pressure stage turbine box through the exhaust pipe, but directly flows into the low-pressure stage turbine box, so that the pressure flow loss is reduced.

Description

Integrated serial two-stage supercharging structure for realizing high-low pressure stage pressure ratio distribution

The technical field is as follows:

the invention relates to the technical field of turbochargers for internal combustion engines, in particular to an integrated series two-stage supercharging structure for realizing high-low pressure stage pressure ratio distribution.

Background art:

the two-stage supercharging technology is that two turbochargers are operated jointly, and air can be compressed in one stage or two stages by a control system according to various adjusting measures in different sequences and different proportions. Compared with single-stage turbocharging, the two-stage turbocharging can obtain higher pressure ratio, and can realize better fuel economy and lower emission index while improving the power of an engine, low-speed torque and transient response. Because the pressure ratio of each stage of pressurization is relatively low, the load of each stage of pressurization is reduced, and the reliability is better.

Tandem two-stage supercharging is one way of arranging a two-stage supercharger structure, see fig. 1-5. When the air compressor works, fresh air firstly enters the low-pressure stage air compressor 1, the temperature and the pressure of the air are improved after the air is compressed by the low-pressure stage air compressor 1, then the air flows into the high-pressure stage air compressor 3, and the pressure is further improved after the air is compressed by the high-pressure stage air compressor 3 again. The air compressed by two stages firstly enters a cylinder of an engine 6 after passing through an intercooler 5, the exhaust gas after combustion flows into a high-pressure stage turbine 4, the exhaust gas discharged after expansion work of the high-pressure stage turbine 4 enters a low-pressure stage turbine 2 to continue to expand work, and finally the exhaust gas is discharged into the atmosphere. The low-pressure stage turbine 2 drives the low-pressure stage compressor 1 to work, and the high-pressure stage turbine 4 drives the high-pressure stage compressor 3 to work. A bypass valve 7 is provided between the inlet and the outlet of the high-pressure stage turbine 4.

The downsizing and weight reduction of the engine 6 are the future development trends. In the current series two-stage supercharging structure, the exhaust gas discharged after the high-pressure stage turbine 4 expands and works enters the low-pressure stage turbine 2 in 2 structural modes, the first structural mode is to design a section of exhaust manifold to introduce the exhaust gas into a turbine box of the low-pressure stage turbine 2, and the second structural mode is to integrate the turbine box of the low-pressure stage turbine 2 and the exhaust manifold. However, in any structure, a large arrangement space is occupied, and the arrangement of the engine is affected. Meanwhile, the exhaust pipeline is long, so that certain pressure loss can be caused.

In addition, in the existing serial two-stage supercharging structure, the low-pressure stage turbine box and the exhaust manifold are designed in an integrated mode, and waste gas exhausted by the high-pressure stage turbine box is introduced into the low-pressure stage turbine box to expand to do work. However, the volume of the supercharger is too large, the weight is increased, and the exhaust pressure is lost.

Disclosure of Invention

The invention aims to solve the technical problem of providing an integrated series two-stage supercharging structure for realizing high-low pressure stage pressure ratio distribution aiming at the technical problem of the existing series two-stage supercharging structure. It is through improving low pressure level turbine case structure and high pressure level turbine case structure, when having designed high, low pressure level booster and all possess the waste gas bypass function, has reduced the space of arranging high, low pressure level turbocharger and occupy, makes its structure compacter to solve above problem.

In order to achieve the purpose, the integrated series two-stage supercharging structure for realizing high-low pressure stage pressure ratio distribution comprises a low-pressure stage compressor, a low-pressure stage turbine, a high-pressure stage compressor and a high-pressure stage turbine; the low-pressure stage turbine drives the low-pressure stage compressor to work, and the high-pressure stage turbine drives the high-pressure stage compressor to work; the low-pressure stage compressor is provided with a low-pressure stage compressed air inlet and a low-pressure stage compressed air outlet, and the high-pressure stage compressor is provided with a high-pressure stage compressed air inlet and a high-pressure stage compressed air outlet; a low-pressure stage compressed air outlet on the low-pressure stage compressor is connected with a high-pressure stage compressed air inlet on the high-pressure stage compressor through a pipeline, a high-pressure stage compressed air outlet on the high-pressure stage compressor is connected with an inlet of the intercooler through a pipeline, an outlet of the intercooler is connected with a cylinder of an engine, an exhaust gas outlet of the cylinder of the engine is connected with an exhaust gas inlet on a high-pressure stage worm gear box of the high-pressure stage turbine, namely an inlet of the high-pressure stage turbine box, through a pipeline, and an exhaust gas outlet on a low-pressure stage worm gear box of the low-pressure stage turbine, namely an outlet of the low-pressure stage turbine box, is evacuated; the exhaust gas outlet on the high-pressure stage worm gear box, namely the outlet of the high-pressure stage turbine box, is directly butted with the exhaust gas inlet on the low-pressure stage worm gear box of the low-pressure stage turbine, namely the inlet of the low-pressure stage turbine box.

In a preferred embodiment of the present invention, the low-pressure stage turbine box is compressed and integrated with a flow path portion of an exhaust gas inlet of the high-pressure stage turbine box, i.e., an inlet of the high-pressure stage turbine box.

In a preferred embodiment of the invention, the exhaust gas inlet on the high-pressure stage turbine case, i.e. the high-pressure stage turbine case inlet, is designed to admit air in a direction parallel to the high-pressure stage rotor shaft of the high-pressure stage turbine.

In a preferred embodiment of the invention, the exhaust gas outlet on the high-pressure stage turbine case, i.e. the high-pressure stage turbine case outlet, is designed to exhaust in a direction parallel to the high-pressure stage rotor shaft of the high-pressure stage turbine.

In a preferred embodiment of the invention, the inlet end face of the exhaust gas inlet on the high-pressure stage worm gear box, namely the inlet of the high-pressure stage turbine box, is designed on the same flange face as the outlet end face of the exhaust gas outlet on the high-pressure stage worm gear box, namely the outlet of the high-pressure stage turbine box,

in a preferred embodiment of the invention, the low-pressure stage rotor shaft of the low-pressure stage turbine is axially perpendicular to the high-pressure stage rotor shaft of the high-pressure stage turbine.

In a preferred embodiment of the invention, the exhaust gas inlet on the low-pressure stage turbine casing of the low-pressure stage turbine, i.e. the low-pressure stage turbine casing inlet, is designed to admit air perpendicular to the direction of the low-pressure stage rotor shaft of the low-pressure stage turbine.

In a preferred embodiment of the invention, the exhaust gas outlet on the low-pressure stage turbine casing of the low-pressure stage turbine, i.e. the low-pressure stage turbine casing outlet, is designed to exhaust gas in the direction of the low-pressure stage rotor shaft of the low-pressure stage turbine before being bent into a direction perpendicular to the low-pressure stage rotor shaft of the low-pressure stage turbine.

In a preferred embodiment of the invention, a low-pressure stage bypass valve is arranged on the tail section of the exhaust gas inlet of the low-pressure stage turbine box of the low-pressure stage turbine, namely the inlet of the low-pressure stage turbine box, the low-pressure stage bypass valve controls the action of a low-pressure stage actuator, and the boost pressure of the low-pressure stage compressor is controlled by the low-pressure stage actuator.

In a preferred embodiment of the present invention, a high-pressure stage bypass valve is disposed at an exhaust gas inlet of a high-pressure stage turbine casing of the high-pressure stage turbine, i.e., at an inlet of the high-pressure stage turbine casing, and the high-pressure stage bypass valve controls an operation of a high-pressure stage actuator, and controls a boost pressure of a high-pressure stage compressor by the high-pressure stage actuator.

In a preferred embodiment of the present invention, the high-pressure stage actuator is disposed on the low-pressure stage worm gear box, and the high-pressure stage actuator is connected to the volute of the high-pressure stage compressor through a rubber pipe.

In a preferred embodiment of the present invention, the high-pressure stage bypass valve is provided on an outlet end surface of an exhaust gas outlet on the high-pressure stage worm gear case, i.e., a high-pressure stage turbine case outlet, and an inlet end surface of an exhaust gas inlet on the low-pressure stage worm gear case of the low-pressure stage turbine, i.e., a low-pressure stage turbine case inlet.

In a preferred embodiment of the invention, an exhaust gas bypass mechanism is arranged between the high-pressure stage worm gear box and the low-pressure stage worm gear box, so that the high-pressure stage and the low-pressure stage are distributed in a pressure ratio.

Compared with the prior art, the invention adopts the technical scheme that the waste gas exhausted after the expansion work of the high-pressure stage turbine is introduced into the low-pressure stage turbine box without passing through the exhaust pipe, but directly flows into the low-pressure stage turbine box, thereby reducing the pressure flow loss. Meanwhile, the low-pressure stage turbine box structure compresses and integrates the inlet part of the high-pressure stage turbine box flow channel, so that the two-stage supercharging arrangement is compact, and the two-stage supercharging weight is effectively reduced. Finally, because the waste gas bypass valve and the waste gas bypass mechanism are designed in the high-pressure stage and the low-pressure stage, the pressure ratio distribution of the high-pressure stage and the low-pressure stage can be realized, and the method is suitable for popularization.

Drawings

Fig. 1 is a schematic diagram of a conventional two-stage supercharger.

Fig. 2 is a schematic diagram of a conventional high-pressure stage supercharger.

Fig. 3 is a schematic structural diagram of a conventional low-pressure stage supercharger.

Fig. 4 is a schematic view (viewed from one direction) of a conventional two-stage supercharger assembly.

Fig. 5 is a schematic view (viewed from another direction) of a conventional two-stage supercharger assembly.

Fig. 6 is a schematic view (from one direction) of the high-pressure stage supercharger of the present invention.

Fig. 7 is a schematic view (viewed from another direction) of the high-pressure stage supercharger of the present invention.

Fig. 8 is a schematic view (from one direction) of the low pressure stage booster configuration of the present invention.

Fig. 9 is a schematic view (viewed from another direction) of the low pressure stage booster configuration of the present invention.

Fig. 10 is a schematic view (from one direction) of the assembled two-stage supercharger of the present invention.

Fig. 11 is a schematic view (viewed from another direction) of the assembled two-stage supercharger of the present invention.

The specific implementation mode is as follows:

the invention is further described below in conjunction with the appended drawings and detailed description.

Referring to fig. 6 to 11, an integrated tandem two-stage supercharging structure for realizing high-low pressure stage pressure ratio distribution is shown, which comprises a low-pressure stage compressor 10, a low-pressure stage turbine 20, a high-pressure stage compressor 30 and a high-pressure stage turbine 40. The low-pressure stage turbine 20 drives the low-pressure stage compressor 10 to work, and the high-pressure stage turbine 40 drives the high-pressure stage compressor 30 to work.

Referring particularly to fig. 8 to 9, the low-pressure stage compressor 10 is provided with a low-pressure stage compressed air inlet 11 and a low-pressure stage compressed air outlet 12, and the low-pressure stage turbine casing 21 of the low-pressure stage turbine 20 is provided with an exhaust gas outlet, i.e., a low-pressure stage turbine casing outlet 22, and an exhaust gas inlet, i.e., a low-pressure stage turbine casing inlet 23.

The exhaust gas inlet on the low-pressure stage worm gear case 21 of the low-pressure stage turbine 20, i.e. the low-pressure stage turbine case inlet 22, is designed to be air-intake in a direction perpendicular to the low-pressure stage rotor shaft (not shown in the figure) of the low-pressure stage turbine 20; the exhaust gas outlet on the low-pressure stage worm gear case 21 of the low-pressure stage turbine 20, that is, the low-pressure stage turbine case outlet 23, is designed to exhaust gas in the direction of the low-pressure stage rotor shaft of the low-pressure stage turbine 20 and then to be bent in the direction perpendicular to the low-pressure stage rotor shaft of the low-pressure stage turbine 20.

Referring particularly to fig. 6 to 7, the high-pressure stage compressor 30 is provided with a high-pressure stage compressed air inlet 31 and a high-pressure stage compressed air outlet 32, and the high-pressure stage worm gear case 41 of the high-pressure stage turbine 40 is provided with an exhaust gas inlet, i.e., a high-pressure stage turbine case inlet 42, and an exhaust gas outlet, i.e., a high-pressure stage turbine case outlet 43.

The exhaust gas inlet on the high-pressure stage worm gear case 41, i.e. the high-pressure stage turbine case inlet 42, is designed to admit air in a direction parallel to the high-pressure stage rotor shaft (not shown in the figures) of the high-pressure stage turbine 40; the exhaust gas outlet on the high-pressure stage turbine case 41, i.e. the high-pressure stage turbine case outlet 43, is designed to exhaust in a direction parallel to the high-pressure stage rotor shaft of the high-pressure stage turbine 40.

The exhaust gas inlet on the high-pressure stage worm gear case 41, i.e. the inlet end face of the high-pressure stage worm gear case inlet 42, and the exhaust gas outlet on the high-pressure stage worm gear case 41, i.e. the outlet end face of the high-pressure stage worm gear case outlet 43, are designed on the same flange face.

Referring to fig. 10 and 11 in particular, after the low-pressure stage compressor 10, the low-pressure stage turbine 20, the high-pressure stage compressor 30 and the high-pressure stage turbine 40 are assembled together by fastening 6 studs and nuts, the low-pressure stage compressed air outlet 12 of the low-pressure stage compressor 10 is connected with the high-pressure stage compressed air inlet 31 of the high-pressure stage compressor 30 through a pipeline, the high-pressure stage compressed air outlet 32 of the high-pressure stage compressor 30 is connected with an inlet of an intercooler (not shown in the figure) through a pipeline, and an outlet of the intercooler is connected with a cylinder (not shown in the figure) of the engine.

The exhaust gas outlet of the engine cylinder is connected by a pipe to the exhaust gas inlet on the high-pressure stage worm gear case 41 of the high-pressure stage turbine 40, i.e. the high-pressure stage turbine case inlet 42, and the exhaust gas outlet on the low-pressure stage worm gear case 21 of the low-pressure stage turbine 20, i.e. the low-pressure stage turbine case outlet 22, is evacuated.

The invention is characterized in that: the exhaust gas outlet on the high pressure stage worm gear case 41, i.e. the high pressure stage turbine case outlet 43, is directly interfaced with the exhaust gas inlet on the low pressure stage worm gear case 21, i.e. the low pressure stage turbine case inlet 23, of the low pressure stage turbine 20.

In addition, the low-pressure stage turbine casing 21 is compressed and integrated with a flow path portion of an exhaust gas inlet of the high-pressure stage turbine casing 41, i.e., a high-pressure stage turbine casing inlet 42.

Meanwhile, the low-pressure stage rotor shaft axis direction of the low-pressure stage turbine 20 is perpendicular to the high-pressure stage rotor shaft axis direction of the high-pressure stage turbine 40.

The invention also provides a low-pressure stage bypass valve 24 at the tail section of the exhaust gas inlet of the low-pressure stage worm gear box 21 of the low-pressure stage turbine 20, namely the inlet 23 of the low-pressure stage turbine box, wherein the low-pressure stage bypass valve 24 controls the action of a low-pressure stage actuator 25, and the low-pressure stage actuator 25 controls the supercharging pressure of the low-pressure stage compressor 10.

A high-pressure stage bypass valve 44 is provided at a high-pressure stage turbine case inlet 42, which is an exhaust gas inlet of the high-pressure stage worm gear case 41 of the high-pressure stage turbine 40, and the high-pressure stage bypass valve 44 controls an operation of a high-pressure stage actuator 45, and controls a boost pressure of the high-pressure stage compressor 30 by the high-pressure stage actuator 45.

Further, a high-pressure stage actuator 45 is arranged on the low-pressure stage worm gear box 21, and the high-pressure stage actuator 45 is connected with a volute of the high-pressure stage compressor 30 through a rubber pipe 46.

The high-pressure stage bypass valve 44 is provided on an outlet end surface of an exhaust gas outlet on the high-pressure stage worm gear case 40, i.e., the high-pressure stage turbine case outlet 43, and an inlet end surface of an exhaust gas inlet on the low-pressure stage worm gear case 21 of the low-pressure stage turbine 20, i.e., the low-pressure stage turbine case inlet 23.

Furthermore, an exhaust gas bypass mechanism (not shown) is disposed between the high-pressure stage worm gear case 41 and the low-pressure stage worm gear case 21, so as to realize the pressure ratio distribution of the high-pressure stage and the low-pressure stage.

Claims (10)

1. An integrated series two-stage supercharging structure for realizing high-low pressure stage pressure ratio distribution comprises a low-pressure stage compressor, a low-pressure stage turbine, a high-pressure stage compressor and a high-pressure stage turbine; the low-pressure stage turbine drives the low-pressure stage compressor to work, and the high-pressure stage turbine drives the high-pressure stage compressor to work; the low-pressure stage compressor is provided with a low-pressure stage compressed air inlet and a low-pressure stage compressed air outlet, and the high-pressure stage compressor is provided with a high-pressure stage compressed air inlet and a high-pressure stage compressed air outlet; a low-pressure stage compressed air outlet on the low-pressure stage compressor is connected with a high-pressure stage compressed air inlet on the high-pressure stage compressor through a pipeline, a high-pressure stage compressed air outlet on the high-pressure stage compressor is connected with an inlet of the intercooler through a pipeline, an outlet of the intercooler is connected with a cylinder of an engine, an exhaust gas outlet of the cylinder of the engine is connected with an exhaust gas inlet on a high-pressure stage worm gear box of the high-pressure stage turbine, namely an inlet of the high-pressure stage turbine box, through a pipeline, and an exhaust gas outlet on a low-pressure stage worm gear box of the low-pressure stage turbine, namely an outlet of the low-pressure stage turbine box, is evacuated; the exhaust gas outlet on the high-pressure stage worm gear box, namely the outlet of the high-pressure stage turbine box, is directly butted with the exhaust gas inlet on the low-pressure stage worm gear box of the low-pressure stage turbine, namely the inlet of the low-pressure stage turbine box.

2. The integrated series two-stage supercharging structure for realizing high-low pressure stage pressure ratio distribution according to claim 1, wherein the low-pressure stage turbine casing is compressed and integrated with a flow passage part of an exhaust gas inlet of the high-pressure stage turbine casing, i.e. an inlet of the high-pressure stage turbine casing.

3. An integrated series two-stage supercharging arrangement for achieving high-low pressure stage ratio division according to claim 2, wherein the exhaust gas inlet on the high-pressure stage turbine case, i.e. the high-pressure stage turbine case inlet, is designed to admit air in a direction parallel to the high-pressure stage rotor shaft of the high-pressure stage turbine; the exhaust gas outlet on the high pressure stage turbine case, i.e. the high pressure stage turbine case outlet, is designed to exhaust in a direction parallel to the high pressure stage rotor shaft of the high pressure stage turbine.

4. An integrated series two-stage supercharging structure for realizing high-low pressure stage pressure ratio distribution according to claim 3, wherein the inlet end face of the exhaust gas inlet on the high-pressure stage worm gear case, i.e. the inlet of the high-pressure stage turbine case, and the outlet end face of the exhaust gas outlet on the high-pressure stage worm gear case, i.e. the outlet of the high-pressure stage turbine case, are designed on the same flange face; the low-pressure stage rotor shaft axis of the low-pressure stage turbine is perpendicular to the high-pressure stage rotor shaft axis of the high-pressure stage turbine.

5. An integrated series two-stage supercharging arrangement according to claim 4, wherein the exhaust gas inlet on the low-pressure stage worm gear case of the low-pressure stage turbine is designed to admit air in a direction perpendicular to the low-pressure stage rotor shaft of the low-pressure stage turbine; the exhaust gas outlet on the low-pressure stage worm gear box of the low-pressure stage turbine, namely the outlet of the low-pressure stage turbine box, is designed to exhaust along the direction of a low-pressure stage rotor shaft of the low-pressure stage turbine and then bend into exhaust in the direction vertical to the low-pressure stage rotor shaft of the low-pressure stage turbine.

6. An integrated series two-stage supercharging structure for realizing high-low pressure stage pressure ratio distribution according to claim 5, wherein a low-pressure stage bypass valve is provided at the tail section of the exhaust gas inlet of the low-pressure stage worm gear box of the low-pressure stage turbine, i.e. the inlet of the low-pressure stage turbine box, and the low-pressure stage bypass valve controls the action of a low-pressure stage actuator, and the supercharging pressure of the low-pressure stage compressor is controlled by the low-pressure stage actuator.

7. An integrated series two-stage supercharging structure for realizing high-low pressure stage pressure ratio distribution according to claim 6, wherein in a preferred embodiment of the present invention, a high-pressure stage bypass valve is provided at an exhaust gas inlet of a high-pressure stage worm gear box of the high-pressure stage turbine, i.e. at an inlet of the high-pressure stage worm gear box, and the high-pressure stage bypass valve controls the action of a high-pressure stage actuator to control the supercharging pressure of the high-pressure stage compressor.

8. An integrated series two-stage supercharging arrangement for achieving high and low stage pressure ratio division according to claim 7, wherein said high stage actuator is mounted on the low stage worm gear case and said high stage actuator is connected to the volute of the high stage compressor by means of a rubber hose.

9. The integrated series two-stage supercharging architecture according to claim 8, wherein the high-pressure stage bypass valve is disposed between an outlet end face of an exhaust gas outlet of the high-pressure stage turbine casing and an inlet end face of an exhaust gas inlet of the low-pressure stage turbine casing of the low-pressure stage turbine.

10. An integrated series two-stage supercharging arrangement for achieving high-low pressure stage pressure ratio division according to claim 9, wherein in a preferred embodiment of the present invention, a waste gas bypass mechanism is provided between the high-pressure stage worm gear case and the low-pressure stage worm gear case to achieve high-low pressure stage pressure ratio division.

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