JP7298525B2 - turbocharger - Google Patents

Description

The present invention relates to turbochargers.

BACKGROUND ART Conventionally, in an internal combustion engine having a plurality of cylinders, there has been proposed a twin-scroll turbocharger capable of avoiding exhaust gas interference from each cylinder and effectively utilizing exhaust pressure pulsation. For example, in an in-line 4-cylinder internal combustion engine, if the order of combustion is 1st cylinder -> 3rd cylinder -> 4th cylinder -> 2nd cylinder, then 1st cylinder and 4th cylinder A first gas flow path that joins the exhaust gases of the second and third cylinders and guides them to the turbine, and a second gas flow path that joins the exhaust gases of the second and third cylinders and guides them to the turbine are separate gas flow paths. , a twin-scroll turbocharger has been proposed in which each gas flow path leads to a turbine.

For example, in the turbocharger described in Patent Document 1, as shown in FIG. Turbine 136 is shown connected to scroll portion 136S2. In the turbine 136 of Patent Document 1 shown in FIG. 9, when viewed from the position of the rotation axis 136J of the turbine wheel 136T, the first gas flow path 136G1 and the second gas flow path 136G2 (or the first scroll portion 136S1 and the second scroll portion 136S2) radially overlap.

Conventionally, there is also a twin-scroll turbocharger turbine 236 shown in the example of FIG. In the turbine 236 shown in the example of FIG. 10, the first scroll portion 236S1 and the second scroll portion 236S2 overlap in the direction along the rotation axis 236J of the turbine wheel 236T.

JP 2016-132996 A

In the turbine 136 described in Patent Document 1 shown in FIG. 9, a first scroll portion 136S1 of about one turn and a second scroll portion 136S2 of about half a turn are arranged on the outer circumference of a turbine wheel 136T. A turbine scroll portion for a total of about 1.5 turns is arranged. When viewed from the rotation axis 136J of the turbine wheel 136T, the first gas flow path 136G1 and the second gas flow path 136G2, and the first scroll portion 136S1 and the second scroll portion 136S2 overlap in the radial direction. That is, the second gas flow path 136G2 and the second scroll portion 136S2 are arranged on the outer circumference of the turbine wheel 136T, and the first gas flow path 136G1 and the first scroll portion 136S1 are arranged further on the outer circumference of the second scroll portion 136S2. . Accordingly, the radial size of turbine 136 is increased. In addition, two scroll portions (first scroll portion 136S1 and second scroll portion 136S2) that revolve toward the turbine wheel 136T are required, and the two scroll portions gradually decrease in diameter while revolving spirally. The shape of is complicated.

In the turbine 236 shown in FIG. 10, the first scroll portion 236S1 and the second scroll portion 236S2 overlap in the direction along the rotation axis 236J of the turbine wheel 236T. That is, the size of the scroll portion of the turbine 236 in the direction along the rotation axis 236J increases. In addition, two scroll portions (first scroll portion 236S1 and second scroll portion 236S2) that revolve toward the turbine wheel 236T are required, and the two scroll portions gradually decrease in diameter while revolving spirally. The shape of is complicated.

In the conventional twin-scroll turbocharger shown in FIGS. 9 and 10, each of the two parallel scroll portions is arranged on the outer circumference of the turbine wheel. Since it exceeds one circumference of the outer circumference of the , they overlap in the radial direction or the axial direction. In the conventional twin-scroll turbocharger shown in FIG. 9, two parallel scroll portions are arranged in the radial direction, so the size in the radial direction is large. Also, in the conventional twin scroll turbocharger shown in FIG. 10, the two parallel scroll portions are aligned in the axial direction, so the size in the axial direction is large.

SUMMARY OF THE INVENTION The present invention has been devised in view of these points, and provides a turbocharger that has a plurality of gas flow paths to the turbine wheel and that has a simpler shape and can be made more compact. The challenge is to

In order to solve the above-mentioned problems, a first invention of the present invention is a turbocharger that supercharges using the energy of exhaust gas of an internal combustion engine, the turbocharger comprising: a turbine wheel rotatably supported around a turbine rotation axis; It has a turbine scroll portion arranged on the outer periphery of the turbine wheel, a gas introduction passage for guiding exhaust gas to the turbine scroll portion, and a gas discharge port through which the exhaust gas generated by rotating the turbine wheel is discharged. In addition, the turbine scroll portion is formed so as to extend only one round in the circumferential direction of the outer circumference of the turbine wheel. A plurality of nozzles for regulating the flow of gas are arranged along the circumferential direction, and at a position from a gas inlet, which is an inlet of exhaust gas in the gas introduction path, to the nozzle, the gas introduction nozzle is provided. An inlet partition is provided dividing the passageway into a plurality of gas passageways. The plurality of gas flow paths are divided so as not to overlap in the radial direction when viewed from the position of the turbine rotation axis, and are divided so as not to overlap in the direction along the turbine rotation axis. Each of the exhaust gases guided from each of the gas flow paths to the turbine scroll portion flows in a direction that rotates the turbine wheel in a predetermined direction by the plurality of nozzles when the exhaust gas is blown against the turbine wheel. It is a turbocharger that is trimmed to.

Next, a second aspect of the present invention is a turbocharger for supercharging using the energy of exhaust gas from an internal combustion engine, comprising: a turbine wheel rotatably supported around a turbine rotation axis; It has a turbine scroll portion arranged on the outer periphery, a gas introduction path for guiding exhaust gas to the turbine scroll portion, and a gas discharge port for discharging the exhaust gas caused by rotating the turbine wheel. In addition, the turbine scroll portion is formed so as to extend only one round in the circumferential direction of the outer circumference of the turbine wheel. A plurality of nozzles for regulating the flow of gas are arranged along the circumferential direction, and at a position from a gas inlet, which is an inlet of exhaust gas in the gas introduction path, to the nozzle, the gas introduction nozzle is provided. An inlet partition is provided dividing the passageway into a plurality of gas passageways. Any one of the plurality of gas flow paths is connected to the turbine scroll so that the exhaust gas guided into the turbine scroll rotates in one direction along the turbine scroll. and any one of the remaining gas flow paths is arranged so that the exhaust gas guided into the turbine scroll section is swirled along the turbine scroll section in a direction opposite to the one direction. is connected to the turbine scroll portion, and each exhaust gas guided to the turbine scroll portion from each of the gas flow paths blows the turbine wheel through the plurality of nozzles when being blown to the turbine wheel. It is a turbocharger arranged to flow in a direction that rotates in a predetermined direction.

Next, a third aspect of the present invention is a turbocharger for supercharging using the energy of exhaust gas from an internal combustion engine, comprising a turbine wheel rotatably supported around a turbine rotation axis; It has a turbine scroll portion arranged on the outer periphery, a gas introduction path for guiding exhaust gas to the turbine scroll portion, and a gas discharge port for discharging the exhaust gas caused by rotating the turbine wheel. In addition, the turbine scroll portion is formed so as to extend only one round in the circumferential direction of the outer circumference of the turbine wheel. A plurality of nozzles for regulating the flow of gas are arranged along the circumferential direction, and at a position from a gas inlet, which is an inlet of exhaust gas in the gas introduction path, to the nozzle, the gas introduction nozzle is provided. An inlet partition is provided dividing the passageway into a plurality of gas passageways. A flow path end partition extending from a position close to the nozzle to an inner wall of the turbine scroll portion is provided around a position opposite to the gas introduction passage in the turbine scroll portion. a scroll portion connected to each of the gas flow passages to direct exhaust gas from each of the gas flow passages to the turbine wheel by means of the inflow side partition wall and the flow passage end partition wall; Each exhaust gas, which is divided in the circumferential direction and guided from each of the gas flow paths to the turbine scroll portion, is directed toward the turbine wheel in a predetermined direction by the plurality of nozzles when the exhaust gas is blown onto the turbine wheel. It is a turbocharger that is arranged to flow in the direction of rotation.

Next, a fourth invention of the present invention is the turbocharger according to the first invention or the second invention, wherein a position opposite to the gas introduction passage in the turbine scroll portion is surrounded by and a flow path end partition extending from a position close to the nozzle to an inner wall of the turbine scroll portion.

Next, a fifth invention of the present invention is the turbocharger according to the third invention or the fourth invention, wherein the gas passages are two, and the inflow side partition wall and the passage end partition wall is one, and the respective gas inlets corresponding to the respective gas flow paths are arranged adjacent to each other along the direction orthogonal to the turbine rotation axis, and the flow path terminal bulkheads is greater than the distance from the gas inlet of the gas flow path on the side where the exhaust gas reaches the turbine wheel without going around the nozzle to the flow path terminal bulkhead via the turbine scroll portion. Provided so that the distance from the gas inlet of the gas flow path on the side of the gas flowing around the nozzle to reach the turbine wheel to the flow path end bulkhead via the turbine scroll portion is shorter. It is a turbocharger.

Next, a sixth invention of the present invention is the turbocharger according to the third invention or the fourth invention, wherein there are two gas flow paths, the inflow side partition wall and the flow path end partition wall. is one, and the respective gas inlets corresponding to the respective gas flow paths are arranged adjacent to each other along the direction orthogonal to the turbine rotation axis, and the flow path terminal bulkheads is the distance from the gas inlet of the gas flow path on the side where the exhaust gas reaches the turbine wheel without going around the nozzle to the end partition wall of the flow path via the turbine scroll portion; is approximately the same as the distance from the gas inlet of the gas flow path on the side of reaching the turbine wheel through the nozzle to the flow path end bulkhead via the turbine scroll portion. It is a turbocharger provided in

Next, a seventh invention of the present invention is the turbocharger according to any one of the third invention to the sixth invention, wherein the end portion of the flow path end partition wall on the nozzle side The nozzle closest to the end flow bulkhead edge is a turbocharger that is adjacent to the end flow bulkhead end.

Next, an eighth invention of the present invention is the turbocharger according to any one of the first invention to the seventh invention, wherein the inflow-side bulkhead, which is an end on the nozzle side of the inflow-side partition wall, has an inflow The nozzle closest to the side bulkhead end is a turbocharger that is adjacent to the inlet side bulkhead end.

According to the first aspect of the invention, the turbine scroll portion is formed for only one round that is continuous in the circumferential direction of the turbine wheel. Further, the plurality of gas flow paths are divided so as not to overlap in the radial direction when viewed from the turbine rotation axis, and are divided so as not to overlap in the direction along the turbine rotation axis. Therefore, as shown in the examples of FIGS. 3 to 5, the turbine (turbocharger) can have a very simple shape and can be made smaller.

According to the second aspect of the invention, the turbine scroll portion is formed for only one round that is continuous in the circumferential direction of the turbine wheel. Also, one of the plurality of gas flow paths is connected to the turbine scroll portion so that the exhaust gas circulates in one direction along the turbine scroll portion. Any one of the remaining gas flow paths is connected to the turbine scroll so that the exhaust gas is swirled along the turbine scroll in the direction opposite to the one direction. Therefore, as shown in the examples of FIGS. 3 to 5, 7 and 8, the turbine (turbocharger) can have a very simple shape and can be made smaller.

According to the third aspect of the invention, the turbine scroll portion is formed for only one round that is continuous in the circumferential direction of the turbine wheel. In addition, the turbine scroll portion is divided in the circumferential direction into respective regions that guide the exhaust gas from the respective gas passages to the turbine wheel by the inflow bulkhead and the flow passage end bulkhead. Therefore, as shown in the examples of FIGS. 3 to 5, 7 and 8, the turbine (turbocharger) can have a very simple shape and can be made smaller.

According to the fourth aspect, collision (interference) of the exhaust gas guided into the turbine scroll portion by the plurality of gas flow passages and swirling within the turbine scroll portion in different turning directions can be avoided by the flow passage terminal bulkhead. .

According to the fifth invention, for example, the length of the longest exhaust gas path on the side that goes around the nozzle and reaches the turbine wheel and the length of the longest exhaust gas path on the side that reaches the turbine wheel without going around the nozzle. By appropriately setting the positions of the end partitions of the flow passages so that the .

According to the sixth aspect of the invention, the length of the path from the gas inlet on the side reaching the turbine wheel around the nozzle to the channel end partition wall, and the length of the gas from the gas inlet on the side reaching the turbine wheel without going around the nozzle. By setting the position of the flow path end bulkhead at an appropriate position so that the length of the path to the flow path end bulkhead is almost the same, the exhaust gas from each gas flow path is efficiently directed to the turbine wheel. can lead.

According to the seventh invention, the end of the partition wall at the end of the flow path and the nozzle located closest to the end of the partition at the end of the flow path are brought close to each other to make the gap very small, so that the exhaust gas can be efficiently discharged. can be led to the turbine wheel.

According to the eighth aspect of the invention, the end of the inflow-side partition wall and the nozzle closest to the end of the inflow-side partition wall are brought close to each other to make the gap very small, so that the exhaust gas can be more efficiently discharged into the turbine. Can lead to the wheel.

1 is a diagram illustrating an example of a schematic configuration of an internal combustion engine system to which a turbocharger of the present invention is applied; FIG. It is a figure explaining the example of the external appearance of the turbocharger of 1st Embodiment. FIG. 3 is a cross-sectional view taken along line III-III in FIG. 2 and is a diagram for explaining the structure of the turbocharger of the first embodiment; It is a figure explaining the structure of the turbocharger of 2nd Embodiment. It is a figure explaining the structure of the turbocharger of 3rd Embodiment. It is a figure explaining the example of the external appearance of the turbocharger of 4th Embodiment. FIG. 7 is a cross-sectional view taken along line VII-VII in FIG. 6 and is a diagram for explaining the structure of the turbocharger of the fourth embodiment; It is a figure explaining the structure of the turbocharger of 5th Embodiment. 1 is a diagram illustrating an example of a conventional turbocharger (1) having a plurality of gas passages; FIG. FIG. 2 is a diagram illustrating an example of a conventional turbocharger (No. 2) having a plurality of gas passages;

● [Example of schematic configuration of internal combustion engine system 1 (Fig. 1)]
A mode for carrying out the present invention will be described below with reference to the drawings. First, an example of a schematic configuration of an internal combustion engine system 1 to which a turbocharger 30 of the present invention is applied will be described with reference to FIG. In the following description, an in-line four-cylinder diesel engine will be described as an example of the internal combustion engine 10 .

The entire system will be described below in order from the intake side to the exhaust side. An air cleaner (not shown) and an intake flow rate detecting means 21 (for example, an intake flow rate sensor) are provided on the inflow side of the intake pipe 11A. Further, the intake air flow rate detection means 21 is provided with an intake air temperature detection means 28A (for example, an intake air temperature sensor) and an atmospheric pressure detection means 23 (for example, an atmospheric pressure sensor).

The outflow side of the intake pipe 11A is connected to the intake inlet 35A of the compressor 35, and the intake outlet 35B of the compressor 35 is connected to the inflow side of the intake pipe 11B. The compressor 35 of the turbocharger 30 is rotationally driven by a turbine 36 rotationally driven by the energy of the exhaust gas, and supercharges the intake air that has flowed in from the intake pipe 11A to the intake pipe 11B.

The intake pipe 11A on the upstream side of the compressor 35 is provided with compressor upstream pressure detection means 24A (for example, a pressure sensor). A compressor downstream pressure detection means 24B (for example, a pressure sensor) is provided in the intake pipe 11B downstream of the compressor 35 (a position between the compressor 35 and the intercooler 16 in the intake pipe 11B).

An intercooler 16 is arranged upstream of the intake pipe 11</b>B, and a throttle device 47 is arranged downstream of the intercooler 16 . Between the intercooler 16 and the throttle device 47, an intake air temperature detection means 28B (for example, an intake air temperature sensor) is provided.

The throttle device 47 is provided with a throttle valve 47V that adjusts the opening degree of the intake pipe 11B based on a control signal from the control device 50. As shown in FIG. Further, the throttle device 47 is provided with a throttle opening detection means 47S (for example, a throttle opening sensor).

The accelerator pedal depression amount detection means 25 is, for example, an accelerator pedal depression angle sensor, and is provided on the accelerator pedal.

An intake manifold pressure detection means 24C (for example, a pressure sensor) is provided downstream of the throttle device 47 in the intake pipe 11B, and the outflow side of the EGR pipe 13 is connected. The outflow side of the intake pipe 11B is connected to the inflow side of the intake manifold 11C, and the outflow side of the intake manifold 11C is connected to the inflow side of the internal combustion engine . EGR gas that has flowed in from the inflow side of the EGR pipe 13 (the connection with the exhaust pipes 12B1 and 12B2) is discharged into the intake pipe 11B from the outflow side of the EGR pipe 13 (the connection with the intake pipe 11B). be done.

The internal combustion engine 10 has a plurality of cylinders 45A-45D, each of which is provided with an injector 43A-43D. Fuel is supplied to the injectors 43A-43D via a common rail 41 and fuel pipes 42A-42D. The injectors 43A-43D are driven by control signals from a control device 50, and are injected into the respective cylinders 45A-45D. Inject fuel.

The internal combustion engine 10 is provided with crank angle detection means 22, coolant temperature detection means 28C, and the like. Although not shown, the internal combustion engine 10 is provided with cam angle detection means. The control device 50 can detect the rotation angle of the crankshaft and the rotation angle of the camshaft based on the detection signal from the crank angle detection means 22 and the detection signal from the cam angle detection means.

The inflow sides of exhaust manifolds 12A1 and 12A2 are connected to the exhaust side of the internal combustion engine 10, and the inflow sides of exhaust pipes 12B1 and 12B2 are connected to the outflow sides of the exhaust manifolds 12A1 and 12A2. In the in-line four-cylinder internal combustion engine 10 shown in the example of FIG. 1, the order of combustion is the first cylinder --> third cylinder --> fourth cylinder --> second cylinder. Accordingly, the exhaust manifolds 12A1 of the first cylinder 45A and the fourth cylinder 45D are connected to the exhaust pipe 12B1, and the exhaust manifolds 12A2 of the second cylinder 45B and the third cylinder 45C are connected to the exhaust pipe 12B1. It is The length of the exhaust manifold 12A1 from the first cylinder to the exhaust pipe 12B1, the length of the exhaust manifold 12A1 from the fourth cylinder to the exhaust pipe 12B1, the length of the exhaust manifold 12A2 from the second cylinder to the exhaust pipe 12B2, The length of the exhaust manifold 12A2 from the third cylinder to the exhaust pipe 12B2 is substantially the same length (equivalent length) in order to effectively utilize the exhaust pressure pulsation.

The inflow side of the EGR pipe 13 is connected to the exhaust pipes 12B1 and 12B2. The EGR pipe 13 allows the exhaust pipes 12B1, 12B2 and the intake pipe 11B to communicate with each other, and allows part of the exhaust gas from the exhaust pipes 12B1, 12B2 to be recirculated to the intake pipe 11B. An EGR cooler 15 and an EGR valve 14 are provided in the EGR pipe 13 . Exhaust temperature detection means 29 is provided in the exhaust pipe 12B2 (or the exhaust pipe 12B1).

The outflow side of the exhaust pipe 12B1 and the outflow side of the exhaust pipe 12B2 are each connected to the gas inlet 36A of the turbine 36, and the gas discharge port 36B of the turbine 36 is connected to the inflow side of the exhaust pipe 12C. When the turbocharger 30 is the turbocharger 30 shown in FIGS. 2 and 3, the outflow side of the exhaust pipe 12B1 is connected to the gas inlet 36A1 shown in FIGS. It is connected to the gas inlet 36A2 shown in FIGS.

The turbine 36 is provided with a nozzle 33 capable of controlling the flow velocity of the exhaust gas led to the turbine 36 (adjusting the opening degree of the flow path leading the exhaust gas to the turbine). 31 adjusts the opening. The control device 50 outputs a control signal to the nozzle driving means 31 to adjust the opening of the nozzle 33 based on the detection signal from the nozzle opening detection means 32 (for example, nozzle opening sensor) and the target nozzle opening. It is possible.

Turbine upstream pressure detection means 26A is provided in the exhaust pipe 12B1 (or exhaust pipe 12B2) on the upstream side of the turbine . A turbine downstream pressure detection means 26B is provided in the exhaust pipe 12C on the downstream side of the turbine 36 .

An exhaust purification device 61 is connected to the outflow side of the exhaust pipe 12C. For example, when the internal combustion engine 10 is a diesel engine, the exhaust purification device 61 includes an oxidation catalyst, a particulate filter, a selective reduction catalyst, and the like.

The vehicle speed detection means 27 is, for example, a vehicle speed detection sensor, and is provided on the wheels of the vehicle. The vehicle speed detection means 27 outputs a detection signal corresponding to the rotation speed of the wheels of the vehicle to the control device 50 .

The control device 50 has a CPU 51, a RAM 52, a storage device 53, a timer 54 and the like. The control device 50 (CPU 51) receives detection signals from the various detection means described above, and the control device 50 (CPU 51) outputs control signals to the various actuators described above. The input/output of the control device 50 is not limited to the detection means and actuators described above. Also, the temperature, pressure, etc. of each part may be calculated by estimation calculation without mounting the sensor. The control device 50 detects the operating state of the internal combustion engine 10 based on detection signals from various detection means including the detection means described above, and controls various actuators including the actuator described above.

In the turbocharger 30 shown in FIG. 1, the turbocharger 30A of the first embodiment to the turbocharger 30E of the fifth embodiment will be described below.

● [Turbocharger 30A of the first embodiment (Figs. 2 and 3)]
FIG. 2 shows an example of the appearance of the turbocharger 30A of the first embodiment, and FIG. 3 shows a sectional view taken along line III-III in FIG. The turbocharger 30A of the first embodiment (and the turbochargers 30B and 30C of the second and third embodiments) is used when the internal combustion engine 10 is, for example, a four-cylinder or two-cylinder internal combustion engine. It corresponds to the case where there are two exhaust pipes from 10.

The turbocharger 30A has a compressor 35 and a turbine 36, as shown in FIGS. 2 and 3. The turbine 36 includes a turbine wheel 36T, a turbine scroll portion 36S, a gas introduction passage 36F, a gas inlet 36A, and a gas outlet. 36B, etc. The compressor 35 also has a compressor wheel 35T (see FIG. 1) rotatably supported together with the turbine wheel 36T, an intake air inlet 35A, an intake air outlet 35B (see FIG. 1), and the like.

The turbocharger 30A has a nozzle drive means 31 which is an electric motor, a nozzle opening detection means 32 such as an encoder, an arm 31A which transmits power from the nozzle drive means 31 to change the opening of the nozzle 33, and the like. are doing. The control device 50 (see FIG. 1) calculates the target opening of the nozzle 33 based on the operating state of the internal combustion engine 10, and the nozzle opening detected by the nozzle opening detector 32 approaches the target opening. The nozzle drive means 31 is controlled as follows.

The turbine wheel 36T is rotatably supported around a turbine rotation axis 36J. The turbine scroll portion 36S is arranged on the outer circumference of the turbine wheel 36T. In addition, the turbine scroll portion 36S is formed for only one round continuous in the circumferential direction of the outer circumference of the turbine wheel 36T.

The gas introduction path 36F is connected to the exhaust pipes 12B1 and 12B2 (see FIG. 1) and guides the exhaust gas to the turbine scroll portion 36S. Gas inlets 36A1 and 36A2 are provided on the inflow side of the gas introduction path 36F so as to be adjacent to each other along the direction orthogonal to the turbine rotation axis 36J. The exhaust pipe 12B1 (see FIG. 1) is connected to the gas inlet 36A1, and the exhaust pipe 12B2 (see FIG. 1) is connected to the gas inlet 36A2. In addition, an introduction path center axis 36FJ, which is the center axis of the gas introduction path 36F, intersects the turbine rotation axis 36J. The gas inlets 36A1 and 36A2 are set to have approximately the same (equal) opening area.

A plurality of nozzles 33 for arranging the flow of the exhaust gas blown onto the turbine wheel 36T are arranged along the circumferential direction on the outer peripheral portion of the turbine wheel 36T within the turbine scroll portion 36S. The nozzle 33 is attached to a nozzle plate 33P, is turned by the operation of the arm 31A, and adjusts the flow direction and flow velocity of the exhaust gas blown from the turbine scroll portion 36S to the turbine wheel 36T.

At a position from the gas inlet 36A, which is the inlet of the exhaust gas, to the nozzle 33 in the gas introduction path 36F, an inflow side partition wall 36H is provided to divide the gas introduction path 36F into a plurality of gas flow paths 36G1 and 36G2. It is

A channel end partition 36K extending from a position close to the nozzle 33 to the inner wall of the turbine scroll portion 36S is provided around a position opposite to the gas introduction path 36F in the turbine scroll portion 36S.

Here, in FIG. 3, from the gas inlet 36A2 of the gas flow path (the gas flow path 36G2 in the case of FIG. 3) on the side where the exhaust gas reaches the turbine wheel 36T without going around the nozzle 33, the turbine scroll portion 36S2 (36S ) to the end partition wall 36K of the flow path is defined as a distance L2. Further, in FIG. 3, from the gas inlet 36A1 of the gas flow path (the gas flow path 36G1 in the case of FIG. 3) on the side where the exhaust gas goes around the nozzle 33 and reaches the turbine wheel 36T, the turbine scroll portion 36S1 (36S) The distance of the path K1 to the flow path end partition 36K is defined as the distance L1. The channel terminal partition wall 36K is provided at a position where the distance L1 and the distance L2 are substantially the same (equivalent).

As shown in FIG. 3, since the introduction passage center axis 36FJ intersects the turbine rotation axis 36J, the turbine rotation axis 36J is on the extension of the inflow side bulkhead 36H. Therefore, the gas flow path 36G1 and the gas flow path 36G2 are divided so as not to overlap in the radial direction when viewed from the position of the turbine rotation axis 36J. Furthermore, the gas flow path 36G1 and the gas flow path 36G2 are arranged side by side along the direction orthogonal to the turbine rotation axis 36J. Therefore, the gas flow path 36G1 and the gas flow path 36G2 are divided so as not to overlap in the direction along the turbine rotation axis 36J.

Further, the turbine scroll portion 36S1 through which the exhaust gas flows from the gas flow path 36G1 to the path K1 and the turbine scroll portion 36S2 through which the exhaust gas flows from the gas flow path 36G2 to the path K2 are arranged in the radial direction when viewed from the turbine rotation axis 36J. , and so as not to overlap in the direction along the turbine rotation axis 36J.

In addition, one of the plurality of gas flow paths 36G1 and 36G2 (the gas flow path 36G1 in the case of FIG. 3) is led into the turbine scroll portion (the turbine scroll portion 36S1 in the case of FIG. 3). The turbine scroll portion (turbine scroll portion 36S1 in the case of FIG. 3) so that the exhaust gas turns in one direction (clockwise direction in the case of FIG. 3) along the turbine scroll portion (turbine scroll portion 36S1 in the case of FIG. 3) 36S1).

In addition, one of the remaining gas flow paths (the gas flow path 36G2 in the case of FIG. 3) passes the exhaust gas guided into the turbine scroll portion (the turbine scroll portion 36S2 in the case of FIG. 3). , along the turbine scroll portion (turbine scroll portion 36S2 in the case of FIG. 3) in a direction opposite to the above one direction (counterclockwise direction in the case of FIG. 3). , turbine scroll portion 36S2).

The flow path end partition 36K includes a turbine scroll portion 36S1 that causes the exhaust gas to swirl in one direction (clockwise direction) and a turbine scroll portion 36S2 that swirls the exhaust gas in the opposite direction (counterclockwise direction). and . At the flow path end partition 36K, the exhaust gas swirling clockwise along the turbine scroll portion 36S1 and the exhaust gas swirling counterclockwise along the turbine scroll portion 36S2 collide and interfere with each other. prevent this from happening.

In FIG. 3, the exhaust gas flows from the gas inlet 36A2 of the gas flow path (the gas flow path 36G2 in the case of FIG. 3) on the side that reaches the turbine wheel 36T without going around the nozzle 33, and passes through the turbine scroll portion 36S2 (36S). Then, the distance of the path K2 up to the flow path end partition 36K is defined as the distance L2. Further, in FIG. 3, from the gas inlet 36A1 of the gas flow path (the gas flow path 36G1 in the case of FIG. 3) on the side where the exhaust gas goes around the nozzle 33 and reaches the turbine wheel 36T, the turbine scroll portion 36S1 (36S) The distance of the route K1 to the flow path end partition 36KA is defined as the distance L1. The channel end partition 36K is provided at a position where the distance L2 and the distance L1 are substantially the same (equivalent).

In addition, the turbine scroll portion 36S that makes one turn around the turbine wheel 36T includes a turbine scroll portion 36S1 that guides the exhaust gas from the gas flow path 36G1 to the turbine wheel 36T by an inflow side partition wall 36H and a flow path end partition wall 36K. and a turbine scroll portion 36S2 that guides the exhaust gas from the gas flow path 36G1 to the turbine wheel 36T. In this way, the turbine scroll portion 36S is only one round of the outer circumference of the turbine wheel 36T, so as described above, it does not overlap in the radial direction and does not overlap in the axial direction either.

In the case of FIG. 3, the turbine wheel 36T rotates in a predetermined direction (in this case, the opposite direction (counterclockwise direction)). In the case of FIG. 3, the exhaust gas swirling in one direction (clockwise direction) guided to the turbine scroll portion 36S1 is regulated by the nozzle 33 so as to swirl in the opposite direction (counterclockwise direction). is also adjusted. Further, the flow direction of the exhaust gas swirling in the opposite direction (counterclockwise direction) guided to the turbine scroll portion 36S2 is maintained in the opposite direction by the nozzle 33, and the flow velocity is adjusted.

That is, when the exhaust gases guided from the gas flow paths 36G1 and 36G2 to the turbine scroll portions 36S1 and 36S2 are blown against the turbine wheel 36T, the plurality of nozzles 33 blow the turbine wheel 36T in a predetermined direction (Fig. In example 3, the flow is arranged to rotate in the opposite direction (counterclockwise direction).

As described above, as shown in FIG. 3, the turbine scroll portion 36S does not overlap because the turbine scroll portion 36S is only one turn continuous in the circumferential direction of the outer circumference of the turbine wheel 36T. Therefore, it is possible to make the radial size W1 of the turbine 36 smaller. Further, as shown in FIG. 2, the size H1 in the axial direction of the turbine 36 (the direction along the turbine rotation axis 36J) can also be made smaller. Moreover, as shown in FIG. 3, the shapes of the gas flow paths 36G1 and 36G2 and the turbine scroll portions 36S1 and 36S2 are very simple.

● [Turbocharger 30B of the second embodiment (Fig. 4)]
Next, the structure of the turbocharger 30B of the second embodiment will be described with reference to FIG. The turbocharger 30B (FIG. 4) of the second embodiment differs from the turbocharger 30A (FIG. 3) of the first embodiment in the position of the channel terminal partition wall 36K (FIG. 3). It is the same. Differences from the turbocharger 30A (FIG. 3) of the first embodiment are mainly described below.

In FIG. 4, the exhaust gas flows from the gas inlet 36A2 of the gas flow path (the gas flow path 36G2 in the case of FIG. 4) on the side that reaches the turbine wheel 36T without going around the nozzle 33, and passes through the turbine scroll portion 36S2 (36S). Then, the distance of the path K2 up to the flow path end partition 36KA is defined as the distance L2. 4, from the gas inlet 36A1 of the gas flow path (the gas flow path 36G1 in the case of FIG. 4) on the side where the exhaust gas goes around the nozzle 33 and reaches the turbine wheel 36T, the turbine scroll portion 36S1 (36S) The distance of the route K1 to the flow path end partition 36KA is defined as the distance L1. The channel end partition 36KA is provided at a position where the distance L1 is shorter than the distance L2.

For example, in the path K1 in which the exhaust gas goes around the nozzle 33, the exhaust gas flows longer until it reaches the turbine wheel 36T than in the path K2 in which the exhaust gas does not go around the nozzle 33. The position of the flow path terminal partition wall 36KA is set so that the flow distance of the exhaust gas is substantially the same (equal). For example, the length of the longest exhaust gas path from the gas inlet 36A1 around the nozzle 33 to reach the turbine wheel 36T and the longest route from the gas inlet 36A2 to the turbine wheel 36T without going around the nozzle 33 The position of the channel terminal partition wall 36KA is set so that the length of the path of the exhaust gas is substantially the same (equivalent). Alternatively, the position at which the exhaust gas from the gas inlet 36A1 (gas flow path 36G1) collides with the exhaust gas from the gas inlet 36A2 (gas flow path 36G2) through experiments or simulations using an actual vehicle. is measured, and the channel end partition 36KA is arranged at this collision position.

As in the first embodiment, the turbine scroll portion 36S is formed for only one round of the outer circumference of the turbine wheel 36T. The turbine scroll portion 36S that makes one turn around the turbine wheel 36T includes a turbine scroll portion 36S1 that guides the exhaust gas from the gas flow path 36G1 to the turbine wheel 36T by an inflow-side partition wall 36H and a flow path terminal partition wall 36KA. and a turbine scroll portion 36S2 that guides the exhaust gas from the gas passage 36G2 to the turbine wheel 36T.

As described above, since the turbine scroll portion 36S is only one round of the outer circumference of the turbine wheel 36T, there is no overlap of the turbine scroll portion 36S. Therefore, it is possible to make the size W1 in the radial direction of the turbine 36 and the size H1 (see FIG. 2) in the axial direction (direction along the turbine rotation axis 36J) of the turbine 36 smaller. It is the same as the embodiment. Also similar to the first embodiment, the shapes of the gas flow paths 36G1 and 36G2 and the turbine scroll portions 36S1 and 36S2 are very simple.

● [Turbocharger 30C of the third embodiment (Fig. 5)]
Next, the structure of turbocharger 30C of the third embodiment will be described with reference to FIG. Unlike the turbocharger 30A (FIG. 3) of the first embodiment, the turbocharger 30C (FIG. 5) of the third embodiment has an inflow-side bulkhead end portion 36H1 that is the end of the inflow-side bulkhead 36H. , in that they are located close to the closest nozzle (inflow-side fixed nozzle 33A). Another difference is that a channel end partition wall end portion 36K1, which is an end portion of the channel end partition wall 36K, is in close proximity to the nearest nozzle (terminal side fixed nozzle 33B). Other structures are the same. Differences from the turbocharger 30A (FIG. 3) of the first embodiment are mainly described below. Note that "proximity" may or may not include contact.

In FIG. 5, the nozzle located closest to the flow path terminal partition wall end 36K1, which is the end of the flow path terminal partition 36K on the nozzle side, is fixed to the turbine scroll portion 36S so as not to turn. It is a fixed nozzle 33B. The flow path terminal partition wall end 36K1 is close to the terminal side fixed nozzle 33B. In other words, the gap between the flow path end partition 36K and the end side fixed nozzle 33B is a very small gap. Therefore, the exhaust gas swirling in one direction (clockwise direction) does not interfere with the exhaust gas swirling in the opposite direction (counterclockwise direction) at the end of the flow path terminal partition wall 36K. energy can be efficiently used to drive the rotation of the turbine wheel. The end-side fixed nozzle 33B may be fixed to the turbine scroll portion, may be fixed to the bearing housing, and may be fixed to any part.

In FIG. 5, the nozzle closest to the inflow-side bulkhead end 36H1, which is the nozzle-side end of the inflow-side bulkhead 36H, is an inflow-side fixed nozzle that is fixed so as not to turn with respect to the turbine scroll portion 36S. 33A. The inflow-side partition wall end portion 36H1 is close to the inflow-side fixed nozzle 33A. That is, the gap between the inflow side partition wall 36H and the inflow side fixed nozzle 33A is a very small gap. Therefore, the exhaust gas swirling in one direction (clockwise direction) does not interfere with the exhaust gas swirling in the opposite direction (counterclockwise direction) at the end of the inflow-side partition wall 36H. Energy can be efficiently used to drive the rotation of the turbine wheel. The inflow-side fixed nozzle 33A may be fixed to the turbine scroll portion, may be fixed to the bearing housing, or may be fixed to any part.

The example shown in FIG. 5 shows an example in which both the channel end partition wall end 36K1 and the terminal side fixed nozzle 33B and the inflow side partition wall end 36H1 and the inflow side fixed nozzle 33A are brought close to each other. You may make it approach one side. In the above example, the terminal side fixed nozzle 33B and the inflow side fixed nozzle 33A are fixed nozzles. good too. In addition, the nozzles other than the end-side fixed nozzle 33B and the inflow-side fixed nozzle 33A may be fixed nozzles or rotating nozzles.

In addition, as in the second embodiment, the position of the flow path end partition 36K is changed from the gas inlet 36A2 on the side where the exhaust gas reaches the turbine wheel 36T without going around the nozzle 33, via the turbine scroll portion 36S2. From the gas inlet 36A1 on the side where the exhaust gas goes around the nozzle 33 and reaches the turbine wheel 36T more than the distance L2 of the route K2 until reaching the flow path terminal partition 36K, it passes through the turbine scroll portion 36S1 to the flow path terminal partition. It may be arranged so that the distance L1 of the route K1 until reaching 36K is shorter.

As in the first embodiment, the turbine scroll portion 36S is formed for only one round of the outer circumference of the turbine wheel 36T. The turbine scroll portion 36S that makes one turn around the turbine wheel 36T includes a turbine scroll portion 36S1 that guides the exhaust gas from the gas flow path 36G1 to the turbine wheel 36T by an inflow-side partition wall 36H and a flow path terminal partition wall 36K. and a turbine scroll portion 36S2 that guides the exhaust gas from the gas passage 36G2 to the turbine wheel 36T.

As described above, since the turbine scroll portion 36S is only one round of the outer circumference of the turbine wheel 36T, there is no overlap of the turbine scroll portion 36S. Therefore, it is possible to make the size W1 in the radial direction of the turbine 36 and the size H1 (see FIG. 2) in the axial direction (direction along the turbine rotation axis 36J) of the turbine 36 smaller. It is the same as the embodiment. Also similar to the first embodiment, the shapes of the gas flow paths 36G1 and 36G2 and the turbine scroll portions 36S1 and 36S2 are very simple.

● [Turbocharger 30D of the fourth embodiment (Figs. 6 and 7)]
The turbochargers of the first to third embodiments described above are examples in which there are two exhaust pipes from the internal combustion engine. This is for the case of three tubes. In this case, the internal combustion engine is, for example, a six-cylinder or three-cylinder engine, and three exhaust pipes are connected to the turbocharger 30D. Unlike the turbocharger 30A (FIG. 3) of the first embodiment, the turbocharger 30D of the fourth embodiment shown in FIGS. 6 and 7 has three gas inlets (gas inlets 36A1 and 36A2). , 36A3), differing in that there are two inflow side partition walls (inflow side partition walls 36HA and 36HB), and the other structures are the same. Differences from the turbocharger 30A (FIG. 3) of the first embodiment are mainly described below.

A gas inlet 36A, which is an exhaust gas inlet in the gas introduction path 36F, is formed such that three gas inlets 36A1, 36A2, and 36A3 are adjacent to each other along a direction orthogonal to the turbine rotation axis 36J. An inflow side partition 36HA is provided at a position from the gas inlet 36A1 to the nozzle 33, and an inflow side partition 36HB is provided at a position from the gas inlet 36A2 to the nozzle 33. As shown in FIG. 7, the paths through which the exhaust gas flows through the inflow-side bulkheads 36HA and 36HB are the gas inlet 36A1-gas flow path 36G1-turbine scroll portion 36S1-nozzle 33, and the gas inlet 36A2-gas flow path. The path 36G2-turbine scroll portion 36S2-nozzle 33 and the gas inlet 36A3-gas flow path 36G3-turbine scroll portion 36S3-nozzle 33 are divided into three paths.

The gas inlets 36A1, 36A2, and 36A3 are set to have approximately the same (equal) opening area. In addition, the inclination angle θ of the inflow side partition walls 36HA and 36HB shown in FIG. 7 is set to an appropriate angle determined by experiments using actual vehicles, simulations, and the like.

In addition, the flow channel terminal partition wall is positioned at the position of the flow channel terminal partition wall 36KA indicated by the solid line (similar to the second embodiment) so that the distance L1 of the route K1 is shorter than the distance L2 of the route K2. Alternatively, the position of the channel end partition 36K indicated by the two-dot chain line (in the first embodiment) is set so that the distance L2 of the route K2 and the distance L1 of the route K1 are approximately the same (equivalent). form).

Further, as in the third embodiment, the end of the channel terminal partition wall 36KA (or channel terminal partition wall 36K) and the nozzle closest to it (fixed terminal nozzle 33B) may be brought close to each other, The respective ends of the inflow-side partition walls 36HA and 36HB may be brought close to the nozzles (inflow-side fixed nozzles 33AA and 33AB) located closest thereto.

In the turbocharger 30D of the fourth embodiment shown in FIGS. 6 and 7, any one of the plurality of gas flow paths 36G1, 36G2, and 36G3 (the gas flow path 36G1 in the example of FIG. 7) is , the turbine scroll portion 36S1 (36S) is connected to the turbine scroll portion 36S1 (36S) so that the exhaust gas guided into the turbine scroll portion 36S1 (36S) turns in one direction (clockwise direction) along the turbine scroll portion 36S1. In addition, one of the remaining gas flow paths 36G2 and 36G3 (the gas flow path 36G2 in the example of FIG. 7) allows the exhaust gas guided into the turbine scroll portion 36S2 (36S) to flow into the turbine scroll. It is connected to the turbine scroll portion 36S2 (36S) so as to turn in the opposite direction (counterclockwise direction) to the one direction along the portion 36S2.

Further, the turbine scroll portion 36S is formed only for one round of the outer circumference of the turbine wheel 36T. The turbine scroll portion 36S that makes one turn around the turbine wheel 36T directs the exhaust gas from the gas flow path 36G1 to the turbine wheel 36T by means of an inflow side partition wall 36HA, an inflow side partition wall 36HB, and a flow path end partition wall 36KA (36K). , a turbine scroll portion 36S2 that guides the exhaust gas from the gas passage 36G2 to the turbine wheel 36T, a turbine scroll portion 36S3 that guides the exhaust gas from the gas passage 36G3 to the turbine wheel 36T, are divided in the circumferential direction into respective regions of .

When the exhaust gases guided from the gas flow paths 36G1, 36G2, 36G3 to the turbine scroll portions 36S1, 36S2, 36S3 are blown against the turbine wheel 36T, the plurality of nozzles 33 blow the turbine wheel 36T to a predetermined level. direction (in the example of FIG. 7, the opposite direction (counterclockwise direction)).

As described above, since the turbine scroll portion 36S is only one round of the outer circumference of the turbine wheel 36T, there is no overlap of the turbine scroll portion 36S. Therefore, it is possible to make the size W1 in the radial direction of the turbine 36 and the size H1 (see FIG. 2) in the axial direction (direction along the turbine rotation axis 36J) of the turbine 36 smaller. It is the same as the embodiment. Also similar to the first embodiment, the shapes of the gas flow paths 36G1, 36G2, 36G3 and the turbine scroll portions 36S1, 36S2, 36S3 are very simple.

● [Turbocharger 30E (Fig. 8) of the fifth embodiment]
In the turbocharger 30A of the first embodiment described above, as shown in FIG. 3, the gas introduction passage 36F is connected to the turbine scroll portion 36S so that the introduction passage central axis 36FJ intersects the turbine rotation axis 36J. there is As shown in FIG. 8, the turbocharger 30E of the fifth embodiment is different in that the introduction passage center axis 36FJ does not intersect the turbine rotation axis 36J, and other structures are the same. Differences from the turbocharger 30A (FIG. 3) of the first embodiment are mainly described below.

As shown in FIG. 8, the gas introduction passage 36F is connected to the turbine scroll portion 36S so that the introduction passage central axis 36FJ is separated from the turbine rotation axis 36J without intersecting. In the example shown in FIG. 8, the gas introduction path 36F is connected at a position corresponding to the tangential line of the arcuate turbine scroll portion 36S2 so that the exhaust gas smoothly flows from the gas flow path 36G2 to the turbine scroll portion 36S2. . The gas inlets 36A1 and 36A2 are arranged adjacent to each other along the direction perpendicular to the turbine rotation axis 36J, similarly to the turbocharger 30A of the first embodiment (see FIG. 3).

In addition, the flow channel terminal partition wall is positioned at the position of the flow channel terminal partition wall 36KA indicated by the solid line (similar to the second embodiment) so that the distance L1 of the route K1 is shorter than the distance L2 of the route K2. Alternatively, the position of the channel end partition 36K indicated by the two-dot chain line (in the first embodiment) is set so that the distance L2 of the route K2 and the distance L1 of the route K1 are approximately the same (equivalent). form).

Further, as in the third embodiment, the end of the channel terminal partition wall 36KA (or channel terminal partition wall 36K) and the nozzle closest to it (fixed terminal nozzle) may be brought close to each other. The end of the side partition 36H and the nozzle closest to it (fixed nozzle on the inflow side) may be brought close to each other.

In the turbocharger 30E of the fifth embodiment shown in FIG. 8, one of the plurality of gas flow paths 36G1 and 36G2 (the gas flow path 36G1 in the example of FIG. 8) has a turbine scroll portion 36S1. (36S) is connected to the turbine scroll portion 36S1 (36S) so as to rotate in one direction (clockwise direction) along the turbine scroll portion 36S1. Any one of the remaining gas flow paths 36G2 (the gas flow path 36G2 in the example of FIG. 8) allows the exhaust gas guided into the turbine scroll portion 36S2 (36S) to flow into the turbine scroll portion 36S2. is connected to the turbine scroll portion 36S2 (36S) so as to turn in the direction opposite to the one direction (counterclockwise direction).

Further, the turbine scroll portion 36S is formed only for one round of the outer circumference of the turbine wheel 36T. The turbine scroll portion 36S, which makes one turn around the turbine wheel 36T, guides the exhaust gas from the gas flow path 36G1 to the turbine wheel 36T by the inflow side partition wall 36H and the flow path end partition wall 36KA (36K). 36S1 and a turbine scroll portion 36S2 that guides the exhaust gas from the gas flow path 36G2 to the turbine wheel 36T.

When the exhaust gases guided from the gas passages 36G1 and 36G2 to the turbine scroll portions 36S1 and 36S2 are blown against the turbine wheel 36T, the plurality of nozzles 33 blow the turbine wheel 36T in a predetermined direction (Fig. In the example of No. 8, the flow is arranged to rotate in the opposite direction (counterclockwise direction).

As described above, since the turbine scroll portion 36S is only one round of the outer circumference of the turbine wheel 36T, there is no overlap of the turbine scroll portion 36S. Therefore, it is possible to make the size W1 in the radial direction of the turbine 36 and the size H1 (see FIG. 2) in the axial direction (direction along the turbine rotation axis 36J) of the turbine 36 smaller. It is the same as the embodiment. Also similar to the first embodiment, the shapes of the gas flow paths 36G1 and 36G2 and the turbine scroll portions 36S1 and 36S2 are very simple.

The turbochargers 30A to 30E of the present invention are not limited to the configuration, structure, appearance, shape, etc. described in the present embodiment, and various modifications, additions, and deletions are possible without changing the gist of the present invention. . For example, the channel terminal partition wall 36K (or the channel terminal partition wall 36KA) may be omitted.

When there is a nozzle adjacent to the inflow side partition wall or the end partition wall of the channel, the adjacent nozzle may be a fixed nozzle that does not rotate, or a variable nozzle that rotates. Other nozzles may be variable nozzles that swivel, or fixed nozzles that do not swivel.

In this embodiment, an example in which there are two exhaust pipes and an example in which there are three exhaust pipes from the internal combustion engine has been described. The number of gas inlets may be changed from the three gas inlets shown in FIG. That is, the turbocharger of the present invention can be applied to a plurality of exhaust pipes, without being limited to two or three exhaust pipes from the internal combustion engine.

Further, the turbocharger of the present invention is not limited to application to diesel engines, and can be applied to internal combustion engines using various fuels such as gasoline, LPG, and natural gas.

Greater than (≧), less than (≦), greater than (>), less than (less than) (<), etc. may or may not include an equal sign.

10 internal combustion engine 11A, 11B intake pipe 11C intake manifold 12A1, 12A2 exhaust manifold 12B1, 12B2, 12C exhaust pipe 13 EGR pipe 14 EGR valve 15 EGR cooler 21 intake flow rate detection means 22 crank angle detection means 23 atmospheric pressure detection means 24A compressor upstream Pressure detection means 24B Compressor downstream pressure detection means 24C Intake manifold pressure detection means 25 Accelerator pedal depression amount detection means 26A Turbine upstream pressure detection means 26B Turbine downstream pressure detection means 27 Vehicle speed detection means 28A, 28B Intake temperature detection means 28C Coolant temperature detection means 29 Exhaust temperature detection means 30, 30A, 30B, 30C, 30D, 30E Turbocharger 31 Nozzle drive means 31A Arm 32 Nozzle opening detection means 33 Nozzle 33A, 33AA, 33AB Inflow side fixed nozzle 33B End side fixed nozzle 33P Nozzle plate 35 Compressor 35A Intake inlet 35B Intake outlet 36 Turbine 36A, 36A1, 36A2, 36A3 Gas inlet 36B Gas outlet 36F Gas introduction path 36FJ Introduction path central axis 36G1, 36G2, 36G3 Gas flow path 36H, 36HA, 36HB Inflow-side bulkhead 36H1 Inflow-side bulkhead end 36J Turbine rotation axis 36K, 36KA Channel terminal bulkhead 36K1 Channel terminal bulkhead end 36S, 36S1, 36S2, 36S3 Turbine scroll section 36T Turbine wheel 41 Common rail 43A-43D Injector 45A-45D Cylinder 47 Throttle device 47S throttle opening detection means 47V throttle valve 50 control device 51 CPU
53 Storage device 61 Exhaust purification device K1, K2 path

Claims (5)

A turbocharger that supercharges using the energy of the exhaust gas of an internal combustion engine,
a turbine wheel rotatably supported around a turbine rotation axis;
a turbine scroll portion disposed on the outer periphery of the turbine wheel;
a gas introduction passage that guides exhaust gas to the turbine scroll portion;
a gas discharge port through which the exhaust gas generated by rotating the turbine wheel is discharged;
has
The turbine scroll portion is formed for only one round continuous in the circumferential direction of the outer circumference of the turbine wheel,
A plurality of nozzles are arranged along the circumferential direction on the outer peripheral portion of the turbine wheel in the turbine scroll portion to adjust the flow of exhaust gas blown to the turbine wheel,
An inflow-side partition dividing the gas introduction path into a plurality of gas flow paths is provided at a position from a gas inlet, which is an inlet for exhaust gas, to the nozzle in the gas introduction path,
The plurality of gas flow paths are divided so as not to overlap in a radial direction when viewed from the position of the turbine rotation axis, and are divided so as not to overlap in a direction along the turbine rotation axis,
Each of the exhaust gases guided from each of the gas passages to the turbine scroll portion is adjusted by the plurality of nozzles to flow in a direction that rotates the turbine wheel in a predetermined direction when the exhaust gas is blown against the turbine wheel. and
A flow path end partition extending from a position close to the nozzle to an inner wall of the turbine scroll is provided around a position opposite to the gas introduction path in the turbine scroll,
There are two gas flow paths,
one inflow-side partition wall and one channel terminal partition wall,
each of the gas inlets corresponding to each of the gas flow paths is arranged so as to be adjacent to each other along a direction orthogonal to the turbine rotation axis,
The flow path terminal partition extends from the gas inlet of the gas flow path on the side where the exhaust gas reaches the turbine wheel without going around the nozzle to the flow path terminal partition via the turbine scroll portion. The distance from the gas inlet of the gas flow path on the side where the exhaust gas goes around the nozzle and reaches the turbine wheel to the flow path end bulkhead via the turbine scroll portion is larger than the distance. designed to be short,
turbocharger. A turbocharger that supercharges using the energy of the exhaust gas of an internal combustion engine,
a turbine wheel rotatably supported around a turbine rotation axis;
a turbine scroll portion disposed on the outer periphery of the turbine wheel;
a gas introduction passage that guides exhaust gas to the turbine scroll portion;
a gas discharge port through which the exhaust gas generated by rotating the turbine wheel is discharged;
has
The turbine scroll portion is formed for only one round continuous in the circumferential direction of the outer circumference of the turbine wheel,
A plurality of nozzles are arranged along the circumferential direction on the outer peripheral portion of the turbine wheel in the turbine scroll portion to adjust the flow of exhaust gas blown to the turbine wheel,
An inflow-side partition dividing the gas introduction path into a plurality of gas flow paths is provided at a position from a gas inlet, which is an inlet for exhaust gas, to the nozzle in the gas introduction path,
Any one of the plurality of gas flow paths is connected to the turbine scroll so that the exhaust gas guided into the turbine scroll circulates in one direction along the turbine scroll. cage,
Any one of the remaining gas flow paths rotates the turbine scroll so that exhaust gas guided into the turbine scroll swirls along the turbine scroll in a direction opposite to the one direction. is connected to the
Each of the exhaust gases guided from each of the gas passages to the turbine scroll portion is adjusted by the plurality of nozzles to flow in a direction that rotates the turbine wheel in a predetermined direction when the exhaust gas is blown against the turbine wheel. and
A flow path end partition extending from a position close to the nozzle to an inner wall of the turbine scroll is provided around a position opposite to the gas introduction path in the turbine scroll,
There are two gas flow paths,
one inflow-side partition wall and one channel terminal partition wall,
each of the gas inlets corresponding to each of the gas flow paths is arranged so as to be adjacent to each other along a direction orthogonal to the turbine rotation axis,
The flow path terminal partition extends from the gas inlet of the gas flow path on the side where the exhaust gas reaches the turbine wheel without going around the nozzle to the flow path terminal partition via the turbine scroll portion. The distance from the gas inlet of the gas flow path on the side where the exhaust gas goes around the nozzle and reaches the turbine wheel to the flow path end bulkhead via the turbine scroll portion is larger than the distance. designed to be short,
turbocharger. A turbocharger that supercharges using the energy of the exhaust gas of an internal combustion engine,
a turbine wheel rotatably supported around a turbine rotation axis;
a turbine scroll portion disposed on the outer periphery of the turbine wheel;
a gas introduction passage that guides exhaust gas to the turbine scroll portion;
a gas discharge port through which the exhaust gas generated by rotating the turbine wheel is discharged;
has
The turbine scroll portion is formed for only one round continuous in the circumferential direction of the outer circumference of the turbine wheel,
A plurality of nozzles are arranged along the circumferential direction on the outer peripheral portion of the turbine wheel in the turbine scroll portion to adjust the flow of exhaust gas blown to the turbine wheel,
An inflow-side partition dividing the gas introduction path into a plurality of gas flow paths is provided at a position from a gas inlet, which is an inlet for exhaust gas, to the nozzle in the gas introduction path,
A flow path end partition extending from a position close to the nozzle to an inner wall of the turbine scroll is provided around a position opposite to the gas introduction path in the turbine scroll,
The turbine scroll portion is connected to each of the gas flow passages, and the inflow side partition wall and the flow passage end partition wall guide the exhaust gas from the respective gas flow passages to the respective regions to the turbine wheel. and divided in the circumferential direction,
Each of the exhaust gases guided from each of the gas passages to the turbine scroll portion is adjusted by the plurality of nozzles to flow in a direction that rotates the turbine wheel in a predetermined direction when the exhaust gas is blown against the turbine wheel. and
There are two gas flow paths,
one inflow-side partition wall and one channel terminal partition wall,
each of the gas inlets corresponding to each of the gas flow paths is arranged so as to be adjacent to each other along a direction orthogonal to the turbine rotation axis,
The flow path terminal partition extends from the gas inlet of the gas flow path on the side where the exhaust gas reaches the turbine wheel without going around the nozzle to the flow path terminal partition via the turbine scroll portion. The distance from the gas inlet of the gas flow path on the side where the exhaust gas goes around the nozzle and reaches the turbine wheel to the flow path end bulkhead via the turbine scroll portion is larger than the distance. designed to be short,
turbocharger. A turbocharger according to any one of claims 1 to 3 ,
The nozzle closest to the end of the flow path terminal partition, which is the end of the flow path terminal partition on the side of the nozzle, is close to the end of the flow path terminal partition.
turbocharger. A turbocharger according to any one of claims 1 to 4 ,
The nozzle located closest to the end of the inflow-side partition, which is the end of the inflow-side partition on the side of the nozzle, is close to the end of the inflow-side partition.
turbocharger.

Images