Dual-channel turbine, turbocharger and engine

Abstract

The present invention relates to the technical field of engines, and specifically discloses a dual-channel turbine, a turbocharger and an engine, wherein the dual-channel turbine comprises a volute, a nozzle ring and a turbine, wherein the volute has two air inlets, two channels and two volute tongues, wherein the two channels are respectively connected to the two volute tongues and the two air inlets; the nozzle ring comprises two half-rings, wherein the two volute tongues are respectively connected to the inlets of the two half-rings, and the outlets of the two half-rings are both used to convey the airflow to the turbine, the two half-rings are connected end to end, and each half-ring is provided with a plurality of guide vanes, and an airflow channel is formed between any two adjacent guide vanes, and each half-ring comprises a first section and a second section which are sequentially arranged along the circumferential direction of the nozzle ring, and along the circumferential direction of the nozzle ring, the spacing angle between any two adjacent guide vanes in the first section is greater than the spacing angle between any two adjacent guide vanes in the second section, thereby enhancing the rectifying effect on the mixed airflow at the volute tongues.

Description

Technical Field

[0001] The present invention relates to the technical field of engines, and in particular to a dual-channel turbine, a turbocharger and an engine. Background Art

[0002] Currently, most supercharger inlet forms adopt a dual-channel turbine with two inlet intakes. This method can achieve pulse separation and effectively utilize pulse exhaust energy. Specifically, the two channels are connected to the two inlets respectively, and the two channels are connected to the left and right halves of the nozzle ring respectively through two volute tongues. The two ends of the left half of the nozzle ring and the two ends of the right half are connected respectively. The nozzle ring includes a plurality of guide vanes evenly distributed along its axial direction. A channel for airflow is formed between two adjacent guide vanes, and the channel transports the airflow to the turbine. However, due to the influence of the engine ignition sequence, the airflow state inside the two intake channels of the dual-channel turbine is often different and uneven, which easily leads to differences in the airflow entering the left and right halves. The airflow at both ends of the left half and the right half is prone to significant mixing and obvious jetting, resulting in a significant increase in flow losses inside the nozzle ring. Summary of the Invention

[0003] The object of the present invention is to provide a dual-channel turbine, a turbocharger and an engine to improve the problem that when the dual-channel air of the dual-channel turbine is uneven, the air flows at both ends of the left half and the right half of the nozzle ring are easily significantly mixed, resulting in increased flow losses inside the nozzle ring.

[0004] On the one hand, the present invention provides a dual-channel turbine, which includes a volute, a nozzle ring and a turbine, wherein the volute has two air inlets, an inner channel and an outer channel respectively connected to the two air inlets, and two volute tongues respectively connected to the inner channel and the outer channel, the nozzle ring includes two half rings, the two volute tongues are respectively connected to the inlets of the two half rings, and the outlets of the two half rings are used to deliver airflow to the turbine, each of the half rings has a first free end and a second free end, the first free end of any of the two half rings is connected to the second free end of the other half ring, and the nozzle ring also It includes guide vanes, and each semi-ring is provided with a plurality of guide vanes. An air flow channel is formed between any two adjacent guide vanes in each semi-ring, and the air flow channel is respectively connected to the inlet of the corresponding semi-ring and the outlet of the corresponding semi-ring. Each semi-ring includes a first section and a second section arranged in sequence along the circumferential direction of the nozzle ring, and the first section of one semi-ring is connected to the second section of the other semi-ring. Along the circumferential direction of the nozzle ring, the spacing angle between any two adjacent guide vanes in the first section is greater than the spacing angle between any two adjacent guide vanes in the second section.

[0005] As a preferred technical solution for the dual-channel turbine, a center angle of the first section corresponding to the nozzle ring is greater than a center angle of the second section corresponding to the nozzle ring.

[0006] As a preferred technical solution for the dual-channel turbine, the central angle of the second section corresponding to the nozzle ring is γ, and γ is between 30° and 70°.

[0007] As a preferred technical solution for the dual-channel turbine, the difference between the number of guide vanes in the second section and the number of guide vanes in the first section within the range of the central angle γ of the nozzle ring is greater than or equal to 1.

[0008] As a preferred technical solution for the dual-channel turbine, the angle between two adjacent guide vanes in the first section is α, the angle between two adjacent guide vanes in the second section is β, and the difference between α and β is less than or equal to 2°.

[0009] As a preferred technical solution for the dual-channel turbine, the central angles of the two half rings corresponding to the nozzle ring are both 180°.

[0010] As an optimal technical solution for the dual-channel turbine, the flow directions of the airflow in the inner channel and the outer channel are the same. Along the flow direction of the airflow in the inner channel or the outer channel, in each semi-ring, the first section is located upstream of the second section.

[0011] As an optimal technical solution for the dual-channel turbine, the flow direction of the airflow in the inner channel and the outer channel is the same. Along the flow direction of the airflow in the inner channel or the outer channel, in each semi-ring, the first section is located downstream of the second section.

[0012] On the other hand, the present invention provides a turbocharger comprising the dual-channel turbine in any of the above solutions.

[0013] In yet another aspect, the present invention provides an engine comprising the turbocharger according to the above solution.

[0014] The beneficial effects of the present invention are:

[0015] The present invention provides a dual-channel turbine, a turbocharger and an engine, wherein the dual-channel turbine comprises a volute, a nozzle ring and a turbine, wherein the volute has two air inlets, an inner channel and an outer channel respectively connected to the two air inlets, and two volute tongues respectively connected to the inner channel and the outer channel, wherein the nozzle ring comprises two half-rings, wherein the two volute tongues are respectively connected to the inlets of the two half-rings, and the outlets of the two half-rings are both used to deliver airflow to the turbine, wherein each of the half-rings has a first free end and a second free end, and the first free end of any of the two half-rings is connected to the second free end of the other half-ring The free ends are connected, and the nozzle ring also includes guide vanes. Each half-ring is provided with a plurality of guide vanes. An airflow channel is formed between any two adjacent guide vanes in each half-ring, and the airflow channel is respectively connected to the inlet and outlet of the corresponding half-ring. Each half-ring includes a first section and a second section arranged sequentially along the circumference of the nozzle ring, and the first section of one half-ring is connected to the second section of the other half-ring. Along the circumference of the nozzle ring, the spacing angle between any two adjacent guide vanes in the first section is greater than the spacing angle between any two adjacent guide vanes in the second section. This arrangement results in a relatively sparse arrangement of the guide vanes in the first section of each half-ring, while a relatively dense arrangement of the guide vanes in the second section. This enhances the rectifying effect on the mixed airflow at the volute tongue, improves the flow field distortion caused by airflow mixing, and brings the airflow angle entering the turbine through the volute tongue closer to the design state, thereby improving turbine performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 The structure of the dual-channel turbine in the embodiment of the present invention is shown as follows Figure 1 ;

[0017] Figure 2 The structure of the dual-channel turbine in the embodiment of the present invention is shown as follows Figure 2 ;

[0018] Figure 3 Schematic diagram of the structure of the nozzle ring in the dual-channel turbine according to an embodiment of the present invention;

[0019] Figure 4 for Figure 3 Magnified view at point A in the middle;

[0020] Figure 5 for Figure 3 Magnified view at point B.

[0021] In the picture:

[0022] 1. Volute; 11. Air inlet; 12. Inner channel; 13. Outer channel; 14. Volute tongue;

[0023] 2. Nozzle ring; 21. Half ring; 211. Inlet; 212. Outlet; 22. Guide vane; 23. Air flow channel; 24. First section; 25. Second section;

[0024] 3. Turbine. DETAILED DESCRIPTION

[0025] The technical solution of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the embodiments described are only some embodiments of the present invention, not all embodiments. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0026] In the description of the present invention, it should be noted that the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and are not intended to indicate or imply that the devices or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention. In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance. Among them, the terms "first position" and "second position" are two different positions, and the first feature being "above", "above" and "above" the second feature includes the first feature being directly above and obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. The first feature being "below", "below" and "below" the second feature includes the first feature being directly below and obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0027] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed, detachable, or integral connections; mechanical or electrical connections; direct or indirect connections through an intermediate medium; and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on the specific circumstances.

[0028] The following describes embodiments of the present invention in detail. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended only to explain the present invention and are not to be construed as limiting the present invention.

[0029] The existing dual-channel turbine is affected by the engine ignition sequence, and the airflow conditions inside the two intake channels of the dual-channel turbine are often different and uneven, which easily leads to differences in the airflow entering the left half and the right half. The airflow at both ends of the left half and the right half is prone to significant mixing and obvious jets, resulting in a significant increase in flow losses inside the nozzle ring.

[0030] In this regard, this embodiment provides a dual-channel turbine to improve the problem that when the dual-channel air of the dual-channel turbine is uneven, the airflow at both ends of the left half and the right half of the nozzle ring is prone to significant mixing, which leads to increased flow losses inside the nozzle ring.

[0031] Specifically, if Figures 1 to 5 As shown, the dual-channel turbine includes a volute 1, a nozzle ring 2 and a turbine 3. Figure 1 As shown, the volute 1 has two air inlets 11, an inner channel 12 and an outer channel 13 respectively connected to the two air inlets 11, and two volute tongues 14 respectively connected to the inner channel 12 and the outer channel 13. The nozzle ring 2 includes two half rings 21. The two volute tongues 14 are respectively connected to the inlets 211 of the two half rings 21. The outlets 212 of the two half rings 21 are used to deliver the airflow to the turbine 3. Each half ring 21 has a first free end and a second free end. The first free end of any half ring 21 of the two half rings 21 is connected to the second free end of the other half ring 21. The nozzle ring 2 also includes guide vanes 22. A plurality of guide vanes 22 are provided in each half ring 21. An airflow channel 23 is formed between any two adjacent guide vanes 22 in each half ring 21. The airflow channel 23 is respectively connected to the inlet 211 of the corresponding half ring 21 and the outlet 212 of the corresponding half ring 21. Among them, the nozzle ring 2 is mounted on the turbine 3, and the exhaust gas generated by the engine can enter the inner channel 12 and the outer channel 13 respectively from the two air inlets 11. The gas entering the inner channel 12 is transported from a volute 14 to a half ring 21 of the nozzle ring 2, and is transported to the outlet 212 of the half ring 21 through several air flow channels 23 and then transported to the turbine 3, and drives the turbine 3 to rotate. The gas entering the outer channel 13 is transported from another volute 14 to the other half ring 21 of the nozzle ring 2, and is transported to the outlet 212 of the half ring 21 through several air flow channels 23 and then transported to the turbine 3, and drives the turbine 3 to rotate.

[0032] The inlet 211 and outlet 212 of the semi-ring 21 are spaced radially apart and extend circumferentially. Specifically, the inlet 211 of the semi-ring 21 is located at its outer edge, and the outlet 212 is located at its inner edge. Several airflow channels 23 within the semi-ring 21 connect the inlet 211 and outlet 212 of the semi-ring 21. Both volute tongues 14 are tongue-shaped structures. Airflow within the inner channel 12 passes through the volute tongue 14 connected to it and directly enters the inlet 211 of its semi-ring 21; airflow within the outer channel 13 passes through the volute tongue 14 connected to it and directly enters the inlet 211 of the other semi-ring 21. The airflow at the inlet 211 of each semi-ring 21 is sequentially distributed to the corresponding airflow channels 23, and then enters the outlet 212 of the semi-ring 21 through the airflow channels 23. Preferably, in this embodiment, the centerline of the airflow channel 23 is inclined and nearly tangent to the circumference of the outer edge of the turbine 3, thereby facilitating the rotation of the turbine 3. Further preferably, the guide vanes 22 can rotate relative to the volute 1, so as to facilitate adjustment of the direction of the center line of the air flow channel 23 and further adjust the power of the dual-channel turbine.

[0033] Because the two ends of the two half-rings 21 are connected in a one-to-one correspondence, that is, the inlets 211 of the two half-rings 21 and the outlets 212 of the two half-rings 21 are connected in a corresponding manner, this can easily lead to mixing of airflows at the connection point between the two half-rings 21. In this embodiment, each half-ring 21 includes a first section 24 and a second section 25 arranged sequentially along the circumference of the nozzle ring 2. The first section 24 of one half-ring 21 is connected to the second section 25 of the other half-ring 21. Along the circumference of the nozzle ring 2, the spacing angle between any two adjacent guide vanes 22 in the first section 24 is greater than the spacing angle between any two adjacent guide vanes 22 in the second section 25. With this arrangement, the guide vanes 22 in the first section 24 of each half ring 21 are arranged relatively sparsely, and the guide vanes 22 in the second section 25 are arranged relatively densely, which enhances the rectifying effect on the mixed airflow at the volute tongue 14, improves the flow field distortion caused by airflow mixing, and makes the airflow angle entering the turbine 3 through the volute tongue 14 closer to the design state, thereby improving the performance of the turbine.

[0034] Optionally, the central angles of the two half rings 21 corresponding to the nozzle ring 2 are both 180°, so that the air intake of the two half rings 21 can be relatively balanced.

[0035] Optionally, the center angle of the first section 24 corresponding to the nozzle ring 2 is greater than the center angle of the second section 25 corresponding to the nozzle ring 2. Figure 3The center angle of the second segment 25 corresponding to the nozzle ring 2 is γ, and γ is the angle between the straight line L1 and the straight line L2, wherein the straight line L1 is a straight line passing through the center of the nozzle ring 2 and the connection between the first segment 24 and the second segment 25 in each semi-ring 21; the straight line L2 is a straight line passing through the center of the nozzle ring 2 and the connection between the two ends of the two semi-rings 21, and γ is between 30° and 70°. For example, γ can be 30°, 35°, 40°, 45°, 50°, 55°, 60°, 65° or 70°.

[0036] Optionally, the difference between the number of guide vanes 22 in the second section 25 and the number of guide vanes 22 within the range of the central angle γ of the nozzle ring 2 in the first section 24 is greater than or equal to 1. That is, when the first section 24 and the second section 25 are cut out to have the same arc length, the difference between the number of guide vanes 22 in the cutout portion of the first section 24 and the number of guide vanes 22 in the second section 25 is X, where X ≥ 1. Of course, in other embodiments, X can be set to a larger or smaller value as needed.

[0037] Alternatively, see Figures 3 to 5 The angle between two adjacent guide vanes 22 in the first section 24 is α, and the angle between two adjacent guide vanes 22 in the second section 25 is β, and the difference between α and β is less than or equal to 2°. Specifically, the difference between α and β can be 0.5°, 0.6°, 0.7°, 0.8°, 0.9°, 1.0°, 1.1°, 1.2°, 1.3°, 1.4°, 1.5°, 1.6°, 1.7°, 1.8°, 1.9°, or 2.0°. Figure 4 and Figure 5 The guide vanes 22 shown by the dashed line are a pattern in which the guide vanes 22 in the second section 25 are denser than those in the first section 24 , and the guide vanes 22 shown by the solid line are a pattern assuming that the guide vanes 22 in the second section 25 maintain the same density as the guide vanes 22 in the first section 24 .

[0038] Optionally, the airflow in the inner channel 12 and the outer channel 13 has the same flow direction. Along the flow direction of the airflow in the inner channel 12 or the outer channel 13, in each semi-ring 21, the first section 24 can be located upstream of the second section 25. Of course, the first section 24 in each semi-ring 21 can also be located downstream of the second section 25 as needed, which can also improve the mixing of the airflow at the connection point between the two semi-rings 21 and avoid the loss of airflow kinetic energy. Figure 3 , an example is given in which the first section 24 is located upstream of the second section 25 along the flow direction of the airflow in the volute tongue 14 .

[0039] In order to further demonstrate the effect of the dual-channel turbine in this case in improving the mixing phenomenon of the airflow at the connection point of the two half-rings 21 and avoiding the loss of airflow kinetic energy, the total static efficiency calculation formula of the dual-channel turbine is introduced. The calculation formula is as follows:

[0040]

[0041]

[0042] Where τ is the turbine output torque, in N·m; ω is the impeller speed, in rad / s; m in1 and m in2 are the masses of the exhaust gas entering the two air inlets 11, T t-in1 and T t-in2 are the temperatures at the two air inlets 11, in K; P t-in1 and P t-in2 The pressure at the two air inlets 11, in Pa; P s-out is the static pressure at the outlet of the dual-channel turbine, in Pa; C p is the isobaric specific heat capacity, which is 1089.25 J / (kg·K); n is the dimensionless air adiabatic coefficient, which is 1.353.

[0043] Using the above formula, the following three models were used for comparison. The basic model: a conventional two-channel turbine, where the spacing between any two guide vanes 22 in the nozzle ring 2 is the same, and corresponds to the spacing between two adjacent guide vanes 22 in the first section 24 of the half-ring 21 in this embodiment. Model 2: a two-channel turbine provided in this embodiment, where the first section 24 can be located upstream of the second section 25 along the flow direction of the airflow within the volute 14. Model 3: a two-channel turbine provided in this embodiment, where the first section 24 can be located downstream of the second section 25 along the flow direction of the airflow within the volute 14. Comparing the total static efficiency of the three models, Model 2 increases the efficiency of the two-channel turbine by 3.77% relative to Model 1. Model 3 increases the efficiency of the two-channel turbine by 2.41% relative to Model 1.

[0044] This embodiment also provides a turbocharger, which includes the dual-channel turbine in the above solution.

[0045] This embodiment also provides an engine, comprising the turbocharger in the above solution.

[0046] Obviously, the above embodiments of the present invention are merely examples for the purpose of clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. Those skilled in the art will appreciate that other variations or modifications can be made based on the above description. It is not necessary and impossible to enumerate all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the claims of the present invention.

Claims

1. A dual-channel turbine, comprising a volute (1), a nozzle ring (2) and a turbine (3), wherein the volute (1) has two air inlets (11), an inner channel (12) and an outer channel (13) respectively connected to the two air inlets (11), and two volute tongues (14) respectively connected to the inner channel (12) and the outer channel (13), wherein the nozzle ring (2) comprises two half rings (21), the two volute tongues (14) respectively connected to the inlets (211) of the two half rings (21), and the outlets (212) of the two half rings (21) are used to deliver airflow to the turbine (3), and each of the Each half ring (21) has a first free end and a second free end, and the first free end of any half ring (21) of the two half rings (21) is connected to the second free end of the other half ring (21). The nozzle ring (2) further includes a guide vane (22), and each half ring (21) is provided with a plurality of guide vanes (22). An air flow channel (23) is formed between any two adjacent guide vanes (22) in each half ring (21), and the air flow channel (23) is respectively connected to the inlet (211) of the corresponding half ring (21) and the outlet (212) of the corresponding half ring (21). The nozzle ring (2) is characterized in that: Each of the half rings (21) comprises a first section (24) and a second section (25) sequentially arranged along the circumferential direction of the nozzle ring (2), and the first section (24) of one half ring (21) is connected to the second section (25) of the other half ring (21), and along the circumferential direction of the nozzle ring (2), the spacing angle between any two adjacent guide vanes (22) in the first section (24) is greater than the spacing angle between any two adjacent guide vanes (22) in the second section (25).

2. The dual-channel turbine according to claim 1, characterized in that: The center angle of the first section (24) corresponding to the nozzle ring (2) is greater than the center angle of the second section (25) corresponding to the nozzle ring (2).

3. The dual-channel turbine according to claim 2, characterized in that: The central angle of the second section (25) corresponding to the nozzle ring (2) is γ, and γ is between 30° and 70°.

4. The dual-channel turbine according to claim 3, characterized in that: The difference between the number of the guide vanes (22) in the second section (25) and the number of the guide vanes (22) in the first section (24) within the range of the central angle γ of the nozzle ring (2) is greater than or equal to 1.

5. The dual-channel turbine according to claim 1, characterized in that: The included angle between two adjacent guide vanes (22) in the first section (24) is α, the included angle between two adjacent guide vanes (22) in the second section (25) is β, and the difference between α and β is less than or equal to 2°.

6. The dual-channel turbine according to claim 1, characterized in that: The center angles of the two half rings (21) corresponding to the nozzle ring (2) are both 180°.

7. The dual-channel turbine according to any one of claims 1 to 6, characterized in that: The flow direction of the airflow in the inner channel (12) and the outer channel (13) is the same. Along the flow direction of the airflow in the inner channel (12) or the outer channel (13), in each of the semi-rings (21), the first section (24) is located upstream of the second section (25).

8. The dual-channel turbine according to any one of claims 1 to 6, characterized in that: The flow direction of the airflow in the inner channel (12) and the outer channel (13) is the same. Along the flow direction of the airflow in the inner channel (12) or the outer channel (13), in each of the semi-rings (21), the first section (24) is located downstream of the second section (25).

9. A turbocharger, characterized in that: A dual-channel turbine comprising the dual-channel turbine according to any one of claims 1 to 8.

10. An engine, characterized in that: Including the turbocharger according to claim 9.

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