Turbine shell and turbine

Abstract

The utility model discloses a turbine shell and a turbine. The turbine shell is provided with a flow channel, the shell is provided with an outer surface and an inner surface, and the flow channel is formed by sinking from the inner surface of the shell to the outer surface of the shell. The flow channel is internally provided with a separation protrusion, the separation protrusion extends in the radial direction of the shell, in the radial direction of the shell, the first end of the separation protrusion is connected with the flow channel, and the second end of the separation protrusion is away from the outer surface of the shell; the flow channel is divided into a first flow channel and a second flow channel by the separation bulge, and the first flow channel and the second flow channel are distributed along the axial direction of the shell; an impeller is arranged in the shell, the impeller is rotatably arranged in the shell, and the impeller and the shell are coaxially arranged; the radius of the impeller is R1, the distance between the second end of the separation protrusion and the center shaft of the shell is R2, and R2 / R1 is larger than 1 and smaller than 1.05. According to the turbine shell, the radius ratio of the separating protrusions is small, the separating protrusions are long, and the efficiency of a turbine can be improved under the multiple air inlet conditions of double flow channels.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of turbine, in particular to a turbine shell and a turbine. BACKGROUND

[0002] A partition wall is arranged in a double-channel volute turbine shell. In previous studies, a shorter partition wall can provide better performance when the two sides of the channel have equal air intake, so the current turbine shell mostly adopts a shorter partition wall as the main design. However, when the two sides of the channel have different air intake and only a single channel has air intake, the shorter partition wall brings poor performance, because the shorter partition wall makes the two sides of the channel more prone to air leakage, thereby affecting the stability of the airflow and further affecting the efficiency of the turbine. CONTENT OF THE UTILITY MODEL

[0003] The present application provides a turbine shell and a turbine to improve the efficiency of the turbine.

[0004] In a first aspect, the present application provides a turbine shell, which is provided with a channel, and has an outer surface and an inner surface, and the channel is recessed from the inner surface of the shell to the outer surface of the shell. A partition protrusion is arranged inside the channel, which extends in the radial direction of the shell. In the radial direction of the shell, the first end of the partition protrusion is connected to the channel, and the second end of the partition protrusion is away from the outer surface of the shell. An impeller is arranged inside the shell, which is rotatably arranged inside the shell and coaxially arranged with the shell. The radius of the impeller is R1, and the distance between the second end of the partition protrusion and the center axis of the shell is R2, wherein 1

[0005] In a specific implementation, in the radial direction of the shell, the distance between the second end of the partition protrusion and the impeller is L, wherein 0.5mm≤L≤1.5mm.

[0006] In a specific implementation, the second end of the partition protrusion has an arc surface, and the radius of the arc surface is R3, wherein 0.3mm≤R3≤1mm.

[0007] In a specific implementation, the second end of the partition protrusion has a first side surface and a second side surface, which are respectively located on both sides of the partition protrusion in the axial direction of the shell, and the first side surface and the second side surface are connected by the arc surface. The included angle between the first side surface and the radial direction of the shell is α, wherein 10°≤α≤70°.

[0008] In one specific implementation, the angle between the second side and the radial direction of the housing is β, where 10°≤β≤70°.

[0009] In one specific implementation, the first end of the separating protrusion has a larger axial dimension in the housing than the second end of the separating protrusion in the housing.

[0010] In one specific implementation, the dividing protrusion extends circumferentially over the housing.

[0011] In one specific implementation, the first flow channel and the second flow channel are connected to the space between the impeller and the second end of the separating protrusion.

[0012] In one specific implementation, the housing is provided with an air inlet and an air outlet, the air inlet and the air outlet are formed on the outer surface of the housing, and the air inlet is connected to the air outlet through the flow channel.

[0013] Secondly, this application also provides a turbine, including an impeller and a turbine housing as described in any of the embodiments of the first aspect above, wherein the impeller is rotatably disposed inside the housing and the impeller is coaxially disposed with the housing.

[0014] Compared with the prior art, the beneficial effects of this application are as follows:

[0015] The turbine casing provided in this application has a smaller ratio of the partition protrusion radius and a longer partition protrusion. Compared with turbines with traditional partition walls, the turbine using this casing improves efficiency by 0.3% to 0.4% when the first and second flow channels have equal air intake; when the first and second flow channels have unequal air intake, the turbine using this casing improves efficiency by approximately 0.55%; and when only one flow channel (either the first or second flow channel) has air intake, the turbine using this casing improves efficiency by approximately 0.2%. In other words, the turbine using this casing achieves better performance and improved efficiency under various dual-flow-channel air intake conditions. Attached Figure Description

[0016] Figure 1 A cross-sectional view of the turbine housing provided in this application along the housing axis is shown;

[0017] Figure 2 A partial structural schematic diagram of the turbine housing provided in this application is shown.

[0018] Figure label:

[0019] 1 - housing; 11 - partition protrusion; 111 - arc surface; 112 - first side surface; 113 - second side surface; 12 - first flow channel; 13 - second flow channel; 14 - air inlet; 15 - air outlet; 2 - impeller. DETAILED DESCRIPTION

[0020] In order to make the purposes, technical solutions and advantages of the present application clearer, the following will further describe the embodiments of the present application with reference to the drawings. However, the example embodiments can be implemented in various forms, and should not be understood as being limited to the embodiments set forth herein. The same reference signs in the drawings represent the same or similar structures, and thus repeated description thereof will be omitted. The expressions of position and direction described in the embodiments of the present application are described with reference to the drawings, but can be changed as needed, and the changes made are included in the scope of protection of the present application. The drawings of the embodiments of the present application are only used to show the relative positional relationship and do not represent the true proportions.

[0021] In the following description, specific details are set forth in order to facilitate understanding of the present application, but the embodiments of the present application can be implemented in various other ways different from those described herein, and those skilled in the art can make similar generalizations without departing from the connotations within the embodiments of the present application. Therefore, the present application is not limited by the specific embodiments disclosed below.

[0022] As one possible application scenario, the turbine housing provided by the embodiments of the present application can be applied to a turbine. The turbine includes an impeller, the impeller is rotatably arranged in an internal space of the housing, and the impeller is coaxially arranged with the housing. The exhaust gas (having a certain temperature and pressure) generated by the engine enters the turbine, providing power for the turbine to drive the impeller to rotate, generating greater negative pressure at the air inlet of the engine, so that the engine can suck in more air, thereby making the fuel burning in the engine more sufficient, and the engine can release more power and the exhaust gas discharge is smaller.

[0023] Reference Figure 1 and Figure 2 , Figure 1 shows a cross-sectional view of the turbine housing provided by the present application along the axial direction of the housing, Figure 2 shows a partial structure schematic diagram of the turbine housing provided by the present application. The embodiments of the present application provide a turbine housing (hereinafter referred to as "housing") as shown in Figure 1 and Figure 2 , the housing 1 is provided with a flow channel, the housing 1 has an outer surface and an inner surface, and the flow channel is formed by recessing from the inner surface of the housing 1 to the outer surface of the housing 1. Referring to the coordinate directions in Figure 1 , the direction indicated by the x-axis represents the axial direction of the housing 1, and the direction indicated by the y-axis represents the radial direction of the housing 1.

[0024] The flow channel is internally provided with a partition protrusion 11, which extends in the radial direction of the shell 1. In the radial direction of the shell 1, the first end of the partition protrusion 11 is connected with the flow channel, specifically, the first end of the partition protrusion 11 is fixedly connected with the inner wall of the flow channel, that is, the first end of the partition protrusion 11 is fixedly connected with the inner surface of the shell 1 forming the flow channel. The second end of the partition protrusion 11 is away from the outer surface of the shell 1 and extends towards the central axis of the shell 1. The partition protrusion 11 divides the flow channel into a first flow channel 12 and a second flow channel 13, which are distributed in the axial direction of the shell 1.

[0025] The shell 1 is internally provided with an impeller 2, which is rotatably arranged in the shell 1 and coaxially arranged with the shell 1. The radius of the impeller 2 is R1, specifically, the radius of the impeller 2 refers to the front edge radius of the impeller 2, that is, the radial dimension corresponding to the outermost edge of the impeller 2. The distance between the second end of the partition protrusion 11 and the central axis of the shell 1 is R2, specifically, the distance is the distance between the innermost edge of the partition protrusion 11 and the central axis of the shell 1. R2 / R1 can be referred to as the radius ratio of the partition protrusion 11, 1

[0026] The turbine shell 1 provided by the embodiment of the present application has a smaller radius ratio of the partition protrusion 11, and the partition protrusion 11 is longer. According to the results of computational fluid dynamics (CFD) analysis, compared with a turbine having a traditional partition wall, the efficiency of the turbine using the shell 1 is improved by 0.3% to 0.4% under the condition that the first flow channel 12 and the second flow channel 13 have the same air intake; the efficiency of the turbine using the shell 1 is improved by about 0.55% under the condition that the first flow channel 12 and the second flow channel 13 have different air intakes; and the efficiency of the turbine using the shell 1 is improved by about 0.2% under the condition that only one side of the flow channel (the first flow channel 12 or the second flow channel 13) has air intake.

[0027] Exemplarily, compared with the shell 1 having a radius ratio of the partition protrusion 11 of 1.09, the turbine using the shell 1 can bring about an equivalent turbine efficiency improvement of about 0.6%, and can bring about a final equivalent turbine efficiency improvement of about 1.04%.

[0028] The turbine shell 1 provided by the embodiment of the present application has a smaller radius ratio of the partition protrusion 11, and the partition protrusion 11 is longer. According to the results of computational fluid dynamics (CFD) analysis, compared with a turbine having a traditional partition wall, the efficiency of the turbine using the shell 1 is improved by 0.3% to 0.4% under the condition that the first flow channel 12 and the second flow channel 13 have the same air intake; the efficiency of the turbine using the shell 1 is improved by about 0.55% under the condition that the first flow channel 12 and the second flow channel 13 have different air intakes; and the efficiency of the turbine using the shell 1 is improved by about 0.2% under the condition that only one side of the flow channel (the first flow channel 12 or the second flow channel 13) has air intake.

[0029] In the embodiment, since the partition protrusion 11 is usually formed by casting, the end of the partition protrusion 11 is a casting surface with large tolerance, and therefore, when the partition protrusion 11 is long, the distance between the second end of the partition protrusion 11 and the leading edge of the impeller 2 cannot be too small. In the radial direction of the shell 1, the distance between the second end of the partition protrusion 11 and the impeller 2 is L, where 0.5 mm≤L≤1.5 mm. For example, L=1.2 mm.

[0030] In a possible implementation, the first flow channel 12 and the second flow channel 13 are communicated through the space between the second end of the partition protrusion 11 and the impeller 2, and the air flows of the first flow channel 12 and the second flow channel 13 on both sides of the partition protrusion 11 can be mixed at the second end of the partition protrusion 11.

[0031] In the embodiment, the second end of the partition protrusion 11 has an arc surface 111, which can be formed by machining. The radius of the arc surface 111 is R3, where 0.3 mm≤R3≤1 mm. Compared with the case where the end of the partition protrusion 11 is a casting surface with large tolerance, machining the second end of the partition protrusion 11 into an arc surface 111 with small radius can reduce the size of the second end of the partition protrusion 11, which can reduce the wake loss when the air flows of the first flow channel 12 and the second flow channel 13 on both sides of the partition protrusion 11 are mixed at the second end of the partition protrusion 11, thereby further improving the efficiency of the turbine. Moreover, forming the arc surface 111 by machining can obtain small tolerance while improving the surface roughness, which also helps to reduce the distance L between the second end of the partition protrusion 11 and the impeller 2. For example, R3=0.8.

[0032] As a possible implementation, the second end of the partition protrusion 11 has a first side surface 112 and a first side surface 113, which are respectively located on both sides of the partition protrusion 11 in the axial direction of the shell 1, and correspond to the first flow channel 12 and the second flow channel 13 respectively. The first side surface 112 and the first side surface 113 are connected by the arc surface 111, and the first side surface 112 can extend to the first end of the partition protrusion 11, and the first side surface 113 can also extend to the first end of the partition protrusion 11. The angle between the first side surface 112 and the radial direction of the shell 1 is α, where 10°≤α≤70°. Specifically, the angle α between the first side surface 112 and the radial direction of the shell 1 can be realized by machining, which can reduce the surface roughness of the first side surface 112 and further improve the efficiency of the turbine. For example, α=15°.

[0033] In a specific embodiment, the first side surface 113 forms an angle β with the radial direction of the casing 1, where 10°≤β≤70°. For example, β=15°. Similar to the angle α described above, machining the angle β can reduce the surface roughness of the first side surface 113, further improving the efficiency of the turbine. In one embodiment, only one side surface of the partition protrusion 11 can be machined, for example, the first side surface 112 is machined to achieve the angle α described above, or the first side surface 113 is machined to achieve the angle β described above. In another embodiment, two side surfaces of the partition protrusion 11 can be machined respectively to achieve the angle α and the angle β described above.

[0034] In a specific embodiment, the first end of the partition protrusion 11 has a larger dimension in the axial direction of the casing 1 than the second end of the partition protrusion 11, i.e., the thickness of the first end of the partition protrusion 11 is larger than the thickness of the second end of the partition protrusion 11, and the partition protrusion 11 has higher structural stability.

[0035] In a specific embodiment, the partition protrusion 11 extends in the circumferential direction of the casing 1 to separate the flow passage into the first flow passage 12 and the second flow passage 13 in the circumferential direction of the casing 1. The shape of the partition protrusion 11 is similar to the shape of the flow passage, for example, when the flow passage is helical, the partition protrusion 11 is also helical.

[0036] In an actual arrangement, the casing 1 is provided with an air inlet 14 and an air outlet 15, the air inlet 14 and the air outlet 15 are formed on the outer surface of the casing 1, and the air inlet 14 is in communication with the air outlet 15 through the flow passage. The exhaust gas generated by the engine enters the casing 1 through the air inlet 14, flows through the flow passage, and flows out of the casing 1 through the air outlet 15.

[0037] The above is only a specific embodiment of the present application, but the protection scope of the present application is not limited to the above-described embodiments. Obviously, those skilled in the art can make various modifications and changes to the present application without departing from the scope and spirit of the present application. If these modifications and changes belong to the scope of the claims of the present application and their equivalent technologies, the intention of the present application also includes these modifications and changes.

Claims

1. A turbomachine casing, characterized in that, The shell is provided with a flow channel, the shell has an outer surface and an inner surface, and the flow channel is formed by recessing the inner surface of the shell towards the outer surface of the shell; The flow channel is internally provided with a partition protrusion, the partition protrusion extends in the radial direction of the shell, the first end of the partition protrusion is connected with the flow channel, and the second end of the partition protrusion is away from the outer surface of the shell; the partition protrusion divides the flow channel into a first flow channel and a second flow channel, and the first flow channel and the second flow channel are distributed along the axial direction of the shell; The shell is internally provided with an impeller, the impeller is rotatably arranged in the shell, and the impeller is coaxially arranged with the shell; the radius of the impeller is R1, and the distance between the second end of the partition protrusion and the central axis of the shell is R2, wherein 1 2. The turbomachine housing according to claim 1, characterized in that In the radial direction of the shell, the distance between the second end of the partition protrusion and the impeller is L, wherein 0.5mm≤L≤1.5mm.

3. The turbomachine housing according to claim 1, characterized in that, The second end of the partition protrusion has an arc surface, and the radius of the arc surface is R3, wherein 0.3mm≤R3≤1mm.

4. The turbomachine housing according to claim 3, characterized in that The second end of the partition protrusion has a first side surface and a second side surface, the first side surface and the second side surface are respectively located on both sides of the partition protrusion in the axial direction of the shell, and the first side surface and the second side surface are connected by the arc surface; The included angle between the first side surface and the radial direction of the shell is α, wherein 10°≤α≤70°.

5. The turbomachine housing according to claim 4, characterized in that The included angle between the second side surface and the radial direction of the shell is β, wherein 10°≤β≤70°.

6. The turbomachine housing of claim 1, wherein, The size of the first end of the partition protrusion in the axial direction of the shell is greater than the size of the second end of the partition protrusion in the axial direction of the shell.

7. The turbomachine housing of claim 1, wherein, The partition protrusion extends in the circumferential direction of the shell.

8. The turbomachine housing of claim 1, wherein, The first flow channel and the second flow channel are communicated through the space between the second end of the partition protrusion and the impeller.

9. The turbomachine housing of claim 1, wherein, The shell is provided with an air inlet and an air outlet, the air inlet and the air outlet are formed on the outer surface of the shell, and the air inlet is communicated with the air outlet through the flow channel.

10. A turbomachine characterized by, The turbine shell comprises an impeller and a turbine shell according to any one of claims 1-9. The impeller is rotatably arranged in the shell, and the impeller is coaxially arranged with the shell.

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