Turbine blade, turbine and supercharger

Abstract

The utility model relates to the technical field of turbines, in particular to a turbine blade, a turbine and a supercharger. The turbine blade sequentially comprises a top area, a connecting area and a root area from the top of the blade to the root of the blade, the thickness D1 of the top area is smaller than or equal to a first preset value, the thickness D2 of the root area is larger than or equal to a second preset value, and the thickness of the connecting area is gradually increased from D1 to D2 from the top of the blade to the root of the blade; in the height direction of the blade, the size of the turbine blade is H, the size of the top area is H1, the size of the root area is H3, H1 / H is larger than or equal to 0.05, and H3 / H is smaller than or equal to 0.3. By optimizing the thickness distribution form of the turbine blades in the height direction, the aerodynamic efficiency of the turbine and the reliability of the turbine are improved.

Description

Technical Field

[0001] The present application relates to the field of turbine technology, and in particular to a turbine blade, a turbine and a supercharger. Background Art

[0002] A turbo compressor is actually an air compressor that uses the inertial force of the exhaust gas discharged by the engine to drive the turbine to rotate, and the turbine in turn drives the coaxial impeller to rotate. The impeller compresses the air to increase the intake volume. The thickness distribution of the turbine blade along the height direction of the blade has a crucial impact on the aerodynamic performance and reliability of the turbine.

[0003] The thickness distribution of existing turbine blades along the height direction of the blade is mainly linear, that is, the thickness of the blade gradually increases from the top of the blade to the root of the blade, and the thickness of the blade is linearly related to the height of the blade. However, the thickness of the top of the blade of the above structure is still too large, which affects the aerodynamic performance of the turbine. At the same time, the stress at the root of the blade is still relatively large, which affects the structural reliability of the blade. Utility Model Content

[0004] The present application discloses a turbine blade, a turbine and a supercharger to improve the aerodynamic performance and reliability of an existing turbine.

[0005] In order to achieve the above objectives, this application provides the following technical solutions:

[0006] In the first aspect, the present application provides a turbine blade, which includes a top area, a connection area and a root area in sequence from the top of the blade to the root of the blade, the thickness D1 of the top area is less than or equal to a first preset value, the thickness D2 of the root area is greater than or equal to a second preset value, and the thickness of the connection area gradually increases from D1 to D2 along the top of the blade to the root of the blade; along the height direction of the blade, the size of the turbine blade is H, the size of the top area is H1, and the size of the root area is H3, wherein H1 / H≥0.05, H3 / H≤0.3.

[0007] Furthermore, the first preset value is 0.5-0.6 mm.

[0008] Further, the second preset value is 4% of the diameter of the turbine blade.

[0009] Furthermore, the thickness D2 of the root region is less than or equal to 7% of the diameter of the turbine blade.

[0010] Furthermore, H1 / H≤0.3, H3 / H≥0.05.

[0011] Furthermore, the connection region includes N sub-regions, wherein N is a positive integer greater than or equal to 1, and the thickness of the N sub-regions gradually increases from the top of the blade to the root of the blade.

[0012] Furthermore, the thickness of any sub-region increases linearly, exponentially, logarithmically or parabolically from the top of the blade to the root of the blade.

[0013] Furthermore, when N≥2, along the thickness direction of the turbine blade, the sizes of the contact surfaces of any two adjacent sub-regions are the same.

[0014] In a second aspect, the present application provides a turbine, comprising the turbine blade of the first aspect.

[0015] In a third aspect, the present application provides a supercharger, comprising the turbine according to the second aspect.

[0016] The turbine blade and turbine provided by the present application, wherein the thickness D1 of the top region of the turbine blade is less than or equal to the first preset value, H1 / H≥0.05, so that the thickness D1 of the top region is as small as possible within the process allowable range, thereby reducing the resistance of the airflow in the top region, reducing the possibility of airflow separation, and improving the flow efficiency of the airflow in the top region, reducing boundary layer loss, airflow wake loss, etc., and improving the aerodynamic efficiency of the turbine as much as possible. Moreover, the thickness of the top region becomes smaller, which can reduce the mass of the entire turbine blade, thereby reducing the centrifugal force during rotation, helping to reduce the mechanical stress of the turbine blade, and improving the durability and life of the turbine blade. At the same time, the root region of the turbine blade is connected to the turbine shaft, and the centrifugal force and other mechanical loads it bears are the largest. The thickness D2 of the root region is greater than or equal to the second preset value, H3 / H≤0.3, so that the thickness D2 of the root region is large enough, so as to provide a higher structural strength, reduce the risk of deformation or fracture of the turbine blade due to excessive centrifugal force during high-speed rotation, and improve the reliability of the turbine. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 is a schematic diagram of the structure of an existing turbine;

[0018] Figure 2 is a cross-sectional view of an existing turbine blade;

[0019] Figure 3 A cross-sectional view of a turbine blade according to an embodiment of the present application;

[0020] Figure 4 A cross-sectional view of a turbine blade according to another embodiment of the present application;

[0021] Figure 5 This is a cross-sectional view of a turbine blade according to another embodiment of the present application.

[0022] Reference numerals: 10, 100 - turbine blades; 20 - turbine shaft; 110 - top region; 120 - connection region; 121 - sub-region; 130 - root region. DETAILED DESCRIPTION

[0023] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0024] Figure 1 The schematic diagram of the existing turbine structure is shown in FIG. Figure 1 The turbine includes a turbine shaft 20 and a plurality of turbine blades 10 connected to the turbine shaft 20, and the plurality of turbine blades 10 rotate around the turbine shaft 20. The thickness distribution of the turbine blades along the height direction of the blades has a crucial influence on the aerodynamic performance and reliability of the turbine. Figure 2 For a cross-sectional view of a conventional turbine blade, refer to Figure 2 The thickness distribution of the 10 turbine blades of the existing turbine along the height direction D of the blades is mainly linear, that is, the thickness of the blade gradually increases from the top of the blade to the root of the blade, and the thickness of the blade is linearly related to the height of the blade. However, the thickness of the top of the blade of the above structure is still too large, which affects the aerodynamic performance of the turbine. At the same time, the stress at the root of the blade is still relatively large, which affects the structural reliability of the blade.

[0025] In view of this, a turbine blade is provided in an embodiment of the present application. Figure 3 This is a cross-sectional view of a turbine blade according to an embodiment of the present application, referring to Figure 3 , along the top of the blade to the root of the blade, the turbine blade 100 includes a top area 110, a connection area 120 and a root area 130 in sequence, the thickness D1 of the top area 110 is less than or equal to a first preset value, the thickness D2 of the root area 130 is greater than or equal to a second preset value, and the thickness of the connection area 120 gradually increases from D1 to D2 along the top of the blade to the root of the blade; along the height direction D of the blade, the size of the turbine blade 100 is H, the size of the top area 110 is H1, the size of the connection area 120 is H2, and the size of the root area 130 is H3, wherein H1 / H≥0.05, H3 / H≤0.3.

[0026] It is understandable that if Figure 3 The cross section shown is any cross section of the turbine blade 100 along the height direction, and the height direction D of the turbine blade 100 is the direction of the line connecting the blade top and the blade root.

[0027] Among them, the thickness of the top area 110 of the turbine blade 100 has the greatest impact on the aerodynamic efficiency of the turbine blade 100. The thickness D1 of the top area 110 is less than or equal to the first preset value. The first preset value can be set according to actual conditions. Optionally, the first preset value can be 0.5-0.6 mm. Exemplarily, the first preset value can be 0.5 mm, 0.52 mm, 0.54 mm, 0.56 mm, 0.58 mm, 0.59 mm or 0.6 mm. It can be understood that within the process allowable range, the top area 110 of the turbine blade 100 is made as thin as possible to reduce the resistance of the airflow in the top area 110, reduce the possibility of airflow separation, and improve the flow efficiency of the airflow in the top area 110, reduce boundary layer losses, airflow wake losses, etc., thereby improving the aerodynamic efficiency of the turbine.

[0028] It can be understood that the root area 130 of the turbine blade 100 is a stress concentration area, and the thickness D2 of the root area 130 is greater than or equal to the second preset value. The thickness needs to be increased to ensure the reliability of the turbine. The second preset value is 4% of the diameter of the turbine blade 100, that is, the thickness D2 of the root area 130 is greater than or equal to 4% of the diameter of the turbine blade 100, so that the root area 130 has a sufficiently large thickness, thereby providing a higher structural strength, reducing the risk of deformation or fracture of the turbine blade 100 due to excessive centrifugal force when rotating at high speed, and improving the reliability of the turbine. The diameter of the turbine blade 100 is the radial distance between the end of the turbine blade 100 away from the turbine shaft and the turbine shaft.

[0029] In some embodiments of the present application, the thickness D2 of the root region 130 is less than or equal to 7% of the diameter of the turbine blade 100. If the thickness D2 of the root region 130 is too large, the mass of the entire turbine blade 100 will increase, the centrifugal force when the turbine blade 100 rotates will increase, and the stress on the turbine blade 100 will increase, thereby affecting the durability of the turbine blade 100.

[0030] Reference Figure 3 , H1 / H≥0.05, to ensure that the top area 110 has a sufficient height to fully improve the flow efficiency of the airflow in the top area 110, thereby improving the aerodynamic efficiency of the turbine. Optionally, H1 / H≥0.1. At the same time, the height H1 of the top area 110 cannot be too high, and optionally, H1 / H≤0.3, to avoid affecting the strength of the turbine blade 100.

[0031] Continue to refer to Figure 3 , H3 / H≤0.3, to avoid the root area 130 being too high, resulting in excessive mass of the turbine blade 100. However, the height of the root area 130 cannot be too small. Optionally, H3 / H≥0.05, to ensure that the root area 130 has an appropriate height to meet the requirements of mechanical strength. Preferably, H3 / H≥0.1.

[0032] In some embodiments of the present application, the connection area 120 includes N sub-areas 121, wherein N is a positive integer greater than or equal to 1, and the thickness of the N sub-areas 121 gradually increases from the top of the blade to the root of the blade. The connection area 120 may include one, two or more sub-areas 121. The connection area 120 serves to connect the top area 110 and the root area 130. The number of sub-areas 121 is not limited in the present application, as long as the thickness of the connection area 120 gradually increases, that is, the thickness continuity increases.

[0033] Figure 4 This is a cross-sectional view of a turbine blade according to another embodiment of the present application, referring to Figure 4 The continuous region includes two sub-regions 121. The thickness of the two sub-regions 121 increases linearly from the top of the blade to the root of the blade, and the thickness of the two sub-regions 121 increases at different rates. The height of the sub-region 121 close to the top region 110 is H2a, and the height of the sub-region 121 close to the root region 130 is H2b. The ratio of H2a and H2b is not limited in this application, as long as H2a+H2b=H2 is satisfied.

[0034] In some embodiments of the present application, the thickness of any sub-region 121 may increase linearly, exponentially, logarithmically, or parabolically from the top of the blade to the root of the blade, that is, the thickness distribution of the connecting region 120 may be a curved distribution.

[0035] Among them, it is worth mentioning that due to the limitations of process conditions or other factors, there may be some deviations or errors in the actual process, resulting in the "linear increase" described above may not be completely accurate. For example, the "linear increase" described above may be a linear increase allowed within the error tolerance range. Of course, "linear increase" can also be understood as "basic linear increase" or "completely linear increase", so the "linear increase" relationship described above only needs to roughly meet the above conditions and is within the scope of protection of this application.

[0036] It is understandable that the meaning of exponential growth, logarithmic growth or parabolic growth can be found in the above description of “linear increase” and will not be repeated here.

[0037] Figure 5 This is a cross-sectional view of a turbine blade according to another embodiment of the present application. Figure 5 As shown, the continuous region includes two sub-regions 121 , and along the direction from the blade top to the blade root, the thickness distribution form of the two sub-regions 121 is a curved distribution.

[0038] Continue to refer to Figure 4 and Figure 5When N≥2, that is, when the connection area 120 includes at least two sub-areas 121, along the thickness direction X of the turbine blade 100, the sizes of the contact surfaces of any two adjacent sub-areas 121 are the same to ensure that the thickness of the connection area increases continuously, avoid stress concentration, and thus improve the durability of the turbine blade 100.

[0039] In summary, in the present application, the thickness distribution of the turbine blade 100 along the height direction is optimized so that the top area 110 is as thin as possible, the root area 130 has sufficient thickness, and the thickness of the connecting area 120 gradually increases from the top area 110 to the root area 130. Compared with the linear thickness distribution of the existing turbine blade 100, the aerodynamic efficiency of the turbine blade 100 in the present application can be effectively improved by at least 0.5%, and at the same time, the stress in the root area 130 of the turbine blade 100 is greatly reduced.

[0040] Based on the same technical concept, an embodiment of the present application provides a turbine, which includes turbine blades in various possible embodiments of the present application. Because it includes the turbine blades in the present application, the turbine also has the advantages of high turbine aerodynamic efficiency and turbine reliability.

[0041] Based on the same technical concept, an embodiment of the present application further provides a supercharger, which includes a turbine in various possible embodiments of the present application.

[0042] Among them, the supercharger can be an air boost system for an internal combustion engine, which can improve the power and efficiency of the engine. When the aerodynamic efficiency of the turbine is improved, more exhaust gas energy is converted into mechanical energy to drive the compressor coaxial with the turbine, thereby effectively improving the efficiency of the compressor and reducing the thermal and mechanical loads of the turbocharger, thereby extending the service life of the supercharger and improving the reliability of the entire system.

[0043] Obviously, those skilled in the art can make various changes and modifications to the embodiments of the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is also intended to include these modifications and variations.

Claims

1. A turbine blade, characterized in that: The turbine blade includes a top region, a connection region and a root region in sequence from the top of the blade to the root of the blade, a thickness D1 of the top region is less than or equal to a first preset value, a thickness D2 of the root region is greater than or equal to a second preset value, and a thickness of the connection region gradually increases from D1 to D2 from the top of the blade to the root of the blade; Along the height direction of the blade, the size of the turbine blade is H, the size of the top area is H1, and the size of the root area is H3, wherein H1 / H≥0.05 and H3 / H≤0.

3.

2. The turbine blade according to claim 1, characterized in that The first preset value is 0.5-0.6 mm.

3. The turbine blade according to claim 1, characterized in that: The second preset value is 4% of the diameter of the turbine blade.

4. The turbine blade according to claim 3, characterized in that The thickness D2 of the root region is less than or equal to 7% of the diameter of the turbine blade.

5. The turbine blade according to claim 1, characterized in that H1 / H≤0.3, H3 / H≥0.

05.

6. The turbine blade according to any one of claims 1 to 5, characterized in that: The connection region includes N sub-regions, wherein N is a positive integer greater than or equal to 1, and the thickness of the N sub-regions gradually increases from the top of the blade to the root of the blade.

7. The turbine blade according to claim 6, characterized in that The thickness of any of the sub-regions increases linearly, exponentially, logarithmically or parabolically from the top of the blade to the root of the blade.

8. The turbine blade according to claim 7, characterized in that When N≥2, along the thickness direction of the turbine blade, the contact surfaces of any two adjacent sub-regions have the same size.

9. A turbine, characterized in that: The turbine comprises the turbine blade according to any one of claims 1-8.

10. A supercharger, characterized in that: The turbine comprises the turbine of claim 9.

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