Turbine blade, turbine and turbocharger
By designing turbine blades with vertical extension sections, external convex sections and internal concave sections, optimizing the airflow channel structure, the problem that turbine blades in the prior art is difficult to take into account both aerodynamic performance and reliability, and achieving higher aerodynamic performance and Stress reduction.
Patent Information
- Application Number
- CN202421334708.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-06-12
- Publication Date
- 2025-01-17
- Estimated Expiration
- 2034-06-12
AI Technical Summary
It is difficult to take into account both aerodynamic performance and reliability during the design process of existing turbine blades, and commonly used stress reduction methods will lead to aerodynamic performance degradation.
Design a turbine blade with the leaf top and leaf roots recessed toward the leaf root side to form an airflow channel, and the outlet edge includes vertical extension sections, outer convex sections and inner concave sections. By optimizing the length and shape of these sections, it can improve the airflow direction. Do work with the blades while reducing stress.
It effectively improves the aerodynamic performance and reliability of the turbine blades, ensures that the stress is reduced under the same centrifugal force, and avoids conflicts between aerodynamic performance and reliability.
Smart Images
Figure CN222363029U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of machinery, in particular to a turbine blade, a turbine and a turbocharger. Background Art
[0002] A turbocharger is actually an air compressor that uses the inertial force of the exhaust gas discharged by the engine to drive the turbine to rotate. The turbine in turn drives the coaxial impeller to rotate, compressing the air to increase the intake volume.
[0003] Because the working environment of the turbine end of the turbocharger is harsh and it is subjected to thermal stress and centrifugal stress, the stress of the turbine blades is generally high, and the blade stress must be considered specifically during the design process.
[0004] At present, the most commonly used method to reduce stress in the industry is to use a straight line bevel at the turbine blade outlet to reduce the blade length to reduce the stress at the blade outlet root. This method can effectively reduce the stress at the blade outlet root, but it will also reduce the turbine aerodynamic performance. Utility Model Content
[0005] The utility model discloses a turbine blade, a turbine and a turbocharger, which are used to simultaneously take into account the aerodynamic performance and reliability of the turbine blade.
[0006] In order to achieve the above object, the utility model provides the following technical solutions:
[0007] In a first aspect, a turbine blade is provided, comprising: a blade top and a blade root arranged opposite to each other, the blade top and the blade root being both recessed toward the blade root side, an airflow channel being formed between the blade top and the blade root, one end of the airflow channel having an inlet facing the longitudinal direction, and the other end having an outlet facing the transverse direction; and an edge of the outlet sequentially comprising a vertical extension section, an outward convex section and an inward concave section in the longitudinal direction away from the inlet; wherein the vertical extension section extends along the longitudinal direction, the outward convex section protrudes in the transverse direction away from the inlet, and the inward concave section is recessed in the transverse direction toward the outlet.
[0008] In the turbine blade, the vertical extension section is longer than the chamfered edge of the outlet, and the middle convex section also makes the middle position of the turbine blade longer, so that the turbine blade guides the airflow better and the blade does more work to ensure the aerodynamic performance of the turbine blade. In addition, the concave section near the blade root can increase the root area of the turbine blade, which can effectively reduce stress under the same centrifugal force to ensure reliability.
[0009] Optionally, the first longitudinal distance B and the total height H satisfy: 0.7≤B / H≤0.9; wherein the first longitudinal distance B represents the distance from the end point of the vertical extension section close to the convex section to the blade root in the longitudinal direction; the total height H represents the height of the edge of the outlet in the longitudinal direction.
[0010] Optionally, the second longitudinal distance A and the total height H satisfy: 0.05≤A / H≤0.25; wherein the second longitudinal distance A represents, in the longitudinal direction, the distance from the end point of the convex section close to the concave section to the blade root.
[0011] Optionally, the third longitudinal distance C and the total height H satisfy: 0.4≤C / H≤0.6; wherein the third longitudinal distance C represents the distance from the highest point of the convex section to the blade root in the longitudinal direction.
[0012] Optionally, the first lateral distance L1 and the second lateral distance L satisfy: 0.05≤(L1-L) / L≤0.2; wherein the first lateral distance L1 represents the distance from the highest point of the convex section to the blade root in the lateral direction; and the second lateral distance L represents the distance from the vertical extension section to the blade root in the lateral direction.
[0013] Optionally, the convex section is an arc section.
[0014] Optionally, the concave section is a circular arc section.
[0015] Optionally, a line connecting two end points of the convex section forms a reference line; in the transverse direction, the reference line gradually moves away from the inlet from the blade top to the blade root.
[0016] In a second aspect, a turbine is provided, comprising the turbine blades described in any of the above technical solutions.
[0017] The advantages of the turbine described are the same as those of the turbine blades described above relative to the prior art, which will not be described in detail here.
[0018] In a third aspect, a turbocharger is provided, which includes the turbine described in the above technical solution.
[0019] The turbocharger has the same advantages as the above-mentioned turbine over the prior art, which will not be described in detail here. BRIEF DESCRIPTION OF THE DRAWINGS
[0020] Figure 1 A schematic diagram of the structure of a turbine blade provided in an embodiment of the present application. DETAILED DESCRIPTION
[0021] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.
[0022] refer to Figure 1 The turbine blade provided in the embodiment of the present application includes: a blade tip 10 and a blade root 20 arranged opposite to each other, the blade tip 10 and the blade root 20 are both recessed toward the blade root 20 side, an airflow channel 50 is formed between the blade tip 10 and the blade root 20, one end of the airflow channel 50 has an inlet 30 facing the longitudinal direction (reference Y-axis direction), and the other end has an outlet 40 facing the transverse direction (reference X-axis direction); and the edge of the outlet 40 includes a vertical extension section 41, an outer convex section 42 and an inner concave section 43 in the longitudinal direction (reference Y-axis direction) in the direction away from the inlet 30; wherein the vertical extension section 41 extends in the longitudinal direction (reference Y-axis direction), the outer convex section 42 protrudes in the transverse direction (reference X-axis direction) in the direction away from the inlet 30, and the inner concave section 43 is recessed in the transverse direction (reference X-axis direction) in the direction close to the outlet 40.
[0023] In the turbine blade, the vertical extension section 41 is longer relative to the chamfered edge of the outlet 40, and the middle convex section 42 also makes the middle position of the turbine blade longer, so that the turbine blade guides the airflow better and does more work to ensure the aerodynamic performance of the turbine blade. In addition, the concave section 43 near the blade root 20 can increase the root area of the turbine blade, and under the same centrifugal force, can effectively reduce stress to ensure reliability.
[0024] In a specific embodiment, the first longitudinal distance B and the total height H satisfy: 0.7≤B / H≤0.9; wherein the first longitudinal distance B represents the distance from the end point of the vertical extension section 41 close to the convex section 42 to the blade root 20 in the longitudinal direction (referenced to the Y-axis direction); the total height H represents the height of the edge of the outlet 40 in the longitudinal direction (referenced to the Y-axis direction). The value of B / H can be 0.7, 0.75, 0.8, 0.85 and 0.9, etc.; if the value of B / H is too large, the length of the vertical extension section 41 will be too small, the turbine blade will guide the airflow poorly, the work of the turbine blade will be reduced, and the aerodynamic performance of the turbine blade will be reduced; if the value of B / H is too small, the length of the convex section 42 and the concave section 43 will be too small, resulting in a decrease in aerodynamic performance and reliability.
[0025] In a specific embodiment, the second longitudinal distance A and the total height H satisfy: 0.05≤A / H≤0.25; wherein the second longitudinal distance A represents the distance from the end point of the convex section 42 close to the concave section 43 to the blade root 20 in the longitudinal direction (reference Y-axis direction). The value of A / H can be 0.05, 0.1, 0.15, 0.2, 0.25, etc.; if the value of A / H is too large, the length of the vertical extension section 41 and the convex section 42 will be too small, the turbine blade will guide the airflow poorly, the work of the turbine blade will be reduced, and the aerodynamic performance of the turbine blade will be reduced; if the value of A / H is too small, the length of the concave section 43 will be too small, resulting in a decrease in aerodynamic performance and reliability.
[0026] In a specific embodiment, the third longitudinal distance C and the total height H satisfy: 0.4≤C / H≤0.6; wherein the third longitudinal distance C represents the distance from the highest point of the convex section 42 to the blade root 20 in the longitudinal direction (reference Y-axis direction). The value of C / H can be 0.4, 0.45, 0.5, 0.55 and 0.6, etc. If the value of C / H is too large, the convex section 42 will be too close to the blade tip 10, the size of the vertical extension section 41 will be compressed, the turbine blade will guide the airflow poorly, the turbine blade will do less work, and the aerodynamic performance of the turbine blade will decrease; if the value of C / H is too small, the convex section 42 will be too close to the blade bottom 20, the length of the concave section 43 will be too small, resulting in a decrease in aerodynamic performance and reliability.
[0027] In a specific embodiment, the first transverse distance L1 and the second transverse distance L satisfy: 0.05≤(L1-L) / L≤0.2; wherein the first transverse distance L1 represents the distance from the highest point of the convex section 42 to the blade root 20 in the transverse direction (referenced to the X-axis direction); the second transverse distance L represents the distance from the vertical extension section 41 to the blade root 20 in the transverse direction (referenced to the X-axis direction). The value of (L1-L) / L can be 0.05, 0.1, 0.15, 0.2, etc. If the value is too large, the convex section 42 will bulge too much, which will increase the stress. If the value is too large, the aerodynamic performance will be reduced due to insufficient length.
[0028] In a specific embodiment, the outer convex section 42 is an arc section to further alleviate the stress concentration problem.
[0029] In a specific embodiment, the inner concave section 43 is an arc section to further alleviate the stress concentration problem.
[0030] In a specific embodiment, the line connecting the two ends of the outer convex section 42 forms a reference line; in the transverse direction (referenced to the X-axis direction), the reference line gradually moves away from the inlet 30 from the blade tip 10 to the blade root 20. By making the edge of the outlet 40 extend as a whole and keep the bevel, the length of the blade at the blade tip 10 can be reduced, thereby reducing the stress at the blade root 20 of the outlet 40.
[0031] Based on the same inventive concept, an embodiment of the present application also provides a turbine, which includes the turbine blades provided in the previous embodiment, and its effects can refer to the turbine blades provided in the previous embodiment.
[0032] Based on the same inventive concept, an embodiment of the present application further provides a turbocharger, which includes the turbine of the above embodiment, and its effect can refer to the above turbine.
[0033] Obviously, those skilled in the art can make various changes and modifications to the embodiments of the present invention without departing from the spirit and scope of the present invention. Thus, if these modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include these modifications and variations.
Claims
1. A turbine blade, characterized in that: include: A blade top and a blade root are arranged opposite to each other, the blade top and the blade root are both recessed toward the blade root side, an air flow channel is formed between the blade top and the blade root, one end of the air flow channel has an inlet facing the longitudinal direction, and the other end has an outlet facing the transverse direction; The edge of the outlet includes a vertical extension section, an outward convex section and an inward concave section in the longitudinal direction away from the inlet; The vertically extending section extends along the longitudinal direction, the convex section protrudes in the lateral direction away from the inlet, and the concave section is concave in the lateral direction toward the outlet.
2. The turbine blade according to claim 1, characterized in that The first longitudinal distance B and the total height H satisfy: 0.7≤B / H≤0.9; wherein, The first longitudinal distance B represents the distance from the end point of the vertical extension section close to the convex section to the blade root in the longitudinal direction; The total height H refers to the height of the edge of the outlet in the longitudinal direction.
3. The turbine blade according to claim 2, characterized in that: The second longitudinal distance A and the total height H satisfy: 0.05≤A / H≤0.25; wherein, The second longitudinal distance A represents the distance from the end point of the convex section close to the concave section to the blade root in the longitudinal direction.
4. The turbine blade according to claim 3, characterized in that The third longitudinal distance C and the total height H satisfy: 0.4≤C / H≤0.6; wherein, The third longitudinal distance C represents the distance from the highest point of the convex section to the blade root in the longitudinal direction.
5. The turbine blade according to any one of claims 1 to 4, characterized in that: The first lateral distance L1 and the second lateral distance L satisfy: 0.05≤(L1-L) / L≤0.2; wherein, The first transverse distance L1 represents the distance from the highest point of the convex section to the blade root in the transverse direction; The second transverse distance L represents the distance from the vertical extension section to the blade root in the transverse direction.
6. The turbine blade according to claim 1, characterized in that The convex section is a circular arc section.
7. The turbine blade according to claim 1, characterized in that The concave section is a circular arc section.
8. The turbine blade according to claim 1, characterized in that The line connecting the two end points of the convex section forms a reference line; In the transverse direction, the reference line gradually moves away from the inlet from the blade tip to the blade root.
9. A turbine, characterized in that: The invention comprises the turbine blade according to any one of claims 1 to 8.
10. A turbocharger, characterized in that: Comprising the turbine as claimed in claim 9.