Turbine blade with V-shaped crack ball convex structure

Abstract

The embodiment of the invention provides a turbine blade with a V-shaped crack ball convex structure. The turbine blade is used for a hot end component of the aero-engine, a heat exchange channel is formed in the turbine blade and provided with a wall face, a ball protrusion is arranged on the wall face, the ball protrusion comprises a first crack and a second crack, and the first crack and the second crack are arranged on the wall face. An included angle I is formed between the projection of the central extension line of the first crack in the plane parallel to the flow direction of the fluid and the projection of the central extension line of the second crack in the plane parallel to the flow direction of the fluid, and the included angle I is an acute angle. According to the turbine blade, the wedge seams with specific angles and positions are formed in the surface of the spherical protrusion, and the flow characteristic of a cooling medium is utilized. Due to the existence of the crack, part of fluid can be guided to penetrate through or bypass the ball protrusions, a more complex vortex system structure is generated, a thermal boundary layer is effectively destroyed, and heat exchange is remarkably enhanced.

Description

Technical Field

[0001] This application relates to the field of turbine blade design technology, and in particular to a turbine blade with a V-shaped slit spherical convex structure. Background Technology

[0002] Turbine blades are key hot-end components in power plants such as gas turbines and aero engines, and their operating environment is usually under extremely high temperature and pressure. In order to ensure that the blade material can maintain sufficient strength and safety margin at high temperatures, modern advanced turbine blades are usually designed with complex internal cooling channels. A relatively low-temperature cooling medium (such as air) flows in the channels to remove the heat absorbed by the blade from the outside through convection heat transfer and other methods.

[0003] To enhance heat transfer efficiency within heat exchange channels, various types of flow-disrupting structures, such as ribs, pillars, pits, or protrusions, are commonly incorporated into the channel walls. These structures disrupt the boundary layer of the cooling medium, increasing flow turbulence and thus improving heat transfer. However, while enhancing heat transfer, traditional flow-disrupting structures often introduce significant flow resistance (pressure drop), leading to increased power consumption in the cooling system. Therefore, effectively enhancing heat transfer while minimizing flow resistance remains a continuous pursuit in turbine blade cooling channel design.

[0004] Existing protrusion structures, such as spherical protrusions, can provide some flow disturbance, but their effectiveness in enhancing flow disturbance and heat transfer still has room for improvement. In particular, how to design the surface features of the protrusions to more precisely control the flow state of the cooling medium and achieve better overall heat transfer performance is a technical problem that needs to be solved.

[0005] It should be noted that the above content is not necessarily prior art, nor is it intended to limit the scope of patent protection of this application. Summary of the Invention

[0006] This application provides a turbine blade with a V-shaped slit spherical convex structure to solve or alleviate one or more of the technical problems mentioned above.

[0007] This application discloses a turbine blade with a V-shaped slit spherical protrusion structure. The turbine blade is used as a hot-end component of an aero-engine. The turbine blade has a heat exchange channel with a wall surface. A spherical protrusion is provided on the wall surface. The spherical protrusion includes a first slit and a second slit. The projection of the center extension line of the first slit in a plane parallel to the flow direction of the fluid and the projection of the center extension line of the second slit in a plane parallel to the flow direction of the fluid form an angle I, which is an acute angle.

[0008] By incorporating slits at specific angles and locations on the surface of the spherical convex surface, the flow characteristics of the cooling medium are utilized. The presence of the slits guides some fluid to penetrate or bypass the convex surface, generating a more complex vortex structure, effectively disrupting the thermal boundary layer, and significantly enhancing heat transfer. Simultaneously, compared to a solid spherical convex surface, this design can, to some extent, guide the flow, avoiding excessively large flow stagnation zones, thereby effectively reducing flow resistance while achieving similar or higher heat transfer intensities. Limiting the included angle Ⅰ between the projections of the first and second slits allows symmetrical and specifically directional turbulence to form on both sides of the convex surface, resulting in a more orderly and efficient flow organization, avoiding the additional losses or localized overheating that may result from asymmetric flow.

[0009] According to an embodiment of this application, in a plane parallel to the flow direction of the fluid, the center extension line of the first split forms an angle II with the horizontal direction, and the center extension line of the second split forms an angle III with the horizontal direction, wherein the angles II and III are acute angles.

[0010] According to an embodiment of this application, the first split and the second split are symmetrically arranged with respect to the central vertical line at the apex of the spherical protrusion, and the included angle II is equal to the included angle III.

[0011] According to an embodiment of this application, the included angle II and the included angle III are each independently between 10° and 50°.

[0012] According to an embodiment of this application, the included angle I is 1°-89°.

[0013] According to an embodiment of this application, the diameter of the spherical protrusion is D, the first slit intersects the diameter of a plane perpendicular to the flow direction of the fluid at a first intersection point, the radial distance from the first intersection point to the outer surface of the spherical protrusion is S1, and the relationship between S1 and D is: 0.1≦S1 / D≦0.4; The diameter of the spherical protrusion is D. The second slit intersects the diameter of a plane perpendicular to the flow direction of the fluid at a second intersection point. The radial distance from the second intersection point to the outer surface of the spherical protrusion is S2. The relationship between S2 and D is: 0.1≦S2 / D≦0.4.

[0014] According to an embodiment of this application, the distance between the spherical protrusion and the wall surface is H, and the diameter of the spherical protrusion is D. The relationship between H and D satisfies: 0.1≤H / D≤0.5.

[0015] According to an embodiment of this application, the wall surface is a rough surface, and the Nu / Nu0 of the rough surface is 1.758-2.981 in the range of 20,000-100,000 Reynolds number. Within the Reynolds number range of 20,000-100,000, the f / f0 of the rough surface is 3.606-5.289; Within the Reynolds number range of 20,000-100,000, the TP of the rough surface is 1.128-1.835.

[0016] According to an embodiment of this application, the spherical protrusions are arranged in an array, and in the heat exchange channel, the distance between two adjacent spherical protrusions along the flow direction is 10mm-40mm; The spherical protrusions are arranged in an array. In the heat exchange channel, in the direction perpendicular to the flow direction, the distance between two adjacent spherical protrusions is 10mm-40mm.

[0017] According to an embodiment of this application, the cross-sectional shape of the first split is wedge-shaped, and the opening angle of the wedge is 45°-89°; The cross-sectional shape of the second split is wedge-shaped, and the opening angle of the wedge is 45°-89°.

[0018] According to an embodiment of this application, the widths of the first split and the second split are independently 0.1mm-3mm. Attached Figure Description

[0019] In the accompanying drawings, unless otherwise specified, the same reference numerals throughout the various drawings denote the same or similar parts or elements. These drawings are not necessarily drawn to scale. It should be understood that these drawings depict only some embodiments disclosed in this application and should not be construed as limiting the scope of this application.

[0020] Figure 1 This is a schematic diagram of the spherical protrusion structure provided in an embodiment of this application; Figure 2 These are schematic diagrams of turbine blades in some embodiments.

[0021] Figure label: 1: Turbine blade; 2: Spherical protrusion. Detailed Implementation

[0022] The embodiments of this application are described in detail below, examples of which are illustrated in the accompanying drawings. In the drawings, for clarity, the dimensions of layers, regions, and elements, as well as their relative dimensions, may be exaggerated. Throughout, the same or similar reference numerals denote 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 only used to explain this application, and should not be construed as limiting this application. It should be noted that, unless otherwise specified, the embodiments and features in the embodiments of this application can be combined with each other.

[0023] It should be understood that when an element or layer is referred to as "on," "adjacent to," "connected to," or "coupled to" other elements or layers, it may be directly on, adjacent to, connected to, or coupled to other elements or layers, or there may be intervening elements or layers. Conversely, when an element is referred to as "directly on," "directly adjacent to," "directly connected to," or "directly coupled to" other elements or layers, there are no intervening elements or layers. It should be understood that although the terms first, second, third, etc., may be used to describe various elements, components, areas, layers, and / or portions, these elements, components, areas, layers, and / or portions should not be limited by these terms. These terms are only used to distinguish one element, component, area, layer, or portion from another element, component, area, layer, or portion. Therefore, without departing from the teachings of this application, the first element, component, area, layer, or portion discussed below may be referred to as a second element, component, area, layer, or portion. And the discussion of a second element, component, area, layer, or portion does not imply that the first element, component, area, layer, or portion necessarily exists in this application.

[0024] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this application are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such terms can be used interchangeably where appropriate so that the embodiments of this application described herein can be implemented, for example, in orders other than those illustrated or described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover a non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0025] In this application, when numerical intervals (i.e., numerical ranges) are involved, unless otherwise specified, the distribution of selectable numerical values ​​within the numerical interval is considered continuous, and includes the two endpoints of the numerical interval (i.e., the minimum and maximum values), as well as every numerical value between these two endpoints. Unless otherwise specified, when a numerical interval refers only to integers within that numerical interval, it includes the two endpoint integers of the numerical range, as well as every integer between the two endpoints, which is equivalent to directly listing every integer. When multiple numerical ranges are provided to describe features or characteristics, these numerical ranges can be merged. In other words, unless otherwise specified, the numerical ranges disclosed in this application should be understood to include any and all subranges included therein. The "numerical value" in the numerical interval can be any quantitative value, such as a number, percentage, ratio, etc. The term "numerical interval" can be broadly included to include percentage intervals, ratio intervals, proportion intervals, etc.

[0026] This application provides a turbine blade with a V-shaped slit spherical convex structure. (Reference) Figure 1 and 2 Turbine blade 1 is used as a hot-end component of an aero-engine. A heat exchange channel is provided on the turbine blade 1. The heat exchange channel has a wall surface. A spherical protrusion 2 is provided on the wall surface. The spherical protrusion 2 includes a first slit and a second slit. The projection of the center extension line of the first slit in a plane parallel to the flow direction of the fluid and the projection of the center extension line of the second slit in a plane parallel to the flow direction of the fluid form an angle I, which is an acute angle.

[0027] By incorporating slits at specific angles and locations on the surface of the spherical convex surface, the flow characteristics of the cooling medium are utilized. The presence of the slits guides some fluid to penetrate or bypass the convex surface, generating a more complex vortex structure, effectively disrupting the thermal boundary layer, and significantly enhancing heat transfer. Simultaneously, compared to a solid spherical convex surface, this design can, to some extent, guide the flow, avoiding excessively large flow stagnation zones, thereby effectively reducing flow resistance while achieving similar or higher heat transfer intensities. Limiting the included angle Ⅰ between the projections of the first and second slits allows symmetrical and specifically directional turbulence to form on both sides of the convex surface, resulting in a more orderly and efficient flow organization, avoiding the additional losses or localized overheating that may result from asymmetric flow.

[0028] Understandable Figure 1 This is a schematic diagram of the structure of a spherical protrusion according to some embodiments of this application, wherein the included angle I in the spherical protrusion is... Figure 1 It is represented as θ.

[0029] In some embodiments, in a plane parallel to the flow direction M of the fluid, the center extension line of the first slit forms an angle II with the horizontal direction, and the center extension line of the second slit forms an angle III with the horizontal direction, wherein angles II and III are acute angles. By defining the angles (II, III) between the projections of the first and second slits and the flow direction, especially by employing a symmetrical acute angle design, symmetrical and specifically directional turbulence can be formed on both sides of the spherical convexity, resulting in a more orderly and efficient flow organization and avoiding additional losses or local overheating that may be caused by asymmetrical flow.

[0030] Furthermore, the first and second slits are arranged symmetrically with respect to the central vertical line at the apex of the spherical protrusion, and the included angle II is equal to the included angle III. This further enhances the heat exchange effect.

[0031] In some embodiments, the included angle I is an acute angle. This further enhances the heat exchange effect.

[0032] In some embodiments, the included angles II and III are independently 10°-50°, for example, 10°, 12°, 15°, 20°, 22.5°, 30°, 35°, 40°, 45°, 50°, etc. Therefore, if included angles II and III are too large, the increase in pressure loss will exceed the increase in heat transfer performance, resulting in a decrease in overall thermal performance; if they are too small, a significant vortex cannot be formed above the raised trailing edge, leading to poor convective heat transfer between the fluid and the wall, failing to meet the heat transfer requirements of the turbine blades.

[0033] In some embodiments, the included angle I is 1°-89°, such as 1°, 20°, 30°, 45°, 50°, 60°, 75°, 80°, 89°, etc. Therefore, if the included angles II and III are too large, it will lead to excessive pressure loss, and the increase in heat transfer performance will be less than the increase in pressure loss, resulting in a decrease in overall thermal performance (TP). If they are too small, it will prevent the formation of large-scale vortex structures on the trailing edge, reducing heat transfer performance and resulting in poor heat transfer uniformity.

[0034] In some embodiments, the diameter of the spherical protrusion is D, the first slit intersects the diameter of a plane perpendicular to the flow direction of the fluid at a first intersection point, and the radial distance from the first intersection point to the outer surface of the spherical protrusion is S1. The relationship between S1 and D is: 0.1 ≤ S1 / D ≤ 0.4. Therefore, a larger induced vortex structure size and better overall thermal performance are achieved while keeping pressure loss within a reasonable range.

[0035] In some embodiments, the diameter of the spherical protrusion is D, and the second slit intersects the diameter of a plane perpendicular to the flow direction of the fluid at a first intersection point. The radial distance from the first intersection point to the outer surface of the spherical protrusion is S2, and the relationship between S2 and D is: 0.1 ≤ S2 / D ≤ 0.4, for example, 0.1, 0.15, 0.2, 0.25, 0.4, etc. Therefore, the optimal value in my numerical calculations is 0.2. The higher the S2 / D ratio, the larger the scale and strength of the vortex structure at the trailing edge, and the higher the heat transfer performance.

[0036] In some embodiments, the distance between the spherical protrusion and the wall is H, and the diameter of the spherical protrusion is D. The relationship between H and D satisfies: 0.1 ≤ H / D ≤ 0.5, for example, 0.1, 0.2, 0.3, 0.4, 0.5, etc. This approach effectively disrupts the flow boundary layer, inducing a more intense secondary flow, increasing the turbulent kinetic energy of the fluid, and improving convective heat transfer. It also keeps pressure loss within a reasonable range.

[0037] Preferably, the distance between the spherical protrusion and the wall surface is H, the diameter of the spherical protrusion is D, and the relationship between H and D satisfies: 0.1≤H / D≤0.3.

[0038] It is understood that the distance between the spherical protrusion and the wall is H, where H refers to the distance between the highest point on the spherical protrusion and the wall.

[0039] In some embodiments, the arrangement of the spherical protrusions is a macroscopic control method for the design of the turbine blade heat exchange channel. It determines the heat transfer intensity, flow resistance, and temperature uniformity of the channel.

[0040] Optionally, the spherical protrusions are arranged in an array, and in the heat exchange channel, the distance between two adjacent spherical protrusions along the flow direction is 10mm-40mm, such as 10mm, 13mm, 19mm, 24mm, 30mm, 35mm, 40mm, etc.

[0041] Optionally, the spherical protrusions are arranged in an array, and in the heat exchange channel, in the direction perpendicular to the flow direction, the distance between two adjacent spherical protrusions is 10mm-40mm.

[0042] In some embodiments, the wall surface is a rough surface. A rough surface is beneficial for disrupting the flow boundary layer, inducing strong secondary flow, and improving convective heat transfer. A rough surface refers to a wall surface with turbulence-inducing structures.

[0043] In some embodiments, the widths of the first and second slits are independently 0.5mm-3mm, for example, 0.5mm, 1mm, 2mm, 3mm, etc. This improves the heat exchange performance of the structure.

[0044] In some embodiments, the wall surface is a rough surface, and the Nu / Nu0 of the rough surface is 1.758-2.981 in the range of 20,000-100,000 Reynolds number. Within the Reynolds number range of 20,000-100,000, the f / f0 of the rough surface is 3.606-5.289; Within the Reynolds number range of 20,000-100,000, the TP of the rough surface is 1.128-1.835.

[0045] Relative Nusselt Number (Nu / Nu0): The ratio between the numerically calculated Nusselt number of the new structure and the Nusselt number Nu0 of the smooth circular tube, under the same Re. It's a criterion for evaluating the heat transfer performance of the structure; the higher the better. It indicates how many times greater the heat transfer capacity of the new structure is compared to the smooth plane. Here, Nu0 is directly calculated using the Dittus-Boelter empirical correlation, which is used to calculate the Nusselt number of the smooth channel, not a result of numerical calculation. Dittus-Boelter empirical correlation: Nu0 = 0.023Re 0.8 Pr 0.4Here, Pr (Prand number) is a physical property parameter of the fluid.

[0046] Relative friction factor f / f0: Under the same Re, the ratio between the numerically calculated friction factor f of the new structure and the friction factor f0 of the fluid on a smooth surface. It's a criterion for evaluating the structural drag characteristics; the lower the better. Essentially, it represents how many times greater the pressure loss generated by the new structure is compared to that of the smooth surface. Here, f0 is directly calculated using the Blasius empirical correlation, which is used to calculate the friction factor of smooth surfaces, not a result of numerical calculation. Blasius empirical correlation: f0 = 0.316Re -0.25 .

[0047] Overall thermal performance TP: Nu / Nu0 and (f / f0) of the new structure calculated numerically under the same Re. 1 / 3 The ratio of .

[0048] (The ultimate metric for evaluating the performance of an enhanced heat exchange structure. While achieving high heat transfer performance, the drag must not be too high. TP (Total Pressure) should be as high as possible.) In some embodiments, in the extension direction of the first split, the cross-sectional shape of the first split is wedge-shaped, and the opening angle of the wedge is 45°-89°, for example, 45°, 50°, 55°, 60°, 65°, 70°, 75°, 80°, 89°, etc. The cross-sectional shape of the second split is also wedge-shaped, and the opening angle of the wedge is 45°-89°, for example, 45°, 50°, 55°, 60°, 65°, 70°, 75°, 80°, 89°, etc. Figure 1 In this design, both included angles are denoted as α. The advantage of this design is that α guides the fluid to flow laterally (treating the direction of fluid flow through the channel as longitudinal), generating a stronger secondary flow (a fluid flow that deviates from the mainstream direction; a vortex structure is a special type of secondary flow), increasing the turbulent kinetic energy within the channel and enhancing heat transfer capacity. Increasing α further strengthens this effect.

[0049] In some embodiments, the width d of the first split and the second split are each independently 0.1mm-3mm, for example 0.1mm, 0.5mm, mm, 2mm, 3mm, etc.

[0050] Exemplary embodiments according to this application will now be described in more detail with reference to the accompanying drawings. It should be understood that these exemplary embodiments may be implemented in many different forms and should not be construed as being limited to the embodiments set forth herein.

[0051] Example 1 A turbine blade is provided, and a heat exchange channel is provided on the turbine blade. The heat exchange channel has a wall, and a spherical protrusion is provided on the wall. A first slit and a second slit are provided on the spherical protrusion. The projection of the center extension line of the first slit in a plane parallel to the flow direction of the fluid and the projection of the center extension line of the second slit in a plane parallel to the flow direction of the fluid form an angle Ⅰ, and the angle Ⅰ is 45°. The diameter of the spherical protrusion is D. The first slit intersects with the diameter of a plane perpendicular to the flow direction of the fluid at a first intersection point. The radial distance from the first intersection point to the outer surface of the spherical protrusion is S1, and the relationship between Ⅰ and D is: S1 / D = 0.2. The second slit intersects with the diameter of a plane perpendicular to the flow direction of the fluid at a second intersection point. The radial distance from the second intersection point to the outer surface of the spherical protrusion is S2, and the relationship between S2 and D is: S2 / D = 0.2. The angle between the two opposite sidewalls of the first slit is 45°.

[0052] Example 2 A turbine blade is provided, and a heat exchange channel is provided on the turbine blade. The heat exchange channel has a wall, and a spherical protrusion is provided on the wall. A first slit and a second slit are provided on the spherical protrusion. The projection of the center extension line of the first slit in a plane parallel to the flow direction of the fluid and the projection of the center extension line of the second slit in a plane parallel to the flow direction of the fluid form an angle Ⅰ, and the angle Ⅰ is 50°. The diameter of the spherical protrusion is D. The first slit intersects with the diameter of a plane perpendicular to the flow direction of the fluid at a first intersection point. The radial distance from the first intersection point to the outer surface of the spherical protrusion is S1, and the relationship between S1 and D is: S1 / D = 0.25. The second slit intersects with the diameter of a plane perpendicular to the flow direction of the fluid at a second intersection point. The radial distance from the second intersection point to the outer surface of the spherical protrusion is S2, and the relationship between S2 and D is: S2 / D = 0.25. The angle between the two opposite sidewalls of the first slit is 45°.

[0053] Example 3 A turbine blade is provided, and a heat exchange channel is provided on the turbine blade. The heat exchange channel has a wall, and a spherical protrusion is provided on the wall. A first slit and a second slit are provided on the spherical protrusion. The projection of the center extension line of the first slit in a plane parallel to the flow direction of the fluid and the projection of the center extension line of the second slit in a plane parallel to the flow direction of the fluid form an angle Ⅰ, and the angle Ⅰ is 45°. The diameter of the spherical protrusion is D. The first slit intersects with the diameter of a plane perpendicular to the flow direction of the fluid at a first intersection point. The radial distance from the first intersection point to the outer surface of the spherical protrusion is S1, and the relationship between S1 and D is: S1 / D = 0.2. The second slit intersects with the diameter of a plane perpendicular to the flow direction of the fluid at a second intersection point. The radial distance from the second intersection point to the outer surface of the spherical protrusion is S2, and the relationship between S2 and D is: S2 / D = 0.2. The angle between the two opposite sidewalls of the first slit is 75˚.

[0054] Comparative Example 1 A turbine blade is provided, and a heat exchange channel is provided on the turbine blade. The heat exchange channel has a wall, and a spherical protrusion is provided on the wall. A first slit and a second slit are provided on the spherical protrusion. The projection of the center extension line of the first slit in a plane parallel to the flow direction of the fluid and the projection of the center extension line of the second slit in a plane parallel to the flow direction of the fluid form an angle Ⅰ, and the angle Ⅰ is 0°. The diameter of the spherical protrusion is D. The first slit intersects with the diameter of a plane perpendicular to the flow direction of the fluid at a first intersection point. The radial distance from the first intersection point to the outer surface of the spherical protrusion is S1, and the relationship between Ⅰ and D is: S1 / D = 0.2. The second slit intersects with the diameter of a plane perpendicular to the flow direction of the fluid at a second intersection point. The radial distance from the second intersection point to the outer surface of the spherical protrusion is S2, and the relationship between S2 and D is: S2 / D = 0.2. The angle between the two opposite sidewalls of the first slit is 45°.

[0055] Test case Heat transfer tests were conducted on the turbine blades of Examples 1-3 and Comparative Example 1: Nu / Nu0, f / f0, and TP were determined using numerical simulation.

[0056] Mesh setup: Local mesh refinement was performed on the structured, rough wall surface, and 15 boundary layer meshes were set on the wall surface through which the fluid flows. The height of the first layer was 0.01 mm to ensure the y-value near the wall surface. + <1. Example 1 has approximately 3.54 million grid cells, and grid independence was verified.

[0057] Numerical simulation settings: The channel inlet is a velocity inlet with an inlet temperature of 293 K. The inlet velocity is determined by the Reynolds number, channel cross-sectional dimensions, and physical properties. The outlet is a pressure outlet with a gauge pressure of 0 Pa. The rough walls of the arrangement are designed as isothermal walls with a temperature of 318 K. The two sides of the channel are translational periodic boundaries. The remaining walls are non-slip, adiabatic walls. The working fluid in the channel is air. Since the temperature difference between the inlet and outlet is less than 5 K, the working fluid can be considered an incompressible fluid with constant physical properties. The Standard k-ω turbulence model is used.

[0058] The Simple algorithm was selected as the solver to couple the pressure and velocity solutions. A second-order scheme was used for the pressure solution, and both turbulent kinetic energy and energy were discretized using a second-order upwind scheme. When the residual value of the energy equation is <10... -8 The residuals of the remaining equations are <10. -5 This can be considered as computational convergence.

[0059] Table 1 As shown in the table above, the turbine blades of Examples 1-3 exhibit better heat transfer performance than those of Comparative Example 1. This is because the turbine blades of this application utilize the flow characteristics of the cooling medium by setting slits at specific angles and positions on the spherical convex surface. The presence of the slits guides some fluid to penetrate or bypass the spherical convex, generating a more complex vortex structure, effectively disrupting the thermal boundary layer, and significantly enhancing heat transfer. Simultaneously, compared to a solid spherical convex, this design can, to a certain extent, guide the flow, avoiding excessively large flow stagnation zones, thereby effectively reducing flow resistance while achieving similar or higher heat transfer intensity. Limiting the included angle I between the projections of the first and second slits allows symmetrical and specifically directional turbulence to form on both sides of the spherical convex, resulting in a more orderly and efficient flow organization, avoiding additional losses or localized overheating that may result from asymmetric flow.

[0060] It should also be noted that the terms "some embodiments," "other embodiments," and "embodiments" used in this application refer to specific features, structures, or characteristics described in connection with those embodiments, which are included in at least one embodiment described in the general description of this application. The appearance of the same expression in multiple places in the specification does not necessarily refer to the same embodiment. Furthermore, when a specific feature, structure, or characteristic is described in connection with any embodiment, the intention is to suggest that implementing such a feature, structure, or characteristic in conjunction with other embodiments also falls within the scope of this application.

[0061] In the above embodiments, the descriptions of each embodiment have different focuses. For parts not described in detail in a certain embodiment, please refer to the relevant descriptions in other embodiments.

[0062] It should also be noted that the above are merely preferred embodiments of this application and do not limit the scope of patent protection of this application. Any equivalent structural or procedural changes made using the content of this application’s specification and drawings, or direct or indirect applications in other related technical fields, are similarly included within the scope of patent protection of this application.

Claims

1. A turbine blade with a V-shaped slit spherical protrusion structure, characterized in that, The turbine blade is used as a hot-end component of an aero-engine. The turbine blade is provided with a heat exchange channel, the heat exchange channel has a wall, and a spherical protrusion is provided on the wall. The spherical protrusion includes a first slit and a second slit. The projection of the center extension line of the first slit in a plane parallel to the flow direction of the fluid and the projection of the center extension line of the second slit in a plane parallel to the flow direction of the fluid form an angle I, and the angle I is an acute angle.

2. The turbine blade according to claim 1, characterized in that, In a plane parallel to the flow direction of the fluid, the center extension line of the first split forms an angle II with the horizontal direction, and the center extension line of the second split forms an angle III with the horizontal direction, wherein angle II and angle III are acute angles.

3. The turbine blade according to claim 2, characterized in that, The first and second cleavages are arranged symmetrically with respect to the central vertical line at the apex of the spherical protrusion, and the included angle II is equal to the included angle III.

4. The turbine blade according to claim 3, characterized in that, The included angle II and the included angle III are each independently between 10° and 50°; And / or, the included angle I is 1°-89°.

5. The turbine blade according to claim 1, characterized in that, The diameter of the spherical protrusion is D. The first slit intersects the diameter of a plane perpendicular to the flow direction of the fluid at the first intersection point. The radial distance from the first intersection point to the outer surface of the spherical protrusion is S1. The relationship between S1 and D is: 0.1≦S1 / D≦0.

4. The diameter of the spherical protrusion is D. The second slit intersects the diameter of a plane perpendicular to the flow direction of the fluid at a second intersection point. The radial distance from the second intersection point to the outer surface of the spherical protrusion is S2. The relationship between S2 and D is: 0.1≦S2 / D≦0.

4.

6. The turbine blade according to claim 1, characterized in that, The distance between the spherical protrusion and the wall is H, and the diameter of the spherical protrusion is D. The relationship between H and D satisfies: 0.1≤H / D≤0.

5.

7. The turbine blade according to claim 1, characterized in that, The wall surface is a rough surface, and the Nu / Nu0 ratio of the rough surface is 1.758-2.981 in the range of 20,000-100,000 Reynolds number. Within the Reynolds number range of 20,000-100,000, the f / f0 of the rough surface is 3.606-5.289; Within the Reynolds number range of 20,000-100,000, the TP of the rough surface is 1.128-1.

835.

8. The turbine blade according to claim 1, characterized in that, The spherical protrusions are arranged in an array, and in the heat exchange channel, the distance between two adjacent spherical protrusions along the flow direction is 10mm-40mm. The spherical protrusions are arranged in an array. In the heat exchange channel, in the direction perpendicular to the flow direction, the distance between two adjacent spherical protrusions is 10mm-40mm.

9. The turbine blade according to claim 1, characterized in that, The cross-sectional shape of the first split is wedge-shaped, and the opening angle of the wedge is 45°-89°; The cross-sectional shape of the second split is wedge-shaped, and the opening angle of the wedge is 45°-89°.

10. The turbine blade according to claim 1, characterized in that, The widths of the first and second splits are independently 0.1mm-3mm.

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