Blade internal cavity micro cooling enhancement structure suitable for additive manufacturing and design method

Abstract

This application relates to a micro-cooling efficiency enhancement structure and design method for the internal cavity of blades suitable for additive manufacturing. It includes: a micro-turbulence column array, composed of multiple integrally formed columnar turbulence units, each with a diameter of 0.3 mm to 2.0 mm, which can be arranged individually or stacked; at least one guide rib, integrally set in the airflow deflection zone within the cooling cavity, with a cross-section of square, elliptical, teardrop, airfoil, or tapered; the micro-turbulence column array is positioned downstream of the guide rib along the cooling airflow direction. Hotspot regions are identified through thermal-fluid coupling simulation. With the goal of maximizing heat transfer intensity and minimizing pressure loss, topology optimization is performed on the layout parameters of the micro-turbulence column array and the profile parameters of the guide rib to achieve an optimized balance and determine the final structural parameters. This solves the problems of insufficient heat transfer and excessive pressure loss in the high-temperature region of the blade trailing edge caused by the inability of traditional casting processes to form complex sub-millimeter-scale internal cavity structures.

Description

Technical Field

[0001] This application relates to the field of aero-engine turbine design technology, and in particular to a micro-cooling efficiency enhancement structure and design method for blade internal cavity suitable for additive manufacturing. Background Technology

[0002] Turbine guide vanes are core components of the hot-end parts of aero-engines, operating in extremely harsh environments. The trailing edge region of the blade is directly subjected to the scouring of high-temperature exhaust gases, with local temperatures exceeding 950°C, far exceeding the allowable range of conventional high-temperature alloy materials. To ensure the structural integrity and service life of the blade under such conditions, forced convection heat transfer must be achieved by introducing cooling gas through internal cooling channels.

[0003] Traditional turbine guide vanes often employ investment casting to form their internal cooling structures. However, due to limitations in wax pattern making and core preparation techniques, this process has inherent limitations in the fine design of cooling channels.

[0004] First, traditional casting processes struggle to produce sub-millimeter-scale structural features. Constrained by core strength and demolding feasibility, the diameter of flow-disrupting structures (such as columnar ribs or flow-disrupting columns) within the flow channels is typically no less than 1 mm, and the flow-guiding structures in the wall thickness direction are similarly limited. This dimensional constraint prevents the design of cooling structures from fully meeting the heat dissipation requirements of localized hot spots, thus limiting the potential for enhanced heat transfer.

[0005] Secondly, traditional casting processes are difficult and costly to produce complex profiles. Casting cores typically use uniform cross-sections or simple transitions, making it difficult to achieve aerodynamically optimized profiles (such as tapered or airfoil sections) in the flow channel. In actual products, the guide structures at flow channel bends are often simple baffles, or even omitted entirely due to process limitations. When cooling gas flows through the bend area of ​​the flow channel, the lack of effective guidance easily leads to flow separation and vortex zones, resulting in significant pressure loss and reducing the effective utilization rate of the cooling gas and downstream heat exchange capacity.

[0006] It should also be noted that traditional uniformly distributed turbulence structures struggle to balance heat transfer intensity and flow resistance. In conventional designs, to simplify the process flow, turbulence columns are typically arranged in a uniform array with equal spacing and diameter. This layout cannot achieve differentiated configurations for the actual heat transfer requirements of different sections of the flow channel: if the overall turbulence density is increased to enhance heat transfer, the flow resistance across the entire channel increases simultaneously, placing higher demands on the supply gas pressure; if the density is reduced to control pressure loss, the problem of insufficient heat transfer in localized high-temperature areas remains unresolved. The trade-off between heat transfer efficiency and flow resistance is difficult to achieve an optimal balance under traditional uniform layouts.

[0007] In summary, traditional cooling channel designs based on casting processes are constrained by dimensional accuracy, profile complexity, and layout flexibility, making it difficult to meet the increasingly demanding cooling requirements of turbine guide vanes, especially in the high-temperature trailing edge region. With the maturity of Selective Laser Melting (SLM) additive manufacturing technology, its high precision and design freedom provide the technological prerequisite for overcoming these limitations. However, how to utilize the advantages of this process to design microscopic cooling structures that combine high heat transfer efficiency with low flow loss remains a pressing problem in this field. Summary of the Invention

[0008] This application provides a micro-cooling efficiency enhancement structure and design method for the inner cavity of blades suitable for additive manufacturing, which solves the problems that traditional casting processes cannot achieve sub-millimeter-level fine cooling structures in the inner cavity of blades, resulting in insufficient heat transfer in the high-temperature region of the trailing edge and excessive airflow pressure loss. By using a micro-turbulence column array (0.3mm to 2mm in diameter) integrally formed by SLM additive manufacturing, the local airflow turbulence is enhanced to strengthen convective heat transfer. At the same time, airfoil or tapered guide ribs guide the airflow to smoothly change direction to reduce pressure loss. The two work together to improve the cooling efficiency of the trailing edge region by more than 40% and reduce the pressure loss by more than 15%, effectively controlling the maximum temperature of the blade within the allowable range of the material.

[0009] The first aspect of this application provides a micro-cooling enhancement structure for the inner cavity of a blade suitable for additive manufacturing, comprising:

[0010] The micro-turbulence column array consists of multiple columnar turbulence units integrally formed with the inner wall of the cooling cavity, with the diameter of a single columnar turbulence unit ranging from 0.3 mm to 2.0 mm;

[0011] At least one guide rib is integrally disposed in the airflow deflection zone within the cooling chamber;

[0012] The guide rib extends along the cooling airflow direction with an arc transition, and the micro-turbulence column array is located downstream of the guide rib along the cooling airflow direction.

[0013] Optionally, in some embodiments, the micro-spoiler column array is non-uniformly distributed, with the spoiler column distribution density in areas with high cooling demand being greater than the distribution density in areas with low cooling demand.

[0014] Optionally, in some embodiments, the cross-sectional shape of the columnar turbulence unit is one of the following: circular, horseshoe-shaped, spindle-shaped, semi-spindle-shaped, maple leaf-shaped, or fan-shaped.

[0015] Optionally, in some embodiments, the columnar turbulence unit is arranged as a single unit in the height direction perpendicular to the cooling chamber wall, or multiple units are stacked along the height direction.

[0016] Optionally, in some embodiments, the angle between the central axis of the columnar turbulence unit and the direction of cooling gas flow is 30° to 150°.

[0017] Optionally, in some embodiments, the ratio P / d of the spacing P between adjacent columnar turbulence units to the characteristic diameter d of the columnar turbulence unit in the micro-turbulence column array ranges from 2.0 to 5.0.

[0018] Optionally, in some embodiments, the ratio d / H of the diameter d of the columnar baffle unit to the height H of the columnar baffle unit ranges from 0.2 to 1.0.

[0019] Optionally, in some embodiments, the wall thickness of the guide rib is 0.2 mm to 3.0 mm.

[0020] Optionally, in some embodiments, the guide ribs are arranged in the direction of the flow line.

[0021] Optionally, in some embodiments, the cross-sectional shape of the guide rib is one of square, elliptical, or teardrop shape.

[0022] Optionally, in some embodiments, the angle between the extending direction of the guide rib and the flow channel normal plane corresponding to the airflow turning zone is 30° to 150°.

[0023] Optionally, in some embodiments, the inner wall surface of the cooling cavity also has a microtexture, which is integrally formed with the inner wall surface and has a surface roughness Ra of 3.2 μm to 6.5 μm.

[0024] Optionally, in some embodiments, the cooling cavity, the micro-turbulence column array, and the guide ribs are integrally formed as a single structure using a laser selective melting (SLM) process.

[0025] Optionally, in some embodiments, the blade is a turbine guide vane, and the airflow deflection zone is the inlet of the cooling chamber or a bend inside the chamber.

[0026] A second aspect of this application provides a design method for a micro-cooling enhancement structure for the inner cavity of a blade suitable for additive manufacturing. The method is used to design the structure as described in any of the preceding embodiments, and includes the following steps:

[0027] Perform thermal-fluid coupling simulation on components with internal cavities to determine the temperature field and hot spot distribution areas;

[0028] Within the cooling cavity section corresponding to the hotspot distribution area, a preliminary array of micro-turbulence columns and guide ribs are arranged;

[0029] With the goal of maximizing heat transfer intensity and minimizing pressure loss, the layout parameters of the micro-turbulence column array and the profile parameters of the guide ribs are optimized by topology to determine the final structural parameters.

[0030] Optionally, in some embodiments, the topology optimization step includes:

[0031] The cross-sectional shape, spacing, radius of curvature, and wall thickness of the guide ribs are iterated to obtain a profile that minimizes the pressure loss of the airflow in the airflow turning zone.

[0032] Furthermore, the characteristic diameter of the columnar turbulence units of the micro-turbulence column array, the spacing between adjacent columnar turbulence units, the distribution density gradient, and the number of stacked units are optimized in a multi-objective manner to achieve a balance between heat transfer intensity and flow resistance.

[0033] A third aspect of this application provides an electronic device, including: a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the program to implement the design method for a micro-cooling enhancement structure for blade cavities suitable for additive manufacturing as described in the above embodiments.

[0034] A fourth aspect of this application provides a computer program product having a computer program stored thereon, which is executed by a processor to implement the design method for a micro-cooling enhancement structure for blade cavities suitable for additive manufacturing as described in the above embodiments.

[0035] The beneficial effects of the embodiments of this application are as follows:

[0036] (1) The micro-cooling enhancement structure of this application significantly reduces the operating temperature of the trailing edge region of the blade, so that the maximum temperature of the blade is effectively controlled within the allowable operating range of the high-temperature alloy material.

[0037] (2) This application suppresses flow separation in the turning region of the airflow by using airfoil / recessed guide ribs, reducing pressure loss in the turning region by more than 15% compared to traditional structures; at the same time, it enhances near-wall turbulence at both macro and micro scales by using micro-turbulence column arrays and micro-textures on the inner wall, improving the overall heat transfer efficiency by more than 40% compared to traditional designs. The synergy between the above-mentioned loss reduction and efficiency improvement solves the technical contradiction in traditional cooling designs where heat transfer enhancement and flow resistance control are difficult to balance.

[0038] (3) This application utilizes the SLM additive manufacturing process to realize sub-millimeter-level cooling enhancement features that cannot be processed by traditional investment casting, including micro-turbulence units with diameters of 0.3 mm to 2.0 mm, airfoil / recessed guide ribs with wall thicknesses of 0.2 mm to 3.0 mm, and inner wall micro-texture structures with surface roughness Ra of 3.2 μm to 6.5 μm, providing a process prerequisite for the refined design of cooling structures.

[0039] (4) The micro-turbulence column array, guide ribs and cooling cavity inner wall of this application are integrally formed by SLM process, which does not require subsequent assembly, welding or mechanical connection, reduces the connection interface, improves structural integrity and reduces the risk of failure due to connection failure under high temperature and high pressure alternating conditions.

[0040] Additional aspects and advantages of this application will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of this application. Attached Figure Description

[0041] The above and / or additional aspects and advantages of this application will become apparent and readily understood from the following description of the embodiments taken in conjunction with the accompanying drawings, wherein:

[0042] Figure 1 This is an overall cross-sectional view of a turbine guide vane according to a specific embodiment of this application;

[0043] Figure 2 This is a cross-sectional schematic diagram of a micro-cooling enhancement structure for the inner cavity of a blade suitable for additive manufacturing, provided according to an embodiment of this application.

[0044] Figure 3 This is a schematic diagram of the arrangement of a micro-turbulence column array according to a specific embodiment of this application;

[0045] Figure 4 This is a flowchart illustrating a design method for a micro-cooling enhancement structure for the inner cavity of a blade suitable for additive manufacturing, according to an embodiment of this application.

[0046] Figure 5 This is a schematic diagram of the original temperature field of a turbine guide vane before optimization according to a specific embodiment of this application;

[0047] Figure 6 This is a schematic diagram of the temperature field of an optimized turbine guide vane according to a specific embodiment of this application;

[0048] Figure 7 This is a block diagram of an electronic device provided according to an embodiment of this application.

[0049] Explanation of reference numerals in the attached figures:

[0050] 100 - Turbine guide vane body, 101 - Leading edge cooling chamber, 102 - Middle chord cooling chamber, 103 - Trailing edge cooling chamber;

[0051] 10-First guide rib, 11-Second guide rib, 12-Main and auxiliary cavity partition plate, 20-Miniature turbulence column array, 21-turbulence rib, 30-Cooling cavity, 41-First air inlet, 42-Second air inlet;

[0052] 701 - Memory, 702 - Processor, 703 - Communication interface. Detailed Implementation

[0053] The embodiments of this application are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application.

[0054] This application provides a micro-cooling enhancement structure for the inner cavity of blades suitable for additive manufacturing. This structure can be integrated into the cooling cavity of various high-temperature components, and is particularly suitable for the internal cooling channel of turbine guide vanes in aero-engines.

[0055] Figure 1 A cross-sectional schematic diagram of a micro-cooling enhancement structure for the inner cavity of a blade suitable for additive manufacturing, provided in a specific embodiment of this application, is shown below. Figure 1 As shown, the turbine guide vane body 100 is internally divided into multiple independent (or controlled connected through specific through holes) regions by longitudinally arranged internal baffles. The main cooling chamber includes a leading-edge cooling chamber 101 and a mid-chord cooling chamber 102, occupying the region from the leading edge to the mid-chord of the blade. The trailing-edge cooling chamber 103 (also referred to as a local cooling chamber or auxiliary cooling chamber) is located entirely in the narrow region of the blade's trailing edge. This physical isolation ensures that each chamber can receive differentiated cooling pressure and flow rate distribution according to its corresponding external heat load.

[0056] The trailing edge cooling chamber 103 has an independent air supply source from the main cooling chamber. The cooling gas does not undergo heat exchange in the leading edge or mid-chord region, but is injected directly from the inlet. This design ensures that the gas delivered to the trailing edge region maintains a low initial temperature, avoiding the decrease in trailing edge cooling efficiency caused by preheating of the airflow in the mid-chord region in conventional flow paths.

[0057] The trailing edge cooling chamber 103 is located in the high-temperature region of the trailing edge of the blade. This region is directly subjected to the scouring of high-temperature combustion gases during operation, and the local temperature can reach 950°C. It is the part of the blade with the most stringent cooling requirements, and is also the core arrangement area of ​​the micro-cooling efficiency enhancement structure of this application.

[0058] Figure 2 A cross-sectional schematic diagram of a micro-cooling efficiency enhancement structure for the inner cavity of a blade suitable for additive manufacturing, provided in an embodiment of this application, is shown below. Figure 2As shown, the miniature cooling enhancement structure of this application embodiment mainly includes: a first guide rib 10, a second guide rib 11, and a miniature baffle array 20. The first air inlet 41 and the second air inlet 42 respectively introduce the source of cooling airflow: the first air inlet 41 is configured to supply air to the main cooling chambers 101 and 102, while the second air inlet 42 is configured to supply air to an independent cold source, which has sufficient dynamic pressure energy for the cold airflow, thereby providing power support for the subsequent passage through the miniature baffle array 20.

[0059] Figure 2 The white dashed arrows indicate the direction of airflow. For example... Figure 2 As shown, this application employs a multi-stage guiding strategy. The first guide rib 10 is located in the core area of ​​the turning zone, serving a rectifying function. Its profile precisely matches the streamline after the turn. The second guide rib 11 is located on the downstream side of the airflow turning zone, guiding the airflow from the main cooling chamber to turn back to the left, guiding the cold airflow smoothly into the narrow trailing edge channel. Through the coordinated guidance of the second guide rib 11 and the first guide rib 10, the impact loss and vortex dissipation that are prone to occur at the confluence of multiple airflows are effectively suppressed.

[0060] The following is combined Figure 2 The arrows in the diagram illustrate the airflow direction, explaining the flow path of the cooling gas in this embodiment.

[0061] like Figure 2 As shown, the cooling gas enters the cooling chamber 30 in two streams. The first stream of cooling gas enters through the first inlet 41, originating from the main cooling chambers 101 and 102. Upon passing the second guide rib 11, it is guided and deflected, then flows along the profile of the first guide rib 10. The second stream of cooling gas enters through the second inlet 42, supplying an independent cooling source. This stream is smoothly guided into the exhaust section at the trailing edge via the streamlined wall of the main / sub-chamber dividing plate 12. After merging in the deflection zone, the two streams of cooling gas form a composite cooling airflow, which continues to flow along the flow path of the cooling chamber 30 under the guidance of the first guide rib 10.

[0062] As the composite cooling airflow flows towards the trailing edge, it is disturbed by the turbulence ribs 21, resulting in localized turbulence on both the pressure and suction sides, further enhancing the turbulence intensity. The cooling gas, after being pre-disturbed by the turbulence ribs 21, then enters the exhaust section region where the micro-turbulence column array 20 is located. Under the multi-channel segmentation and strong disturbance of the micro-turbulence column array 20, it completes high-intensity convective heat transfer and is finally discharged from the trailing edge of the blade.

[0063] In this application, the first guide rib 10 is set at the turn-off point of the flow channel. Its cross-section adopts an airfoil or tapered aerodynamic profile, which can guide the cooling gas to smoothly turn along its profile and effectively suppress flow separation and vortex generation.

[0064] The cooling gas from the second air inlet 42 is rectified by the main and secondary cavity partition plate 12 and flows smoothly along the cavity flow direction (or towards the trailing edge of the blade), entering the region where the micro-turbulence column array 20 is located downstream of the turbulence rib 21. The turbulence rib 21 is located downstream of the main and secondary cavity partition plate 12 to perform secondary turbulence on the rectified cooling gas, further enhancing the turbulence of the airflow before entering the micro-turbulence column array 20. In this embodiment, the main and secondary cavity partition plate 12 is streamlined, and its wall surface is aligned with the flow direction of the cooling gas in the cooling cavity 30, used to smoothly guide the cooling airflow from the second air inlet 42 into the trailing edge exhaust section.

[0065] The micro-turbulence column array 20 is composed of multiple integrated columnar turbulence units. When the cooling gas flows through the array, the airflow is divided and disturbed by multiple channels, and the turbulence is significantly enhanced, thereby achieving efficient convective heat transfer in the near-wall region.

[0066] Furthermore, the micro-turbulence column array 20 is disposed downstream of the turbulence rib 21. In this embodiment, the turbulence rib 21 is disposed on the inner wall of the pressure side and the inner wall of the suction side of the cooling chamber 30, respectively, to pre-disturb the cooling gas before it enters the micro-turbulence column array 20, so as to improve the local heat transfer efficiency and enhance the airflow turbulence.

[0067] It should be clarified that the large, transversely penetrating columnar structure within the cooling cavity 30 is a macroscopic reinforcing rib of the blade (as shown in the background in the figure), while the characteristic dimension (diameter d) of the micro-turbulence column array 20 of this application is much smaller than that of the macroscopic reinforcing rib. This sub-millimeter-scale microstructure array is integrated within the gap channels between the reinforcing ribs, thereby enhancing the convective heat transfer intensity of the wall surface by inducing high-frequency micro-turbulence within the confined space.

[0068] It should be noted that, in this embodiment of the application, the first guide rib 10, the second guide rib 11, the main and secondary cavity partition plate 12, the turbulence rib 21, the micro-turbulence column array 20, and the inner wall of the cooling cavity 30 are integrally formed by laser selective melting (SLM) process. The first guide rib 10, the second guide rib 11, and the columnar turbulence column unit penetrate the inner wall of the cooling cavity along the height direction of the cooling cavity, passing through the inner wall of the pressure side and the suction side of the cooling cavity.

[0069] The first guide rib 10 and the second guide rib 11 in this embodiment are core components for achieving efficient airflow deflection. Their geometric profiles and wall thickness distributions have been aerodynamically optimized to achieve the lowest flow loss within a limited space. The first guide rib 10 and the second guide rib 11 extend from the pressure sidewall to the suction sidewall within the cooling cavity 30, traversing the entire height of the cavity.

[0070] Specifically, the cross-section of the guide rib is composed of an airfoil curve with aerodynamically optimized characteristics. This airfoil profile features a smooth leading edge and a gradually thinning trailing edge: in the leading edge region facing the incoming flow, the radius of curvature is large, exhibiting a smooth transition to conform to the incoming flow direction and reduce inlet impact loss; along the airflow turning path, the profile gradually narrows, and the radius of curvature decreases accordingly, ultimately forming a tapering tail profile at the trailing end. This airfoil structure with a smooth leading edge and a tapering trailing end in this application results in the overall cross-section of the guide rib exhibiting a geometric feature of smooth tapering from the inlet end to the outlet end.

[0071] Furthermore, the wall thickness of the guide rib exhibits a smooth, gradually decreasing gradient along the airflow turning path. In this embodiment, the wall thickness of the guide rib at the inlet end near the air inlet is preferably 0.6 mm to ensure structural rigidity under the impact of high-pressure cooling airflow; along the airflow turning direction, the plate thickness gradually decreases in a continuously decreasing manner, reducing to 0.2 mm at the outlet end. Preferably, the wall thickness of the guide rib can be adjusted within the range of 0.2 mm to 3 mm according to specific operating conditions to adapt to the geometric constraints and airflow parameters of different cooling chambers. Those skilled in the art can set it according to actual operating conditions, and no specific limitation is made here.

[0072] It should be noted that the aforementioned non-uniform thickness ultrathin irregular structure, namely the guide rib that simultaneously possesses an airfoil curved surface shape and a gradually decreasing wall thickness, is achieved through the integrated forming capability of selective laser melting (SLM) additive manufacturing technology. Traditional investment casting processes are limited by the feasibility of core preparation and demolding, making it difficult to process such complex curved thin-walled parts with sub-millimeter-level variable cross-sections. This application fully utilizes the design freedom of the SLM process, enabling the guide rib and the cavity wall of the cooling cavity 30 to be integrally formed without subsequent assembly or welding, thus achieving complex geometry while ensuring the integrity and reliability of the structure.

[0073] The first guide rib 10 and the second guide rib 11 are disposed in the airflow turning zone within the cooling chamber 30. The airflow turning zone includes the inlet of the cooling chamber 30 or the reversal point inside the chamber. The first guide rib 10 and the second guide rib 11 are integrally disposed at the location where the cross-sectional shape and / or direction of the flow channel changes abruptly. In conventional structures without guide ribs, when cooling gas flows through such sharp turning areas, due to flow inertia, the gas cannot tightly adhere to the wall surface, easily forming a large-scale flow separation zone on the inside of the bend, accompanied by strong vortex motion, resulting in significant total pressure loss and weakening the kinetic energy of the airflow entering the downstream region.

[0074] In this application, the radii of curvature of the first guide rib 10 and the main-secondary cavity partition plate 12 are precisely matched with the local streamlines of the airflow turning zone. Specifically, the airfoil profiles of the first guide rib 10 and the main-secondary cavity partition plate 12 are designed inversely based on the flow characteristics of this region, so that their wall profiles are basically consistent with the streamline trajectories of theoretical non-separated flow. The airfoil profiles of the first guide rib 10 and the main-secondary cavity partition plate 12 are the optimal profiles obtained based on a multi-objective topology optimization algorithm to minimize the local total pressure loss in the airflow turning zone. After entering through the inlets 41 and 42, the cooling airflow is guided by the airfoil profile and flows smoothly along the profiles of the first guide rib 10 and the main-secondary cavity partition plate 12, effectively suppressing the airflow separation phenomenon and the generation of large-scale vortices that are prone to occur in the turning zone. During this process, the tapering wall thickness of the first guide rib 10 and the main-secondary cavity partition plate 12 further conforms to the acceleration trend of the airflow during the turning process, reducing the frictional resistance of the wall surface to the airflow.

[0075] Through the synergistic effect of suppressing separation and reducing eddy current losses, the first guide rib 10 and the main-sub-cavity partition plate 12 significantly reduce the pressure loss of cooling gas flowing through the turning zone. Simulation verification shows that compared with traditional structures without guide ribs or only with equal-thickness baffles, the airfoil-recessed first guide rib 10 and main-sub-cavity partition plate 12 of this application can reduce the pressure loss in the turning zone by more than 15%. Furthermore, due to the effective control of pressure loss, the cooling gas can enter the downstream micro-turbulence column array 20 region with higher dynamic pressure energy and flow velocity, providing a sufficient power source for subsequent high-intensity convective heat transfer. This application achieves quantitative minimization of pressure loss through profile optimization. At the same time, the smooth and high-speed airflow can effectively scour the downstream wall surface, further disrupting the thermal boundary layer, thereby synergistically improving the overall heat transfer coefficient in subsequent stages.

[0076] Optionally, the guide ribs in this embodiment can be replaced with a flow-guiding fin array to achieve a similar function.

[0077] In this application, the micro-turbulence column array 20 and the turbulence ribs 21 are core heat transfer enhancement components arranged downstream of the main and secondary cavity partition plate 12. The composite cooling airflow, after multi-stage guiding and rectification, enters the array region with high dynamic pressure energy, where it completes high-intensity convective heat transfer to the trailing edge wall of the blade. The micro-turbulence column array 20 consists of multiple columnar turbulence units integrally formed with the inner wall of the cooling cavity 30. Each columnar turbulence unit extends from the inner wall of the pressure side to the inner wall of the suction side of the cooling cavity 30, penetrating the entire height of the inner cavity. The spatial arrangement of each turbulence unit follows a geometric law determined by topology optimization.

[0078] To accurately describe the spatial topology of the micro-turbulence column array 20, the following is combined with... Figure 3 The top view shown defines and explains the key geometric parameters involved in this application. Figure 3The planar layout of the micro-turbulence column array 20 in the exhaust section region of the cooling chamber 30 is shown from a top-down perspective. Arrows in the figure indicate the main direction of the cooling gas passing through the array.

[0079] like Figure 3 As shown, each spoiler column unit in the micro spoiler column array 20 is a cylindrical structure with a circular cross-section. The cross-sectional diameter of a single columnar spoiler unit is defined as the spoiler column diameter d. In this embodiment, this diameter is preferably 0.8 mm.

[0080] Regarding the planar arrangement of the array, this application defines the following parameters: In the direction perpendicular to the mainstream cooling gas (i.e., the transverse direction), the distance between the center lines of two adjacent baffle columns is defined as the transverse spacing (pitch) P, which is a key parameter that determines the flow channel opening ratio and flow capacity; In the direction parallel to the mainstream cooling gas (i.e., the longitudinal direction), the distance between the center lines of two adjacent rows of baffle columns is defined as the longitudinal row spacing S.

[0081] In this embodiment, the micro-spoiler column array 20 adopts an interlaced (diamond-shaped) array arrangement, that is, adjacent rows of spoiler columns are staggered by half a pitch in the lateral direction. To fully define this interlaced layout, Figure 3 The following parameters are further defined: the distance between the centers of two diagonally adjacent spoiler columns is defined as the diagonal spacing X; the offset used to quantify the degree of lateral stagger between two adjacent rows is defined as the lateral offset (base distance) B. The above staggered arrangement forces the cooling gas to travel along a detour when flowing through the array, which, compared with the straight-line layout, can achieve a longer effective contact path and a stronger airflow disturbance effect under the same pitch conditions.

[0082] To achieve an engineerable spatial layout and to accommodate geometric scaling requirements at different blade scales, the embodiments of this application define the aforementioned geometric parameters in the form of dimensionless proportional relationships. These dimensionless proportions are the core design criteria established by this application after multi-objective topology optimization.

[0083] In terms of planar topology, the ratio P / d of the lateral spacing P to the diameter d of the baffle columns is preferably 2.3. Preferably, this ratio can be adjusted within the range of 2.0 to 5.0 according to the specific geometry of the cooling cavity and the cooling requirements. The ratio S / d of the longitudinal spacing S to the diameter d of the baffle columns is preferably 2.3.

[0084] It should be noted that the selection of the above-mentioned P / d to S / d ratio range takes into account the following two requirements: First, sufficient flow cross-section needs to be maintained between adjacent turbulence columns to avoid a sharp increase in flow resistance due to excessive blockage effect, ensuring that the cooling gas can pass through the array area with a reasonable pressure loss; second, the spacing should not be too large, otherwise the interference and mixing effect of the turbulence columns on the airflow will be significantly weakened, making it impossible to establish a fully developed turbulent state in the near-wall region, and the heat transfer enhancement effect will be greatly reduced. The P / d range of 2.0 to 5.0 established in the embodiments of this application is an optimized balance achieved between the two contradictory objectives of heat transfer intensity and flow resistance.

[0085] In terms of three-dimensional morphology, the angle between the extending directions of the first guide rib 10 and the second guide rib 11 and the flow channel normal plane corresponding to the airflow turning zone is 30° to 150°.

[0086] In terms of three-dimensional morphology, there is an optimized proportional relationship between the diameter d of the columnar baffle unit and its height H (i.e., the inner cavity height of the cooling cavity 30 in the exhaust section region). In the embodiments of this application, the ratio d / H of the diameter d to the height H is preferably 0.3. Preferably, this ratio can be adjusted in the range of 0.2 to 1.0.

[0087] The aforementioned d / H ratio range has clear engineering significance. Specifically, when the d / H value is too small (i.e., the turbulence column is too slender), the slender column structure is prone to warping deformation due to thermal stress during the SLM molding process, and the difficulty of removing powder in narrow gaps increases. Simultaneously, the slender turbulence column may suffer from insufficient structural strength under the continuous impact of high-velocity cooling gas. Conversely, when the d / H value is too large (i.e., the turbulence column tends to be short and thick), its segmentation and disturbance effect on the flow channel cross-section weakens, and the airflow mainly flows around both sides of the column when passing through the array. The range of the wake turbulence zone generated downstream of the column shrinks, and the heat transfer enhancement capacity decreases accordingly. Therefore, the d / H range of 0.2 to 1.0 selected in this application embodiment is the result of achieving a balance between the feasibility of the SLM molding process, the reliability of structural strength, and the heat transfer efficiency after verification by thermo-fluid-structure interaction simulation.

[0088] Furthermore, the micro-turbulence column array 20 of this application does not adopt a uniform spacing arrangement across the entire domain, but rather exhibits a non-uniform distribution characteristic with gradient changes in distribution density along the mainstream direction of the cooling gas.

[0089] Specifically, in the upstream region of the micro-turbulence column array 20, which is the first heat transfer section after the cooling gas has completed multi-stage turning, the distribution density of the turbulence columns is relatively high. Here, a dense sub-array is formed with a small lateral spacing P and a longitudinal row spacing S. This upstream region is the first heat transfer interval for the cooling gas entering the exhaust section. At this point, the cooling gas temperature is the lowest, the temperature difference between the gas and the blade trailing edge wall is the largest, and the heat flux density is the most concentrated. Setting a high density of turbulence columns here can quickly establish a strong three-dimensional turbulent state within the shortest flow distance, significantly improving the convective heat transfer coefficient near the wall to cope with the intense thermal impact in this region.

[0090] The cooling gas flows downstream along the direction of the cooling gas flow, entering the middle and lower reaches of the micro-turbulence column array 20. At this point, the cooling gas has absorbed a significant amount of heat from the wall in the upstream section, and its temperature gradually increases, correspondingly reducing the heat exchange-driven temperature difference with the wall. If the high-density layout of the upstream section is maintained in this region, the cooling gas must continuously overcome the frictional and geometric resistance caused by the dense turbulence columns, significantly increasing the cumulative pressure loss of the entire flow channel. This places higher demands on the gas supply system and may weaken the final exhaust velocity. Therefore, this application appropriately reduces the distribution density of the turbulence columns in the middle and lower reaches of the array, moderately widening the spacing P and row spacing S between adjacent turbulence columns based on preferred values. This gradually sparse layout effectively reduces the total pressure loss of the entire flow channel while ensuring sufficient heat exchange capacity in this region, allowing the cooling gas to be smoothly discharged with a reasonable back pressure after effective heat exchange.

[0091] The non-uniform density gradient distribution strategy of the micro-turbulence column array 20 in this application embodiment, characterized by "dense upstream and sparse downstream," is a layout scheme established based on thermal-fluid coupling simulation and multi-objective topology optimization. This strategy achieves an optimal balance between the two mutually constraining objectives of heat transfer intensity and flow resistance. In other words, it ensures sufficient turbulence enhancement in the upstream high heat flux density region while avoiding excessive loss of airflow energy in the downstream region due to excessive flow resistance.

[0092] Optionally, the shape of the turbulence column in the embodiments of this application may be horseshoe-shaped, spindle-shaped, semi-spindle-shaped, maple leaf-shaped, teardrop-shaped, and fan-shaped, etc., to further optimize flow resistance and heat transfer.

[0093] The inner wall surface of the cooling cavity 30 in this embodiment also has a microtexture structure naturally formed by the SLM additive manufacturing process. This microtexture is not obtained through subsequent machining or chemical treatment, but rather is an inherent micromorphology formed on the molded surface during the SLM layer-by-layer melting and deposition process due to the molten pool dynamics and interlayer overlap effect. The microtexture and the inner wall surface of the cooling cavity 30 are integrally formed in the same manufacturing process, requiring no additional steps.

[0094] In this embodiment, the surface roughness Ra of the microtexture on the inner wall surface of the cooling cavity 30 is controlled within the range of 3.2 μm to 6.5 μm. It should be noted that this roughness value is not adjusted by changing the main forming parameters of the SLM process (such as laser power, scanning speed, layer thickness, etc.), but rather by utilizing the controllability of the formed surface quality through the SLM process. While ensuring the overall density and mechanical properties of the part, the melting and solidification conditions of the inner cavity surface area are specifically adjusted to obtain the surface micromorphology within the aforementioned target range.

[0095] Specifically, the microtexture with Ra of 3.2 μm to 6.5 μm exhibits an irregular undulating morphology at the microscale, composed of numerous tiny peaks and troughs. The vertical distance between peaks and troughs is on the order of micrometers, and the lateral spacing between peaks is also on the order of tens of micrometers. This morphological scale is much larger than that of a mirror-polished surface (Ra is typically less than 0.1 μm), but much smaller than the characteristic size (d = 0.8 mm) of the micro-turbulence column array 20 described in this application. Therefore, a hierarchical heat transfer enhancement system with two scales, "macro-turbulence" and "micro-texture," is formed within the cooling cavity 30.

[0096] The microtextured structure of this embodiment has a dual enhancement effect on the convective heat transfer process within the cooling cavity 30.

[0097] Specifically, the microtextured structure significantly increases the actual surface area of ​​the inner wall of the cooling cavity 30. Compared to a smooth wall, the surface with microtextures of Ra 3.2μm to 6.5μm has a significantly larger ratio of unfolded area to projected area. Within the same cooling cavity geometric envelope size, a larger effective heat transfer area means more interfaces for heat exchange between wall atoms and cooling gas molecules, thereby improving the overall heat transfer at a macroscopic level.

[0098] Secondly, and more importantly, the mechanism lies in the ability of microtextures to induce microscale turbulence in the near-wall region. In macroscopic flow, when cooling gas flows over a wall at a certain velocity, a thermal boundary layer with a large velocity gradient forms near the wall. Heat transfer within this thermal boundary layer mainly relies on molecular conduction, and since gases have low thermal conductivity, the thermal boundary layer constitutes the main thermal resistance in the convective heat transfer process. When the wall is smooth, the thermal boundary layer is relatively stable and thick; however, when the wall has microtextures with a thickness of Ra 3.2 μm to 6.5 μm, micron-sized peak structures penetrate into the bottom layer of the thermal boundary layer, creating continuous low-intensity disturbances to the wall-attached flow. Although these disturbances are not as strong as the large-scale turbulence induced by the micro-turbulence column array 20, their effective region is located precisely at the bottom layer of the boundary layer with the greatest thermal resistance. This effectively reduces the thickness of the thermal boundary layer, promoting a transition from the laminar bottom layer to the turbulent bottom layer, thereby significantly reducing the conductive thermal resistance in the near-wall region.

[0099] In summary, the microtexture structure of this application embodiment improves the overall convective heat transfer coefficient of the cooling cavity 30 at the microscale by means of "expanding the effective heat transfer area" and "breaking the near-wall thermal boundary layer", based on the macroscopic turbulence established by the micro-turbulence column array 20.

[0100] Preferably, those skilled in the art can adjust the roughness Ra value of the microtexture within the range allowed by the SLM process according to specific working conditions and heat exchange requirements; this application does not impose specific limitations in this regard.

[0101] The micro-cooling enhancement structure of this application embodiment is integrally formed using selective laser melting (SLM) additive manufacturing process. Specifically, the first guide rib 10, the second guide rib 11, the micro-turbulence column array 20, the cooling cavity 30, and the aforementioned inner wall micro-texture are all simultaneously formed in the SLM equipment by layer-by-layer powder spreading and selective laser melting, forming an integral structure that requires no subsequent assembly, welding, or mechanical connection.

[0102] In this embodiment, the main parameters of the SLM process can be configured as follows: laser power 120W to 180W, scanning speed 900mm / s to 1050mm / s, powder layer thickness 30μm, and substrate preheating temperature 100℃ to 120℃. Within the above process window, those skilled in the art can make appropriate adjustments according to the specific grade of the selected high-temperature alloy powder (such as modified IN738 or cobalt-based alloys) to obtain a molded part with satisfactory density and internal cavity surface quality.

[0103] After molding, the blade undergoes stress-relieving heat treatment to eliminate the thermal stress accumulated during the rapid solidification process of SLM. Subsequently, the inner cavity is subjected to powder removal treatment, using compressed gas and vibration assistance to completely remove unmelted metal powder from the complex internal cavity channels, ensuring the unobstructed flow of the cooling channels. After the above post-processing steps, a finished turbine guide vane with the micro-cooling efficiency enhancement structure of this application is obtained.

[0104] In summary, such as Figure 1 and Figure 2 As shown, this application achieves efficient thermal protection for the blade trailing edge by constructing an integrated system of "segmented air supply," "multi-stage guidance," and "microscopic enhancement." The first air inlet 41 and the second air inlet 42 respectively deliver cooling airflow from different sources to the trailing edge cooling chamber 103; the second guide rib 11 and the first guide rib 10 sequentially perform segmented rectification and smooth guidance of the main cooling airflow, reducing the flow resistance of the main cooling airflow; the main and secondary chamber partition plate smoothly guides the secondary cooling airflow, enabling it to overcome turning resistance while precisely injecting into the micro-turbulence column array 20 located in the downstream exhaust section.

[0105] Ultimately, the cooling gas undergoes high-intensity heat exchange under the intense disturbance of the micro-turbulence columns and is discharged from the blade trailing edge. This topology-integrated structure, based on SLM technology and optimized from macroscopic flow channel configuration to microscopic surface, reduces overall flow channel pressure loss while improving the cooling reliability of the blade trailing edge under extreme high-temperature environments.

[0106] Next, referring to the accompanying drawings, a design method for a micro-cooling efficiency enhancement structure for the inner cavity of a blade suitable for additive manufacturing is described according to an embodiment of this application. This method is used to design the aforementioned micro-cooling efficiency enhancement structure for the inner cavity of a blade suitable for additive manufacturing. This method systematically determines the optimal structural parameters of the micro-turbulence column array 20 and guide ribs 10 and 11 through three main steps: thermal-fluid coupling simulation, preliminary layout, and topology optimization, in order to achieve a multi-objective balance between maximizing heat transfer intensity and minimizing pressure loss. The following is a combination of... Figure 4 The flowchart shown below provides a detailed explanation of this design method.

[0107] Figure 4 This is a flowchart illustrating the design method of a micro-cooling enhancement structure for the inner cavity of a blade suitable for additive manufacturing, as described in this application embodiment. Figure 4 As shown, the design method for a micro-cooling enhancement structure for the inner cavity of blades suitable for additive manufacturing includes the following steps:

[0108] Step S401: Perform thermal-fluid coupling simulation on the component containing the internal cavity to determine the temperature field and hot spot distribution area.

[0109] Specifically, a three-dimensional geometric model containing internal cavity components (such as turbine guide vanes) is first established. This model includes complete geometric information of the blade's external profile and internal cooling channels. Furthermore, during the modeling process, the flow channel features such as the cooling cavity 30 and air inlets 41 and 42 are expressed parametrically to allow for flexible adjustment of each geometric parameter during subsequent optimization.

[0110] Subsequently, the boundary conditions of the blade's operating environment are set. These boundary conditions include, but are not limited to: the temperature field distribution, pressure field distribution, and velocity distribution of the high-temperature combustion gas flow outside the blade; the inlet total temperature, inlet total pressure, and flow rate of the internal cooling gas; and the thermophysical properties of the blade material (thermal conductivity, specific heat capacity, etc.). Furthermore, these boundary conditions are determined based on the actual operating conditions of the engine. For example, the external combustion gas temperature can be set to 950°C or higher, and the cooling gas inlet temperature can be set to the compressor bleed air temperature.

[0111] Based on this, computational fluid dynamics (CFD) numerical calculations and heat transfer analysis are used to couple the solution of the high-temperature gas flow field outside the blade and the internal cooling gas flow field. During the coupled solution process, the convective heat transfer of the external gas to the blade wall, the heat conduction within the wall, and the convective heat transfer of the internal cooling gas to the wall are calculated simultaneously, thereby obtaining the three-dimensional temperature field distribution across the entire blade. Based on this global temperature field, key regions where the temperature exceeds a preset threshold (e.g., ≥900℃) are identified, namely the "hot spot distribution areas" described in this application. These hot spot distribution areas are typically concentrated near the blade trailing edge and exhaust section, and are the key areas for the micro-cooling enhancement structure of this application. The identification of hot spot distribution areas not only refers to the absolute temperature value but also combines the wall temperature gradient distribution to determine the geometric boundaries where heat transfer needs to be strengthened.

[0112] In step S402, a micro-turbulence column array 20 and guide ribs (first guide rib 10 and / or second guide rib 11) are initially arranged in the cooling cavity 30 section corresponding to the hot spot distribution area.

[0113] Specifically, based on the spatial location and geometric boundaries of the hotspot distribution area identified in step S401, the target section within the cooling cavity 30 where the cooling efficiency enhancement structure needs to be arranged is determined. Within this target section, based on engineering experience or simplified one-dimensional flow analysis, the following layout parameters are initially determined:

[0114] For guide ribs 10 and 11, their initial placement locations (corresponding to airflow turning areas, such as the inlet of cooling cavity 30 or the reversal point inside the cavity), initial radius of curvature range, and initial wall thickness distribution are initially determined. For the micro-turbulence column array 20, its coverage area (corresponding to the exhaust section area downstream of the guide ribs), the initial value of the turbulence column diameter d, the initial values ​​of the lateral spacing P and the longitudinal spacing S, and the approximate gradient of the initial distribution density (e.g., a qualitative trend of denser upstream and sparser downstream) are initially determined.

[0115] The initial design obtained in step S402 has not yet reached its optimal parameters, but it provides a reasonable starting point for subsequent topology optimization steps, which helps to improve the optimization convergence efficiency.

[0116] In step S403, with the goal of maximizing heat transfer intensity and minimizing pressure loss, the layout parameters of the micro-turbulence column array 20 and the profile parameters of the guide ribs 10 and 11 are optimized to determine the final structural parameters.

[0117] Those skilled in the art will understand that in cooling channel design, "maximizing heat transfer intensity" and "minimizing pressure loss" are two contradictory objectives: enhancing heat transfer usually requires increasing airflow turbulence and flow resistance, while reducing pressure loss requires the channel to be as smooth as possible. The essence of this step S403 is to seek the Pareto optimal solution between these two objectives.

[0118] Specifically, the topology optimization process is carried out simultaneously with two sets of parameters:

[0119] The first set of parameters: optimization of the airfoil profile parameters of the guide ribs. The curvature radius and wall thickness of the first guide rib 10 and / or the second guide rib 11 are iterated. In each iteration, the pressure loss value of the airflow in the turning region under the current airfoil parameters is calculated based on a computational fluid dynamics (CFD) model. With minimizing pressure loss as the optimization objective, the curvature radius and wall thickness parameters are updated along the direction of decreasing pressure loss using optimization algorithms such as gradient descent or genetic algorithms. The iteration process continues until the pressure loss converges to a minimum or a preset convergence condition is met (e.g., the change in pressure loss between two adjacent iterations is less than a preset threshold). Finally, the airfoil or tapered profile that minimizes the pressure loss of the airflow in the turning region is obtained.

[0120] The second set of parameters: optimization of the layout parameters of the micro-turbulence column array. Multi-objective optimization is performed on the diameter d of the micro-turbulence columns, the spacing P (and S) between adjacent columns, and the distribution density gradient of the micro-turbulence column array 20. In each iteration, two objective function values ​​are calculated based on the CFD model under the current layout parameters: heat transfer intensity index (such as the average convective heat transfer coefficient of the trailing edge wall) and flow resistance index (such as the total pressure loss at the inlet and outlet of the array region). Using maximizing heat transfer intensity and minimizing flow resistance as the two optimization objectives, a multi-objective optimization algorithm, such as NSGA-II (Non-dominated Sorting Genetic Algorithm II), is used to search for the Pareto front in the parameter space. During the optimization process, constraints were imposed on the following parameters: the diameter d of the turbulence columns ranged from 0.3 mm to 2 mm; the ratio of the lateral spacing P to the diameter d, P / d, ranged from 2.0 to 5.0; and the ratio of the diameter d to the height H, d / H, ranged from 0.1 to 1. Simultaneously, the gradient variation of the turbulence column distribution density along the airflow direction (dense upstream, sparse downstream) was incorporated into the optimization variables. Finally, one or more optimal parameter combinations were selected from the Pareto front as the final structural parameters.

[0121] It should be noted that the SLM process constraints must also be considered during the above topology optimization process. Specifically, the diameter d of the turbulence column must not be less than the minimum feature size that can be stably formed by the SLM process; the wall thickness of the guide rib must not be less than the minimum wall thickness limit of the SLM process; and the overhang angle of each forming surface must be controlled within the critical angle range for unsupported forming by the SLM process. These process constraints are introduced into the optimization model in the form of constraint conditions to ensure that the optimization results have good process feasibility.

[0122] Furthermore, to verify the effectiveness of the design method and the obtained structure of this application, the trailing edge cooling cavity of a certain type of turbine guide vane was optimized using the design process of steps S401 to S403 described above. Figure 5 This is a schematic diagram of the original temperature field of the turbine guide vane before optimization in a specific embodiment of this application, as shown below. Figure 5 As shown, before optimization, the highest temperature in the trailing edge region of the original blade reached 1074℃, and the temperature in a large area exceeded 1000℃, which exceeded the allowable range of the material.

[0123] After optimization of the design method of this application, the optimized blade was subjected to a second thermal-fluid-structure interaction simulation verification using the combination scheme of the first guide rib 10, the second guide rib 11 and the micro-turbulence column array 20. Figure 6 This is a schematic diagram of the temperature field of an optimized turbine guide vane according to a specific embodiment of this application, as shown below. Figure 6 As shown, simulation results indicate that, under the same inlet boundary conditions, the maximum temperature in the blade trailing edge region is significantly reduced from 1074℃ to approximately 840℃, a decrease of about 200℃. Simultaneously, the total pressure loss of the cooling airflow within the entire trailing edge cooling chamber 103 is reduced by more than 15% compared to the traditional design.

[0124] The simulation results above demonstrate that the design method of this application can effectively determine the optimal structural parameters of the micro-turbulence column array and guide ribs through multi-objective topology optimization. The obtained micro-cooling enhancement structure achieves an optimal balance between maximizing heat transfer intensity and minimizing pressure loss. At the same time, by iterating the parameters of the curvature radius and wall thickness of the guide ribs, the profile that minimizes pressure loss is obtained. By performing multi-objective optimization on the diameter, spacing and distribution density gradient of the turbulence columns, a balance is achieved between heat transfer intensity and flow resistance.

[0125] According to the embodiments of this application, a micro-cooling efficiency enhancement structure and design method for blade internal cavity suitable for additive manufacturing is proposed. This structure addresses the technical challenge of stringent cooling requirements in the high-temperature region of turbine guide vane trailing edge and the difficulty in achieving refined cooling characteristics through traditional casting processes. By synergistically working through a multi-stage guiding system composed of the first guide rib 10 and the second guide rib 11, a micro-turbulence enhancement system composed of the micro-turbulence column array 20, and a near-wall boundary layer disturbance system composed of inner wall microtextures, the heat transfer efficiency enhancement mechanism at three scales significantly improves the heat transfer efficiency of the trailing edge region while reducing the pressure loss of the cooling airflow.

[0126] Simulation results show that, after adopting the micro-cooling enhancement structure of this application embodiment, the highest temperature in the blade trailing edge region is reduced from 1074℃ in the original structure to approximately 840℃, a temperature reduction of about 200℃. Simultaneously, the total pressure loss of the cooling airflow within the trailing edge cooling cavity 103 is reduced by more than 15% compared to the traditional design. Therefore, this application, by deeply integrating the design freedom of the SLM additive manufacturing process with a multi-objective topology optimization method, successfully overcomes the technical bottleneck of traditional casting processes in designing complex internal cavity cooling structures at the sub-millimeter level. It achieves an optimized balance between maximizing heat transfer intensity and minimizing pressure loss, providing effective cooling assurance for the reliable service of high-temperature alloy materials under 950℃ operating conditions.

[0127] Figure 7 A schematic diagram of the structure of an electronic device provided in an embodiment of this application. The electronic device may include:

[0128] The memory 701, the processor 702, and the computer program stored on the memory 701 and executable on the processor 702.

[0129] When the processor 702 executes the program, it implements the design method of the micro-cooling efficiency enhancement structure for blade cavity in additive manufacturing provided in the above embodiments.

[0130] Furthermore, electronic devices also include:

[0131] Communication interface 703 is used for communication between memory 701 and processor 702.

[0132] The memory 701 is used to store computer programs that can run on the processor 702.

[0133] The memory 701 may include high-speed RAM (Random Access Memory) memory, and may also include non-volatile memory, such as at least one disk storage.

[0134] If the memory 701, processor 702, and communication interface 703 are implemented independently, then the communication interface 703, memory 701, and processor 702 can be interconnected via a bus to complete communication between them. The bus can be an ISA (Industry Standard Architecture) bus, a PCI (Peripheral Component Interconnect) bus, or an EISA (Extended Industry Standard Architecture) bus, etc. The bus can be divided into address bus, data bus, control bus, etc. For ease of representation, Figure 7 The bus is represented by a single thick line, but this does not mean that there is only one bus or one type of bus.

[0135] Optionally, in a specific implementation, if the memory 701, processor 702, and communication interface 703 are integrated on a single chip, then the memory 701, processor 702, and communication interface 703 can communicate with each other through an internal interface.

[0136] The processor 702 may be a CPU (Central Processing Unit), an ASIC (Application Specific Integrated Circuit), or one or more integrated circuits configured to implement the embodiments of this application.

[0137] This application also provides a computer program product storing a computer program that, when executed by a processor, implements the above-described design method for a micro-cooling enhancement structure for blade cavities suitable for additive manufacturing.

[0138] In the description of this specification, the terms "an embodiment," "some embodiments," "example," "specific example," and "some examples," etc., refer to a specific feature, structure, material, or characteristic described in connection with that embodiment or example, which is included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0139] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, "N" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0140] Any process or method described in the flowchart or otherwise herein can be understood as representing a module, segment, or portion of code comprising one or N executable instructions for implementing custom logic functions or processes, and the scope of the preferred embodiments of this application includes additional implementations in which functions may be performed not in the order shown or discussed, including substantially simultaneously or in reverse order depending on the functions involved, as should be understood by those skilled in the art to which embodiments of this application pertain.

[0141] It should be understood that the various parts of this application can be implemented using hardware, software, firmware, or a combination thereof. In the above embodiments, the N steps or methods can be implemented using software or firmware stored in memory and executed by a suitable instruction execution system. For example, if implemented in hardware, as in another embodiment, it can be implemented using any one or more of the following techniques known in the art: discrete logic circuits having logic gates for implementing logical functions on data signals, application-specific integrated circuits (ASICs) having suitable combinational logic gates, programmable gate arrays (FPGAs), field-programmable gate arrays (FPGAs), etc.

[0142] Those skilled in the art will understand that all or part of the steps of the methods in the above embodiments can be implemented by a program instructing related hardware. The program can be stored in a computer-readable storage medium, and when executed, the program includes one or a combination of the steps of the method embodiments.

[0143] Although embodiments of this application have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting this application. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of this application.

Claims

1. A micro-cooling enhancement structure for the inner cavity of blades suitable for additive manufacturing, characterized in that, include: The micro-turbulence column array consists of multiple columnar turbulence units integrally formed with the inner wall of the cooling cavity, with the diameter of a single columnar turbulence unit ranging from 0.3 mm to 2.0 mm; At least one guide rib is integrally disposed in the airflow deflection zone within the cooling chamber; The guide rib extends along the cooling airflow direction with an arc transition, and the micro-turbulence column array is located downstream of the guide rib along the cooling airflow direction.

2. The structure according to claim 1, characterized in that, The micro-turbulence column array is non-uniformly distributed, with a higher distribution density of turbulence columns in areas with high cooling demand than in areas with low cooling demand.

3. The structure according to claim 1, characterized in that, The cross-sectional shape of the columnar turbulence unit is one of the following: circular, horseshoe, spindle, semi-spindle, maple leaf, or fan-shaped; and / or, the columnar turbulence unit is arranged as a single unit in the height direction perpendicular to the cooling chamber wall, or multiple units are stacked along the height direction; and / or, the angle between the central axis of the columnar turbulence unit and the cooling gas flow direction is 30° to 150°.

4. The structure according to claim 1, characterized in that, In the micro-turbulence column array, the ratio P / d of the spacing P between adjacent columnar turbulence units to the characteristic diameter d of the columnar turbulence unit ranges from 2.0 to 5.0; and / or, the ratio d / H of the diameter d of the columnar turbulence unit to the height H of the columnar turbulence unit ranges from 0.2 to 1.

0.

5. The structure according to claim 1, characterized in that, The wall thickness of the guide rib is 0.2 mm to 3.0 mm.

6. The structure according to claim 1, characterized in that, The cross-sectional shape of the guide rib is one of square, elliptical or teardrop shape; and / or, the angle between the extension direction of the guide rib and the flow channel normal plane at the corresponding position of the airflow turning zone is 30° to 150°.

7. The structure according to any one of claims 1 to 6, characterized in that, The inner wall surface of the cooling cavity also has microtextures, which are integrally formed with the inner wall surface, and the surface roughness Ra is 3.2μm to 6.5μm.

8. The structure according to any one of claims 1 to 6, characterized in that, The cooling cavity, the micro-turbulence column array, and the guide rib are integrally formed by laser selective melting (SLM) process; the blades are turbine guide blades, and the airflow deflection zone is the inlet of the cooling cavity or the bend inside the cavity.

9. A design method for enhancing micro-cooling efficiency in the inner cavity of blades suitable for additive manufacturing, the method being used to design the structure according to any one of claims 1 to 8, characterized in that, The method includes the following steps: Perform thermal-fluid coupling simulation on components with internal cavities to determine the temperature field and hot spot distribution areas; Within the cooling cavity section corresponding to the hotspot distribution area, a preliminary array of micro-turbulence columns and guide ribs are arranged; With the goal of maximizing heat transfer intensity and minimizing pressure loss, the layout parameters of the micro-turbulence column array and the profile parameters of the guide ribs are optimized by topology to determine the final structural parameters.

10. The method according to claim 9, characterized in that, The steps of the topology optimization include: The cross-sectional shape, spacing, radius of curvature, and wall thickness of the guide ribs are iterated to obtain a profile that minimizes the pressure loss of the airflow in the airflow turning zone. Furthermore, the characteristic diameter of the columnar turbulence units of the micro-turbulence column array, the spacing between adjacent columnar turbulence units, the distribution density gradient, and the number of stacked units are optimized in a multi-objective manner to achieve a balance between heat transfer intensity and flow resistance.

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