Engine vane structure

Abstract

The utility model discloses an engine static vane structure. The engine static vane structure includes blade structure and shell body, and blade structure connects shell body, and blade structure includes blade shell body, and the inside of blade shell body defines first flow channel, and first flow channel is used for conveying cooling medium, and at least part blade shell body includes micropore network, and micropore network includes first micropore structure, and first micropore structure communicates first flow channel, and first micropore structure can guide cooling medium to the outer surface of blade shell body through capillary action and evaporate. Wherein, along the thickness direction of blade structure, first micropore structure includes oppositely distributed first end and second end, and the orthographic projection of second end on the plane perpendicular to the thickness direction of blade structure is located on the inside of first end. The utility model can improve the heat dissipation efficiency, service life and lightweight degree of engine static vane structure.

Description

Technical Field

[0001] This utility model relates to the field of engine technology, and in particular to an engine stator structure. Background Technology

[0002] In modern aerospace and industrial applications, the engine, as the core power component, directly impacts the operational efficiency and reliability of the entire system. The engine's operating principle relies on converting the heat energy generated by burning fuel into mechanical energy; however, this process inevitably produces a significant amount of waste heat. Traditional cooling systems typically include a complex series of cooling channels, heat sinks, and cooling medium circulation systems, designed to effectively remove this waste heat from critical components such as blades and casings. The design of these systems requires balancing multiple factors, such as cooling efficiency, weight, cost, and environmental impact. To achieve optimal cooling performance, engineers often employ various methods, including using high thermal conductivity materials, optimizing flow channel design, and introducing highly efficient cooling media.

[0003] While traditional cooling systems can meet basic cooling requirements to some extent, they are often bulky and heavy, increasing the overall weight of the equipment and potentially affecting its mobility and energy efficiency. This is particularly true in the aviation field, where every kilogram of added weight significantly impacts flight range, payload capacity, and fuel economy. Furthermore, existing systems are complex to design, expensive to maintain, and structural limitations make it difficult to achieve uniform and effective heat dissipation, leaving some critical areas at risk of overheating. Therefore, heat dissipation efficiency still needs improvement. Utility Model Content

[0004] The main objective of this invention is to propose an engine stator blade structure that can improve the engine's heat dissipation efficiency, service life, and lightweight design.

[0005] An embodiment of the first aspect of this utility model provides an engine stator blade structure, which includes a blade structure and a housing. The blade structure is circumferentially arranged around a first axis and connected to the housing. The blade structure includes a blade shell, and the interior of the blade shell defines a first flow channel for conveying a cooling medium. At least a portion of the blade shell includes a microporous network, which includes a first microporous structure. The first microporous structure communicates with the first flow channel and is capable of guiding the cooling medium to the outer surface of the blade shell and evaporating it through capillary action. Along the thickness direction of the blade structure, the first microporous structure includes a first end and a second end that are relatively distributed. The orthographic projection of the first end onto a plane perpendicular to the thickness direction of the blade structure is the first projection, and the orthographic projection of the second end onto a plane perpendicular to the thickness direction of the blade structure is the second projection. The second projection is located inside the first projection.

[0006] In some embodiments, the blade structure has an initial state and a target state. In the initial state, the blade structure has a plurality of through holes extending along its own thickness direction. In the target state, the through holes are filled with a first microporous structure.

[0007] In some embodiments, along the axial direction of the through hole, the diameter of one end of the through hole is larger than that of the other end, so that the first microporous structure filling the through hole is tapered.

[0008] In some embodiments, the microporous network further includes a second microporous structure that covers at least a portion of the blade shell along the extension direction of the blade shell.

[0009] In some embodiments, the engine stator structure can guide gas along a first direction, which is parallel to a first axis. The blade structure includes a first side and a second side that are distributed opposite to each other along the first direction. The first microporous structure and / or the second microporous structure can guide the cooling medium to the outer surface of the blade shell through capillary action and evaporate it, and form a gas film on the surface of the first side and / or the second side.

[0010] In some embodiments, the second microporous structure includes micropores with a depth ranging from 0.5 mm to 1.5 mm.

[0011] In some embodiments, the interior of the outer casing is hollow to form a second flow channel for conveying a cooling medium, and the second flow channel is connected to the first flow channel.

[0012] In some embodiments, the engine stator structure further includes an output pipe and an input pipe, both of which are connected to a second flow channel. The input pipe is adapted to introduce cooling medium into the second flow channel, and the output pipe is adapted to discharge cooling medium from the second flow channel.

[0013] In some embodiments, the output conduit includes a first main pipe and a plurality of first branches circumferentially distributed around a first axis, the two ends of the first branches being connected to the first main pipe and a second flow guide channel, respectively; and / or, The input pipeline includes a second main pipeline and multiple second branches distributed circumferentially around the first axis. The two ends of the second branches are respectively connected to the second main pipeline and the second diversion channel.

[0014] In some embodiments, the cooling medium includes aviation kerosene or water.

[0015] According to the above embodiments, the beneficial effects of this utility model are: The engine stator blade structure of this application includes a blade structure and a housing. The blade structure is circumferentially arranged around a first axis and connected to the housing to guide airflow. The blade structure includes a blade shell, the interior of which defines a first flow channel. For example, the blade shell may be hollow, with the cavity configured as the first flow channel for conveying cooling medium. At least a portion of the blade shell includes a microporous network, which includes a first microporous structure connected to the first flow channel. The first microporous structure guides the cooling medium within the first flow channel to the outer surface of the blade shell through capillary action. Under high external temperatures, the cooling medium on the outer surface of the blade shell evaporates, cooling the surface of the blade shell. Furthermore, under the influence of airflow, the evaporated cooling medium is deposited on the surface of the blade shell, forming an air film, further enhancing the protection of the blade shell.

[0016] Specifically, along the thickness direction of the blade structure, the first microporous structure includes a first end and a second end that are relatively distributed. The orthographic projection of the first end onto a plane perpendicular to the thickness direction of the blade structure is the first projection, and the orthographic projection of the second end onto a plane perpendicular to the thickness direction of the blade structure is the second projection. The second projection is located inside the first projection. Since the second projection falls inside the first projection, one end of the first microporous structure has a larger area than the other; for example, the first microporous structure may be conical. This design of the first microporous structure facilitates the rapid absorption of the cooling medium from the wider end under capillary force and accelerated seepage from the narrower outlet end. The seeping liquid adheres closely to the metal surface, evaporates and vaporizes upon heating, forming a low-oxygen partial-pressure gas film that carries away a large amount of latent heat. The gas film also prevents high-temperature combustion gases from directly scouring the metal substrate, achieving dual cooling through evaporative cooling and gas film insulation. Because the micropores of the cone are completely embedded within the wall thickness, the aerodynamic shape of the blade remains intact and smooth. This eliminates flow losses caused by traditional surface grooves or bosses and avoids the risk of external micropores being easily clogged by dust and carbon deposits. This improves the cooling reliability and maintenance convenience of the stationary blade in high-temperature and high-pollution environments. Therefore, this application achieves a balance between lightweight, high-strength, and efficient heat dissipation in the engine stationary blade structure without adding parts or changing the shape. It not only has high heat dissipation efficiency but also extends the service life of the engine stationary blade structure.

[0017] Furthermore, traditional approaches tend to involve superimposing micro-spray arrays on the outside of the blade or adding a pumping system inside, resulting in a chain reaction of contradictions regarding flow resistance, weight, and sealing. The entire cooling system in this application is integrated into the blade housing, eliminating the need for external pumps and secondary coatings. This significantly reduces the number of parts, shortens the manufacturing process, and lowers the weight, achieving both high-efficiency heat dissipation and lightweight design, which are difficult to achieve with traditional multi-component solutions.

[0018] Additional aspects and advantages of this invention 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 the invention. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0020] Figure 1 This is a three-dimensional structural diagram of the engine stator blade structure viewed from a first perspective in one embodiment of the present invention. Figure 2 This is a three-dimensional structural diagram of the engine stator blade structure viewed from a second perspective in one embodiment of the present invention; Figure 3 This is a three-dimensional structural diagram of the engine stator blade structure viewed from a third-person perspective in one embodiment of the present invention; Figure 4 This is a three-dimensional structural diagram of the engine stator blade structure viewed from a fourth perspective in one embodiment of the present invention. Figure 5 This is a three-dimensional structural diagram of the engine stator blade structure viewed from a fifth perspective in one embodiment of the present invention; Figure 6 for Figure 5 A schematic diagram of the cross-sectional structure of the engine stator blade structure cut by the plane DD; Figure 7 This is a schematic diagram of the engine stator structure in its initial state according to one embodiment of the present invention; Figure 8 This is a schematic diagram of the engine stator blade structure in the target state according to one embodiment of the present invention; Figure 9 yes Figure 8 A schematic diagram of the cross-sectional structure of the engine stator blade structure obtained by plane II and a partial enlarged view of point A; Figure 10 This is a schematic diagram of the structure of a tapered microporous network in one embodiment of the present invention; Figure 11 This is a schematic diagram of the engine stator structure when viewed from another perspective.

[0021] Explanation of icon numbers: Engine stator structure 10; Blade structure 100; blade shell 110; through hole 111; microporous network 120; 200mm outer casing; Input pipe 300; Output pipe 400; First direction X.

[0022] The realization of the purpose, functional features and advantages of this utility model will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0023] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0024] It should be noted that if the embodiments of this utility model involve directional indicators (such as up, down, left, right, front, back, etc.), the directional indicators are only used to explain the relative positional relationship and movement of the components in a specific posture. If the specific posture changes, the directional indicators will also change accordingly.

[0025] Furthermore, if the embodiments of this utility model involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the use of "and / or," "and / or," or "and / or" throughout the text implies three parallel solutions. For example, "A and / or B" includes solution A, solution B, or a solution where A and B are simultaneously satisfied. Furthermore, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed by this utility model.

[0026] The following is for reference. Figures 1 to 11 The engine stator vane structure 10 according to an embodiment of the present invention will be described below. (Refer to...) Figures 1 to 6The engine stator structure 10 of this application includes a blade structure 100 and a housing 200. The blade structure 100 is circumferentially arranged around a first axis and is connected to the housing 200 to form a function of guiding airflow. The blade structure 100 includes a blade shell 110, the interior of which defines a first flow channel. For example, the blade shell 110 is hollow, and the cavity is configured as the first flow channel for conveying cooling medium. At least a portion of the blade shell 110 includes a microporous network 120, which includes a first microporous structure. The first microporous structure communicates with the first flow channel and can guide the cooling medium in the first flow channel to the outer surface of the blade shell 110 through capillary action. Under the action of a high-temperature environment, the cooling medium at the outer surface of the blade shell 110 is heated and evaporated, thus cooling the surface of the blade shell 110. In addition, under the action of airflow, the evaporated and vaporized cooling medium is laid on the surface wall of the blade shell 110 to form an air film, which further enhances the protection of the blade shell 110.

[0027] Specifically, along the thickness direction of the blade structure 100, the first microporous structure includes a first end and a second end that are relatively distributed. The orthographic projection of the first end onto a plane perpendicular to the thickness direction of the blade structure 100 is the first projection, and the orthographic projection of the second end onto a plane perpendicular to the thickness direction of the blade structure 100 is the second projection. The second projection is located inside the first projection. Since the second projection falls inside the first projection, one end of the first microporous structure has a larger area and the other end has a smaller area; for example, the first microporous structure may be conical. This design of the first microporous structure facilitates the rapid absorption of the cooling medium from the wider end under capillary force and accelerated seepage at the narrower outlet end. The seeping liquid adheres closely to the metal surface, evaporates and vaporizes upon heating, forming a low-oxygen partial-pressure gas film that carries away a large amount of latent heat. The gas film also prevents high-temperature combustion gases from directly scouring the metal substrate, achieving dual cooling through evaporative cooling and gas film insulation. Because the micropores of the cone are completely embedded within the wall thickness, the aerodynamic shape of the blade remains intact and smooth. This eliminates the flow losses caused by traditional surface grooves or bosses, and avoids the risk of external micropores being easily clogged by dust and carbon deposits. This improves the cooling reliability and maintenance convenience of the stationary blade in high-temperature and high-pollution environments. Therefore, this application achieves a balance between lightweight, high strength, and efficient heat dissipation of the engine stationary blade structure 10 without adding parts or changing its shape. It not only has high heat dissipation efficiency but also extends the service life of the engine stationary blade structure 10.

[0028] Furthermore, traditional approaches tend to involve superimposing micro-spray arrays on the outside of the blade or adding a pumping system inside, resulting in a chain reaction of contradictions regarding flow resistance, weight, and sealing. The entire cooling system of this application is integrated into the blade housing 110, eliminating the need for external pumps and secondary coatings. This significantly reduces the number of parts, shortens the manufacturing process, and lowers the weight, achieving both high-efficiency heat dissipation and lightweight design, which are difficult to achieve with traditional multi-component solutions.

[0029] In some embodiments, the blade structure has an initial state and a target state, as referenced. Figure 2 and Figure 7 In its initial state, the blade structure has multiple through-holes 111 extending along its thickness direction. In its target state, the through-holes 111 are filled with a first microporous structure. The through-holes 111 retained in the initial stage reduce the processing difficulty before sintering and lay a spatial foundation for the continuity of subsequent powder filling and capillary channels. (Refer to...) Figures 8 to 11 When the through-hole 111 is filled with the first microporous structure, the originally discrete and large-sized pores are transformed into dense and interconnected micron-sized pores. This expands the cooling medium transport path from a few concentrated channels into a three-dimensional network, improving the uniformity of liquid distribution and response speed. At the same time, the filling of the through-hole 111 by the first microporous structure eliminates the potential for localized high-temperature hot spots, making the temperature gradient on the blade surface more gradual and alleviating thermal stress concentration. This, in turn, improves the reliability and lifespan of the blade under long-term high-temperature service conditions.

[0030] Reference Figures 8 to 11 In some embodiments, the blade structure is transformed from an initial state to a target state through a sintering process. After medium-temperature sintering, the pore size of the microporous network 120 ranges from 1 μm to 50 μm, for example, 1 μm, 10 μm, 30 μm, and 50 μm. Pores within this range can generate sufficient capillary force to promote the intake and transport of the cooling medium. If the pore size is too small, the transport resistance may be too high; if the pore size is too large, the capillary effect may be weakened. In the target state, the first microporous structure fills the through-holes 111, and the microporous network 120 also includes a second microporous structure. Along the extension direction of the blade shell 110, the second microporous structure covers at least a portion of the blade shell 110. This embodiment introduces the sintering process into the blade forming process, so that during the transformation of the blade from the initial through-hole 111 state to the target first microporous structure state, both structural densification and three-dimensional construction of the functional layers are achieved. With the help of the sintering process, the surface of the residual powder is partially fused while the interior remains porous, and the originally isolated large-sized through-holes 111 are replaced by a continuous, interconnected micron-scale capillary network. The second microporous structure is continuously distributed along the extension direction of the blade shell 110. Combined with the first microporous structure, the cooling medium can uniformly penetrate and rapidly evaporate throughout the entire wall area, improving heat exchange efficiency. Simultaneously, the metallurgical bonding brought about by sintering strengthens the interparticle connections, eliminating stress concentration caused by the presence of the through-holes 111, thus giving the blade higher structural integrity in high-temperature, high-pressure combustion environments. The integrated process also reduces the secondary bonding steps between the traditional porous layer and the substrate, lowering interfacial thermal resistance and the risk of detachment, and extending the lifespan of the blade structure.

[0031] Reference Figure 1 , Figure 2 , Figure 9and Figure 11 In some embodiments, along the axial direction of the through-hole 111, the diameter of one end of the through-hole 111 is larger than that of the other end, so that the first microporous structure filling the through-hole 111 after sintering is conical. By setting the through-hole 111 to a tapered shape with one end larger than the other, the first microporous structure formed after sintering naturally presents a conical structure. The conical channel can generate a gradually accelerating liquid transport effect under capillary action. The larger end is conducive to the rapid absorption of cooling medium, while the smaller end increases the local flow rate and enhances surface wetting, ultimately forming a continuous and uniformly distributed liquid film on the outer surface of the blade. The conical micropores also increase the evaporation area, allowing the latent heat of vaporization to be fully released, thereby improving cooling efficiency. At the same time, the necking structure at the outlet can effectively suppress droplet splashing or premature detachment, ensuring that the cooling medium can remain stably and continue to evaporate under the scouring of high-temperature combustion gases. In summary, with this design, the blade shell 110 achieves synergistic optimization of coolant supply, evaporation, and gas film formation while maintaining structural strength, improving the thermal protection performance and lifespan of the hot-end components.

[0032] In some embodiments, to further optimize the design of the conical first micropore structure, different cooling effects can be achieved by adjusting the diameter ratio at both ends of the through-hole 111. For example, setting the inlet diameter to twice the outlet diameter allows the cooling medium to have a larger flow area when entering the blade, enabling it to accelerate rapidly near the outer surface and promote evaporation efficiency. This design facilitates rapid cooling, which is particularly advantageous for aero-engine blades operating under high loads.

[0033] In some embodiments, a segmented tapered design is employed. Specifically, multiple tapered segments are arranged at different positions of the through-hole 111, each with a different diameter ratio. For example, the portion near the first guide channel uses a gentler taper to reduce flow resistance, while the portion near the blade surface uses a steeper taper to increase the flow rate and evaporation rate of the cooling medium. In this way, the flow characteristics and evaporation efficiency of the cooling medium can be flexibly adjusted without changing the overall blade structure, meeting diverse application requirements. Furthermore, this design can further optimize the mechanical strength and heat dissipation performance of the blade by changing the number and arrangement of the tapered segments.

[0034] Reference Figures 1 to 6In some embodiments, the engine stator structure 10 can guide gas along a first direction X, which is parallel to a first axis. The blade structure 100 includes a first side and a second side distributed opposite to each other along the first direction X. The microporous network 120 can guide the cooling medium to the outer surface of the blade shell 110 through capillary action and evaporate it, forming a gas film on the surface of the first side and / or the second side. This design utilizes the inherent function of the stator to guide the gas flow along the axis. By arranging the microporous network 120 on the two heat-bearing surfaces of the first and second sides of the blade, the cooling medium arrives and evaporates synchronously under capillary force, forming a continuous gas film on both sides of the blade. The dual-sided cooling method of this application effectively covers the high-temperature areas of the pressure and suction surfaces, avoiding local overheating and improving the uniformity of thermal stress distribution. Simultaneously, the water vapor or fuel vapor generated by evaporation migrates downstream with the mainstream gas flow, without disrupting the flow path. Instead, it adheres to the wall surface through the Coanda effect, further enhancing the heat insulation effect. By deeply integrating the cooling function with the aerodynamic guide structure, the stator blades achieve efficient and low-resistance radiative cooling without the need for an additional power source, reducing the impact of heat load on material performance degradation and providing a reliable guarantee for the long-term stable operation of the engine.

[0035] In some embodiments, the second micropore structure includes micropores with a depth ranging from 0.5 mm to 1.5 mm, such as 0.5 mm, 1.0 mm, and 1.5 mm. Limiting the micropore depth to between 0.5 mm and 1.5 mm ensures that the cooling medium is sufficiently drawn to the outer surface of the blade under capillary action, without becoming stagnant or unevenly distributed due to excessive resistance in excessively long channels. The depth range in this embodiment balances liquid transport efficiency and structural integrity. For example, if the depth is too shallow, the evaporation surface is insufficient, hindering the realization of cooling potential; if it is too deep, it may weaken the shell strength and increase weight. This design ensures that the blade shell 110 provides suitable residence and evaporation space for the cooling medium while maintaining mechanical performance, ensuring that the liquid rapidly vaporizes upon reaching the surface and carries away heat. This maintains stable evaporative cooling and film protection under high-temperature conditions, extending the blade's service life and improving the overall reliability of the engine.

[0036] Reference Figures 1 to 6The engine stator structure 10 also includes a housing 200, with blade structures 100 arranged circumferentially around a first axis and connected to the housing 200. The housing 200 is hollow to form a second flow channel for transporting cooling medium, and the second flow channel connects to the first flow channel. Specifically, by providing a second flow channel within the housing 200 and connecting it to the first flow channel within the blade housing 110, a staged cooling supply integrated stator structure is constructed. The housing 200 acts as an annular distributor, uniformly guiding the cooling medium to the inner cavity of each blade, avoiding the uneven flow caused by traditional single-point injection. Simultaneously, the hollow housing reduces the overall weight and utilizes internal flow to achieve additional cooling at the blade root. After the blades are connected to the outer casing 200, the microporous network 120 directly benefits from a stable and continuous supply of cooling medium. For example, the cooling medium flows through the second guide channel of the outer casing 200 to the first guide channel inside the blade structure, and then exits from the microporous network 120. This staged flow, like the veins of a leaf, drives the cooling medium to the target location step by step through the main channels. Even under high-temperature combustion gas impact, it can maintain sufficient liquid replenishment and continuous gas film coverage, thereby improving the overall thermal consistency and structural reliability of the stator blades. This layout simplifies external piping, reduces high-pressure sealing points, and provides comprehensive benefits for the assembly, maintenance, and weight reduction of the engine's hot-end module.

[0037] Reference Figures 1 to 6 In some embodiments, the engine stator structure 10 further includes an output pipe 400 and an input pipe 300. Both the input pipe 300 and the output pipe 400 are connected to a second guide channel. The input pipe 300 is adapted to introduce the cooling medium into the second guide channel, and the output pipe 400 is adapted to discharge the cooling medium from the second guide channel. By adding the input and output pipes 400 to the outer casing 200, a circulating cooling medium loop is formed in the second guide channel. The input pipe 300 introduces the liquid cooling medium into the inner cavity of the outer casing 200, achieving uniform liquid supply at multiple points through the circumferentially symmetrical distribution of the stator blades. The output pipe 400 can promptly recover unevaporated portions or heat-carrying vapors, preventing liquid stagnation that could lead to localized overcooling or pressure buildup. This closed-loop design not only ensures continuous renewal of the cooling medium and keeps the capillary network in optimal wetting condition, but also allows for flexible control of the cooling intensity by adjusting the flow rate, adapting to different engine operating conditions. Meanwhile, the fluid inlet and outlet ports of the pipeline are integrated into the outer casing 200, reducing external joints and sealing links, lowering the risk of leakage and simplifying the maintenance process, which helps to extend the service life of the engine stator structure 10.

[0038] Reference Figures 1 to 6In some embodiments, the output pipe 400 includes a first main pipe and multiple first branches circumferentially distributed around a first axis, with the two ends of each first branch connected to the first main pipe and a second flow guide channel, respectively. In some embodiments, the input pipe 300 includes a second main pipe and multiple second branches circumferentially distributed around a first axis, with the two ends of each second branch connected to the second main pipe and the second flow guide channel, respectively. By providing a tree-like flow channel structure of the main pipe and circumferential branches within the housing 200, the cooling medium can enter or leave the second flow guide channel from multiple directions, improving the uniformity and response speed of fluid distribution. The first branches are arranged at multiple points circumferentially, which can disperse and transport the cooling medium in the main pipe to various locations at the root of the stationary blades, avoiding uneven flow and local impact caused by single-point injection. During reverse operation, the second branches are distributed circumferentially, and the second branches play a role in convergence and recovery, ensuring smooth return of unevaporated medium and steam, maintaining system pressure balance, and further reducing thermal stress differences caused by circumferential temperature differences. This design integrates the main pipe with the outer casing 200, eliminating a large number of external hoses and joints, reducing weight and leakage risks, while facilitating overall disassembly and maintenance, and providing a simple and reliable cooling medium circulation channel for the engine hot end stator vanes.

[0039] In some embodiments, the cooling medium includes aviation kerosene or water. Choosing aviation kerosene or water as the cooling medium utilizes readily available on-site working fluid resources that do not require additional transport. Aviation kerosene, after absorbing heat, can rapidly atomize and participate in downstream combustion, achieving energy recovery from cooling to re-combustion and avoiding additional emissions. Water, with its high latent heat of vaporization and chemical stability, rapidly evaporates at high temperatures to form a dense gas film, effectively isolating the blade surface from direct scouring and oxidation by the combustion gases. Both media are well-matched with the micron-level microporous network 120, ensuring stable capillary suction, rapid evaporation response, and no solid residue clogging the channels, ensuring long-term reliable operation of the radiative cooling system and reducing maintenance requirements and operating costs.

[0040] In some embodiments, phase change materials (PCMs) are used as an auxiliary cooling medium. PCMs can absorb or release large amounts of heat while maintaining a relatively constant temperature, making them suitable for cooling systems of engine blades. For example, a small PCM reservoir is installed within the blade casing 110. When the cooling medium passes through the PCM reservoir, the PCM absorbs excess heat and undergoes a phase change, thereby maintaining the blade surface temperature within a relatively stable range. This method not only improves the response speed of the cooling system but also reduces mechanical stress caused by temperature fluctuations, extending the blade's service life.

[0041] In summary, this application constructs a continuous first flow channel inside the stator blade shell and generates a three-dimensional interconnected microporous network 120 in situ within the shell wall thickness range. The microporous network 120 is directly connected to the first flow channel, relying on capillary action to continuously and uniformly draw the cooling medium to the outer surface of the blade. When the engine is running, the cooling medium rapidly evaporates under the action of high-temperature combustion gases, absorbing a large amount of latent heat of vaporization and forming a continuous gas film on the blade surface, achieving dual cooling of "evaporation phase change heat absorption + gas film insulation". Through this mechanism, the stator blade can operate safely at higher combustion gas temperatures, and the engine's thermal efficiency, thrust, and fuel utilization are simultaneously improved.

[0042] To achieve the above functions, the stator blade structure adopts a process design from the initial stage to the target stage. Specifically, in the initial state, a hollow blade blank is formed by 3D printing, with through holes 111 pre-reserved along the thickness direction in the wall thickness. Subsequently, medium-temperature surface sintering is performed at a temperature lower than the powder's complete densification temperature, causing the residual metal powder in the through holes 111 to fuse only at the particle neck, preserving the original voids, thereby transforming the through holes 111 into a first microporous structure composed of micron-sized pores. The diameter of the through holes 111 is larger at one end and smaller at the other, forming a conical first microporous structure that provides better capillary effect. During the sintering process, a second microporous structure is also generated on the outer surface of the blade. The first and second microporous structures are connected, and together they form a continuous, interconnected microporous network 120 connected to the first flow channel. Since the sintering temperature is always lower than the material's melting point, the blade's shape, internal cavity dimensions, and outer shell structure 200 remain intact, requiring no secondary straightening, making the process simple and reliable.

[0043] To further optimize the cooling effect, the pore size of the microporous network 120 is gradient-distributed along the thickness direction. By layering spherical powders of different particle sizes, with an average particle size difference between adjacent layers greater than or equal to 5 μm, a variable gradient pore structure with varying pore sizes is naturally formed after sintering. The coarse-pore layer acts as a low-resistance transport channel, while the fine-pore layer provides strong capillary suction, enabling continuous, uniform, and rapid transport of the cooling medium along the thickness direction. This increases the evaporation area and makes the gas film coverage more stable. The gradient pore structure also allows for a continuous transition in the coefficient of thermal expansion, alleviating thermal stress concentration, suppressing the initiation of microcracks during cycle start-up and shutdown, and improving the mechanical reliability and lifespan of the stationary blades in high-temperature, high-pressure gas environments.

[0044] At the system level, the stator blades and the outer casing 200 together form a ring-shaped cooling module. The hollow interior of the outer casing 200 forms a second flow channel, which is connected to the engine cooling system through circumferentially distributed input and output pipes 400. The cooling medium is evenly distributed to the first flow channel of each blade through the second flow channel, and then seeps out and evaporates through the microporous network 120. Excess medium and vapor are recovered through the output pipes 400, forming a closed-loop circulation. The outer casing 200 and the blades are formed in one piece, with no interface thermal resistance, resulting in a lightweight overall design, fewer sealing components, and convenient maintenance. The cooling medium can be either aviation kerosene or water. The former absorbs heat and can participate in downstream combustion, while the latter generates water vapor that can react with unburned fuel to release heat, further improving engine efficiency. The entire solution deeply integrates capillary transport like plant veins and evaporative cooling like animal sweat glands with the aerodynamic structure of aero engines, providing a feasible, economical, and scalable technical approach to breaking through the current limits of film cooling temperature.

[0045] The above are merely preferred embodiments of this utility model and do not limit the patent scope of this utility model. Any equivalent structural transformations made based on the inventive concept of this utility model and the contents of this utility model specification and drawings, or direct / indirect applications in other related technical fields, are included within the patent protection scope of this utility model.

Claims

1. An engine stator vane structure, characterized in that, The engine stator structure includes a blade structure and a housing. The blade structure is circumferentially arranged around a first axis and connected to the housing. The blade structure includes a blade shell, and the interior of the blade shell defines a first flow channel for conveying a cooling medium. At least a portion of the blade shell includes a microporous network, and the microporous network includes a first microporous structure. The first microporous structure communicates with the first flow channel and can guide the cooling medium to the outer surface of the blade shell and evaporate it through capillary action. Wherein, along the thickness direction of the blade structure, the first microporous structure includes a first end and a second end that are relatively distributed. The orthographic projection of the first end on a plane perpendicular to the thickness direction of the blade structure is a first projection, and the orthographic projection of the second end on a plane perpendicular to the thickness direction of the blade structure is a second projection. The second projection is located inside the first projection.

2. The engine stator vane structure according to claim 1, characterized in that, The blade structure has an initial state and a target state. In the initial state, the blade structure has a plurality of through holes that extend along its own thickness direction. In the target state, the through holes are filled by the first microporous structure.

3. The engine stator vane structure according to claim 2, characterized in that, Along the axial direction of the through hole, the diameter of one end of the through hole is larger than that of the other end, so that the first micropore structure filling the through hole is conical.

4. The engine stator vane structure according to claim 2, characterized in that, The microporous network further includes a second microporous structure that covers at least a portion of the blade shell along the extension direction of the blade shell.

5. The engine stator vane structure according to claim 4, characterized in that, The engine stator structure can guide gas along a first direction, which is parallel to the first axis. The blade structure includes a first side and a second side that are distributed opposite to each other along the first direction. The first microporous structure and / or the second microporous structure can guide the cooling medium to the outer surface of the blade shell and evaporate it through capillary action, and form a gas film on the surface of the first side and / or the second side.

6. The engine stator vane structure according to claim 4, characterized in that, The second microporous structure includes micropores, the depth of which ranges from 0.5 mm to 1.5 mm.

7. The engine stator vane structure according to claim 1, characterized in that, The interior of the outer shell is hollow to form a second flow channel, which is used to transport the cooling medium and is connected to the first flow channel.

8. The engine stator vane structure according to claim 7, characterized in that, The engine stator structure further includes an output pipe and an input pipe, both of which are connected to the second flow channel. The input pipe is adapted to introduce the cooling medium into the second flow channel, and the output pipe is adapted to discharge the cooling medium from the second flow channel.

9. The engine stator vane structure according to claim 8, characterized in that, The output pipeline includes a first main pipeline and a plurality of first branches circumferentially distributed around the first axis, wherein the two ends of the first branches are respectively connected to the first main pipeline and the second flow guiding channel; and / or, The input pipeline includes a second main pipeline and a plurality of second branches distributed circumferentially around the first axis, with the two ends of the second branches connected to the second main pipeline and the second flow guide channel, respectively.

10. The engine stator vane structure according to claim 1, characterized in that, The cooling medium includes aviation kerosene or water.

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