Mixed-flow structure of a turbine engine based on a three-period minimal surface and a turbine engine

Abstract

The present invention belongs to the technical field of turbine engines, and discloses a mixed flow structure of a turbine engine and a turbine engine based on triply periodic minimal surfaces. A triply periodic minimal surface core body is clamped between an outer pipe and an inner pipe. The triply periodic minimal surface core body forms mutually staggered but non-communicating first network channels and second network channels in three-dimensional space. A partition pipe is provided at the head end of the triply periodic minimal surface core body. A first annular cavity for accessing a first fluid is formed between the partition pipe and the outer pipe, and a second annular cavity for accessing a second fluid is formed between the partition pipe and the inner pipe. A first sealing plate is provided at the entrance of the first network channel located at the head end of the triply periodic minimal surface core body and within the first annular cavity, and a second sealing plate is provided at the entrance of the second network channel located at the head end of the triply periodic minimal surface core body and within the second annular cavity. The present invention further improves the mixing effect of combustible gas and cold air on the premise of minimizing the increase in the weight of the engine.

Description

Technical Field

[0001] The present invention belongs to the technical field of turbine engines, and particularly relates to a mixed-flow structure of a turbine engine based on triply periodic minimal surfaces and a turbine engine. Background Art

[0002] The working principle of a turbine engine is to mix combustible gas with cold air and then introduce it into the afterburner to optimize the energy release process of combustion products, thereby enhancing the thrust and overall efficiency of the engine. In this process, the degree of uniformity of the mixture of combustible gas and cold air has become a key factor restricting the further improvement of engine performance. An ideal mixing state can not only promote the full combustion of combustion products in the afterburner, but also effectively increase the heat release, thereby increasing the thrust output and enhancing the comprehensive performance of the engine.

[0003] In the design of the mixing structure of combustible gas and cold air in a turbine engine, the prior art mainly relies on a lobe mixer to achieve effective mixing of the two gases. Specifically, the combustible gas flows through the inner duct of the lobe mixer, while the cold air flows through the outer duct. The unique structural design of the lobe mixer can guide the combustible gas in the inner duct to interact with the cold air in the outer duct, thereby achieving a preliminary mixing effect.

[0004] However, in practical applications, the lobe mixer itself has certain limitations. The mixing effect of the lobe mixer largely depends on the number of "lobes": the more the number of lobes, the larger the contact area between the two gases after passing through the lobe mixer, and the better the mixing effect. However, in actual use, the number of "lobes" cannot be increased indefinitely. Because as the number of lobes increases, the overall weight of the engine will also increase accordingly. Under the condition of a limited number of "lobes", the contact surface between the two gases that the lobe mixer can create is limited, resulting in a still limited mixing effect between the combustible gas and the cold air. Therefore, how to further improve the mixing effect of combustible gas and cold air on the premise of minimizing the increase in engine weight has become an urgent problem to be solved in the current development of turbine engine technology. Summary of the Invention

[0005] Aiming at the problems existing in the prior art, the present invention provides a mixed-flow structure of a turbine engine based on triply periodic minimal surfaces and a turbine engine, which further improves the mixing effect of combustible gas and cold air on the premise of minimizing the increase in engine weight.

[0006] To solve the above technical problems, the present invention is realized through the following technical solutions:

[0007] According to a first aspect of the present invention, a mixed flow structure of a turbine engine based on a triply periodic minimal surface is provided, including an outer tube and an inner tube nested in the outer tube. A triply periodic minimal surface core is clamped between the outer tube and the inner tube. The triply periodic minimal surface core forms mutually staggered but non-connected first network channels and second network channels in three-dimensional space.

[0008] A first distance is reserved between the head end of the triply periodic minimal surface core and the head end of the outer tube. A separator tube is provided at the head end of the triply periodic minimal surface core. A first annular cavity for accessing a first fluid is formed between the separator tube and the outer tube, and a second annular cavity for accessing a second fluid is formed between the separator tube and the inner tube.

[0009] A first sealing plate is provided at the entrance of the first network channel located at the head end of the triply periodic minimal surface core and within the first annular cavity, and a second sealing plate is provided at the entrance of the second network channel located at the head end of the triply periodic minimal surface core and within the second annular cavity.

[0010] In a possible implementation manner of the first aspect, the triply periodic minimal surface core is any one of a Gyroid surface, a Diamond surface, a Schwarz P Surface, and a Schwarz D Surface.

[0011] In a possible implementation manner of the first aspect, when the triply periodic minimal surface core is a Gyroid surface, the distance between the inner wall of the outer tube and the outer wall of the inner tube is 40% - 60% of the inner diameter of the afterburner chamber of the turbine engine, and the height of the unit cell of the Gyroid surface is 1 / 8 - 1 / 16 of the distance between the inner wall of the outer tube and the outer wall of the inner tube.

[0012] In a possible implementation manner of the first aspect, the wall thickness of the Gyroid surface is 1 mm - 4 mm.

[0013] In a possible implementation manner of the first aspect, the first distance is 5 - 10 times the height of the unit cell of the Gyroid surface.

[0014] In a possible implementation manner of the first aspect, the tail end of the triply periodic minimal surface core is located within the outer tube, and a second distance is reserved between the tail end of the triply periodic minimal surface core and the tail end of the outer tube.

[0015] In a possible implementation manner of the first aspect, the second distance is 100 mm - 300 mm.

[0016] In a possible implementation manner of the first aspect, the outer tube, the inner tube, and the separator tube are all coaxial circular tubes.

[0017] In a possible implementation of the first aspect, the ratio of the distance between the outer wall of the partition pipe and the inner wall of the outer pipe to the distance between the inner wall of the partition pipe and the outer wall of the inner pipe is equal to the ratio of the first fluid flow rate to the second fluid flow rate.

[0018] According to the second aspect of the present invention, there is provided a turbine engine comprising the turbine engine mixing flow structure based on triply periodic minimal surfaces as described above.

[0019] Compared with the prior art, the present invention has at least the following beneficial effects:

[0020] For the turbine engine mixing flow structure based on triply periodic minimal surfaces provided by the present invention, through the unique three-dimensional staggered network channel design of the triply periodic minimal surface core, the combustible gas and the cold air flow along their respective paths inside the triply periodic minimal surface core and do not directly meet until they flow out of the triply periodic minimal surface core and then intersect with each other. By utilizing the strong turbulent shear layer formed by the differences in flow velocity, direction and temperature, the efficient mixing between the two gases is greatly promoted. Compared with the lobe mixer, the mixing flow structure of the present invention can provide a more sufficient mixing effect under the same weight, thereby improving the energy release process of the combustion products and further enhancing the thrust and overall efficiency of the engine. The structural characteristics of the triply periodic minimal surface core enable it to achieve a smaller weight while ensuring high mixing performance. Specifically, due to the dense and staggered layout of the first network channel and the second network channel in three-dimensional space, there is no need to rely on a large number of "lobes" like the lobe mixer to increase the contact area, thus avoiding the increase in the engine weight caused by increasing the number of "lobes", making the mixing flow structure of the present invention more in line with the requirements of the turbine engine for lightweight design. In summary, the present invention further improves the mixing effect of the combustible gas and the cold air on the premise of minimizing the increase in the engine weight.

[0021] To make the above objects, features and advantages of the present invention more obvious and understandable, the following specific preferred embodiments are given and described in detail in conjunction with the accompanying drawings as follows. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the technical solutions in the specific embodiments of the present invention, the following will briefly introduce the drawings required for the description of the specific embodiments. Obviously, the following drawings are some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0023] Figure 1 It is a schematic diagram of the overall structure of a turbine engine mixing flow structure based on triply periodic minimal surfaces of the present invention;

[0024] Figure 2Front view of a mixed-flow structure of a turbine engine based on triply periodic minimal surfaces according to the present invention;

[0025] Figure 3 Schematic diagram of a partially enlarged structure of a mixed-flow structure of a turbine engine based on triply periodic minimal surfaces according to the present invention from the front-end perspective;

[0026] Figure 4 Schematic diagram of a partially enlarged structure of a mixed-flow structure of a turbine engine based on triply periodic minimal surfaces according to the present invention from the rear-end perspective.

[0027] In the figure: 1, outer tube; 2, inner tube; 3, triply periodic minimal surface core; 31, first network channel; 32, second network channel; 4, partition tube; 41, first annular cavity; 42, second annular cavity; 51, first sealing plate; 52, second sealing plate. Detailed implementation manners

[0028] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings. Apparently, the described embodiments are some, but not all, of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0029] Combined with Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown in

[0030] It should be noted that the leading ends of the three-period minimal surface core body 3 and the outer tube 1 both face the oncoming flow direction; the first fluid and the second fluid are respectively any one of combustible gas and cold air. In other words, when the first fluid is combustible gas, the second fluid is cold air; when the first fluid is cold air, the second fluid is combustible gas.

[0031] Specifically, the outer tube 1 serves as an external support structure, and its diameter is determined according to the overall design requirements of the turbine engine. The inner tube 2 is located inside the outer tube 1, and a certain annular space is formed between the two to provide an installation space for the three-period minimal surface core body 3. The three-period minimal surface core body 3 utilizes the complex geometric characteristics of the three-period minimal surface to construct non-connected first network channels 31 and second network channels 32 that intersect with each other in three-dimensional space, greatly increasing the contact area between the first fluid and the second fluid at the tail-end outlet of the three-period minimal surface core body 3, thereby promoting the improvement of the mixing efficiency. It should be noted that the material of the three-period minimal surface core body 3 needs to consider strength, heat resistance, and lightweight requirements. Exemplarily, the three-period minimal surface core body 3 is made of a high-temperature alloy or a ceramic matrix composite material.

[0032] At the leading end of the three-period minimal surface core body 3, a partition tube 4 is provided. The partition tube 4 further divides the annular space between the outer tube 1 and the inner tube 2 into two independent annular cavities, namely the first annular cavity 41 and the second annular cavity 42. The first annular cavity 41 is used to access the first fluid (such as combustible gas), while the second annular cavity 42 is used to access the second fluid (such as cold air). It should be understood that the partition tube 4 needs to ensure the effective isolation of the first annular cavity 41 and the second annular cavity 42, and at the same time facilitate the smooth access of the fluid.

[0033] In order to control the flow paths of the first fluid and the second fluid, a first sealing plate 51 is provided at the position corresponding to the entrance of the first network channel 31 in the first annular cavity 41, and a second sealing plate 52 is provided at the position corresponding to the entrance of the second network channel 32 in the second annular cavity 42. That is to say, the first fluid entering the first annular cavity 41 can only enter the second network channel 32 from the entrance of the second network channel 32, and the second fluid entering the second annular cavity 42 can only enter the first network channel 31 from the entrance of the first network channel 31. After the first fluid and the second fluid enter their respective corresponding network channels, due to the structural characteristics of the three-period minimal surface core body 3 (constructing non-connected first network channels 31 and second network channels 32 that intersect with each other in three-dimensional space), the first fluid and the second fluid will fully contact at the tail end of the three-period minimal surface core body 3 and form a strong turbulent shear layer, thereby achieving efficient mixing.

[0034] Specifically, during the operation of the engine, the first fluid is introduced into the first annular cavity 41 and then enters the second network channel 32 through the inlet of the second network channel 32. At the same time, the second fluid is introduced into the second annular cavity 42 and enters the first network channel 31 through the inlet of the first network channel 31. Due to the special design of the triply periodic minimal surface core 3, the first network channel 31 and the second network channel 32 are arranged in a staggered pattern in three-dimensional space. The first fluid and the second fluid flow along their respective paths inside the triply periodic minimal surface core 3 and do not directly meet until they flow out from the respective corresponding outlets at the tail end of the triply periodic minimal surface core 3. At the tail end of the triply periodic minimal surface core 3, since the outlets of the first network channel 31 and the second network channel 32 are also staggered. Therefore, when the first fluid flows out from the outlet of the second network channel 32, it will encounter the second fluid flowing out from the adjacent outlet of the first network channel 31. Due to the differences in the flow rates, directions, and temperatures of the first fluid and the second fluid, a strong turbulent shear layer will be formed between them, and the turbulent shear layer greatly promotes the efficient mixing between the first fluid and the second fluid. Compared with the traditional lobe mixer, due to the characteristic that the first network channel 31 and the second network channel 32 are arranged in a staggered pattern in three-dimensional space in the triply periodic minimal surface core 3, the denser the first network channel 31 and the second network channel 32 are, the lighter the weight of the triply periodic minimal surface core 3 is. Therefore, while maintaining the efficient mixing performance, the entire mixing structure can effectively control the weight of the engine, meeting the requirements of the turbine engine for lightweight design.

[0035] In an implementable manner, the triply periodic minimal surface core 3 is any one of a Gyroid surface, a Diamond surface, a Schwarz P Surface, and a Schwarz D Surface.

[0036] It should be understood that the Gyroid surface is a triple-periodic minimal surface structure proposed by physicist Alan Schoen in 1970. The Gyroid surface has high symmetry and continuous non-crossing characteristics. The Diamond surface also belongs to the triple-periodic minimal surface structure and has the advantages of a large specific surface area and a light weight. The Schwarz P Surface is a minimal surface with regular boundaries and rich spatial variations. The Schwarz D Surface is also a minimal surface with regular boundaries. Similar to the Schwarz P Surface, its spatial structure also shows rich variations.

[0037] Preferably, when the three - period minimal surface core 3 is a Gyroid surface, the distance between the inner wall of the outer tube 1 and the outer wall of the inner tube 2 is 40% - 60% of the inner diameter of the after - combustion chamber of the turbine engine, and the unit cell height of the Gyroid surface is 1 / 8 - 1 / 16 of the distance between the inner wall of the outer tube 1 and the outer wall of the inner tube 2.

[0038] Specifically, the distance between the inner wall of the outer tube 1 and the outer wall of the inner tube 2 is set to be 40% - 60% of the inner diameter of the after - combustion chamber of the turbine engine, and the unit cell height of the Gyroid surface is set to be 1 / 8 - 1 / 16 of the distance between the inner wall of the outer tube 1 and the outer wall of the inner tube 2. The coordinated limitation of the distance between the inner wall of the outer tube 1 and the outer wall of the inner tube 2, and the unit cell height of the Gyroid surface makes the first network channels 31 and the second network channels 32 of the three - period minimal surface core 3 denser. As a result, the first fluid and the second fluid come into contact more fully at the corresponding channel outlets at the tail end of the three - period minimal surface core 3, and this sufficient contact helps the first fluid and the second fluid to mix more uniformly and fully.

[0039] Preferably, the wall thickness of the Gyroid surface is 1 mm - 4 mm. When manufacturing the three - period minimal surface core 3 of the Gyroid surface type, the wall thickness is one of the key factors affecting the processing difficulty and cost. An overly thin wall thickness will cause the three - period minimal surface core 3 to be fragile or deformed during the processing, while an overly thick wall thickness will increase the material consumption and weight. Therefore, the wall thickness range of 1 mm - 4 mm ensures the processing convenience while also meeting the requirement of lightweight for the three - period minimal surface core 3.

[0040] In an implementable manner, the first distance from the head end of the three - period minimal surface core 3 to the head end of the outer tube 1 is 5 - 10 times the unit cell height of the Gyroid surface. Specifically, in a turbine engine, the first fluid (such as combustible gas) and the second fluid (such as cold air) are mixed through a mixing structure. When these fluids impact their respective corresponding sealing plates, a back - flow vortex will be formed. If the first distance is too small, the geometric size of the back - flow vortex will be larger, which will lead to an increase in the loss of fluid kinetic energy, thus reducing the performance of the turbine engine. And an overly long first distance will increase the weight of the structure, thus affecting the overall performance of the engine. Therefore, by reasonably setting the first distance within the range of 5 - 10 times the unit cell height of the Gyroid surface, the geometric size of the back - flow vortex can be reduced, and the loss of fluid kinetic energy can be decreased.

[0041] In an implementable manner, the tail end of the three - period minimal surface core 3 is located inside the outer tube 1, and a second distance is reserved from the tail end of the three - period minimal surface core 3 to the tail end of the outer tube 1. Preferably, the second distance from the tail end of the three - period minimal surface core 3 to the head end of the outer tube 1 is 100 mm - 300 mm.

[0042] Specifically, in order to ensure the sufficient mixing of the first fluid (such as combustible gas) and the second fluid (such as cold air), a second distance is reserved between the tail end of the triply periodic minimal surface core 3 and the tail end of the outer tube 1. The second distance ensures that the two fluids have sufficient mixing time in the mixing structure after being ejected from their respective corresponding duct outlets, while avoiding excessive overall weight caused by too large a distance.

[0043] In one implementable manner, the outer tube 1, the inner tube 2, and the partition tube 4 are all circular tubes arranged coaxially. The coaxial circular tube design can adapt to the geometric shapes of the corresponding components to be connected upstream and downstream of the mixing structure of the turbine engine, facilitating docking and installation.

[0044] In one implementable manner, the ratio of the distance between the outer wall of the partition tube 4 and the inner wall of the outer tube 1 to the distance between the inner wall of the partition tube 4 and the outer wall of the inner tube 2 is equal to the ratio of the flow rate of the first fluid to the flow rate of the second fluid. Specifically, in a turbine engine, the flow rates of the first fluid (such as combustible gas) and the second fluid (such as cold air) are often different. By designing the distance ratio between the partition tube 4 and the outer tube 1 and the inner tube 2, it can be ensured that the flow resistance of these two fluids in the mixing structure matches their flow rates. The fluid with a large flow rate flows in a wider space and is less obstructed, thereby improving the fluid dynamics performance of the entire engine system.

[0045] The embodiment of the present invention provides a turbine engine, which includes a turbine engine mixing structure based on a triply periodic minimal surface in the above-mentioned implementation manner. Through the turbine engine mixing structure based on a triply periodic minimal surface in the above-mentioned implementation manner, the mixing effect of combustible gas and cold air is further improved on the premise of minimizing the increase in the weight of the engine.

[0046] Specifically, the turbofan engine mainly consists of a compressor, a front combustion chamber, a turbine, a rear combustion chamber, and a tail nozzle. Among them, a turbofan engine mixing structure based on a triply periodic minimal surface is provided at the front end of the rear combustion chamber. The first annular cavity 41 is used to receive combustible gas from the combustion chamber, and the second annular cavity 42 is used to receive cold air from the compressor. During the operation of the engine, the combustible gas generated by the front combustion chamber is introduced into the first annular cavity 41, and then enters the second network duct 32 through the inlet of the second network duct 32. The cold air is introduced from the compressor into the second annular cavity 42 and enters the first network duct 31 through the inlet of the first network duct 31. The combustible gas and the cold air flow along their respective paths inside the triply periodic minimal surface core 3 and do not meet directly until the combustible gas and the cold air flow out from the respective corresponding outlets at the tail end of the triply periodic minimal surface core 3. At the tail end of the triply periodic minimal surface core 3, since the outlets of the first network duct 31 and the second network duct 32 are also staggered. Therefore, when the combustible gas flows out from the outlet of the second network duct 32, it will encounter the cold air flowing out from the adjacent outlet of the first network duct 31. Due to the differences in the flow velocity, direction, and temperature of the combustible gas and the cold air, a strong turbulent shear layer will be formed between them, and the turbulent shear layer greatly promotes the efficient mixing between the combustible gas and the cold air.

[0047] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "upper", "lower", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present invention.

[0048] In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one of such features. In the description of the present invention, the meaning of "a plurality" is at least two, such as two, three, etc., unless otherwise specifically and clearly defined.

[0049] In the present invention, unless otherwise clearly specified and limited, the terms "connected" and "coupled" should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or integrated; it may be a mechanical connection, an electrical connection, or communication with each other; it may be directly connected, or indirectly connected through an intermediate medium, and may be the internal communication of two elements or the interaction relationship between two elements, unless otherwise clearly limited. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0050] In the present invention, unless otherwise explicitly specified or limited, the first feature being "on" or "under" the second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, the first feature being "above", "over" and "on top of" the second feature may mean that the first feature is directly above or obliquely above the second feature, or merely indicates that the horizontal height of the first feature is higher than that of the second feature. The first feature being "under", "beneath" and "underneath" the second feature may mean that the first feature is directly below or obliquely below the second feature, or merely indicates that the horizontal height of the first feature is less than that of the second feature.

[0051] In the present invention, the terms "an embodiment", "some embodiments", "example", "specific example", or "some examples", etc. mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, without contradiction, those skilled in the art can combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples.

[0052] Finally, it should be noted that the above-described embodiments are only specific embodiments of the present invention, used to illustrate the technical solutions of the present invention, rather than to limit it. The protection scope of the present invention is not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that any person skilled in the art within the technical scope disclosed by the present invention can still modify the technical solutions recorded in the foregoing embodiments, or can easily think of changes, or make equivalent replacements for some of the technical features; and these modifications, changes or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention, and should all be covered by the protection scope of the present invention.

Claims

1. A mixed flow structure of a turbine engine based on a three - period minimal surface, characterized in that, It includes an outer tube (1) and an inner tube (2) nested in the outer tube (1). A three-period minimal surface core (3) is clamped between the outer tube (1) and the inner tube (2). The three-period minimal surface core (3) forms mutually staggered but non-connected first network channels (31) and second network channels (32) in three-dimensional space. A first distance is reserved between the head end of the three-period minimal surface core (3) and the head end of the outer tube (1). A separating tube (4) is provided at the head end of the three-period minimal surface core (3). A first annular cavity (41) for accessing the first fluid is formed between the separating tube (4) and the outer tube (1). A second annular cavity (42) for accessing the second fluid is formed between the separating tube (4) and the inner tube (2). A first sealing plate (51) is provided at the entrance of the first network channel (31) located at the head end of the three-period minimal surface core (3) and within the first annular cavity (41). A second sealing plate (52) is provided at the entrance of the second network channel (32) located at the head end of the three-period minimal surface core (3) and within the second annular cavity (42).

2. The mixed-flow structure of a turbine engine based on a three-period minimal surface according to claim 1, wherein The three-period minimal surface core (3) is any one of a Gyroid surface, a Diamond surface, a Schwarz P Surface, and a Schwarz D Surface.

3. The mixed flow structure of a turbine engine based on a three - period minimal surface according to claim 2, characterized in that, When the three-period minimal surface core (3) is a Gyroid surface, the distance between the inner wall of the outer tube (1) and the outer wall of the inner tube (2) is 40% - 60% of the inner diameter of the afterburner chamber of the turbine engine. The unit height of the Gyroid surface is 1 / 8 - 1 / 16 of the distance between the inner wall of the outer tube (1) and the outer wall of the inner tube (2).

4. A mixed flow structure of a turbine engine based on a three - period minimal surface according to claim 3, characterized in that, The wall thickness of the Gyroid surface is 1 mm - 4 mm.

5. The mixed flow structure of a turbine engine based on a three - period minimal surface according to claim 3, wherein The first distance is 5 - 10 times the unit height of the Gyroid surface.

6. The mixed flow structure of a turbine engine based on a three - period minimal surface according to claim 1, wherein, The tail end of the three-period minimal surface core (3) is located within the outer tube (1), and a second distance is reserved between the tail end of the three-period minimal surface core (3) and the tail end of the outer tube (1).

7. A mixed-flow structure of a turbine engine based on a three-period minimal surface according to claim 6, characterized in that, The second distance is 100 mm - 300 mm.

8. A mixed-flow structure of a turbine engine based on a three-period minimal surface according to claim 1, characterized in that, The outer tube (1), the inner tube (2), and the separating tube (4) are all circular tubes arranged coaxially.

9. A mixed flow structure of a turbine engine based on a three - period minimal surface according to claim 8, characterized in that, The ratio of the distance between the outer wall of the separating tube (4) and the inner wall of the outer tube (1) to the distance between the inner wall of the separating tube (4) and the outer wall of the inner tube (2) is equal to the ratio of the flow rate of the first fluid to the flow rate of the second fluid.

10. A turbine engine, characterized in that, A turbine engine mixed-flow structure based on a three-period minimal surface according to any one of claims 1 to 9 is included.

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