Nacelle skin with divergent enhanced heat exchange structure

Abstract

The invention relates to the technical field of aircrafts, in particular to a nacelle skin with a divergent enhanced heat transfer structure, which comprises a skin body, and a plurality of surface structure infinitesimal elements are arranged on the connecting surface of the skin body and a surface structure; the surface structure infinitesimal element comprises a plurality of protrusions, one protrusion is arranged corresponding to the jet flow holes of the flute-shaped pipe, and the other protrusions form a plurality of protrusion layers and are arranged around the protrusions corresponding to the jet flow holes respectively. According to the technical scheme, the technical problem that the heat exchange effect is affected due to the fact that the area, directly acting on the nacelle skin, of hot air sprayed out of the jet flow holes in the prior art is small can be effectively solved.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft skins, and in particular to a nacelle skin with a divergent enhanced heat exchange structure. Background Art

[0002] Aircraft icing has always been an important factor threatening flight safety. Relevant practices and studies have shown that the ice layer on the surface of the aircraft wing will seriously damage the aerodynamic shape of the wing, thereby causing deterioration of flight performance and possibly causing damage to the aircraft. Hot gas deicing is the most commonly used method for aircraft wing deicing. Its basic structure includes: flute, hot gas cavity, hot gas impact hole, jet impact surface, etc. The high-temperature air introduced from the compressor is first introduced into the hot gas cavity through a pressure regulating valve, and then impacts the inside of the deicing surface through the jet hole on the wall of the flute. Driven by the temperature difference between the inner and outer walls, heat is transferred from the inner surface to the outer surface through convection heat transfer, which increases the temperature of the deicing surface. The supercooled droplets will no longer produce condensation nuclei when they hit the surface with a higher temperature, and thus no ice accumulation will form.

[0003] However, the heat exchange area of ​​the hot air ejected from the jet hole directly acting on the nacelle skin is small, which affects the heat exchange effect. Therefore, in order to meet the anti-icing requirements of the engine front compartment, more hot air needs to be consumed.

[0004] Therefore, providing a nacelle skin with a divergent enhanced heat exchange structure that can increase the heat exchange area is a technical problem that needs to be urgently solved by those skilled in the art. Summary of the invention

[0005] The invention discloses a nacelle skin with a divergent enhanced heat exchange structure to solve the technical problem in the related art that the area on which hot air ejected from a jet hole directly acts on the nacelle skin is small, thus affecting the heat exchange effect.

[0006] In order to solve the above problems, the present invention adopts the following technical solutions: A nacelle skin with a divergent enhanced heat exchange structure comprises a skin body, wherein a connection surface between the skin body and the surface structure has a plurality of surface structure micro-elements; The surface structure microelement includes a plurality of protrusions, one of which corresponds to the jet hole arrangement of the flute, and the other protrusions form a plurality of protrusion layers and respectively surround the protrusion arrangement corresponding to the jet hole.

[0007] In some embodiments, any two projection layers have the same number of projections.

[0008] In some embodiments, the protrusions of any two adjacent protrusion layers are arranged alternately.

[0009] In some embodiments, the protrusion is cylindrical, and the height of the protrusion along its own axis is 0.5 times the diameter of the protrusion.

[0010] In some embodiments, the protrusion is cylindrical, and the height of the protrusion along its own axis is the same as the diameter of the protrusion.

[0011] In some embodiments, the protrusion is in a truncated cone shape, and the diameter of the end of the protrusion close to the skin body is larger than the diameter of the end away from the skin body; The height of the protrusion along its own axial direction is 0.3 times the diameter of the larger end face of the protrusion, and the diameter of the larger end face of the protrusion is twice the diameter of the smaller end face.

[0012] In some embodiments, the distances between any two adjacent protrusion layers are equal; the distance between the innermost protrusion layer and the protrusions corresponding to the jet holes is equal to the distance between any two adjacent protrusion layers.

[0013] In some embodiments, the protrusion corresponding to the jet hole and the plurality of protrusion layers satisfy the relationship: P / d=3, Wherein, d is the diameter of the jet hole; P is the distance between any two adjacent protrusion layers, or the distance between the innermost protrusion layer and the protrusion of the corresponding jet hole.

[0014] In some embodiments, the nacelle skin is wrapped around the engine.

[0015] In some aspects, the engine is used in an aircraft.

[0016] The technical solution adopted by the present invention can achieve the following beneficial effects: In the nacelle skin of the present application, after the airflow ejected from the jet hole of the flute tube encounters the middlemost protrusion, the flow direction, speed and pressure will change, which is conducive to the airflow breaking the laminar state and promoting the formation of turbulence. As the airflow continues to flow, several protrusion layers disturb the airflow, causing the airflow to form a more complex flow structure and increase the turbulence of the airflow. High turbulence means that there are a large number of vortices and irregular motions in the fluid, which will continuously change the speed and direction of the fluid, thereby increasing the contact area and contact frequency between the fluid and the skin body. Moreover, under high turbulence conditions, the temperature distribution in the fluid is more uneven, the temperature gradient increases, and heat conduction is enhanced, making it easier for heat to transfer from the high temperature area to the low temperature area, improving the heat exchange efficiency, and thus solving the technical problem in the related art that the hot air ejected from the jet hole directly acts on the nacelle skin with a small area, affecting the heat exchange effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0018] Figure 1 The following are some examples of the state of the nacelle skin of the present invention. Figure 1 ; Figure 2 yes Figure 1 The enlarged view of point A in the middle; Figure 3 The following are some examples of the state of the nacelle skin of the present invention. Figure 2 ; Figure 4 yes Figure 3 The enlarged view of point B in the middle; Figure 5 The following are some examples of the state of the nacelle skin of the present invention. Figure 3 ; Figure 6 yes Figure 5 Enlarged view of point C in the middle; Figure 7 is a top view of the nacelle skin of the present invention; Figure 8 yes Figure 7 The enlarged view of point D in the middle; Fig. 9 It is a front view of the flute.

[0019] In the figure: 100-skin body, 110-surface structure microelement, 111-protrusion, 120-protrusion layer; 200- flute, 210- jet hole. DETAILED DESCRIPTION

[0020] To make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be described in detail below. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other implementation methods obtained by ordinary technicians in this field without creative work belong to the scope of protection of the present invention.

[0021] The terms "first", "second", etc. in the specification and claims of the present application are used to distinguish similar objects, and are not used to describe a specific order or sequence. It should be understood that the data used in this way can be interchangeable under appropriate circumstances, so that the embodiments of the present application can be implemented in an order other than those illustrated or described here, and the objects distinguished by "first", "second", etc. are generally of one type, and the number of objects is not limited. For example, the first object can be one or more. In addition, "and / or" in the specification and claims represents at least one of the connected objects, and the character " / " generally indicates that the objects associated with each other are in an "or" relationship.

[0022] In each embodiment of the present application, "proximal end" and "distal end" refer to the position of each component relative to the user in the use environment, wherein the end closer to the user is designated as the "proximal end" and the end farther from the user is designated as the "distal end".

[0023] The applicant found in use that the existing hot air ejected from the jet hole 210 has a low turbulence after contacting the nacelle skin, resulting in insufficient diffusion, which in turn reduces the heat exchange area and affects the heat exchange effect. Therefore, in order to meet the anti-icing requirements of the engine front compartment, more hot air needs to be consumed.

[0024] The following is combined with Figures 1 to 9 , a nacelle skin with a divergent enhanced heat exchange structure provided in the present application is described in detail through specific embodiments and application scenarios.

[0025] Some embodiments of the present application provide a nacelle skin having a divergent enhanced heat exchange structure, such as Figure 1 , Figure 3 , Figure 5 and Figure 7 As shown, a skin body 100 is included, and the skin body 100 is covered on the surface structure.

[0026] As a preferred embodiment of the present invention, during the installation and matching of the skin body 100 and the surface structure, a plurality of installation holes are firstly processed on the front edge of the skin body 100, and then the surface structure is knocked into the installation holes by means of interference fit, thereby achieving the installation of the skin body 100 and the surface structure.

[0027] In this embodiment, the skin body 100 may be coated with thermally conductive silicone on the connection surface with the surface structure, so that there is no air between the skin body 100 and the surface structure, thereby reducing the additional thermal resistance caused by processing.

[0028] The skin body 100 may be made of a variety of materials, such as aluminum alloy, titanium alloy, carbon fiber composite material, etc. Of course, the material of the skin body 100 is not limited to the above three materials, and may also be other materials.

[0029] like Figure 1-Figure 8 As shown, the connection surface between the skin body 100 and the surface structure has a plurality of surface structure micro-elements 110, and each surface structure micro-element 110 corresponds to a jet hole 210 of the flute 200. The surface structure micro-element 110 can change the flow direction, speed and pressure of the airflow to increase the turbulence of the airflow, which is beneficial to increase the heat exchange area. In addition, by adopting a method of corresponding one jet hole 210 to one surface structure micro-element 110, the airflow ejected from each jet hole 210 can contact the surface structure micro-element 110, thereby improving the heat exchange efficiency of the skin body 100. Compared with the nacelle skin in the prior art, the skin body 100 in this embodiment has a higher temperature increase under the premise of the same air consumption.

[0030] In this embodiment, the plurality of jet holes 210 of the flute tube 200 are arranged in a plurality of rows, such as Fig. 9 As shown, any two adjacent columns of jet holes 210 are arranged alternately. Therefore, the arrangement of the plurality of surface structure micro-elements 110 and the jet holes 210 is the same, so that one jet hole 210 can correspond to one surface structure micro-element 110 .

[0031] like Figure 2 , Figure 4 , Figure 6 and Figure 8 As shown, the surface structure microelement 110 includes a plurality of protrusions 111 , wherein one protrusion 111 is arranged corresponding to the jet hole 210 of the flute 200 , and the other protrusions 111 form a plurality of protrusion layers 120 , and are arranged respectively around the protrusions 111 corresponding to the jet hole 210 .

[0032] It should be noted that the orthographic projections of the plurality of protrusion layers 120 along the axial direction of the protrusion 111 are all circular, and the diameters of the plurality of protrusion layers 120 are different, forming a layered surrounding structure.

[0033] When the airflow ejected from the jet hole 210 of the flute 200 encounters the middle protrusion 111, the flow direction, speed and pressure will change, which is conducive to breaking the laminar flow state and promoting the formation of turbulence. As the airflow continues to flow, the plurality of protrusion layers 120 disturb the airflow, causing the airflow to form a more complex flow structure and increase the turbulence of the airflow.

[0034] High turbulence means that there are a large number of vortices and irregular motions in the fluid, which will constantly change the speed and direction of the fluid, thereby increasing the contact area and contact frequency between the fluid and the skin body 100. In addition, under high turbulence conditions, the temperature distribution in the fluid is more uneven, the temperature gradient increases, and heat conduction is enhanced, making it easier for heat to transfer from the high temperature area to the low temperature area, thereby improving the heat exchange efficiency.

[0035] In this embodiment, the number of the protruding layers 120 may be 2, 3, 4 or other numbers. In this embodiment, 3 protruding layers 120 are preferably provided after calculation and experiment.

[0036] In this embodiment, the number of the protrusions 111 may be 5, 6, 7, 8, 9 or other numbers. In this embodiment, 8 protrusions 111 are preferably provided after calculation and experiment.

[0037] In some embodiments, Figure 4 As shown, the protrusion 111 is cylindrical, and the height of the protrusion 111 along its own axis is 0.5 times the diameter of the protrusion 111. In the process of airflow diffusing to the surroundings, the height of the protrusion 111 along its own axis is 0.5 times the diameter of the protrusion 111, which can ensure that the airflow generates sufficient vortices in the process of passing through the protrusion 111. If the height of the protrusion 111 is insufficient, the generation and maintenance of the vortex will be limited, thereby affecting the improvement of turbulence. In addition, if the height of the protrusion 111 is too low, the airflow may lack sufficient disturbance and mixing when passing through the protrusion 111, becoming more gentle, resulting in a decrease in the turbulence of the airflow.

[0038] In some embodiments, Figure 2 As shown, the protrusion 111 is cylindrical, and the height of the protrusion 111 along its own axis is the same as the diameter of the protrusion 111. In the process of airflow diffusing to the surroundings, the height of the protrusion 111 along its own axis is the same as the diameter of the protrusion 111, which can ensure that the airflow does not consume too much energy during the flow. If the protrusion 111 is too high, the height of the protrusion 111 increases the obstacle to the flow of the fluid, so that the fluid needs to consume more energy to pass through. This increase in resistance may cause the fluid speed to slow down, and even cause stagnation or backflow of the fluid flow in some cases.

[0039] In summary, in the embodiment where the protrusions 111 are cylindrical, a protrusion 111 with a height of 0.5 times the diameter is used, sacrificing a certain degree of turbulence to minimize the energy consumed by the airflow passing through the protrusion layer 120. A protrusion 111 with the same height and diameter is used, increasing a certain amount of energy consumption to maximize the turbulence of the airflow.

[0040] In some embodiments, Figure 6As shown, the protrusion 111 can also be in a truncated cone shape, and the diameter of the end of the protrusion 111 close to the skin body 100 is larger than the diameter of the end away from the skin body 100; the height of the protrusion 111 along its own axial direction is 0.3 times the diameter of the larger end face of the protrusion 111, and the diameter of the larger end face of the protrusion 111 is 2 times the diameter of the smaller end face. In the process of airflow spreading to the surroundings, the side of the truncated cone-shaped protrusion 111 will make the airflow more turbulent and complex, thereby greatly increasing the turbulence of the airflow.

[0041] When the cylindrical protrusion 111 and the truncated cone protrusion 111 have the same height, the turbulence of the airflow generated by the truncated cone protrusion 111 is significantly greater than that of the cylindrical protrusion 111. However, if the turbulence of the airflow is too high, the impact on the skin body 100 will be stronger, which may cause vibration. Therefore, by setting the diameter of the protrusion 111 to 0.3 times the diameter of the larger end face, the diameter of the larger end face of the protrusion 111 is twice the diameter of the smaller end face, which can effectively solve the above problem and avoid the occurrence of excessive turbulence of the airflow.

[0042] like Figure 2 , Figure 4 , Figure 6 and Figure 8 As shown, any two protrusion layers 120 have the same number of protrusions 111. By having any two protrusion layers 120 have the same number of protrusions 111, the multiple protrusion layers 120 form a uniform airflow distribution area, and the airflow can more evenly cover a larger area of ​​the skin body 100 during the diffusion process, thereby avoiding local overheating or insufficient cooling.

[0043] like Figure 2 , Figure 4 , Figure 6 and Figure 8 As shown, the protrusions 111 of any two adjacent protrusion layers 120 are arranged alternately. In the process of diffusion, the airflow will gradually pass through the multiple protrusion layers 120, and in the process of the airflow passing through the multiple protrusion layers 120, the protrusions 111 of any two adjacent protrusion layers 120 are arranged alternately, which can more effectively disturb the airflow, so that the airflow forms a more complex flow on the surface of the skin body 100, further increasing the turbulence of the airflow.

[0044] In this embodiment, among the three protrusions 111 alternately arranged on any two adjacent protrusion layers 120, the angles between one protrusion 111 of one protrusion layer 120 and two adjacent protrusions 111 of the other protrusion layer 120 are equal, which not only enables the airflow to form a more complex flow when passing through the protrusion layers 120, but also makes the airflow flow more uniform, thereby covering a larger area of ​​the skin body 100.

[0045] like Figure 2 , Figure 4 , Figure 6 and Figure 8 As shown, the distance between any two adjacent convex layers 120 is equal, and the distance between the innermost convex layer 120 and the convexity 111 corresponding to the jet hole 210 is equal to the distance between any two adjacent convex layers 120. After the airflow is ejected from the jet hole 210 of the flute 200, it hits the middle convexity 111 and then diffuses to the surroundings. After each airflow diffuses over a fixed area, it passes through the convex layer 120, further allowing the airflow to more evenly cover a larger area of ​​the skin surface during the diffusion process, thereby avoiding the occurrence of local overheating or insufficient cooling.

[0046] Specifically, Figure 8 and Fig. 9 As shown, the protrusion 111 corresponding to the jet hole 210 and the plurality of protrusion layers 120 satisfy the relationship: P / d=3, Wherein, d is the diameter of the jet hole 210 ; P is the distance between any two adjacent protrusion layers 120 , or the distance between the innermost protrusion layer 120 and the protrusion 111 corresponding to the jet hole 210 .

[0047] When the aperture of the jet hole 210 and the distance between two adjacent protrusion layers 120, or the distance between the innermost protrusion layer 120 and the protrusion 111 corresponding to the jet hole 210 satisfies the above relationship, the airflow ejected from the jet hole 210 can cover the largest area of ​​the skin body 100 and has the highest heat exchange efficiency. Compared with the nacelle skin in the prior art, under the same temperature condition, the air consumption of the nacelle skin of this embodiment is significantly reduced; under the same air consumption condition, the temperature of the nacelle skin of this embodiment is significantly increased.

[0048] In summary, the nacelle skin of this embodiment achieves efficient anti-icing effect with a smaller bleed air volume by setting reasonable surface structure micro-element 110, saving precious hot air of the engine and reducing the load of the engine. The nacelle skin adopted in this embodiment is an optimized configuration obtained through experiments and numerical calculations, the purpose of which is to enhance heat exchange. This design can maximize the turbulence on the one hand, and the heat exchange area on the other hand. It is an optimization result obtained through fluid mechanics, heat transfer experiments and numerical calculations, which can play a good role in enhancing the heat exchange effect, thereby improving the performance of the anti-icing system.

[0049] Some embodiments of the present application also provide an engine, wherein the nacelle skin is covered on the engine.

[0050] Some embodiments of the present application also provide an aircraft having the above-mentioned engine.

[0051] It should be noted that the aircraft may be a drone, a fixed-wing aircraft, etc., which is not limited in this embodiment.

[0052] It should be noted that, in this article, the terms "include", "comprises" or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, an element defined by the sentence "comprises a ..." does not exclude the existence of other identical elements in the process, method, article or device including the element.

[0053] In addition, it should be noted that the scope of the methods and devices in the embodiments of the present application is not limited to performing functions in the order shown or discussed, and may also include performing functions in a substantially simultaneous manner or in a reverse order according to the functions involved. For example, the described methods may be performed in an order different from that described, and various steps may be added, omitted, or combined. In addition, features described with reference to certain examples may be combined in other examples.

[0054] The above description is only a specific implementation mode of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

Claims

1. A nacelle skin with a divergent enhanced heat exchange structure, characterized in that: It comprises a skin body, wherein the connection surface between the skin body and the surface structure has a plurality of surface structure micro-elements; The surface structure microelement includes a plurality of protrusions, one of which is arranged corresponding to the jet hole of the flute, and the other protrusions form a plurality of protrusion layers and respectively surround the protrusion arrangement corresponding to the jet hole.

2. The nacelle skin with a divergent enhanced heat exchange structure according to claim 1, characterized in that: The numbers of the protrusions in any two of the protrusion layers are the same.

3. The nacelle skin with a divergent enhanced heat exchange structure according to claim 1, characterized in that: The protrusions of any two adjacent protrusion layers are arranged alternately.

4. The nacelle skin with a divergent enhanced heat exchange structure according to claim 1, characterized in that: The protrusion is cylindrical, and the height of the protrusion along its own axial direction is 0.5 times the diameter of the protrusion.

5. The nacelle skin with a divergent enhanced heat exchange structure according to claim 1, characterized in that: The protrusion is cylindrical, and the height of the protrusion along its own axial direction is the same as the diameter of the protrusion.

6. The nacelle skin with a divergent enhanced heat exchange structure according to claim 1, characterized in that: The protrusion is in a truncated cone shape, and the diameter of the end of the protrusion close to the skin body is larger than the diameter of the end away from the skin body; The height of the protrusion along its own axial direction is 0.3 times the diameter of the larger end surface of the protrusion, and the diameter of the larger end surface of the protrusion is twice the diameter of the smaller end surface.

7. The nacelle skin with a divergent enhanced heat exchange structure according to any one of claims 1 to 6, characterized in that: The distance between any two adjacent protrusion layers is equal; the distance between the innermost protrusion layer and the protrusion corresponding to the jet hole is equal to the distance between any two adjacent protrusion layers.

8. The nacelle skin with a divergent enhanced heat exchange structure according to claim 7, characterized in that: The protrusion corresponding to the jet hole and the plurality of protrusion layers satisfy the relationship: P / d=3, In the formula, d is the diameter of the jet hole; P is the distance between any two adjacent protrusion layers, or the distance between the innermost protrusion layer and the protrusion corresponding to the jet hole.

9. The nacelle skin with a divergent enhanced heat exchange structure according to claim 1, characterized in that: The nacelle skin covers the engine.

10. The nacelle skin with a divergent enhanced heat exchange structure according to claim 9, characterized in that: The engine is applied to an aircraft.

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