Wing rotating hot air ice preventing and removing structure

Abstract

The invention relates to the technical field of aircrafts, and discloses a wing rotation hot air ice preventing and removing structure which comprises a heat exchange cavity formed in an aircraft wing, and the heat exchange cavity extends in the length direction of the aircraft wing; an air inlet channel is formed in one axial side of the heat exchange cavity, and air enters the heat exchange cavity through the air inlet channel and forms circumferential rotational flow; the tail end of the heat exchange cavity is further provided with an air outlet channel, and air in the heat exchange cavity is exhausted outwards through the air outlet channel. The technical problem that the closer to the tail end, the poorer the anti-icing and deicing effects of an aircraft wing in the related technology can be solved.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft anti-icing, and in particular to a wing rotating hot air anti-icing 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 possible damage to the aircraft. Hot gas deicing is the most commonly used method for aircraft wing deicing. The high-temperature air introduced from the compressor is introduced into the hot gas cavity through a pressure regulating valve. By utilizing heat exchange, 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 anti-icing 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, as the hot air flows from the front end to the end in the hot air cavity, the heat is lost quickly, resulting in a large temperature difference between the part of the hot air cavity near the front end and the part near the end. As a result, the closer the aircraft wing is to the end, the worse the anti-icing effect.

[0004] Therefore, providing a hot gas deicing structure that can improve the temperature uniformity of the aircraft wing surface is a technical problem that needs to be solved urgently by those skilled in the art. Summary of the invention

[0005] The invention discloses a wing rotating hot air anti-icing structure to solve the technical problem in the related art that the anti-icing effect of an aircraft wing becomes worse as it approaches the end.

[0006] In order to solve the above problems, the present invention adopts the following technical solutions: A wing rotating hot air anti-icing structure comprises a heat exchange chamber arranged on the wing of an aircraft, the heat exchange chamber extending along the length direction of the wing of the aircraft; an air inlet channel is provided on one side of the axial direction of the heat exchange chamber, and gas enters the heat exchange chamber through the air inlet channel and forms a circumferential swirl; The end of the heat exchange chamber is also provided with an air outlet channel, and the gas in the heat exchange chamber is discharged to the outside through the air outlet channel.

[0007] In some schemes, the orthographic projection of the heat exchange chamber along a direction perpendicular to its own axis is perpendicular to the orthographic projection of the air inlet passage along a direction perpendicular to the axis of the heat exchange chamber; The orthographic projection of the heat exchange chamber along a direction perpendicular to the axial direction of the heat exchange chamber is perpendicular to the orthographic projection of the air outlet passage along a direction perpendicular to the axial direction of the heat exchange chamber.

[0008] In some embodiments, the air inlet passage is arranged along a tangential direction of the heat exchange chamber.

[0009] In some embodiments, the gas outlet channel is arranged along a tangential direction of the heat exchange chamber.

[0010] In some embodiments, the aircraft wing has an upper end surface and a lower end surface, the air inlet passage is disposed proximate to one of the upper end surfaces, and the air outlet passage is disposed proximate to the other end surface.

[0011] In some embodiments, there are multiple air inlet passages.

[0012] In some embodiments, the distances between any two adjacent inlet passages are equal.

[0013] In some embodiments, the projection of the heat exchange chamber along its own axial direction is circular.

[0014] In some aspects, the heat exchange chamber is disposed at a leading edge of an aircraft wing.

[0015] In some embodiments, a wing rotating hot gas de-icing structure is applied to an aircraft.

[0016] The technical solution adopted by the present invention can achieve the following beneficial effects: The high-temperature gas generated by the engine is introduced into the heat exchange chamber. During this process, the gas is injected into the heat exchange chamber through the inlet channel, and forms a circumferential vortex in the heat exchange chamber, and is discharged through the outlet channel at the end of the heat exchange chamber. When the gas is in the heat exchange chamber, driven by the temperature difference between the inner and outer walls, the heat is transferred from the inner surface to the outer surface through convection heat transfer, so that the temperature of the anti-icing surface increases, and the supercooled droplets will no longer produce condensation nuclei when they hit the surface with a higher temperature, and thus no ice will accumulate. The gas forms a circumferential vortex, and during the rotation process, it will be affected by centrifugal force and Coriolis force. These forces will change the flow state of the fluid and increase the disturbance of the fluid. The increase in fluid disturbance helps to destroy the boundary layer, so that the fluid micro-groups collide and mix more frequently in space, thereby strengthening the turbulent mixing near the wall; at the same time, the generated thermal boundary layer becomes smaller, which reduces the resistance to heat transfer, thereby improving the heat exchange efficiency and the uniformity of the temperature on the aircraft wing surface. 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 It is a structural schematic diagram of the hot gas anti-icing structure of the present invention; Figure 2 It is a front view of the hot gas anti-icing structure of the present invention; Figure 3 yes Figure 2Sectional view of the AA plane; Figure 4 yes Figure 2 Sectional view of the BB plane.

[0019] In the figure: 100-aircraft wing, 110-upper end surface, 120-lower end surface, 130-wing leading edge; 200 - heat exchange chamber, 210 - air inlet channel, 220 - air outlet channel. 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 applicant discovered during use that the existing heat exchange method usually adopts the impact jet heat exchange method. In the process of hot air flowing from the front end to the end in the hot air cavity, the heat loss is fast, resulting in a large temperature difference between the part of the hot air cavity close to the front end and the part close to the end. As a result, the closer the aircraft wing 100 is to the end, the worse the anti-icing effect.

[0022] The following is combined with Figures 1 to 4 , a wing rotating hot air anti-icing structure provided by the present application is described in detail through specific embodiments and application scenarios.

[0023] Some embodiments of the present application provide a wing rotating hot air deicing structure, such as Figure 1 As shown, the heat exchange chamber 200 is provided on the aircraft wing 100. The high-temperature gas generated by the engine is introduced into the heat exchange chamber 200. Driven by the temperature difference between the inner and outer walls, the heat is transferred from the inner surface to the outer surface through convection heat transfer, and heat exchange is completed with the outer surface of the aircraft wing 100 in the heat exchange chamber 200. During the flight of the aircraft, supercooled droplets will hit the aircraft wing 100. Due to the existence of the heat exchange chamber 200, the supercooled droplets will no longer generate condensation nuclei when hitting the surface with a higher temperature, and thus no ice will be formed.

[0024] like Figure 1As shown, the heat exchange chamber 200 extends along the length direction of the aircraft wing 100. After being introduced into the heat exchange chamber 200, the high temperature gas of the engine will flow in the heat exchange chamber 200. The heat exchange chamber 200 extending along the length direction of the aircraft wing 100 allows the gas to flow along the length direction of the aircraft wing 100, thereby completing heat exchange on the entire outer surface of the aircraft wing 100, thereby avoiding the occurrence of ice accumulation caused by supercooled droplets hitting the aircraft wing 100.

[0025] In addition, in the heat exchange chamber 200 extending along the length direction of the aircraft wing 100, the distance traveled by hot air in the heat exchange chamber 200 is the shortest, so the heat loss when the heat flows from the front end of the heat exchange chamber 200 to the end position is also minimal, ensuring that the outer surface of the aircraft wing 100 corresponding to the end of the heat exchange chamber 200 can also have a sufficient surface temperature to prevent the formation of ice accumulation.

[0026] in, Figure 1 The dashed arrows in the figure indicate the flow direction of the supercooled droplets.

[0027] Further, such as Figure 1 , Figure 3 and Figure 4 As shown, the heat exchange chamber 200 is disposed at the wing leading edge 130 of the aircraft wing 100. During the flight of the aircraft, the wing leading edge 130 of the aircraft wing 100 is prone to ice formation due to its large windward area, which affects flight safety. Therefore, the heat exchange chamber 200 is disposed at the wing leading edge 130 to directly exchange heat with the outer surface of the wing leading edge 130, thereby preventing the occurrence of ice formation and significantly improving the flight safety and reliability of the aircraft.

[0028] like Figure 1-Figure 4 As shown, the heat exchange chamber 200 has an air inlet channel 210 on one axial side, and the gas enters the heat exchange chamber 200 through the air inlet channel 210 and forms a circumferential swirl, as shown in FIG. Figure 3 and Figure 4 The gas forms a circumferential swirl, which is affected by centrifugal force and Coriolis force during the rotation process. These forces change the flow state of the fluid and increase the disturbance of the fluid. The increase of fluid disturbance helps to destroy the boundary layer, making the fluid micro-groups collide and mix more frequently in space, thereby strengthening the turbulent mixing near the wall; at the same time, the generated thermal boundary layer becomes smaller, making the resistance of heat transfer smaller, thereby improving the heat exchange efficiency and improving the surface temperature uniformity of the aircraft wing 100.

[0029] like Figure 2 and Figure 3As shown, the air inlet channel 210 is arranged along the tangent direction of the heat exchange chamber 200. The air inlet channel 210 is arranged along the tangent direction of the heat exchange chamber 200, which can naturally guide the incoming gas to flow along the tangent direction of the heat exchange chamber 200. This flow mode helps the gas to form a circumferential swirl in the heat exchange chamber 200. When the tangentially flowing gas contacts the inner wall of the heat exchange chamber 200, it will be subject to the resistance of the wall, thereby generating centrifugal force, pushing the gas to make a circular motion along the chamber wall.

[0030] in, Figure 3 The dotted arrow in shows the flow direction of the gas into the heat exchange chamber 200 along the air inlet passage 210 .

[0031] When the air inlet channel 210 is arranged in a tangential manner, the incoming gas has a certain initial tangential velocity. This initial velocity can enhance the intensity of the swirl flow, so that the gas forms a more stable and strong circumferential swirl flow in the heat exchange chamber 200. Strong swirl flow helps to increase the contact area between the gas and the heat exchange wall surface, thereby improving the heat exchange efficiency.

[0032] The tangentially arranged air inlet channel 210 also helps to reduce flow resistance. When the gas enters the heat exchange chamber 200 in a tangential manner, the angle between its flow direction and the heat exchange wall surface is small, thereby reducing the resistance loss during the flow process. This helps to reduce energy consumption and improve the overall efficiency of the system.

[0033] like Figure 1 As shown, there are several air inlet passages 210. The aircraft has different requirements for heat exchange in different flight phases and environments. Several air inlet passages 210 can adjust the flow rate and flow rate of the airflow according to actual needs, thereby enhancing the adaptability of the heat exchange chamber 200. This flexibility enables the heat exchange chamber 200 to better cope with various working conditions and load changes, ensuring that the aircraft can maintain efficient operation under various conditions.

[0034] Specifically, the number of the air intake channels 210 may be 1, 2, 3, 4 or more, and may be flexibly set according to usage requirements, which is not limited in this embodiment.

[0035] like Figure 1 As shown, the spacing between any two adjacent air inlet channels 210 is equal. The design of the equally spaced air inlet channels 210 can ensure that the airflow is more evenly distributed in the heat exchange chamber 200. When the airflow enters the heat exchange chamber 200 through the equally spaced air inlet channels 210, each air inlet channel 210 can obtain a relatively balanced airflow volume, thereby avoiding the situation where the airflow is too concentrated or sparse in a local area. This uniform airflow distribution helps to maintain the temperature stability inside the wing and improve the heat exchange efficiency.

[0036] like Figure 1 , Figure 3 and Figure 4 As shown, the end of the heat exchange chamber 200 is also provided with an outlet channel 220, and the gas in the heat exchange chamber 200 is discharged to the outside through the outlet channel 220. During the heat exchange process in the heat exchange chamber 200, the gas is smoothly discharged through the outlet channel 220 after the heat exchange is completed, avoiding accumulation in the heat exchange chamber 200, thereby ensuring the continuous and efficient heat exchange process.

[0037] like Figure 2 and Figure 4 As shown, the gas outlet channel 220 is arranged along the tangential direction of the heat exchange chamber 200. Since the gas forms a circumferential swirl in the heat exchange chamber 200, the tangentially arranged gas outlet channel 220 can make the gas flow out of the heat exchange chamber 200 in a relatively smooth manner, avoiding the situation where the gas accumulates in the heat exchange chamber 200 and cannot be discharged in time. On the contrary, if the design of the gas outlet channel 220 is unreasonable, during the heat exchange process, the gas may be retained in the heat exchange chamber 200 and cannot be discharged in time, which affects the subsequent flow of the gas and affects the heat exchange efficiency.

[0038] in, Figure 4 The dotted arrow in shows the flow direction of the gas from the heat exchange chamber 200 into the gas outlet channel 220 .

[0039] like Figure 1 As shown, the orthographic projection of the heat exchange chamber 200 perpendicular to its own axis is perpendicular to the orthographic projection of the air inlet channel 210 perpendicular to the axis of the heat exchange chamber 200. When the orthographic projections of the air inlet channel 210 and the heat exchange chamber 200 are perpendicular to each other, the gas entering the heat exchange chamber 200 will be subjected to an impact force perpendicular to the axis of the heat exchange chamber 200, and this impact force will cause the fluid to form a tangential velocity component in the heat exchange chamber 200, thereby enhancing the strength of the circumferential swirl.

[0040] At the same time, it also helps the gas to form complex flow patterns in the heat exchange chamber 200, including vortices, shear layers, turbulence, etc. These flow patterns can significantly improve the mixing degree of the gas, making the gas more evenly distributed in the heat exchange chamber 200, thereby improving the heat exchange efficiency.

[0041] like Figure 1 As shown, the orthographic projection of the heat exchange chamber 200 perpendicular to its own axis is perpendicular to the orthographic projection of the gas outlet channel 220 perpendicular to the axis of the heat exchange chamber 200. When the orthographic projection of the heat exchange chamber 200 is perpendicular to the gas outlet channel 220, it helps to reduce the flow resistance of the fluid at the entrance of the gas outlet channel 220, so that the gas can enter the gas outlet channel 220 more smoothly, avoiding gas accumulation in the heat exchange chamber 200, increasing the flow rate of the gas, and thus enhancing heat exchange.

[0042] like Figure 1 , Figure 3 and Figure 4 As shown, the aircraft wing 100 has an upper end surface 110 and a lower end surface 120, an air inlet passage 210 is arranged near one of them, and an air outlet passage 220 is arranged near the other. The air inlet passage 210 and the air outlet passage 220 are arranged near the upper end surface 110 and the lower end surface 120 of the wing respectively, which can simplify the structural layout of the hot gas anti-icing structure, and is conducive to reducing maintenance and processing costs.

[0043] As a matter of course, the upper end surface 110 is the top end surface of the aircraft wing 100, and the lower end surface 120 is the bottom end surface of the aircraft wing 100. In terms of positional relationship, the upper end surface 110 is located above the lower end surface 120.

[0044] In some embodiments, the air inlet passage 210 is disposed close to the lower end surface 120 of the aircraft wing 100 , and the air outlet passage 220 is disposed close to the upper end surface 110 of the aircraft wing 100 .

[0045] In some embodiments, the air inlet passage 210 is disposed close to the upper end surface 110 of the aircraft wing 100 , and the air outlet passage 220 is disposed close to the lower end surface 120 of the aircraft wing 100 .

[0046] like Figure 1 , Figure 3 and Figure 4 As shown, the projection of the heat exchange chamber 200 along its own axis is circular. The circular heat exchange chamber 200 helps the gas to maintain a stable flow state during the flow process, and the centrifugal force generated is more uniform, making it easier for the gas to form a stable circumferential swirl, thereby improving the heat exchange efficiency.

[0047] like Figure 1 , Figure 3 and Figure 4 As shown, the air inlet channel 210 and the air outlet channel 220 are located on the same side of the heat exchange chamber 200. Designing the air inlet channel 210 and the air outlet channel 220 on the same side of the heat exchange chamber 200 to fit the structure of the aircraft wing 100 can significantly optimize space utilization and make the hot air deicing structure more compact.

[0048] In summary, compared with the hot gas anti-icing structure in the prior art, the hot gas anti-icing structure of the present embodiment significantly improves the temperature of the outer surface corresponding to the end position of the aircraft wing 100 and the heat exchange chamber 200 under the condition of consuming the same hot gas, thereby improving the hot gas heat exchange efficiency and the surface temperature uniformity of the aircraft wing 100.

[0049] In addition, compared with the hot gas anti-icing structure in the prior art, the hot gas anti-icing structure of this embodiment consumes less hot gas while reaching the same temperature, thereby reducing the load on the engine and the impact on the engine performance, thereby achieving an efficient anti-icing effect with a smaller air intake volume.

[0050] In some embodiments, an aircraft includes the hot gas deicing structure of this embodiment.

[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] 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.

[0053] 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 wing rotating hot air deicing structure, characterized in that: The invention comprises a heat exchange chamber arranged on the wing of an aircraft, wherein the heat exchange chamber extends along the length direction of the wing of the aircraft; an air inlet passage is provided on one axial side of the heat exchange chamber, and gas enters the heat exchange chamber through the air inlet passage and forms a circumferential swirl; The end of the heat exchange chamber is also provided with an air outlet channel, and the gas in the heat exchange chamber is discharged to the outside through the air outlet channel.

2. A wing rotating hot air deicing structure according to claim 1, characterized in that: The orthographic projection of the heat exchange chamber along a direction perpendicular to its own axis is perpendicular to the orthographic projection of the air inlet passage along a direction perpendicular to the axis of the heat exchange chamber; The orthographic projection of the heat exchange chamber perpendicular to its own axis is perpendicular to the orthographic projection of the air outlet channel perpendicular to the axis of the heat exchange chamber.

3. The wing rotating hot air deicing structure according to claim 1, characterized in that: The air inlet passage is arranged along a tangential direction of the heat exchange chamber.

4. A wing rotating hot air deicing structure according to claim 3, characterized in that: The air outlet channel is arranged along the tangential direction of the heat exchange chamber.

5. A wing rotating hot air deicing structure according to claim 4, characterized in that: The aircraft wing has an upper end surface and a lower end surface, the air inlet passage is arranged close to one of them, and the air outlet passage is arranged close to the other one.

6. The wing rotating hot air deicing structure according to claim 1, characterized in that: The number of the air intake passages is several.

7. A wing rotating hot air deicing structure according to claim 6, characterized in that: The distance between any two adjacent air inlet channels is equal.

8. The wing rotating hot air deicing structure according to claim 1, characterized in that: The projection of the heat exchange chamber along its own axial direction is circular.

9. The wing rotating hot air deicing structure according to claim 1, characterized in that: The heat exchange chamber is arranged at the leading edge of the aircraft wing.

10. The wing rotating hot air deicing structure according to claim 1, characterized in that: The wing rotating hot air deicing protection structure is applied to an aircraft.

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