A wing rotating hot air anti-icing structure

Abstract

The present invention relates to the field of aircraft technology and discloses a wing rotating hot gas deicing structure. The structure comprises a heat exchange chamber disposed within the aircraft wing, extending along the length of the wing. An air inlet passage is defined along one axial side of the heat exchange chamber, through which gas enters the heat exchange chamber and forms a circumferential vortex. Furthermore, an air outlet passage is defined at the distal end of the heat exchange chamber, through which gas in the heat exchange chamber is discharged. This invention addresses the technical problem in related art whereby the deicing effect of aircraft wings decreases toward the distal end.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft anti-icing and de-icing, and in particular to a wing rotating hot air anti-icing and de-icing structure. Background Art

[0002] Aircraft icing has always been a significant threat to flight safety. Relevant practices and research have shown that ice deposits on aircraft wing surfaces can severely damage the wing's aerodynamic shape, leading to deteriorated flight performance and potentially damage to the aircraft. Hot gas de-icing is the most commonly used method for aircraft wing de-icing. High-temperature air from the compressor is introduced into the hot gas cavity through a pressure regulating valve. Using heat exchange, driven by the temperature difference between the inner and outer walls, heat is transferred from the inner surface to the outer surface via convection, raising the temperature of the de-icing surface. Supercooled droplets impacting the higher temperature surface no longer form condensation nuclei, preventing ice accumulation.

[0003] However, as the hot air flows from the front 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 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 present 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:

[0007] A wing rotating hot gas deicing structure includes a heat exchange chamber provided on the wing of an aircraft, the heat exchange chamber extending along the length 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;

[0008] 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.

[0009] In some embodiments, the orthographic projection of the heat exchange chamber perpendicular to its own axis is perpendicular to the orthographic projection of the air inlet passage perpendicular to the axis of the heat exchange chamber;

[0010] 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.

[0011] In some solutions, the air inlet passage is arranged along a tangential direction of the heat exchange chamber.

[0012] In some embodiments, the gas outlet channel is arranged along a tangential direction of the heat exchange chamber.

[0013] 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.

[0014] In some solutions, there are multiple air inlet channels.

[0015] In some embodiments, the distances between any two adjacent air inlet channels are equal.

[0016] In some embodiments, the projection of the heat exchange chamber along its own axis is circular.

[0017] In some aspects, the heat exchange chamber is disposed at a leading edge of an aircraft wing.

[0018] In some embodiments, a wing rotating hot gas de-icing structure is applied to an aircraft.

[0019] The technical solution adopted by the present invention can achieve the following beneficial effects:

[0020] 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, forming a circumferential vortex within the chamber and exiting through the outlet channel at the end of the heat exchange chamber. While in the heat exchange chamber, driven by the temperature difference between the inner and outer walls, heat is transferred from the inner surface to the outer surface through convection, raising the temperature of the anti-icing surface. Supercooled droplets impacting the higher-temperature surface no longer form condensation nuclei, thus preventing ice accumulation. This circumferential vortex of gas is subject to centrifugal and Coriolis forces during rotation. These forces alter the flow state of the fluid and increase fluid turbulence. This increased fluid turbulence helps to disrupt the boundary layer, causing fluid particles to collide and mix more frequently in space, thereby enhancing turbulent mixing near the wall. Simultaneously, the resulting thermal boundary layer is reduced, reducing resistance to heat transfer, thereby improving heat transfer efficiency and enhancing temperature uniformity across the aircraft wing surface. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. 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 any creative work.

[0022] Figure 1 2. It is a schematic structural diagram of the hot gas anti-icing structure of the present invention;

[0023] Figure 2This is a front view of the hot gas anti-icing structure of the present invention;

[0024] Figure 3 yes Figure 2 Sectional view of the AA plane;

[0025] Figure 4 yes Figure 2 Cross-sectional view of the middle BB plane.

[0026] In the picture:

[0027] 100-aircraft wing, 110-upper end surface, 120-lower end surface, 130-wing leading edge;

[0028] 200-heat exchange chamber, 210-air inlet channel, 220-air outlet channel. DETAILED DESCRIPTION

[0029] To make the objectives, technical solutions, and advantages of the present invention more apparent, the technical solutions of the present invention will be described in detail below. Obviously, the embodiments described are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other implementations obtained by those of ordinary skill in the art without inventive effort are within the scope of protection of the present invention.

[0030] The applicant discovered during use that the existing heat exchange method usually adopts the impingement jet heat exchange method. In the process of hot air flowing from the front end to the end in the hot air cavity, heat loss is fast, 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 100 is to the end, the worse the anti-icing effect.

[0031] 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.

[0032] Some embodiments of the present application provide wing rotating hot air anti-icing structures, such as Figure 1 As shown, the heat exchange chamber 200 is disposed on the aircraft wing 100. 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, heat is transferred from the inner surface to the outer surface via convection, completing heat exchange with the outer surface of the aircraft wing 100 within the heat exchange chamber 200. During flight, supercooled liquid droplets may impact the aircraft wing 100. Due to the presence of the heat exchange chamber 200, the supercooled droplets will no longer form condensation nuclei when impacting higher-temperature surfaces, thus preventing ice accumulation.

[0033] like Figure 1As shown, heat exchange chamber 200 extends along the length of aircraft wing 100. After being introduced into heat exchange chamber 200, high-temperature gas from the engine flows within heat exchange chamber 200. Heat exchange chamber 200 extending along the length of aircraft wing 100 allows gas to flow along the length of aircraft wing 100, thereby completing heat exchange across the entire outer surface of aircraft wing 100 and preventing ice accumulation caused by supercooled liquid droplets impacting aircraft wing 100.

[0034] In addition, the heat exchange chamber 200 extends along the length of the aircraft wing 100, and the distance traveled by hot air in the heat exchange chamber 200 is the shortest. Therefore, the heat loss when the heat flows from the front end to the end position of the heat exchange chamber 200 is also minimized, ensuring that the outer surface of the aircraft wing 100 near the end of the heat exchange chamber 200 can also maintain a sufficient surface temperature to prevent the formation of ice accumulation.

[0035] in, Figure 1 The dashed arrows in the figure indicate the flow direction of the supercooled droplets.

[0036] Further, such as Figure 1 、 Figure 3 and Figure 4 As shown, heat exchange chamber 200 is disposed at leading edge 130 of aircraft wing 100. During flight, wing leading edge 130 is susceptible to ice formation due to its large windward area, potentially impacting flight safety. Therefore, heat exchange chamber 200 is disposed at leading edge 130 to directly exchange heat with the outer surface of wing leading edge 130, preventing icing and significantly improving aircraft flight safety and reliability.

[0037] like Figures 1-4 As shown, the heat exchange chamber 200 has an air inlet channel 210 on one axial side. 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 fluid disturbance. The increased fluid disturbance helps to destroy the boundary layer, causing fluid particles to collide and mix more frequently in space, thereby strengthening turbulent mixing near the wall. At the same time, the generated thermal boundary layer becomes smaller, reducing the resistance to heat transfer, thereby improving heat exchange efficiency and enhancing the surface temperature uniformity of aircraft wing 100.

[0038] like Figure 2 and Figure 3As shown, the air inlet channel 210 is arranged tangentially to the heat exchange chamber 200. This arrangement naturally guides the incoming gas to flow tangentially to the heat exchange chamber 200. This flow pattern helps the gas form a circumferential swirl within the heat exchange chamber 200. When the tangentially flowing gas contacts the inner wall of the heat exchange chamber 200, it encounters resistance from the wall, generating centrifugal force that propels the gas in a circular motion along the chamber wall.

[0039] in, Figure 3 The dotted arrow in represents the flow direction of the gas into the heat exchange chamber 200 along the air inlet channel 210 .

[0040] When the inlet passages 210 are arranged tangentially, the incoming gas has a certain initial tangential velocity. This initial velocity can enhance the intensity of the swirl flow, allowing the gas to form a more stable and intense circumferential swirl flow within the heat exchange chamber 200. The strong swirl flow helps increase the contact area between the gas and the heat exchange wall surface, thereby improving heat exchange efficiency.

[0041] The tangentially arranged inlet channel 210 also helps reduce flow resistance. When gas enters the heat exchange chamber 200 tangentially, the angle between its flow direction and the heat exchange wall surface is smaller, thereby reducing resistance losses during the flow process. This helps reduce energy consumption and improve the overall efficiency of the system.

[0042] like Figure 1 As shown, there are multiple inlet channels 210. Aircraft heat exchange requirements vary during different flight phases and environments. The multiple inlet channels 210 can adjust the airflow rate and velocity based on 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 operating conditions and load changes, ensuring efficient aircraft operation under all conditions.

[0043] Specifically, the number of the air inlet 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.

[0044] like Figure 1 As shown, the spacing between any two adjacent inlet channels 210 is equal. The design of evenly spaced inlet channels 210 ensures a more uniform airflow distribution within the heat exchange chamber 200. When air enters the heat exchange chamber 200 through the evenly spaced inlet channels 210, each inlet channel 210 receives a relatively balanced airflow volume, thus avoiding excessively concentrated or sparse airflow in certain areas. This uniform airflow distribution helps maintain temperature stability within the wing and improves heat exchange efficiency.

[0045] like Figure 1 、 Figure 3 and Figure 4 As shown, the heat exchange chamber 200 further has an outlet channel 220 at the end thereof, through which the gas within the heat exchange chamber 200 is discharged. 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, thereby preventing accumulation within the heat exchange chamber 200 and ensuring continuous and efficient heat exchange.

[0046] like Figure 2 and Figure 4 As shown, the outlet channel 220 is arranged tangentially to the heat exchange chamber 200. Because the gas forms a circumferential vortex within the heat exchange chamber 200, the tangential arrangement of the outlet channel 220 allows the gas to flow out of the heat exchange chamber 200 more smoothly, preventing gas from accumulating in the heat exchange chamber 200 and being unable to be discharged in a timely manner. Conversely, if the outlet channel 220 is poorly designed, during the heat exchange process, gas may remain in the heat exchange chamber 200 and be unable to be discharged in a timely manner, affecting the subsequent flow of gas and thus reducing heat exchange efficiency.

[0047] in, Figure 4 The dotted arrow in represents the flow direction of the gas from the heat exchange chamber 200 into the gas outlet channel 220 .

[0048] 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. This impact force will cause the fluid to form a tangential velocity component within the heat exchange chamber 200, thereby enhancing the intensity of the circumferential swirl.

[0049] At the same time, it also helps the gas form complex flow patterns in the heat exchange chamber 200, including vortices, shear layers, and turbulence. 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.

[0050] like Figure 1 As shown, the orthographic projection of the heat exchange chamber 200, which is perpendicular to its own axis, is perpendicular to the orthographic projection of the gas outlet channel 220, which is perpendicular to the axis of the heat exchange chamber 200. When the orthographic projections of the heat exchange chamber 200 and the gas outlet channel 220 are perpendicular, this helps reduce the flow resistance of the fluid at the entrance of the gas outlet channel 220, allowing the gas to enter the gas outlet channel 220 more smoothly, preventing gas accumulation in the heat exchange chamber 200, increasing the gas flow rate, and thus enhancing heat exchange.

[0051] like Figure 1 、 Figure 3 and Figure 4 As shown, aircraft wing 100 has an upper end surface 110 and a lower end surface 120, with an inlet duct 210 disposed near one of the upper and lower end surfaces 110 and 120 disposed near the other. Placing inlet duct 210 and outlet duct 220 near the upper and lower end surfaces 110 and 120, respectively, simplifies the layout of the hot gas anti-icing structure, reducing maintenance and processing costs.

[0052] 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 .

[0053] In some embodiments, the air inlet passage 210 is disposed near the lower end surface 120 of the aircraft wing 100 , and the air outlet passage 220 is disposed near the upper end surface 110 of the aircraft wing 100 .

[0054] In some embodiments, the air inlet passage 210 is disposed near the upper end surface 110 of the aircraft wing 100 , and the air outlet passage 220 is disposed near the lower end surface 120 of the aircraft wing 100 .

[0055] like Figure 1 、 Figure 3 and Figure 4 As shown, the heat exchange chamber 200 is projected in a circular shape along its own axis. The circular heat exchange chamber 200 helps the gas maintain a stable flow state during the flow process, generates a more uniform centrifugal force, and makes it easier for the gas to form a stable circumferential vortex, thereby improving the heat exchange efficiency.

[0056] 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 gas deicing structure more compact.

[0057] In summary, compared with the hot gas anti-icing structure of the prior art, the hot gas anti-icing structure of this embodiment significantly improves the temperature of the outer surface of the aircraft wing 100 corresponding to the end position of the heat exchange chamber 200 while consuming the same hot gas, thereby improving the hot gas heat exchange efficiency and the surface temperature uniformity of the aircraft wing 100.

[0058] 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, and achieving efficient anti-icing effect with a smaller air intake volume.

[0059] In some embodiments, an aircraft includes the hot gas deicing structure of this embodiment.

[0060] It should be noted that the aircraft may be a drone, a fixed-wing aircraft, etc., and this embodiment does not limit this.

[0061] Furthermore, it should be noted that the scope of the methods and apparatuses in the embodiments of the present application is not limited to performing functions in the order shown or discussed, but may also include performing functions substantially simultaneously or in reverse order depending on the functions involved. For example, the methods described may be performed in an order different from that described, and various steps may be added, omitted, or combined. Furthermore, features described with reference to certain examples may be combined in other examples.

[0062] The above description is only a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any technician familiar with this technical field can easily think of changes or replacements within the technical scope disclosed by the present invention, which should be covered by the scope of protection of the present invention.

Claims

1. A wing rotating hot air deicing structure, characterized in that: The heat exchange chamber includes a heat exchange chamber provided on a wing of an aircraft, the heat exchange chamber extending 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, gas enters the heat exchange chamber through the air inlet passage, and forms a circumferential swirl in a plane perpendicular to the axial direction of the heat exchange chamber; The other side of the heat exchange chamber is provided with an air outlet channel, through which the gas in the heat exchange chamber is discharged outwards; The air inlet channel is arranged along a tangential direction of the heat exchange chamber.

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

4. The wing rotating hot air deicing structure according to claim 3, 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 the upper end surface and the air outlet passage is arranged close to the other end surface.

5. The wing rotating hot air deicing structure according to claim 1, characterized in that: There are multiple air intake channels.

6. The wing rotating hot air deicing structure according to claim 5, characterized in that: The distances between any two adjacent air inlet channels are equal.

7. 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.

8. 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.

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

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