Passage active cooling leading edge structure for high-speed aircraft

Abstract

The invention belongs to the technical field of radiator configuration, and particularly relates to a channel active cooling leading edge structure for a high-speed aircraft, which comprises a plurality of upper cooling pipeline units and lower cooling pipeline units distributed on the inner sides of the upper and lower wing surfaces of a wing; the inlet pipeline is connected with the inlets of the upper cooling pipeline units and the inlets of the lower cooling pipeline units; the upper outlet pipeline is respectively connected with the outlets of the plurality of upper cooling pipeline units; the lower outlet pipeline is respectively connected with the outlets of the plurality of lower cooling pipeline units; the wing leading edge cooling pipeline is arranged on the foremost edge of the wing in the spanwise direction, an inlet of the wing leading edge cooling pipeline is connected with the inlet pipeline, and an outlet is connected with the upper outlet pipeline or / and the lower outlet pipeline; wherein a cooling medium flows in from the inlet pipeline and flows out from the upper outlet pipeline and the lower outlet pipeline, compared with a passive thermal protection structure, the passive thermal protection structure can select light materials, and therefore under the condition that the temperature is controllable, the structure weight is reduced, and the bearing capacity is improved.

Description

Technical Field

[0001] The present application belongs to the technical field of radiator configuration, and in particular relates to a channel active cooling leading edge structure for high-speed aircraft. Background Art

[0002] When a high-speed aircraft flies at high altitude and high speed, its surface is subjected to intense aerodynamic heating, which poses a huge challenge to the temperature resistance and load-bearing capacity of the structure. The leading edge of the wing is a part that is severely subjected to aerodynamic heating. It is locally subjected to megawatt-level heat flux, and the equilibrium temperature can reach over 600 degrees Celsius. It is difficult to use ordinary materials. At the same time, high temperature will reduce the strength limit and load-bearing capacity of the material. In severe cases, it may damage the structure of the aircraft and affect the safe operation of the aircraft. Therefore, it is necessary to adopt certain thermal protection designs. Summary of the invention

[0003] In order to solve the above problems, the present application provides a channel active cooling leading edge structure for high-speed aircraft, comprising: A plurality of upper cooling pipe units distributed on the inner side of the upper wing surface; A plurality of lower cooling pipe units distributed on the inner side of the lower wing surface; An inlet pipeline is located at the inner side of the wing leading edge and is respectively connected to the inlets of the plurality of upper cooling pipeline units and the inlets of the plurality of lower cooling pipeline units; Upper outlet pipelines respectively connected to outlets of a plurality of upper cooling pipeline units; Lower outlet pipelines respectively connected to outlets of the plurality of lower cooling pipeline units; The wing leading edge cooling pipeline is arranged at the leading edge of the wing along the span direction, the inlet of the pipeline is connected to the inlet pipeline, and the outlet is connected to the upper outlet pipeline and / or the lower outlet pipeline; The cooling medium flows in from the inlet pipeline and flows out from the upper outlet pipeline and the lower outlet pipeline.

[0004] Preferably, a plurality of upper cooling pipeline units are located in the same plane to form an upper cooling network, a plurality of lower cooling pipeline units are located in the same plane to form a lower cooling network, and the upper cooling network, the lower cooling network and the inlet pipeline form a wedge-shaped structure.

[0005] Preferably, each upper cooling pipe unit and each lower cooling pipe unit respectively comprises a plurality of mutually parallel sub-channels arranged in an inverse fractal configuration structure, wherein the sub-channels are divided into multiple levels from front to back along the chord direction, and every two sub-channels of the upper level merge into a sub-channel of the lower level.

[0006] Preferably, the included angle of the sub-channels at the confluence is 60°.

[0007] Preferably, all sub-channels have rectangular cross-sections.

[0008] Preferably, the ratio of the width of the sub-channel of the previous stage to the width of the sub-channel of the next stage is 1:1.4.

[0009] Preferably, adjacent upper cooling pipeline units are parallel to each other, and adjacent lower cooling pipeline units are parallel to each other.

[0010] Preferably, the inlet pipeline is connected to a main input pipeline for providing cooling medium, and the upper outlet pipeline and the lower outlet pipeline are both connected to a main output pipeline for discharging cooling medium.

[0011] Preferably, the cross-sectional area of ​​the wing leading edge cooling pipeline gradually decreases along the flow direction of the cooling medium, the cross-sectional areas of the upper outlet pipeline and the lower outlet pipeline gradually increase along the flow direction of the cooling medium, and the main output pipeline is connected to the upper outlet pipeline and the lower outlet pipeline at the largest cross-sectional area.

[0012] Advantages of this application include: 1. Compared with passive thermal protection structures, this application can use lighter materials, thereby reducing the weight of the structure and improving the bearing capacity while ensuring that the temperature can be controlled.

[0013] 2. This application can ensure that the structure operates at a lower temperature in a high temperature environment, and realize the application of low-temperature resistant materials in a high temperature environment.

[0014] 3. Compared with other wing leading edge structure solutions, this application makes the overall temperature uniformity of the wing leading edge structure good and the thermal stress level low.

[0015] 4. The present invention has small flow resistance, and the cooling effect is more evenly distributed on the leading edge. The cooling medium is difficult to vaporize, has high utilization efficiency, has no flow stagnation zone, and is not easy to be blocked.

[0016] Therefore, compared with existing solutions, the present invention has significant advantages in high-speed flight leading edge structure application and heat bearing characteristics. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a perspective view of a channel active cooling leading edge structure for high-speed aircraft according to a preferred embodiment of the present application. DETAILED DESCRIPTION

[0018] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be further described in detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments in the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0019] like Figure 1 As shown, in order to solve the above problems, the present application provides a channel active cooling leading edge structure for high-speed aircraft, comprising: A plurality of upper cooling pipe units 7 distributed on the inner side of the upper wing surface; A plurality of lower cooling pipe units 8 distributed on the inner side of the lower wing surface; An inlet pipeline 5 is located at the inner side of the wing leading edge and is connected to the inlets of the plurality of upper cooling pipeline units 7 and the inlets of the plurality of lower cooling pipeline units 8 respectively; Upper outlet pipelines 3 connected to outlets of a plurality of upper cooling pipeline units 7 respectively; Lower outlet pipelines 2 respectively connected to outlets of a plurality of lower cooling pipeline units 8; The wing leading edge cooling pipeline 6 is arranged at the leading edge of the wing along the span direction, and its inlet is connected to the inlet pipeline 5, and its outlet is connected to the upper outlet pipeline 3 and / or the lower outlet pipeline 2; the wing leading edge cooling pipeline 6 is located in front of the inlet pipeline 5; The cooling medium flows in from the inlet pipeline 5 and flows out from the upper outlet pipeline 3 and the lower outlet pipeline 2 .

[0020] Preferably, multiple upper cooling pipe units 7 are located in the same plane to form an upper cooling network, and multiple lower cooling pipe units 8 are located in the same plane to form a lower cooling network. The upper cooling network, the lower cooling network and the inlet pipe 5 form a wedge-shaped structure, and the whole is mirror-symmetrical along the center line. The inlet pipe 5 is arranged on the wing closer to the nose of the aircraft, and its position is close to the windward side of the leading edge of the wing. The upper outlet pipe 3 and the lower outlet pipe 2 are arranged at the rear away from the nose of the aircraft. The purpose is to make the cooling medium temperature at the inlet lower so that it can preferentially contact the leading edge of the wing with a higher temperature; it is used to cool most of the upper and lower surfaces of the leading edge structure and to cool the overall heat load of the leading edge structure.

[0021] The wing leading edge cooling pipeline 6 is a single cooling channel, which is located at the front and is used to cool the high heat load at the front end.

[0022] Preferably, each upper cooling pipe unit 7 and lower cooling pipe unit 8 respectively comprises a plurality of mutually parallel sub-channels arranged in an inverse fractal configuration structure, wherein the sub-channels are divided into multiple levels from front to back along the chord direction, and every two sub-channels of the upper level merge into a sub-channel of the lower level.

[0023] Preferably, all sub-channels have rectangular cross-sections, and the upper outlet pipeline 3, the lower outlet pipeline 2, the wing leading edge cooling pipeline 6, and the inlet pipeline 5 are all rectangular, which can increase the contact area with the inner surface of the wing.

[0024] Preferably, the ratio of the width of the sub-channel of the previous level to the width of the sub-channel of the next level is 1:1.4, the angle of the sub-channel at the confluence is 60°, the adjacent upper cooling pipe units 7 are parallel to each other, and the adjacent lower cooling pipe units 8 are parallel to each other, which can avoid the formation of flow stagnation areas and has small flow resistance.

[0025] Preferably, the inlet pipeline 5 is connected to a main input pipeline 4 for providing cooling medium, and the upper outlet pipeline 3 and the lower outlet pipeline 2 are both connected to a main output pipeline 1 for discharging cooling medium.

[0026] Preferably, the cross-sectional area of ​​the wing leading edge cooling pipeline 6 gradually decreases along the flow direction of the cooling medium, the cross-sectional areas of the upper outlet pipeline 3 and the lower outlet pipeline 2 gradually increase along the flow direction of the cooling medium, and the main output pipeline 1 is connected to the upper outlet pipeline 3 and the lower outlet pipeline 2 at the points with the largest cross-sectional areas.

[0027] The cooling medium enters the inlet pipeline 5 and the wing leading edge cooling pipeline 6 from the main input pipeline 4, and the cooling medium in the inlet pipeline 5 enters the upper cooling pipeline unit 7 and the lower cooling pipeline unit 8 in turn, and the cooling medium in the upper cooling pipeline unit 7 and the lower cooling pipeline unit 8 enters the upper outlet pipeline 3 and the lower outlet pipeline 2 respectively; the wing leading edge cooling pipeline 6 also enters the upper outlet pipeline 3 and the lower outlet pipeline 2, and is finally discharged through the main output pipeline 1.

[0028] The performance of the active cooling leading edge structure is analyzed below in conjunction with a specific embodiment. In order to verify whether the structure has a good temperature control effect, in a specific embodiment, additive manufacturing is used to manufacture a metal test piece using TC4 titanium alloy material.

[0029] In order to verify the cooling characteristics of the channel active cooling leading edge structure, a test system was constructed, and 12 heating quartz lamps were arranged on the surface of the test piece to heat the test piece to simulate aerodynamic heating. The upper and lower surfaces of the test piece close to the leading edge half are partition one, and the upper and lower surfaces close to the trailing edge half are partition two. There are three lamp tubes on the upper and lower surfaces of partition one and partition two respectively; the power of the lamp tubes in each partition is equal; a total of 5L of cooling water is used as the cooling medium, and the supply flow rate of the cooling medium is adjusted to 3.5L / min. Cooling water is supplied to the test piece, and the cooling water inlet and outlet temperatures are measured by thermocouples, the cooling water flow rate is measured by a flowmeter, and the temperature of multiple positions on the surface of the active cooling leading edge structure is measured by thermocouples.

[0030] According to the test results, under the action of channel cooling, the temperature at different positions of the leading edge structure can be effectively controlled below 320°C, which is far lower than the high temperature of 700°C that can be reached by ambient heating, playing a good role in structural temperature control; at the same time, the temperatures of the temperature measuring points on the surface of the structure are similar, which also proves that the channel actively cooled leading edge structure has a good temperature equalization effect.

[0031] The test results also show that under harsh heating conditions, TC4 titanium alloy material (with a long-term temperature resistance upper limit of 400°C) can be stably used in high-temperature environments; compared with other high-temperature resistant metals, TC4 titanium alloy has a lower density, which also shows that this solution has the potential to reduce structural weight.

[0032] The wing leading edge cooling pipeline 6 has a strong heat exchange capacity, and at the same time avoids the flow stagnation zone at the leading edge where the heat load is concentrated, thereby achieving the matching of cooling capacity and heat load and efficient heat exchange.

[0033] Therefore, this embodiment further proves that the channel active cooling leading edge structure proposed in the present invention has excellent performance and practicality.

[0034] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A channel active cooling leading edge structure for high-speed aircraft, characterized in that: include: A plurality of upper cooling pipe units (7) distributed on the inner side of the upper wing surface of the wing; A plurality of lower cooling pipe units (8) distributed on the inner side of the lower wing surface; An inlet pipeline (5) is located on the inner side of the wing leading edge and is respectively connected to the inlets of the plurality of upper cooling pipeline units (7) and the inlets of the plurality of lower cooling pipeline units (8); Upper outlet pipelines (3) respectively connected to outlets of a plurality of upper cooling pipeline units (7); Lower outlet pipelines (2) respectively connected to outlets of a plurality of lower cooling pipeline units (8); A wing leading edge cooling pipeline (6) is arranged at the leading edge of the wing along the span direction, with its inlet connected to the inlet pipeline (5) and its outlet connected to the upper outlet pipeline (3) and / or the lower outlet pipeline (2); The cooling medium flows in from the inlet pipeline (5) and flows out from the upper outlet pipeline (3) and the lower outlet pipeline (2).

2. The channel active cooling leading edge structure for high-speed aircraft according to claim 1, characterized in that: A plurality of upper cooling pipeline units (7) are located on the same plane to form an upper cooling network, and a plurality of lower cooling pipeline units (8) are located on the same plane to form a lower cooling network. The upper cooling network, the lower cooling network and the inlet pipeline (5) form a wedge-shaped structure.

3. The channel active cooling leading edge structure for high-speed aircraft according to claim 1, characterized in that: Each upper cooling pipeline unit (7) and lower cooling pipeline unit (8) respectively comprises a plurality of mutually parallel sub-channels arranged in an inverse fractal configuration structure, wherein the sub-channels are divided into multiple levels from front to back along the chord direction, and every two sub-channels of the upper level merge into a sub-channel of the lower level.

4. The channel active cooling leading edge structure for high-speed aircraft according to claim 3, characterized in that: The included angle of the sub-channels at the confluence is 60°.

5. The channel active cooling leading edge structure for high-speed aircraft according to claim 3, characterized in that: All sub-channels have rectangular cross-sections.

6. The channel actively cooled leading edge structure for high-speed aircraft according to claim 5, characterized in that: The ratio of the width of the sub-channel of the previous level to the width of the sub-channel of the next level is 1:1.

4.

7. The channel active cooling leading edge structure for high-speed aircraft according to claim 3, characterized in that: Adjacent upper cooling pipeline units (7) are parallel to each other, and adjacent lower cooling pipeline units (8) are parallel to each other.

8. The channel active cooling leading edge structure for high-speed aircraft according to claim 3, characterized in that: The inlet pipeline (5) is connected to a main input pipeline (4) for providing a cooling medium, and the upper outlet pipeline (3) and the lower outlet pipeline (2) are both connected to a main output pipeline (1) for discharging the cooling medium.

9. The channel active cooling leading edge structure for high-speed aircraft according to claim 1, characterized in that: The cross-sectional area of ​​the wing leading edge cooling pipeline (6) gradually decreases along the flow direction of the cooling medium.

10. The channel actively cooled leading edge structure for high-speed aircraft according to claim 8, characterized in that: The cross-sectional areas of the upper outlet pipeline (3) and the lower outlet pipeline (2) gradually increase along the flow direction of the cooling medium, and the main output pipeline (1) is connected to the upper outlet pipeline (3) and the lower outlet pipeline (2) at the points where the cross-sectional areas are the largest.

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