Flat heat pipe and fin-based rectification support plate hot air heat pipe composite anti-icing device

Abstract

The invention discloses a rectification support plate hot air heat pipe composite anti-icing device based on flat heat pipes and fins. The aero-engine anti-icing device comprises a supporting plate, a flat plate heat pipe and a fin part. A vertical cavity is formed in the supporting plate, a hot air inlet is formed in the upper end of the vertical cavity, and a hot air outlet is formed in the lower end of the vertical cavity; the flat plate heat pipe is arranged in the front of the supporting plate, one part of the flat plate heat pipe is directly connected with the supporting plate, the other part of the flat plate heat pipe extends to the vertical cavity, and fins are arranged on the two sides of the flat plate heat pipe and can greatly increase the heat exchange area of the heat pipe to fully exchange heat with hot air; the support plates, the flat heat pipes and the fins are integrally designed and integrally processed and formed; according to the device, the surface temperature uniformity of the rectification support plate under the anti-icing working condition is improved, and the hot air utilization rate is increased.

Description

Technical Field

[0001] The present invention belongs to the field of aero-engine anti-icing, and relates to a composite anti-icing device for a fairing strut hot gas heat pipe based on a flat heat pipe and fins. Background Art

[0002] Ice formation on the windward surface during flight is a major problem affecting aircraft safety; when an aircraft passes through a cloud containing supercooled water droplets, all components located at the front of the engine are vulnerable to direct impact by supercooled water droplets and cause icing; among them, there are various anti-icing methods for the front-end components of the engine, and the hot gas anti-icing system is a mature, reliable and most widely used anti-icing system, but the traditional hot gas anti-icing system has a low heat exchange efficiency. Recently, with the increase in engine thrust, the requirement for anti-icing air extraction volume has gradually decreased, and a more efficient heat exchange structure needs to be designed; in addition, the previous heat exchange structure of the fairing strut mainly focused on whether heat transfer can be enhanced, while ignoring the uniformity of heat exchange along the strut. Summary of the Invention

[0003] In view of the above problems, the object of the present invention is to propose a composite anti-icing device for a fairing strut hot gas heat pipe based on a flat heat pipe and fins.

[0004] The technical solution of the present invention is as follows: A composite anti-icing device for a fairing strut hot gas heat pipe based on a flat heat pipe and fins, comprising a strut, a vertical cavity is opened inside the strut, a hot gas outlet is opened at the upper end of the vertical cavity, and a hot gas inlet is opened at the lower end thereof;

[0005] Both the hot gas inlet and the hot gas outlet are communicated with the vertical cavity;

[0006] A flat heat pipe is further installed on one side inside the strut, the flat heat pipe is placed in the front part of the strut, a part of it is directly connected to the strut, and the other part extends into the vertical cavity.

[0007] Furthermore, fins are arranged on both sides of the flat heat pipe extending into the vertical cavity in a uniformly distributed manner; the fins can greatly increase the heat exchange area of the flat heat pipe and fully exchange heat with the hot gas;

[0008] Furthermore, the vertical cavity is opened in the rear half part of the strut and does not cross the drawn chordwise midline.

[0009] Furthermore, the strut, the flat heat pipe and the fins are integrally designed and integrally processed.

[0010] Furthermore, the strut, the outer shell of the flat heat pipe and the fins are integrally formed by 3D printing with aluminum alloy materials.

[0011] Further, the thickness of the leading edge of the support plate on the side away from the vertical cavity is not less than 3.5 mm.

[0012] Further, the internal working fluid of the flat heat pipe is acetone.

[0013] Further, a part of the height of the flat heat pipe is the same as that of the support plate, its thickness is not less than 3 mm, the wall thickness is not more than 0.5 mm, and the length is not less than 50% of the chord length of the support plate.

[0014] The beneficial effects of the present invention are as follows: The device improves the surface temperature uniformity of the rectifying support plate under the anti-icing condition and improves the utilization rate of hot gas. Description of the Drawings

[0015] Figure 1 is a schematic diagram of the overall structure of the present invention;

[0016] Figure 2 is the front view of the present invention;

[0017] Figure 3 is the top view of the present invention;

[0018] Figure 4 is the curve graph of the leading edge temperature distribution of the present invention in the icing environment;

[0019] In the figure, 1 is the support plate, 2 is the flat heat pipe, 3 is the hot gas outlet, 4 is the hot gas inlet, 5 is the leading edge of the support plate, 6 is the fin, and 7 is the chordwise midline. Detailed Embodiments

[0020] The following further elaborates on the specific technical solutions of the present invention with reference to specific examples.

[0021] As shown in the figure, a hot gas heat pipe composite anti-icing device for a rectifying support plate based on a flat heat pipe and fins according to the present invention includes a support plate 1 and a flat heat pipe 2. A vertical cavity is provided inside the support plate 1. The lower end of the vertical cavity in the support plate is the hot gas outlet 3, and the upper end is the hot gas inlet 4. The present invention is installed on the intake casing of the engine, connected to the intake casing fairing at the upper end and communicated with the air intake pipe, and connected to the cap at the lower end. Under the anti-icing condition, hot gas flows in from the hot gas inlet 4, passes through the hot gas cavity (vertical cavity) and flows out from the hot gas outlet 3. During this process, heat is quickly transferred to the leading edge 5 of the support plate 1 through the flat heat pipe 2.

[0022] Further, the support plate 1 used in the present invention should be made of aluminum alloy material, meeting the material requirements of lightweight and high strength for aero-engines, and taking into account the pipe material requirements of the flat heat pipe 2. The wall thickness between the leading edge 5 of the support plate and the internal steam cavity of the flat heat pipe 2 should be above 0.8 mm to ensure the strength under the vibration environment.

[0023] Further, the flat heat pipe 2 used in the present invention is an aluminum-acetone heat pipe, with an operating temperature between -20 and 300 degrees Celsius, a height of not less than 3 mm, a wall thickness of not more than 0.3 mm, and its internal structure is a groove structure. One end close to the leading edge 5 of the support plate is consistent with the contour of the leading edge 5 of the support plate.

[0024] Further, the length of the flat heat pipe 2 used in the present invention is the same as the length of the actually used support plate 1. The upper and lower ends are caps. To facilitate the control of the precision of 3D printing, the thickness of the caps can be appropriately adjusted.

[0025] As Figure 3 shown, the vertical cavity is located in the latter half of the support plate 1 and does not cross the chordwise midline 7; the vertical cavity is not limited to the shape shown in the schematic diagram and can be adjusted according to the size of the support plate 1 used, but it should be ensured that the tail of the support plate 1 has a width of more than 30 mm.

[0026] As Figure 3 shown, the size of the fin 6 used in the present invention is 2.5 mm in height, 0.5 mm in width, the length is the same as the length of the support plate 1, the spacing is 2 mm, and a group of 12 is arranged on each side of the flat heat pipe 2.

[0027] In the working environment where the external flow temperature, the oncoming flow airspeed, and the liquid water content of the present invention are 263.15 K, 0.477 Ma, and 2 g / m 3 respectively, anti-icing is carried out with hot air at a temperature of 540 K and a flow rate of 9.6 g / s, and the leading edge temperature distribution of the fairing support plate 1 with and without a heat pipe is obtained. As Figure 4 shown, the leading edge temperature of the structure without a heat pipe gradually decreases along the span direction, the temperature in some areas is lower than the freezing point, and it is difficult to meet the anti-icing requirements in some areas. Compared with the present invention, its leading edge temperature drops rapidly. After the flat heat pipe 2 is arranged at the front of the support plate 1 of the present device, the overall heat transfer inside the support plate 1 is more uniform, avoiding the rapid decrease of the temperature of the leading edge 5 of the support plate along the span direction; at the same time, the lowest temperature under this working condition is about 16 K higher than the freezing point, indicating that the present device can further reduce the amount of hot air required for anti-icing and has a good anti-icing effect.

Claims

1. A composite anti-icing device for hot gas heat pipes based on flat heat pipes and fins, characterized in that: It comprises a support plate (1), a vertical cavity is opened inside the support plate (1), a hot air outlet (3) is opened at the upper end of the vertical cavity, and a hot air inlet (4) is opened at the lower end.

2. A composite anti-icing device for hot gas and heat pipes based on flat heat pipes and fins according to claim 1, characterized in that: The hot air outlet (3) and the hot air inlet (4) are both connected to the vertical cavity.

3. A composite anti-icing device for hot gas and heat pipes based on flat heat pipes and fins according to claim 1, characterized in that: A flat heat pipe (2) is also installed on one side of the inner part of the support plate (1). The flat heat pipe (2) is built into the front part of the support plate (1), with one part connected to the support plate (1) and the other part extending into the vertical cavity.

4. A composite anti-icing device for hot gas and heat pipes based on flat heat pipes and fins, characterized in that: Evenly distributed fins (6) are arranged on both sides of the flat heat pipe (2) extending into the vertical cavity.

5. A composite anti-icing device for hot gas and heat pipes based on flat heat pipes and fins, characterized in that: The vertical cavity is opened in the rear half of the support plate (1) and does not cross the chord-wise midline (7).

6. A composite anti-icing device for hot gas and heat pipes based on flat heat pipes and fins according to claim 4, characterized in that: The support plate (1), the flat plate heat pipe (2) and the fins (6) are designed as an integrated whole and are integrally processed and formed.

7. A composite anti-icing device for hot gas and heat pipes based on flat heat pipes and fins, characterized in that: The support plate (1), the outer shell of the flat heat pipe (2) and the fins (6) are integrally formed by 3D printing of an aluminum alloy material.

8. A composite anti-icing device for hot gas and heat pipes based on flat heat pipes and fins according to claim 1, characterized in that: The thickness of the front edge (5) of the support plate (1) away from the vertical cavity is ≥3.5 cm.

9. A composite anti-icing device for hot gas and heat pipes based on flat heat pipes and fins, characterized in that: The internal working fluid of the flat plate heat pipe (2) is acetone.

10. A composite anti-icing device for hot gas and heat pipes based on flat heat pipes and fins, characterized in that: The height of part of the flat plate heat pipe (2) is consistent with that of the support plate (1), its thickness is ≥3 mm, its wall thickness is ≤0.5 mm, and its length is ≥50% of the chord length of the support plate (1).

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