Rectification support plate hot air heat pipe composite anti-icing structure based on cylindrical heat pipe

Abstract

The invention discloses a rectification support plate hot air heat pipe composite anti-icing structure based on a cylindrical heat pipe. Belongs to the field of aero-engine anti-icing and comprises a support plate and cylindrical heat pipes, a hot air cavity is formed in the support plate, a hot air inlet is formed in the upper end of the support plate, a hot air outlet is formed in the lower end of the support plate, and the two are communicated with the hot air cavity; reserved row holes are formed in the supporting plate and used for containing cylindrical heat pipes. The reserved exhaust holes are not communicated with the hot air cavity; the cylindrical heat pipe is internally provided with reserved row holes in the front part of the support plate and is not directly exposed to a hot air cavity of the support plate; the supporting plate and the cylindrical heat pipe are assembled after being processed separately, and in order to facilitate assembly, the supporting plate is generally divided into two parts to be processed and then combined and welded with the cylindrical heat pipe. The surface temperature uniformity of the rectification supporting 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 aircraft engine anti-icing, and relates to a rectifier support plate hot gas heat pipe composite anti-icing structure based on a cylindrical heat pipe, which is specifically applied to the anti-icing measures of the aircraft engine air intake casing support structure (rectifier support plate) under severe weather conditions. Background Art

[0002] At present, ice formation on the windward surface during flight is a major problem affecting aircraft safety. There are often flight accidents caused by ice formation. As the engine is the power output, ice formation may be fatal to flight safety. When the aircraft passes through a cloud layer containing supercooled water droplets, all components located at the front of the engine (cap, rectifier support plate, guide vane, first-stage compressor blade) are susceptible to direct impact by supercooled water droplets and cause ice formation. Therefore, in order to avoid the adverse effects of flow field deterioration, thrust reduction, structural damage, etc. caused by engine ice formation, an engine anti-icing system must be designed. Among them, there are many ways to prevent ice formation on the front end components of the engine, such as electric heating anti-icing, hot gas anti-icing, lubricating oil anti-icing, etc. Among them, the hot gas anti-icing system is a mature, reliable and most widely used anti-icing system. The heat exchange efficiency of the traditional hot gas anti-icing system is low. In recent years, with the increase of engine thrust, the requirements for anti-icing air volume have gradually decreased. Therefore, it is necessary to design a more efficient heat exchange structure to improve the utilization efficiency of hot gas. In addition, the previous rectifier support plate heat exchange structure mainly focused on whether it could enhance heat transfer, but ignored the uniformity of heat transfer along the support plate. Therefore, it is urgent to design a new structure that takes into account both heat transfer efficiency and uniformity of heat transfer along the support plate. Summary of the invention

[0003] In view of the above problems, the present invention aims to propose a composite anti-icing structure of a rectifying support plate hot gas heat pipe based on a cylindrical heat pipe.

[0004] The technical solution of the present invention is: a rectifier support plate hot gas heat pipe composite anti-icing structure based on a cylindrical heat pipe according to the present invention comprises a support plate and a cylindrical heat pipe;

[0005] A vertical cavity (hot air cavity) is provided inside the support plate, a hot air inlet is provided at the upper end thereof, and a hot air outlet is provided at the lower end thereof, both of which are connected to the vertical cavity (hot air cavity);

[0006] A reserved row of holes is opened inside the support plate for placing cylindrical heat pipes;

[0007] The reserved row holes are not connected to the vertical cavity (hot air cavity);

[0008] The cylindrical heat pipe is built into the reserved row holes in the front of the support plate and is not directly exposed to the vertical cavity (hot air cavity) of the support plate. The two are assembled after separate processing. In order to facilitate assembly, the support plate is generally processed into two parts and then combined with the cylindrical heat pipe and welded.

[0009] Furthermore, the splitter plate is formed by 3D printing with titanium alloy material.

[0010] Furthermore, the thickness of the leading edge of the splitter plate at the front end of the splitter plate is not less than 3.5 mm.

[0011] Furthermore, the vertical cavity (hot gas cavity) of the splitter plate is located in the rear half of the splitter plate and does not cross the defined chordwise midline.

[0012] Furthermore, a heat-conducting material coating is provided between the splitter plate and the cylindrical heat pipe.

[0013] Furthermore, the cylindrical heat pipe should be a titanium-water heat pipe or a copper-water heat pipe, with a diameter not less than 3 mm and a wall thickness not greater than 0.5 mm.

[0014] Furthermore, the length of the cylindrical heat pipe is not less than 50% of the chord length of the splitter plate.

[0015] The beneficial effects of the present invention are as follows: The cylindrical heat pipe - hot gas composite anti-icing structure for the anti-icing of the fairing splitter plate of an aeroengine described in the present invention improves the surface temperature uniformity of the fairing splitter plate under anti-icing conditions and improves the utilization rate of hot gas. Description of the Drawings

[0016] Figure 1 is the overall structural schematic diagram of the present invention;

[0017] Figure 2 is the front view of the present invention;

[0018] Figure 3 is the top view of the present invention;

[0019] Figure 4 is the partial structural schematic diagram of the present invention;

[0020] Figure 5 is the curve graph of the leading edge temperature distribution of the present invention in an icing environment;

[0021] In the figure, 1 is the splitter plate, 2 is the cylindrical heat pipe, 3 is the hot gas outlet, 4 is the hot gas cavity, 5 is the leading edge of the splitter plate, 6 is the hot gas inlet, 7 is the graphite thermal conductive adhesive, and 8 is the chordwise midline. Detailed Embodiment

[0022] The following further elaborates on the specific technical solutions of the present invention with reference to specific examples.

[0023] As shown in the figure, a combined anti-icing structure of a rectifying strut and a heat pipe using heat pipe technology according to the present invention includes a strut 1 and a cylindrical heat pipe 2. A vertical cavity (hot gas cavity 4) is provided at the rear of the strut. The lower end of the vertical cavity (hot gas cavity 4) is a hot gas outlet 3, and the upper end is a hot gas inlet 6. The present invention is installed on the engine inlet casing, connected to the inlet casing fairing at the upper end and communicated with the air intake pipeline, and connected to a cap at the lower end. In the anti-icing condition, hot gas flows in from the hot gas inlet 6, passes through the hot gas cavity 4 and flows out from the hot gas outlet 3. During this process, heat is quickly transferred to the leading edge 5 of the strut through the cylindrical heat pipe 2.

[0024] Furthermore, the strut 1 used in the present invention should be made of titanium alloy material to meet the material requirements of lightweight and high strength for aero-engines. The wall thickness between the leading edge 5 of the strut and the reserved drainage holes should be above 0.8 mm to ensure the strength under vibration conditions.

[0025] Furthermore, the cylindrical heat pipe 2 used in the present invention should be a normal temperature heat pipe such as a titanium-water heat pipe or a copper-water heat pipe with an operating temperature between -20 and 300 degrees Celsius, a diameter not less than 3 mm, and a wall thickness not greater than 0.5 mm. Its internal structure is not limited, and one end close to the leading edge 5 of the strut should be designed to fit the contour of the leading edge 5 of the strut as much as possible.

[0026] Furthermore, the number of the cylindrical heat pipes 2 used in the present invention is not limited to that shown in the schematic diagram, but can be appropriately increased or decreased according to the length of the actually used strut 1. In Figure 1 it, the spacing between the cylindrical heat pipes 2 is 0.5 mm. To facilitate the control of the processing accuracy of 3D printing, the spacing can be appropriately increased.

[0027] Furthermore, as Figure 3 shown, the hot gas cavity 4 is located in the rear half of the strut 1 and does not cross the drawn chordwise midline 8; the hot gas cavity 4 is not limited to the shape shown in the schematic diagram and can be adjusted according to the size of the used strut 1, but it should be ensured that the tail of the strut 1 has a width of more than 30 mm;

[0028] The reserved drainage holes provided inside the strut 1 are used to place the cylindrical heat pipes 2, and their sizes should be slightly larger than the actually used cylindrical heat pipes 2;

[0029] The gap between the strut 1 and the cylindrical heat pipe 2 is filled with graphite thermal conductive adhesive 7 or a plastic material with similar performance.

[0030] Furthermore, in the working environment where the external flow temperature, oncoming flow airspeed, and liquid water content are 263.15 K, 0.477 Ma, and 2 g / m 3 respectively, anti-icing is carried out with hot gas at a temperature of 540 K and a flow rate of 9.6 g / s, and the leading edge temperature distribution of the rectifying strut 1 with and without heat pipes is obtained. As Figure 5As shown, the temperature of the leading edge without a heat pipe structure 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, the temperature of its leading edge decreases rapidly. After arranging the cylindrical heat pipe 2 at the front of the strut 1 in the present invention, the overall heat transfer inside the strut 1 is more uniform, avoiding the rapid decrease of the leading edge temperature along the span direction; at the same time, the lowest temperature under this condition is about 20K higher than the freezing point, indicating that this device has a good anti-icing effect and can further reduce the amount of hot gas required for anti-icing.

Claims

1. A composite anti-icing structure of a rectifier support plate hot gas heat pipe based on a cylindrical heat pipe, characterized in that: It comprises a support plate (1), wherein a plurality of arranged reserved holes are opened inside one side of the support plate (1), and cylindrical heat pipes (2) are installed in each of the reserved holes.

2. The composite anti-icing structure of a rectifier support plate hot gas heat pipe based on a cylindrical heat pipe according to claim 1, characterized in that: A hot air cavity (4) is also provided inside the support plate (1), a hot air inlet (6) is provided at the upper end of the hot air cavity (4), and a hot air outlet (3) is provided at the lower end thereof.

3. The composite anti-icing structure of a rectifier support plate hot gas heat pipe based on a cylindrical heat pipe according to claim 2, characterized in that: The hot air cavity (4) is a vertical cavity, and one side of the hot air cavity is wrapped around the outside of the reserved row holes.

4. The composite anti-icing structure of a rectifier support plate hot gas heat pipe based on a cylindrical heat pipe according to claim 2, characterized in that: The hot air inlet (6) and the hot air outlet (3) are both connected to the hot air cavity (4); The reserved drain holes and the hot air cavity (4) are not connected to each other.

5. The composite anti-icing structure of a rectifier support plate hot gas heat pipe based on a cylindrical heat pipe according to claim 2, characterized in that: The cylindrical heat pipe (2) is built into the reserved row holes at the front of the support plate (1) and is not exposed to the hot air cavity (4) opened on the support plate (1).

6. The composite anti-icing structure of a rectifier support plate hot gas heat pipe based on a cylindrical heat pipe according to claim 1, characterized in that: The thickness of the front edge (5) of the support plate (1) on the side away from the hot air cavity (4) is ≥3.5 cm.

7. The composite anti-icing structure of a rectifier support plate hot gas heat pipe based on a cylindrical heat pipe according to claim 1, characterized in that: The hot air cavity (4) is arranged at the rear half of the support plate (1) and does not cross the chord-wise midline (8).

8. The composite anti-icing structure of a rectifier support plate hot gas heat pipe based on a cylindrical heat pipe according to claim 1, characterized in that: A heat-conducting material coating is applied between the support plate (1) and the cylindrical heat pipe (2).

9. The composite anti-icing structure of a rectifier support plate hot gas heat pipe based on a cylindrical heat pipe according to claim 1, characterized in that: The support plate (1) is formed by 3D printing of titanium alloy material; The cylindrical heat pipe (2) is a titanium-water heat pipe or a copper-water heat pipe, with a diameter of ≥3 mm and a wall thickness of ≤0.5 mm.

10. The composite anti-icing structure of a rectifying support plate hot gas heat pipe based on a cylindrical heat pipe according to claim 1, characterized in that: The length of the cylindrical heat pipe (2) is not less than 50% of the chord length of the support plate (1).

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