Heat dissipation integrated structure and aircraft

Abstract

The application relates to a heat dissipation integrated structure and an aircraft. The heat dissipation integrated structure comprises an electric drive cabin, a cooler, a wind guide ring and a propeller. The cooler is sleeved on the outer circumferential side of the electric drive cabin. Heat conducting medium can circulate between the cooler and a heat source of the electric drive cabin, so as to transfer heat in the electric drive cabin to the cooler. The propeller is arranged on the windward side of the cooler and is connected to the output end of the electric drive cabin. The wind guide ring is sleeved on the outer circumferential side of the cooler along one end of the axial direction of the wind guide ring, and the other end of the wind guide ring extends towards the direction close to the propeller. A wind guide channel is formed between the wind guide ring and the electric drive cabin, so that the airflow generated during the flight of the aircraft and the airflow generated by the propeller can flow to the cooler through the wind guide channel, so as to dissipate heat of the cooler. The heat dissipation integrated structure and the aircraft provided by the application solve the problem that the auxiliary electronic fan arranged on the aircraft significantly increases the volume and weight of the cabin of the aircraft.

Claims

1. A heat dissipation integrated structure, characterized in that, It includes an electric drive compartment (100), a cooler (200), a wind deflector (500), and a propeller (300). The cooler (200) is fitted on the outer periphery of the electric drive compartment (100). The heat transfer medium can circulate between the cooler (200) and the heat source of the electric drive compartment (100) to transfer the heat in the electric drive compartment (100) to the cooler (200). The propeller (300) is located on the windward side of the cooler (200) and connected to the output end of the electric drive nacelle (100). One end of the air guide ring (500) along its own axis is fitted onto the outer periphery of the cooler (200), and the other end extends toward the direction close to the propeller (300). An air guide channel (510) is formed between the air guide ring (500) and the electric drive nacelle (100) so that the airflow generated during the flight of the aircraft and the airflow generated by the propeller (300) can flow through the air guide channel (510) to the cooler (200) to dissipate heat from the cooler (200).

2. The heat dissipation integrated structure according to claim 1, characterized in that, The cooler (200) includes an inlet manifold (210), an outlet manifold (220), and a flat tube (230). The inlet manifold (210) and the outlet manifold (220) are respectively disposed and connected to the two ends of the flat tube (230). Multiple arc-shaped flat tubes (230) are arranged at intervals along the radial direction of the electric drive compartment (100). The inlet manifold (210), the outlet manifold (220), and the flat tube (230) together form an annular cooler (200) and are sleeved on the outer periphery of the electric drive compartment (100).

3. The heat dissipation integrated structure according to claim 2, characterized in that, The number of liquid inlet manifold (210) and liquid outlet manifold (220) is one each, and they are defined as the first liquid inlet manifold (211) and the first liquid outlet manifold (221) respectively. The flat tube (230) includes a first tube (231) and a second tube (232). The first tube (231) is arranged around one side of the outer peripheral area of ​​the electric drive compartment (100). Multiple first tubes (231) are arranged at radial intervals along the electric drive compartment (100). The second tubes (232) are arranged around the other side of the outer peripheral area of ​​the electric drive compartment (100). Multiple second tubes (232) are arranged at radial intervals along the electric drive compartment (100). The first liquid inlet manifold (211), multiple first tubes (231), first liquid outlet manifold (221) and multiple second tubes (232) are sequentially connected and enclosed to form an integral cooler (200).

4. The heat dissipation integrated structure according to claim 2, characterized in that, The number of the liquid inlet manifold chamber (210) and the liquid outlet manifold chamber (220) is two, which are respectively defined as the second liquid inlet chamber (212), the third liquid inlet chamber (213), the second liquid outlet chamber (222) and the third liquid outlet chamber (223). The flat tube (230) includes a third tube (233) and a fourth tube (234). The second liquid inlet chamber (212), a plurality of the third tubes (233) and the second liquid outlet chamber (222) are sequentially connected to form a first branch disposed on one side of the electric drive cabin (100). The third liquid inlet chamber (213), a plurality of the fourth tubes (234) and the third liquid outlet chamber (223) are sequentially connected to form a second branch disposed on the other side of the electric drive cabin (100). The first branch and the second branch enclose to form the split cooler (200).

5. The integrated heat dissipation structure according to claim 1, characterized in that, The electric drive cabin (100) includes a large-diameter section (130), a diversion section (140) and a small-diameter section (150) which are sequentially arranged and connected along the direction from the propeller (300) to the air guide ring (500). The outer diameter of the large-diameter section (130) is larger than the outer diameter of the small-diameter section (150). Along the direction from the large-diameter section (130) to the small-diameter section (150), the outer diameter of the diversion section (140) shows a decreasing trend. The cooler (200) is sleeved on the outer peripheral side of the small-diameter section (150), and the cylindrical air guide ring (500) is sleeved on the outer peripheral sides of the diversion section (140) and a part of the large-diameter section (130).

6. The heat dissipation integrated structure according to claim 5, characterized in that, The outer diameter D of the large-diameter section (130) and the outer diameter d of the small-diameter section (150) satisfy 0.6 ≤ d / D ≤ 0.

95.

7. The heat dissipation integrated structure according to claim 5, characterized in that, Along the direction from the large-diameter section (130) to the small-diameter section (150), the outer diameter of the diversion section (140) shows a uniformly decreasing trend; Alternatively, along the direction from the large-diameter section (130) to the small-diameter section (150), the amplitude of the decrease in the outer diameter of the diversion section (140) shows an increasing trend.

8. The integrated heat dissipation structure according to claim 1, characterized in that, The distance H between the cooler (200) and the propeller (300) along the axis of the propeller (300) satisfies 5 cm < H < 20 cm, and the length L of the air guide channel (510) along the axis of the propeller (300) satisfies 厘米≤ L < H.

9. The integrated heat dissipation structure according to claim 1, characterized in that, [[ID=,6]]The air guide ring (500) includes a plurality of segments (520) arranged in sequence along its circumferential direction. Each segment (520) includes a fixed section (521) and a diameter-changing section (522). The fixed sections (521) of adjacent segments (520) are fixedly connected, and the diameter-changing section (522) is movably connected to one end of the fixed section (521) close to the propeller (300); The air guide ring (500) also includes a controller, an adjusting motor (530), and an adjusting arm (540). The body of the adjusting motor (530) is installed on the fixed section (521). One end of the adjusting arm (540) is fixedly connected to the output end of the adjusting motor (530), and the other end of the adjusting arm (540) is connected to the variable diameter section (522). Alternatively, the body of the adjusting motor (530) is installed on the variable diameter section (522), one end of the adjusting arm (540) is fixedly connected to the output end of the adjusting motor (530), and the other end is connected to the fixed section (521). The controller can control the regulating motor (530) to drive the regulating arm (540) to rotate forward or reverse, so as to drive the end of the variable diameter section (522) away from the fixed section (521) to be tilted towards or away from the electric drive compartment (100), so as to increase or decrease the flow area of ​​the air guide channel (510).

10. An aircraft, characterized in that, It includes the heat dissipation integrated structure as described in any one of claims 1-9.

Images