Aero-engine cooling device

Abstract

The invention discloses an aero-engine cooling device. The aero-engine cooling device structurally comprises a device body, a water inlet valve, ventilation ports and water flow channels, wherein theinner part of the device body is hollow, the shape of the device body is cylindrical, the water inlet valve communicates with an outer shell, moreover, the connecting mode of the water inlet valve andthe outer shell is a fixed connection mode, the outer shell is connected with an inner shell through the ventilation ports, the ventilation ports are uniformly distributed on the device body, the water flow channels are distributed around the ventilation ports, the water flow channels communicate with one another, moreover, the water flow channels are closed in the device body, the connecting mode of the inner shell and fixing screw holes is a fixed connection mode, the fixing screw holes are uniformly distributed inside the device body. According to the aero-engine cooling device, the waterinlet valve, the ventilation ports and the water flow channels are arranged on the aero-engine cooling device so that water cooling, air cooling and air flow cooling can be performed when an aero-engine is used, so that the cooling modes of the aero-engine are greatly increased, and the functionality is complete.

Description

technical field [0001] The invention relates to a cooling device for an aero-engine, which belongs to the technical field of aeronautical equipment. Background technique [0002] In the development of the aviation field, China has always been in the leading position in the world, but for aviation engines, there is still a big gap between China and other developed countries. It can still keep its temperature within a controllable range, and still can't come up with a good solution, and the heat dissipation method of the existing aero-engine is still to dissipate heat from the engine through different heat dissipation devices, but this The method can not achieve effective heat dissipation, and its single heat dissipation method cannot solve the heat problem that the aviation engine in work produces all the time. Contents of the invention [0003] Aiming at the deficiencies in the prior art, an aero-engine cooling device of the present invention has a structure comprising a ...

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Problems solved by technology

[0002] In the development of the aviation field, China has always been in the leading position in the world, but for aviation engines, there is still a big gap between China and other developed countries. It can still keep its temperature within a controllable range, and still can't come up with a good solution, and the heat dissipation method of the existing aero-engine is still to dissipate heat from the engine through different heat dissipation devices, but this The method cannot achieve effective heat dissipation, and its single heat dissipation method can never solve the heat problem generated by the aircraft engine in operation.

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