Engine compartment cooling device

A cooling device and engine compartment technology, applied to the cooling system of the power unit, etc., can solve the problems of increasing air resistance, high temperature, destroying the smooth and continuous characteristics of the aircraft skin, and achieving the goal of reducing air resistance and uniform temperature distribution Effect

Pending Publication Date: 2021-03-09
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] 1) Due to the air intake, the smooth and continuous characteristics of the aircraft skin are destroyed, and the air resistance is increased;
[0005] 2) Limited by the location, the air intake can only be set on one side

Method used

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  • Engine compartment cooling device
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Example Embodiment

[0030]In order to make the objects, technical solutions, and advantages of the present application, the technical solutions in the present application embodiment will be described in more detail below in connection with the drawings in the present application embodiment.

[0031]In order to overcome the defects pointed out in the prior art, the present application provides an engine compartment cooling device that reduces air resistance and makes the air flow uniform in the engine compartment.

[0032]Such asfigure 1 withfigure 2As shown, the engine compartment cooling device 40 provided herein is disposed between the intake passage 20 and the engine 30, the generator cooling device 40 including a first metal ring 41, a second metal ring 42, and a restricted sheet 43.

[0033]The first metal ring 41 can be used as a transition portion between the inlet outlet and the engine inversion, and a plurality of intake opening 411 are provided on the circumferential direction. The second metal ring 4...

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Abstract

The invention provides an engine compartment cooling device. The device is arranged between an engine air inlet channel and an engine inlet. The engine compartment cooling device comprises: a first metal ring used for forming an airplane gas inlet channel and provided with a plurality of air inlet openings in the circumferential direction; a second metal ring arranged on the outer side of the first metal ring in a sleeving mode, wherein the second metal ring and the first metal ring form an annular gas collecting cavity capable of containing gas, and a plurality of gas outlet openings communicated with the annular gas collecting cavity are formed in the circumferential direction of the second metal ring; and a limiting piece arranged on the outer side of the gas outlet opening and coveringthe gas outlet opening, wherein the limiting piece and the gas outlet opening form a one-way valve which can only exhaust gas from the annular gas collecting cavity to the gas outlet opening. The non-ram gas inlet can be formed in the outer surface of an airplane, so that the gas resistance in flight is reduced, the engine compartment cooling gas inlets are formed in the forefront part of the engine compartment and are annularly and uniformly formed, and cooling gas flow in the engine compartment basically has no flowing dead zone, temperature distribution is uniform, and no local high-temperature zone exists.

Description

technical field [0001] The application belongs to the technical field of aero-engines, in particular to an engine compartment cooling device Background technique [0002] The engine is the power equipment required by the aircraft, and all aero-engines in the prior art utilize chemical energy to produce the power required for aircraft flight. In the process of power conversion, it is inevitable to dissipate heat to the surrounding space, so it is necessary to dissipate heat in the cabin where the engine is located. [0003] At present, the cooling of the cabin where the engine is located mostly adopts the method of setting ram air intakes on the surface of the aircraft, and the outside air is introduced into the engine compartment to cool it. Although the structure of this method is simple, it has the following disadvantages: [0004] 1) Due to the air intake, the smooth and continuous characteristics of the aircraft skin are destroyed, and the air resistance is increased; ...

Claims

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Application Information

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IPC IPC(8): B64D33/08
CPCB64D33/08
Inventor 杨子仲卞静于静
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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