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Liquid metal heat dissipation system of aero-engine and aero-engine

A technology of aero-engine and liquid metal, which is applied in the field of aerospace, can solve the problems of low heat dissipation efficiency of aero-engines, achieve high-efficiency heat transport and heat dissipation, improve heat dissipation and cooling performance, and achieve the effects of unique material science and thermophysical properties

Inactive Publication Date: 2019-10-29
YUNAN JINGCHUANG LIQUID METAL THERMAL CONTROL TECH RES & DEV CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0007] What the present invention aims to solve is the technical problem of low cooling efficiency of existing aero-engines

Method used

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  • Liquid metal heat dissipation system of aero-engine and aero-engine
  • Liquid metal heat dissipation system of aero-engine and aero-engine
  • Liquid metal heat dissipation system of aero-engine and aero-engine

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Embodiment Construction

[0032] Embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings and examples. The following examples are used to illustrate the present invention, but should not be used to limit the scope of the present invention.

[0033] In the description of the present invention, unless otherwise stated, the meaning of "plurality" is two or more; the terms "upper", "lower", "left", "right", "inner", "outer" , "Top", "Bottom", "Front", "Back", "Head", "Tail", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of description The present invention and simplified description do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and thus should not be construed as limiting the present invention. In addition, the terms...

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Abstract

The invention relates to the technical field of aerospace, in particular to an aero-engine and a liquid metal heat dissipation system thereof. The liquid metal heat dissipation system of the aero-engine comprises an outer shell, an air inlet channel and a combustion chamber, wherein the air inlet channel is arranged in the outer shell, the combustion chamber is arranged in the air inlet channel, aliquid metal cooling tube is arranged between the outer shell and the air inlet channel, liquid metal is circulated in the liquid metal cooling tube, and the liquid metal cooling tube is arranged corresponding to the combustion chamber. The aero-engine is provided with the liquid metal heat dissipation system. According to the liquid metal heat dissipation system, the liquid metal cooling tube isarranged between the outer shell and the air inlet channel, the liquid metal is circulated in the liquid metal cooling tube, the liquid metal serves as a cooling medium, the temperature of the spacebetween the outer shell and the air inlet channel can be effectively reduced, the temperature of the space between the air inlet channel and the combustion chamber can be further reduced through heatconduction, so that the heat dissipation and cooling performance of the aero-engine is further improved, and the heat dissipation efficiency of the aero-engine is improved.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a liquid metal cooling system for an aero-engine and the aero-engine. Background technique [0002] The working characteristics of the combustion chamber of an aero-engine are: the inlet airflow velocity is very high; the volume of the combustion chamber is small (large heat capacity); the working temperature is high (up to 2500K); the airflow temperature at the outlet is limited by the strength of the turbine blades and cannot be too high ; Import parameters vary greatly. [0003] Therefore, a good combustion chamber must ensure normal operation under a wide range of these parameters, at least the flame cannot be turned off, so as to ensure that the engine can generate thrust and the aircraft can fly safely. Moreover, this task must be achieved with minimum pressure loss, maximum heat release in a limited available space, high efficiency and low pollution, that is, high effi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/16F02C7/14F03D9/28
CPCF02C7/14F02C7/16F03D9/28Y02E10/72
Inventor 舒红林陈志章朱奎董鑫段锦熙张秀梅盛磊刘静
Owner YUNAN JINGCHUANG LIQUID METAL THERMAL CONTROL TECH RES & DEV CO LTD
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