The invention discloses a supersonic aircraft engine anti-frosting heat preservation method, and relates to the technical field of engine heat preservation. The supersonic aircraft engine anti-frosting heat preservation method comprises the following steps: 1, enabling a temperature sensor to sense the temperature of an aircraft engine shell, and enabling an operator to make a judgment according to the sensed temperature; 2, based on the step 1, when the threshold value of the frosting temperature is reached, heating the engine shell; 3, connecting a plurality of first-stage heat conduction pipes in series, and transferring the heat of a heating device to the engine shell; 4, carrying out electric pushing and stretching of a second-stage heat conduction pipe, so that the contact area withthe first-stage heat conduction pipes is increased, and the heat conduction efficiency is improved; and 5, recycling heat exhausted from a tail end opening of the engine, and forming heat circulationin a heat conduction inner cavity in the inner side of the engine shell. According to the supersonic aircraft engine anti-frosting heat preservation method, a heat transfer structure has adjustability, the second-stage heat conduction pipe can be independently used in cooperation according to actual use requirements and use conditions, and the heat transfer efficiency is higher.
本发明公开了一种超声速飞行器发动机防结霜保温方法,涉及发动机保温技术领域,本发明包括以下步骤:步骤一:温度感应器对飞行器发动机外壳温度进行感应,操作人员根据感应温度作出判断;步骤二:基于步骤一,到达结霜温度的阈值时对发动机外壳进行加热;步骤三:若干一级导热管串联,将加热装置的热量传递给发动机外壳;步骤四:二级导热管进行电动推伸,与一级导热管的接触面积增加,提升导热效率;步骤五:将发动机尾端口排出的热量进行回收,于发动机外壳内侧导热内腔内形成热循环。本发明一种超声速飞行器发动机防结霜保温方法,其热传递结构具备可调节性,根据实际使用需求及使用情况,其二级导热管可进行独立配合使用,热传递效率更高。
Supersonic aircraft engine anti-frosting heat preservation method
一种超声速飞行器发动机防结霜保温方法
2020-09-08
Patent
Electronic Resource
Chinese
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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