飞机发动机一体化热管理系统建模与性能研究

Modeling and Performance Study of the Integrated Thermal Management System for Aircraft Engines

面对具有大幅变化范围的飞行器飞行条件,飞机和发动机热载荷也在随之发生剧烈变化,飞机/发动机如何有效解决宽范围下热载荷散热问题变得尤为突出。设计了基于闭式空气循环、燃油热管理系统以及装备蓄冷油箱的三涵道发动机的飞机发动机一体化热管理系统,并对此系统进行建模和数值仿真分析。分别建立一体化热管理系统在亚音速巡航、加速爬升和超音速巡航状态下的调控方案和热沉组合形式。三涵道模式给一体化热管理系统带来散热能力的提升。加速爬升和超音速巡航状态下,蓄冷油箱在严苛的飞行状态下能有效缓解单一燃油热沉在热管理系统中散热能力的局限性,提升热管理系统散热能力,保障飞行器安全可靠地工作。

Faced with the flight conditions of aircraft with a significant range of changes,the thermal loads of aircraft and engines are also undergoing drastic changes,and how to effectively solve the heat dissipation problem of thermal loads in a wide range of aircraft/engines is particularly prominent.This paper designs an integrated thermal management system for aircraft engines based on closed air circulation,the fuel thermal management system and a threeducted engine equipped with a cold-storage tank,conducts modeling and numerical simulation analysis on this system,and establishes control schemes and heat sink combination forms for the system in subsonic cruise,accelerated climb and supersonic cruise states respectively.The three-ducted model improves the heat dissipation capability of the integrated thermal management system.Under accelerated climb and supersonic cruise conditions,the coldstorage tank can effectively alleviate the limitations of the heat dissipation ability of a single fuel heat sink in the heat management system under harsh flight conditions,improve the heat dissipation ability of the heat management system,and ensure the safe and reliable operation of aircraft.