航空发动机热防护超临界CO_(2)闭式循环方案设计  

Aeroengine Thermal Protection Design Based on Closed Supercritical Carbon Dioxide Brayton Cycle

作　　者：李星剑 连华奇 李育隆[1,2] 徐思远[3] 马旭[3] LI Xing-jian;LIAN Hua-qi;LI Yu-long;XU Si-yuan;MA Xu(School of Energy and Power Engineering,Beihang University,Beijing 100191,China;Collaborative Innovation Center for Advanced Aero-Engine,Beijing 100191,China;Beijing Power Machinery Research Institute,Beijing 100074,China)

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100083 [2]北京航空航天大学先进航空发动机协同创新中心,北京100083 [3]北京动力机械研究所,北京100074

出　　处：《航空发动机》2024年第4期88-94,共7页Aeroengine

基　　金：中央高校基本科研业务费专项资金资助。

摘　　要：针对航空飞行器高速飞行时发动机热环境严峻、冷源有限的问题,提出了一种应用于航空发动机热防护、以超临界CO_(2)为工质的闭式布雷顿冷却循环方案。采用能量分析法构建布雷顿循环的数学模型,对比分析了简单循环、回热循环与间冷循环3种循环结构的优劣,比较了高温部件冷却通道的串并联结构对循环性能的影响。结果表明:回热循环能够提高系统热效率约4%,但热沉利用率降低50%;间冷循环能够降低系统热沉消耗8%,但会导致系统总质量增大;超临界CO_(2)简单循环是最符合发动机中间工质冷却循环工作需求的循环结构。对于简单循环而言,高温部件冷却通道并联结构的热效率比串联结构的高6%,但需要的碳氢燃料质量流量提高了2.7%,在碳氢燃料质量充足的条件下,并联结构的性能更优。In response to the harsh thermal environment and limited cold source of aeroengine during high-speed flight,an aeroengine thermal protection scheme based on a closed Brayton cycle using supercritical CO_(2) as the working fluid was proposed.Energy analysis was used to construct the mathematical model of the closed Brayton cycle.The advantages and disadvantages of three different cycle structures,namely simple cycle,recuperated cycle,and intercooled cycle were compared and analyzed.The influences of series and parallel connection of the cooling channels of high-temperature components on cycle performance were compared.The results show that compared to the simple cycle,the recuperated cycle increases thermal efficiency by over 4%,but decreases heat sink utilization rate by 50%;the intercooled cycle can decreases heat sink consumption by 8%,but will lead to an increase in the total mass of the system;the simple cycle is the best structure for meeting the requirements of aeroengine intermediate cooling cycle.For the simple cycle,the thermal efficiency of the parallel connection is 6%higher than that of the series connection,and the required mass flow rate of hydrocarbon fuel is increased by 2.7%.The parallel connection has better performance than the series connection given adequate hydrocarbon fuel.

关 键 词：热防护 闭式布雷顿循环 超临界CO_(2) 循环结构 航空发动机 高超声速飞行器 

分 类 号：V233.5[航空宇航科学与技术—航空宇航推进理论与工程]