基于进发匹配的自适应循环发动机总体性能设计初步研究

Adaptive cycle engine performance design based on inlet/engine matching concept

建立了自适应循环发动机与进气道的流量匹配数学模型,提出了一种可行的自适应循环发动机总体性能设计方法,并以此为基础对采用FLADE(Fan on Blade)的自适应循环发动机的设计参数选取和性能优化开展了研究。结果表明,自适应循环发动机性能设计,需综合考虑超声速进气道高空大飞行马赫数设计点和发动机地面静止起飞设计点的进发流量匹配需求;发动机设计点FLADE涵道比取值,应随着进气道设计马赫数及该飞行状态下冷却用气需求量的增加而增大。

Based on a mathematical model of inlet/adaptive cycle engine airflow match, a feasible performance design method potentially applied to the adaptive cycle engine(ACE)was proposed and employed to implement a study on the design parameters selection and performance optimization of FLADE-ACE. It is demonstrated by research results that the airflow matching requirement of inlet high altitude/ high Mach number design point and engine SLS design point should be considered during FLADE-ACE performance design process and FLADE bypass ratio at engine design point should be increased as inlet design Mach number or cooling air requirement at this flight condition increases.