In combination with intercooler

recuperator and intercooler duct model

an intercooled recuperated aero-engine(IRA) performance simulation methodology was developed based on conventional cycle two-spool unmixed flow high bypass ratio turbofan engine model. And an IRA performance calculation program was compiled. The characteristics of the IRA with separate intercooler duct exhaust were calculated and analyzed for the altitude velocity and throttling. The results indicate that

heat exchange process of the recuperator can always take place and IRA can operate normally in the flight envelope. In different conditions

the net thrust of the IRA is close to or higher than that of the conventional turbofan engine

while the specific fuel consumption of the IRA is reduced by 9% to 20%.