| 摘要 |
FIELD: aircraft industry. ^ SUBSTANCE: proposed turbofan aircraft engine includes fan, high pressure compressor, combustion chamber, high-and low-pressure turbines, mixer at turbine duct outlet and common jet nozzle for air flow from fan and gas flow from turbine duct. Acoustical shield is installed in jet nozzle. Outer duct wall of shield forms diffuser annular channel with duct wall of nozzle to pass fan air. Degree of widening of diffuser annular channel of acoustical shield with duct wall of nozzle is 1.055-4.255. Invention increases noise damping of jet of turbofan aircraft engine with mixing of gas flow from turbine duct and air flow from fan, it reduces secondary losses and provides optimum spectrum of noise. ^ EFFECT: improved noise damping. ^ 6 cl, 4 dwg |
