FIELD: engines and pumps.
SUBSTANCE: proposed aircraft engine comprises hollow nacelle, fan, gas turbine engine hot flow generator, fan channel inner fairing and multiple shutters. Fan channel inner fairing makes an external member of hot air generator to set, along with aforesaid nacelle, the boundaries of cold air channel and, with engine fairing, the boundaries of annular-section intermediate chamber. The latter has its rear section accommodating an appliance to allow communication of intermediate chamber with external side, nearby the boundary between cold and hot flows. Aforesaid shutters are fitted at the fairing rear to open only at gas turbine engine rpm higher than threshold value corresponding to at least aircraft cruising speed. Open shutters divert separate jets of hot air from hot flow into intermediate chamber, wherefrom hot air escapes via aforesaid communication aplliance.
EFFECT: reduced noise level.
15 cl, 23 dwg
