FIELD: engines and pumps.
SUBSTANCE: invention relates to aircraft engine production primarily to designing appliances reducing noise propagating in aerodynamic channels of turbojet machines namely in subsonic flow speed for example noise in two-stage turbojet turbine or blower. Turbojet annular and/or circular section silencer arranged ahead of or behind noise source incorporates closed circular grilles and noise absorbing enclosure. Circular grills form channel section that reflects noise, while noise absorbing enclosure partially or completely overlapping channel wall, forms channel section absorbing noise. Channel section with noise absorbing enclosure is arranged between noise source and channel section with closed circular grills.
EFFECT: higher noise absorption efficiency.
4 dwg
