Gas flow mixer for turbofan engine of supersonic aircraft, has lobes formed of lateral walls, where each wall is connected to panels articulated at upstream end and deployed as fan in nozzle during deployment of lobes

摘要

The mixer has a nozzle placed around a gas generator of a turbofan engine. The nozzle has air intake openings in which lobes (30) are mounted. Each lobe is formed of lateral walls (32) connected by a base (34) and is moved between closed and deployed positions. The lobes close the openings in the closed position. The lobes disengage the openings and radially deployed in the nozzle to permit intake of external air. Each wall is connected to external and intermediate panels (36, 38) articulated at an upstream end. Each wall is deployed as a fan in the nozzle during deployment of the lobes.