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

#CMT# #/CMT# 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. #CMT#USE : #/CMT# Gas flow mixer for a turbofan engine (claimed) of a supersonic aircraft that is utilized for civil transport applications. #CMT#ADVANTAGE : #/CMT# The lateral wall connected to the panels is deployed as fan in the nozzle during deployment of the lobes, thus increasing effective surface for intaking the external air, and hence ensuring better mixture of an external air flow admitted in the nozzle and a gas flow from the generator. The jet noise of the engine is therefore reduced. The mixer does not disturb the gas flow when the lobes are in closed position. #CMT#DESCRIPTION OF DRAWINGS : #/CMT# The drawing shows a perspective view of a lobe of a gas flow mixer in closed position. 30 : Lobes 32 : Lateral walls 34 : Base 36 : External panel 38 : Intermediate panel.