EXHAUST ASSEMBLY FOR A HIGH SPEED CIVIL TRANSPORT AIRCRAFT ENGINE

摘要

Patent 13DV-9241 An exhaust assembly is provided for a gas turbine engine effective for propelling an aircraft from takeoff through subsonic and supersonic velocity. The exhaust assembly is effective for receiving exhaust gases discharged from an outlet of a core engine of an aircraft gas turbine engine. The assembly includes a casing, a variable area converging-diverging nozzle attached to the casing and including a first throat and an outlet for channeling exhaust gases received from the core engine. A plurality of retractable chutes are disposed upstream of the nozzle outlet and are positionable in a deployed position forming a converging nozzle having a second throat with a flow area less than that of the first throat. Means are provided for channeling air along aft facing surfaces of the chutes into the CD nozzle for mixing with the exhaust gases when the chutes are disposed in the deployed position for reducing noise from the exhaust gases.