MULTI-NOZZLE FLOW DIVERTER FOR JET ENGINE

摘要

An exhaust system for a variable cycle aircraft engine. The exhaust system comprises a core exhaust for bypass air and hot gases of combustion. The core exhaust includes a convergent-divergent nozzle. The convergent-divergent nozzle is formed from a plurality of flaps and seals. The exhaust system comprises a third air duct for a third stream of air. The third stream of air is selectively exhausted from the third duct through a secondary nozzle or divergent slots in the convergent-divergent nozzle, or both depending upon the flight mode. A diverter valve is positioned in the third stream duct to selectively control the flow of third stream air through the secondary nozzle, the divergent slots and combinations thereof.

主权项

1. An aircraft turbofan engine, having a fan portion providing three streams of air flow to the engine, comprising:
an engine core receiving core air flow that is exhausted through a primary nozzle; a bypass duct receiving bypass air flow; and a third air duct receiving third stream air flow, the third stream airflow flowing through the third duct, the third air duct having an air inlet and an air outlet, the air outlet of the third duct further comprising a secondary nozzle, the primary nozzle and a flow diverter valve to direct the third air flow to at least one of the secondary nozzle or the primary nozzle.