| 摘要 |
<p>Aircraft turbofan engine (110) having a fan portion (116,136) providing three streams of airflow to the engine, and further comprising a core engine (114,120,122), a bypass duct (118) and a third air duct (132), where the third stream of air is selectively exhausted from the third duct through a secondary nozzle (142) or a primary nozzle (128), or both depending upon the flight mode. A diverter valve (140) is positioned in the third stream duct to selectively control the flow of third stream air through the secondary nozzle, the primary nozzle or combinations thereof.</p> |
