ACTUATION OF A TURBOFAN ENGINE BIFURCATION TO CHANGE AN EFFECTIVE NOZZLE EXIT AREA

摘要

The invention relates to a turbine engine (10) that includes a spool (14) supporting at least one of a compressor (16) and a turbine (18). A turbofan (20) is coupled to the spool (14). The spool (14) is arranged in a core nacelle (12) and the turbofan (20) is arranged upstream from the core nacelle (12). A fan nacelle (34) surrounds the turbofan (20) and the core nacelle (12) and provides a bypass flow path (39). A structure (52) extends radially between the core (12) and fan (34) nacelles to support the core nacelle (12) relative to the fan nacelle (34). Surfaces (56) are supported relative to the fixed structure (52) and are moveable between closed and open positions to selectively obstruct bypass flow (13) through the bypass flow path (39), thereby changing the effective area of the exit nozzle (40). A change in the effective area of the nozzle exit (40) can be used to improve the efficiency and operation of the turbine engine.