GAS TURBINE ENGINE BIFURCATION LOCATED FAN VARIABLE AREA NOZZLE

摘要

A gas turbine engine (20) comprises a core engine defined about an axis (A). The core engine includes a low pressure turbine (18) which defines a pressure ratio that is greater than about five (5). The engine further includes a fan (20) driven by the core engine about the engine axis (A) to generate a bypass flow (B) and a variable area flow system (42) which operates to effect said bypass flow (B).