Method of operating an aircraft bypass turbofan engine having variable fan outlet guide vanes

摘要

The method governs operation of an aircraft bypass turbo-fan engine, which has a longitudinally extending axis extending forward and aft, a longitudinally aft-most row of generally radially outwardly extending fan rotor blades. A core nacelle is disposed longitudinally aft of the blades and has a forward end defining a flow splitter. A fan nacelle circumferentially surrounds the blades and at least a part of the core nacelle. A row of variable-pitch fan outlet guide vanes is radially disposed between the fan and core nacelles and longitudinally disposed aft of the flow splitter. The method involves sensing an engine out condition for the engine, and repeatedly measuring fan rotor speed during the engine out condition.