REAR MOUNTED REVERSE CORE ENGINE THRUST REVERSER

摘要

In one embodiment, a gas turbine engine for mounting to a rear of an aircraft fuselage has a propulsor that rotates on a first axis, and an engine core including a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section. The engine core is aerodynamically connected to the propulsor and has a second axis. A nacelle is positioned around the propulsor and engine core. The nacelle is attached to the wing of the aircraft. A downstream end of the nacelle has at least one pivoting door with an actuation mechanism to pivot the door between a stowed position and a vertical deployed position in which the door inhibits a flow to provide a thrust reverse of the flow.

主权项

1. A gas turbine engine for mounting to a rear of an aircraft fuselage comprising:
a propulsor that rotates on a first axis; an engine core including a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section, the engine core being aerodynamically connected to the propulsor and having a second axis; a nacelle positioned around the propulsor and engine core, the nacelle attached to the fuselage of the aircraft, wherein a downstream end of the nacelle has at least one pivoting door with an actuation mechanism to pivot the at least one door between a stowed position and a vertical deployed position in which the at least one door inhibits a flow to provide a thrust reverse of the flow.