AVIATION GAS TURBINE THRUST REVERSING DEVICE
The invention relates to an aviation gas turbine thrust reversing device comprising an engine (10) and a radially outer engine casing (28) which at least partially encloses a core engine (30) to form a bypass duct (29). A rear section of the engine casing (28) can be displaced from a closed forward thrust position into a rear thrust reversal position. The invention is characterized in that the rear section of the engine casing (28) is designed in the form of at last two thrust reversal gates (31) which can be moved along a substantially arc-shaped path (32) relative to a central axis (1) of the engine. The bypass duct (29) is entirely open in the forward thrust position, while a trailing edge (33) of the thrust reversal gates (31) rests against a casing (34) of the core engine (30) in the thrust reversal position.