Systems and methods of operating a thrust reverser for a turbofan propulsion system

Abstract

The present invention relates to systems and methods of operating thrust reversers for turbofan propulsion systems. A thrust reverser assembly for a turbofan engine assembly is provided. The engine assembly includes a core gas turbine engine; a core shroud surrounding the core gas turbine engine; and a nacelle positioned radially outside the core shroud to define a fan nozzle duct between the core shroud and a portion of the nacelle, the nacelle including a stationary shroud. The thrust reverser assembly includes: a first translating cowl slidably coupled to the nacelle, the first translating cowl being positionable relative to the fixed cowl; a second translating cowl slidably coupled to the nacelle such that the first translating cowl is between the shield and the second translating shield, the second translating shield being positionable relative to the first translating shield; a positioning assembly coupled to the first translating shield; and operatively coupled to the second translating shield for selectively moving the second translating shield An actuator assembly configured to engage the positioning assembly to selectively move the first translating shield.

Description

technical field [0001] The field of the invention relates generally to aircraft gas turbine propulsion systems, and more specifically, to systems and methods for operating thrust reversers for turbofan propulsion systems. Background technique [0002] At least some known turbofan engines include a fan assembly, a core gas turbine engine enclosed in an annular core shroud, and a fan nacelle surrounding a portion of the core gas turbine engine. The fan nacelle is spaced radially on the outside with respect to the annular core shroud such that the core shroud and the fan nacelle form a fan nozzle duct with a discharge area. [0003] At least some known turbofan propulsion systems include thrust reverser assemblies. At least some known thrust reverser assemblies include a first stationary shroud, a second shroud axially translatable relative to the first shroud, and a third shroud axially translatable relative to the second shroud. More specifically, in some known thrust rever...

AI Technical Summary

Problems solved by technology

By including a second locking system between the first shroud and the second shroud, the thrust reverser assembly shown in the '713 patent may require flexible hoses and / or cables to bridge the gap between the fixed shroud and the first shroud during operation. gaps between enclosures, which can undesirably expose these components to adverse environmental conditions

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