Patent ID: 9016040
Filing Date: 2015-04-28
Classification: F02K,Y02T

Abstract:
1. A thrust reverser system for a gas turbine engine having a core engine, a core cowl surrounding the core engine, a nacelle surrounding the core cowl and comprising a fan cowl, and a bypass duct defined by and between the nacelle and the core cowl, the thrust reverser system comprising: a translating cowl mounted to the nacelle and adapted to translate in an aft direction of the gas turbine engine away from the fan cowl to define a circumferential opening therebetween, the translating cowl having a radially inner wall that defines a radially outer flow surface of the bypass duct; a fixed structure within the nacelle that does not translate when the translating cowl is translated in the aft direction; a cascade system mounted to the nacelle and adapted to move between a stowed position and a deployed position, the cascade system having a fore end and an oppositely-disposed aft end, the cascade system translating in the aft direction of the gas turbine engine and away from the fan cowl as the cascade system moves from the stowed position to the deployed position thereof, the aft end of the cascade system projecting into the bypass duct and the cascade system being operable to divert bypass air within the bypass duct through the circumferential opening when the cascade system is in the deployed positions thereof, the fore end of the cascade system being adapted for translating the cascade system in the aft direction, the aft end of the cascade system being adapted for initially causing the aft end to translate in the aft direction as the fore end translates in the aft direction and then subsequently pivot about the fore end so that further translation of the cascade system in the aft direction causes the cascade system to move to the deployed position into the bypass duct.