Abstract: A thrust reverser for a fan-type turbojet engine is disclosed for use in a turbojet engine structure having an engine housing defining a primary gas flow duct and a fan housing generally coaxially arranged about the jet engine housing and defining therebetween a generally annular secondary gas flow duct. The thrust reverser has at least one thrust reverser door attached to the fan housing by a forward linkrod pivotally attached to a forward portion of the thrust reverser door and pivotally attached to the fan housing, and a rear linkrod pivotally attached to a rear portion of the thrust reverser door and also pivotally attached to the engine housing. The linkrod attaching mechanism enables the thrust reverser door to be movable between a forward thrust position wherein the door outer surface is substantially flush with an outer surface of the fan housing and a reverse thrust position wherein the thrust reverser door redirects the gases flowing through the secondary gas flow duct to provide a reverse thrust.

Abstract: A thrust reverser for a turbojet engine is disclosed in which the thrust erser baffles have one or more deflectors to direct the cold gas flow over an inner surface of the baffles to ensure that the inner surface remains out of contact with the hot gas flow. The deflectors are movably mounted on the baffles such that, when the baffles are in their forward thrust positions, the deflectors are retracted so as to be generally flush with the inner surface of the baffle so as not to interfere with the forward thrust flow of gases. The deflectors may be automatically deployed to their extended positions when the baffles are moved to their reverse thrust positions.