Thrust reverser for a dual-flow turbine engine nacelle

A thrust reverser for a nacelle of a turbofan jet engine comprising:

• an upstream structure,
• fixed diverting means attached to the fixed upstream structure the means being capable of diverting at least part of a cold air stream of a turbojet engine outside the nacelle,
• a cowl sliding in translation in a direction substantially parallel to a longitudinal axis of the nacelle,
• at least one blocker door pivot mounted at an upstream end on the sliding cowl, the blocker door(s) being driven via a driving link,
• the sliding cowl being mobile via at least one actuating cylinder, and the blocker door also being connected to an actuating cylinder via at least one driving link so that a movement in translation of the actuating cylinder(s) of the sliding cowl and of the actuating cylinder of the blocker door enable the sliding cowl to move alternatively from a closed position, in which the blocker door is in stowed position and the sliding cowl ensures aerodynamic continuity of the nacelle by covering the diverting means, to an open position in which the sliding cowl opens a passageway in the nacelle by uncovering the diverting means and the blocker door is in pivoted position blocking part of an annular bypass duct of the nacelle,
• wherein the diverting means and the actuating cylinders are arranged in two substantially parallel planes one above the other in a radial direction of the nacelle, and at least one of the blocker doors is driven by one or both adjacent blocker doors controlled by an actuating cylinder.