Patent ID: 8316632

Claim:
A thrust reverser for use with an aircraft nacelle, the thrust reverser comprising: a sleeve positioned at a rear of the aircraft nacelle and configured to translate rearward during thrust reverser deployment; a fan ramp positioned within the aircraft nacelle including an arcuate outward flare configured to provide an aerodynamic path to the airflow during thrust reverser deployment; a torque beam positioned within the aircraft nacelle including a radial ring extending inward from a fan cowl and a circumferential outer band axially extending from the radial ring to form a cavity between the circumferential outer band and the fan cowl and the torque beam configured to limit airflow into the aircraft nacelle during thrust reverser deployment; a plurality of cascades positioned radially outward of the circumferential outer band around the circumference of the torque beam during thrust reverser stowage and configured to translate from the cavity to direct air flow forward during thrust reverser deployment; and a plurality of blocker doors positioned in alignment with the plurality of cascades and configured to direct airflow through the plurality of cascades during thrust reverser deployment.