Inflatable cascade assembly, system, and method for a cascade thrust reverser system

An inflatable cascade system for a cascade thrust reverser system of an engine of an air vehicle, the inflatable cascade system comprising:

• an inflatable cascade assembly coupled to a fixed portion of a nacelle of the engine, the inflatable cascade assembly comprising a plurality of inflatable cascade members movable between a stowed deflated state, when the cascade thrust reverser system is in a stowed forward thrust mode, and a deployed inflated state, when the cascade thrust reverser system is in a deployed reverse thrust mode, each inflatable cascade member comprising a forward end, an aft end, and a body formed between the forward end and the aft end;
• a forward flow valve coupled to the forward end;
• a pressurized fluid supply system coupled to the forward flow valve, the pressurized fluid supply system providing pressurized fluid to the plurality of inflatable cascade members, via the forward flow valve, to inflate the plurality of inflatable cascade members;
• a translating aft cascade support ring coupled at the aft end;
• and
• an aft flow valve coupled to the aft end.

A method of using an inflatable cascade system for a cascade thrust reverser system in an engine of an air vehicle, to provide a reduced aerodynamic drag of the engine, and to provide an increased fan nozzle efficiency of the engine, the steps of the method comprising:

• installing the inflatable cascade system for the cascade thrust reverser system, in the engine of the air vehicle, the inflatable cascade system comprising:
• an inflatable cascade assembly coupled to a fixed portion of a nacelle of the engine, the inflatable cascade assembly comprising a plurality of inflatable cascade members movable between a stowed deflated state, when the cascade thrust reverser system is in a stowed forward thrust mode, and a deployed inflated state, when the cascade thrust reverser system is in a deployed reverse thrust mode, each inflatable cascade member comprising a forward end, an aft end, and a body formed between the forward end and the aft end;
• a forward flow valve coupled to the forward end;
• a pressurized fluid supply system coupled to the forward flow valve, the pressurized fluid supply system having a pressurized fluid;
• a translating aft cascade support ring coupled at the aft end;
• and
• an aft flow valve coupled to the aft end,
• wherein the inflatable cascade system provides the reduced aerodynamic drag of the engine, and provides the increased fan nozzle efficiency of the engine;
• upon landing of the air vehicle, concurrently deploying from the stowed forward thrust mode, the translating aft cascade support ring, and a reduced length translating sleeve and one or more blocker doors, of the cascade thrust reverser system;
• opening the forward flow valve, and fully inflating the plurality of inflatable cascade members with the pressurized fluid from the pressurized fluid supply system, to form a trapped fluid in the plurality of inflatable cascade members, and to move the plurality of inflatable cascade members from the stowed deflated state to the deployed inflated state;
• redirecting a fan air flow with the fully inflated plurality of inflatable cascade members and with the one or more deployed blocker doors, to generate the deployed reverse thrust mode of the cascade thrust reverser system;
• closing the forward flow valve, and opening the aft flow valve to release the trapped fluid from the fully inflated plurality of inflatable cascade members, out through one or more pressure relief vents in the reduced length translating sleeve, and to move the plurality of inflatable cascade members from the deployed inflated state back to the stowed deflated state;
• and
• moving concurrently the translating aft cascade support ring, and the reduced length translating sleeve and the one or more blocker doors, from the deployed reverse thrust mode back to the stowed forward thrust mode, and closing the aft flow valve.