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Rotor/wing aircraft including vectorable nozzle

  • US 9,878,785 B2
  • Filed: 04/21/2014
  • Issued: 01/30/2018
  • Est. Priority Date: 11/02/2005
  • Status: Active Grant
First Claim
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1. An aircraft comprising:

  • a propulsion system operable to produce an exhaust flow;

    a turbine including an inlet, a valve disposed in the inlet, an outlet, a vortical chamber and a chamber outlet, the inlet to receive the exhaust flow from the propulsion system;

    a nozzle disposed at an aft end of the aircraft to eject at least a portion of the exhaust flow;

    a first conduit fluidly coupling the outlet to the nozzle; and

    a second conduit fluidly coupling the chamber outlet to the first conduit, the valve operable between (1) a first position in which the exhaust flow is directed from the inlet to the outlet of the turbine during a fixed mode of operation, the exhaust flow provided to the nozzle via the first conduit in the fixed mode of operation, and (2) a second position in which the exhaust flow is directed from the inlet, through the vortical chamber, to the chamber outlet in a rotary mode of operation, the exhaust flow provided to the nozzle via the first conduit in the rotary mode of operation, the nozzle being vectorable between (1) an aftward direction to produce forward thrust during the fixed mode of operation and (2) a downward direction to produce vertical thrust at the aft end of the aircraft during the rotary mode of operation.

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