Rotor/wing aircraft including vectorable nozzle
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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Abstract
A method of operating an aircraft having a rotor/wing assembly and a nozzle comprises vectoring the nozzle into a position for creating vertical thrust, and using the rotor/wing assembly and the nozzle together to create vertical thrust during a rotary mode of operation.
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Citations
20 Claims
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1. An aircraft comprising:
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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. - View Dependent Claims (2, 3, 4, 5, 15, 16, 17, 18)
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6. A propulsion system comprising:
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a turbine engine; a vectorable nozzle at an aft end of an aircraft configured to receive exhaust flow from the turbine engine, the vectorable nozzle movable between (1) an aftward direction to produce forward thrust during a fixed mode of operation and (2) a downward direction to produce vertical thrust at the aft end of the aircraft during a rotary mode of operation; a conduit fluidly coupling the turbine engine to the vectorable nozzle; a vertical lift assembly including a rotor/wing, and a drive shaft and gear box; and a turbine to drive the vertical lift assembly in the rotary mode of operation, the turbine disposed in the conduit, wherein, in the fixed mode of operation, the exhaust flow from the turbine engine bypasses the turbine and flows through the conduit to the vectorable nozzle, and in the rotary mode of operation, the exhaust flow is directed through a chamber of the turbine to rotate the rotor/wing and create lift, a chamber outlet of the turbine being fluidly coupled to the conduit to provide the exhaust flow exiting the turbine to the nozzle at the aft end of the aircraft during the rotary mode of operation. - View Dependent Claims (19, 20)
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7. An aircraft comprising:
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a propulsion system operable to produce an exhaust flow; a radial inflow turbine to drive a vertical lift assembly, configured to be driven by the propulsion system to produce vertical thrust, from the exhaust flow during a rotary mode of operation; and a nozzle disposed at an aft end of the aircraft to eject at least a portion of the exhaust flow from the propulsion system, the nozzle vectored between (1) an aftward direction to produce forward thrust during a 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. - View Dependent Claims (8, 9, 10, 11, 12, 13, 14)
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Specification