Mixed flow exhaust thrust reverser with area control nozzle systems and methods
AssigneeRohr, Inc.
InventorJohann Steven Schrell
Life of this patent
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Abstract
An articulating exhaust nozzle thrust reverser includes an outer articulating panel comprising an outer skin and an outer thrust reverser door and an inner articulating panel comprising a forward inner skin, an aft inner skin, and an inner thrust reverser door. The outer articulating panel is configured to pivot to vary a nozzle exit area. The forward inner skin is configured to pivot to vary a nozzle throat area. The outer thrust reverser door is pivotally coupled to the outer skin. The inner thrust reverser door is pivotally coupled to the aft inner skin. The outer articulating panel and the inner articulating panel may be individually operated to independently vary the exhaust nozzle throat area and/or the exhaust nozzle exit area.
Claims20
An exhaust nozzle for an aircraft engine nacelle, comprising:
- a forward bulkhead;
- an outer articulating panel comprising an outer skin and an outer thrust reverser door, the outer articulating panel is configured to pivot with respect to the forward bulkhead;
- an inner articulating panel comprising a forward inner skin, an aft inner skin, and an inner thrust reverser door, the inner articulating panel configured to pivot with respect to the forward bulkhead;
- a nozzle throat at least partially defined at an interface between the forward inner skin and the aft inner skin;
- a nozzle exit at least partially defined at an aft end of the inner articulating panel;
- a first nozzle actuator configured to vary an angle of the outer articulating panel with respect to the forward bulkhead;
- and
- a second nozzle actuator configured to vary an angle of the forward inner skin with respect to the forward bulkhead;
- wherein a nozzle throat area of the nozzle throat is configured to be varied by the second nozzle actuator independent of a nozzle exit area of the nozzle exit;
- and
- the nozzle exit area is configured to be varied by the first nozzle actuator independent of the nozzle throat area.
A thrust reverser, comprising:
- an outer articulating panel comprising an outer skin and an outer thrust reverser door, the outer articulating panel is configured to pivot to vary a nozzle exit area;
- and
- an inner articulating panel comprising a forward inner skin, an aft inner skin, and an inner thrust reverser door, the forward inner skin configured to pivot to vary a nozzle throat area.
Dependencies are inferred from the claim text.