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A thrust reverser having an engine cowl, a nacelle, a blocker door, a nacelle door and a cascade vane. The engine cowl has a hollow body that shrouds a jet engine and which includes a cowl opening. The nacelle surrounds the engine cowl and includes a nacelle opening that is positioned outwardly of

A thrust reverser having an engine cowl, a nacelle, a blocker door, a nacelle door and a cascade vane. The engine cowl has a hollow body that shrouds a jet engine and which includes a cowl opening. The nacelle surrounds the engine cowl and includes a nacelle opening that is positioned outwardly of the cowl opening. The blocker door is associated with the engine cowl and movable between a first position, wherein the blocker door closes the cowl opening, and a second position, wherein the blocker door is disposed in the propulsive air flow and substantially clears the cowl opening. The nacelle door is associated with the nacelle and movable between a forward position, which substantially closes the nacelle opening, and a rearward position, which substantially clears the nacelle opening. The cascade vane is disposed between the engine cowl and the nacelle and positioned between the cowl and nacelle openings.

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What is claimed is: 1. A thrust reverser system for an aircraft having a jet engine, the jet engine producing a propulsive air flow, the thrust reverser system comprising: an engine cowl having a generally hollow body, the body being configured to shroud at least a portion of the jet engine and inc

What is claimed is: 1. A thrust reverser system for an aircraft having a jet engine, the jet engine producing a propulsive air flow, the thrust reverser system comprising: an engine cowl having a generally hollow body, the body being configured to shroud at least a portion of the jet engine and including a cowl opening; a nacelle surrounding at least a portion of the engine cowl, the nacelle including a nacelle opening that is positioned radially outwardly of the cowl opening; a blocker door associated with the engine cowl and movable between a first position and a second position, wherein the blocker door is generally parallel the propulsive air flow and closes the cowl opening when the blocker door is placed in the first position, and wherein the blocker door is disposed in the propulsive air flow and substantially clears the cowl opening when the blocker door is placed in the second position; a nacelle cowl associated with the nacelle and movable between a forward position and a rearward position, wherein placement of the nacelle cowl in the forward position substantially closes the nacelle opening and wherein placement of the nacelle cowl in the rearward position substantially clears the nacelle opening; and a cascade vane disposed between the engine cowl and the nacelle and positioned between the cowl opening and the nacelle opening. 2. The thrust reverser system of claim 1, further comprising a first hydraulic actuator and a second hydraulic actuator, the first hydraulic actuator being employed to move the blocker door between the first and second positions and the second actuator being employed to move the nacelle cowl between the forward and rearward positions. 3. The thrust reverser system of claim 2, wherein the first hydraulic actuator includes a drag link that is pivotably coupled to the engine cowl at a first end and pivotably coupled to the blocker door at a second end. 4. The thrust reverser system of claim 3, wherein the first hydraulic actuator is a linear actuator. 5. The thrust reverser system of claim 2, wherein the second hydraulic actuator is a linear actuator. 6. The thrust reverser system of claim 1, further comprising a plurality of engine mounts, the engine mounts being configured to couple the jet engine to the engine cowl. 7. A jet aircraft comprising: an engine cowl having a cowl opening; a jet engine disposed in the engine cowl and producing a propulsive air flow that travels through at least a portion of the engine cowl; a nacelle disposed about at least a portion of the engine cowl, the nacelle having a nacelle opening that is positioned radially outwardly of the cowl opening; a cascade vane disposed between the engine cowl and the nacelle; a blocker door associated with the engine cowl, the blocker door being movable between a first position, which substantially closes the cowl opening, and a second position, which substantially clears the cowl opening, the blocker door operably re-directing at least a portion of the propulsive air flow out of the cowl opening and into the cascade vane when the blocker door is placed in the second position; and a nacelle door associated with the nacelle, the nacelle being movable between a closed position, which substantially closes the nacelle opening, and an open position, which substantially clears the nacelle opening; wherein no portion of the propulsive air flow flows between the engine cowl and the nacelle when the blocker door is in the first position and the nacelle door is in the closed position. 8. The jet aircraft of claim 7, further comprising a plurality of engine mounts coupling the jet engine to the engine cowl. 9. The jet aircraft of claim 7, further comprising a first actuator and a second actuator, the first actuator being employed to move the blocker door between the first and second positions and the second actuator being employed to move the nacelle cowl between the forward and rearward positions. 10. The thrust reverser system of claim 9, wherein the first actuator includes a drag link that is pivotably coupled to the engine cowl at a first end and pivotably coupled to the blocker door at a second end. 11. The thrust reverser system of claim 10, wherein the first actuator is a linear actuator. 12. The thrust reverser system of claim 9, wherein the second actuator is a linear actuator.