Patent ID: 7334395

Claim:
An aircraft engine fan duct structure, comprising: a duct comprising an inlet for fluid flow into the duct in a thrust direction, a first outlet for fluid flow out of the duct, the duct being configured to guide fluid flow out of the duct through the first outlet in an at least partially reversed direction relative to fluid flow into the duct to reverse thrust, and a closure member in the form of a translating cowl member configured to selectively prevent fluid flow out off the duct through the first outlet, wherein the closure member is moveable relative to the duct between a deployed position for fluid flow out of the duct through the first outlet and a stowed position for preventing fluid flow out of the duct through the first outlet, wherein the reversed direction of fluid flow through the first outlet is greater than 90 degrees relative to a direction of fluid flow into the duct; and a slot adjacent a sidewall of the duct, the slot configured to control fluid flow through the duct to minimize flow separation, wherein the slot converges towards the first outlet to accelerate fluid flow.