Patent ID: 8443585

Claim:
A gas turbine engine system, comprising: a first nozzle section; a second nozzle section, wherein the first nozzle section and the second nozzle section at least partially define a gas turbine engine bypass passage, wherein the second nozzle section is axially translatable relative to the first nozzle section such that there is a gap between the first nozzle section and the second nozzle section when the second nozzle section is moved from a first position to a second position; and a moveable door at least partially between the first nozzle section and the second nozzle section for selectively opening and closing the gap, wherein the moveable door includes a thrust reverse cascade between a radially inner surface of the moveable door and a radially outer surface of the moveable door relative to an engine centerline, the thrust reverse cascade including tracks to guide the moveable door during axial translation.