Aircraft gas turbine engine nacelle

An aircraft gas turbine engine nacelle comprising:

• a thrust reversal arrangement including:
• at least one first circumferentially spaced fixed thrust reverser cascade box and at least one second circumferentially spaced fixed thrust reverser cascade box, each of the first and second circumferentially spaced fixed thrust reverser cascade boxes including a plurality of thrust reverser vanes configured to direct air forward in an axial direction of a gas turbine engine;
• and
• at least one circumferential turning vane configured to direct air in a direction having at least a circumferential component, the at least one circumferential turning vane being moveable between (i) a stowed position provided between or forward of the at least first and the at least second circumferentially spaced fixed thrust reverser cascade boxes, and (ii) a deployed position located axially rearward of the at least first and the at least second circumferentially spaced fixed thrust reverser cascade boxes, wherein:
• in the deployed position, an annular gap exists in the axial direction between the at least first and the at least second circumferentially spaced fixed thrust reverser cascade boxes and an axially forward edge of an aft cowling, and
• the at least one circumferential turning vane moves with the aft cowling through an inter-cascade gap and into the annular gap when in the deployed position to be located axially rearward of the at least first and the at least second circumferentially spaced fixed thrust reverser cascade boxes.