Abstract: An aircraft has two vectorable front nozzles each mounted in a bearing located within the fuselage near an adjacent wing. Each nozzle is rotatable from a first position in which exhaust air is directed downwards to a second position in which the exhaust air is directed rearwards. In the first position the nozzle resides within a cavity formed in the wing root to reduce nozzle drag when the aircraft is propelled by its rear nozzle only. The front nozzles rotate out of their respective cavities to the second position when they are used for forward thrust. Additionally, the cavity is extended to form a passage through which secondary air entrained by exhaust from the front nozzle operating in the first position adds to the vertical thrust and reduces suck down effects.

Abstract: A valve for selectively changing the direction of flow of working fluid through a variable cycle engine which comprises a first and second compressor 14,16 spaced along a flow duct 26. The duct 26 having air intakes 42 leading to the second compressor 16 and outlets leading to nozzles 44. The valve comprising a sleeve 30 axially movable along the duct. The sleeve 30 having openings 31 in it in which are located doors 32. Links 36 are connected to each of the doors 32 so that as the sleeve 30 is moved axially the doors 32 are pulled open to open the air inlets 42 and the outlets and simultaneously obturate the flow duct 26. In a second position of the sleeve 30 the doors 32 and the sleeve 30 close off the air inlets and outlets and open the duct to allow the first compressor to supercharge the second compressor.