A system, 10, and method includes a thrust system, 24; a generator, 16, for providing electric power to at least one electromechanical actuator of the thrust system; a turbine, 14, for driving the generator, 16; a speed control valve, 20, for metering prop...

An aircraft gas turbine engine (7) axisymmetric vectoring nozzle has an interface ring centered about a nozzle centerline (8), a vectoring ring (86) disposed radially inwardly of and apart from the interface ring (20), and a bearing (22) radially disposed ...