Abstract: A vectorable nozzle for directing the thrust produced by a gas turbine engine includes a duct, at least one toroidal nozzle segment, and a carrier ring for mounting the nozzle segment to the duct. The nozzle segment is hinged to the outer circumferential surface of the carrier ring about its toroidal axis. The carrier ring is rotatably mounted to the external surface of the duct at the downstream end thereof by means of a roller element bearing. The arrangement is such that the nozzle segment is moveable between a stowed location within the airframe space envelope and a deployed location. Once deployed the carrier ring is able to rotate the nozzle segment relative to the duct in order to vector the thrust produced by the engine.

Abstract: In a reheat system of an aircraft gas turbine engine there is provided a cantilever mounting for a ceramic tubular flameholder 10 on a metal bracket 11, the bracket being provided with a face having an upstanding annular flange 16 adapted to mate with the outer surface 19 of an end portion of the flameholder, there being further provided fastener means 12 adapted to retain the end face of said end portion of the flame holder adjacent and facing said face of the bracket, characterized in that said end portion of the flameholder is provided by a frusto-conical section 27 having first and second surfaces 18, 19 of different angles such that line extensions of each surface coincide at respective imaginary vertices on the axis of the flame holder.

Abstract: A low drag surface comprises at its upstream edge an intermittent linear vortex producing means extending transverse to the flow of fluid across the surface. The vortex producing means produces a succession of rolling vortices which roll across the surface reducing the drag between the main flow and the surface.