Abstract: A turbofan engine has: an engine core producing a core exhaust flow; an upstream fan; a bypass duct carrying a bypass air flow produced by the fan; an exhaust assembly. The turbofan engine afterburner system has: a core plug; second core flow duct, and entrance(s) from the first core flow duct for diversion into the second of a portion of the core exhaust flow, and exit for re-joining the diverted portion of the core exhaust flow to the undiverted portion of the core exhaust flow; door(s) open during normal operation of the engine but closable, during a reheat operation, to block the entrances to the second core flow duct; and fuel injector(s) and igniter(s) operable, during the reheat operation, to inject and ignite fuel within the second core flow duct, providing a reheat flow into the core exhaust flow from the exit of the second core flow duct.

Abstract: A mounting arrangement of a gas turbine engine comprising a core engine, surrounded by a nacelle having a bypass duct, the mounting arrangement comprising a front mount, a rear mount and characterized by the mounting arrangement further comprising a fail-safe mount axially spaced from the front and rear mounts. The fail-safe mount comprises a number of A-frames connecting the core engine and the bypass duct. In normal operation the fail-safe mount does not transmit loads between the engine and a pylon, except in the event of damage to either the front or rear mounts.

Abstract: A gas turbine engine comprising a bypass duct defined radially outwardly by a nacelle and radially inwardly by a core engine casing. The nacelle comprises a thrust reverser unit having at least one blocker door rotatably attached to a static part and slidably connected to a translating part. The translating part is arranged to move between a stowed position and a deployed position and in the deployed position the blocker door spans the bypass duct. In the stowed position the blocker door is stowed inside the translating part and does not form part of an airwash surface of the bypass duct.

Abstract: A gas turbine engine comprising a core engine a fan and a fan casing surrounding the fan and extending rearwardly to attach to an array of outlet guide vanes characterised in that a cascade is rigidly attached to the fan casing and is connected to the core engine via a second support.

Abstract: A mounting system for use in mounting a gas turbine engine having an engine core to an aircraft comprises an engine support arrangement and front and rear mounting assemblies to mount the engine support arrangement to a casing surrounding the engine core. Each of the front and rear mounting assemblies comprises a plurality of circumferentially spaced mounting members to effect the aforesaid mounting of the engine support arrangement to the casing.

Abstract: A mounting assembly (10) for mounting a gas turbine engine on an aircraft. The assembly (10) comprising four equispaced hydraulic piston and cylinder thrust links (16) connecting between the engine fan case (12) and the air intake (14), which intake (14) is mounted to the airframe.

Abstract: A gas turbine engine comprising a bypass duct defined radially outwardly by a nacelle and radially inwardly by a core engine casing. The nacelle comprises a thrust reverser unit having at least one blocker door rotatably attached to a static part and slidably connected to a translating part. The translating part is arranged to move between a stowed position and a deployed position and in the deployed position the blocker door spans the bypass duct. In the stowed position the blocker door is stowed inside the translating part and does not form part of an airwash surface of the bypass duct.