Abstract: A power transmission arrangement comprises a first power transmission member connectable to a first main shaft of an engine. The arrangement also includes a second power transmission member connectable to a second main shaft of the engine and to a third power transmission member. A coupling assembly is provided which has a selectable coupling condition to couple the first power transmission member to the second power transmission member to allow power to be transmitted from the third power transmission member to the first main shaft of the engine via the first power transmission member. The coupling assembly has a decoupling condition to decouple the first power transmission member from the second power transmission member to allow power to be transmitted from the main shaft of the engine to the third power transmission member via the second power transmission member.

Abstract: A nacelle assembly 40 adapted for mounting on a ducted fan gas turbine engine 20 comprising a generally annular body 46 having an air inlet 42 and an air outlet 44, the generally annular body 46 encircling a region of the engine 20 when working in operative association with the engine 20 and has a first attachment means 48 to a rigid member 58 and a second attachment means 52 to a casing assembly 34 on the engine 20 wherein the second attachment means 52 is frangible.

Abstract: A gas turbine engine (10) is provided with a stage of turbine blades (22) surrounded by hollow shroud segments (28). Cooling of the shroud segments (28) is achieved by providing a flow of engine leakage air from space volume (48) centrally of the engine (10) via an annular compartment (46) wherein it is diverted away from the blade cooling system and passed via piping (44) within each guide vane (20) to shroud segments (28). The flow impingement cools the shroud segments (28) and then passes into the gas annulus via slots (60).

Abstract: A gas turbine engine (10) is provided with a stage of turbine blades (22) surrounded by hollow shroud segments (28). Cooling of the shroud segments (28) is achieved by providing a flow of engine leakage air from space volume (48) centrally of the engine (10) via an annular compartment (46) wherein it is diverted away from the blade cooling system and passed via piping (44) within each guide vane (20) to shroud segments (28). The flow impingement cools the shroud segments (28) and then passes into the gas annulus via slots (60).

Abstract: A method of assembly for a gas turbine engine and nacelle includes the steps of aligning the nacelle assembly and the engine substantially parallel to the rotational axis of the engine and translating the nacelle assembly along the axis to engage a first and a second attachment and securing the first attachment.

Abstract: A coupling arrangement (20) comprises a first article defining an elongate recess (26), and a second article having an elongate projection (27). The recess (26) and the projection (27) have opposite tapering faces (28, 30, 36, 38). When the projection (27) is received in the recess (26), the corresponding faces of the projection (27) and the recess (26) engage each other in co-operative coupling engagement. The arrangement further includes securing means (44, 46) to secure the first and second articles to each other in said co-operative coupling engagement. In the preferred embodiment, the projection (27) and the recess (26) are generally circular, and the faces (28, 30, 36, 38) are frustoconical.

Abstract: A nacelle assembly 40 adapted for mounting on a ducted fan gas turbine engine 20 comprising a generally annular body 46 having an air inlet 42 and an air outlet 44, the generally annular body 46 encircling a region of the engine 20 when working in operative association with the engine 20 and has a first attachment means 48 to a rigid member 58 and a second attachment means 52 to a casing assembly 34 on the engine 20 wherein the second attachment means 52 is frangible.

Abstract: A gas turbine engine has an assembly of circumferentially spaced rotor blades each having a radial tip. A plurality of seal segments mounted for radial movement circumscribe the rotor blades. Each segment is connected to the casing through a seal carrier provided with a flexible membrane which divides high pressure air from low pressure into two channels.