Gas turbine engine casing

Claim 1

A containment assembly comprising a gas turbine engine attached to an aircraft structure, said gas turbine engine having a longitudinal axis and an annular casing around which a plurality of fibrous layers are wrapped, a reinforcing plate being supported radially outward of the fibrous layers, the reinforcing plate being spaced apart from the fibrous layers and being rigidly attached to the aircraft structure, the reinforcing plate having sides which extend parallel to the longitudinal axis of the engine, the axially extending sides of the reinforcing plate being inclined radially inwardly towards the engine casing so that in operation, in the event of a rotating part of the gas turbine engine becoming detached, the rotating part will be contained within the annular casing by the fibrous layers with the fibrous layers distorting to absorb the energy of the rotating part, the distortion travelling through the fibrous layers around the annular engine casing, the axially extending sides of the reinforcing plate acting to deflect the distorted fibrous layers away from the aircraft structure so that the amount of interaction between the distorted fibrous layers and the aircraft structure is minimized.