Patent ID: 7402022

Claim:
A gas turbine engine rotor blade containment assembly comprising: a generally cylindrical, or frustoconical, casing, the casing having an axis and at least one integral member, the at least one integral member having a first portion extending radially from the casing and a second portion extending axially from the first portion of the at least one integral member; and at least one cassette comprising an upstream end, a base portion and a downstream end, the upstream end of the at least one cassette being arranged to extend radially inwardly from the base portion and in an axially downstream direction, the base portion of the at least one cassette being arranged to abut the inner surface of the casing, one or more liner panels being arranged in the at least one cassette, the upstream end of the at least one cassette being locatable on the second portion of the at least one integral member, the upstream end of the at least one cassette being shaped to correspond to the shape of the first and second portions of the at least one integral member to protect the first and second portions of the at least one integral member, and the downstream end of the at least one cassette having at least one axially extending member removably securable to the casing.