| 摘要 |
A gas turbine engine (10, figure 1) has a bladed rotor 44 surrounded by a casing (40, figure 1) having a blade containment system 62 which includes at least one layer of fibre metal laminate 78. The blade containment system 62 may also include a honeycomb layer 64 positioned radially exterior of an inner portion 66 of the annular casing (40), wherein the layer of fibre metal laminate 78 is positioned radially exterior or interior of the honeycomb layer 64. The blade containment system 62 may also include a radially exterior layer of Kevlar wrap (82, figure 4). The fibre metal laminate 78 may comprise aluminium and glass, aluminium and aramid, or titanium and graphite. In order to allow the fibre metal laminate 78 to be formed into a circumferential arrangement, a plurality of gore cuts may be provided therein. The fibre metal laminate 78 may be spliced together at its ends to form an annular shape. |
