Patent ID: 9169045
Filing Date: 2015-10-27
Classification: B65D,F01D,F02K,F05D

Abstract:
1. A turbofan gas turbine engine comprising a fan, a fan casing and a fan blade containment arrangement, the fan comprising a fan rotor having a plurality of fan blades, the fan casing surrounding the fan rotor and fan blades, the fan blade containment arrangement surrounding the fan rotor and fan blades, the fan blade containment arrangement being arranged radially between the fan casing and the fan, the fan blade containment arrangement being axially shorter than the fan casing, the fan blade containment arrangement comprising a first layer of cellular material radially within an inner surface of the fan casing, a septum layer radially within an inner surface of the first layer of cellular material, a second layer of cellular material radially within an inner surface of the septum layer, a ductile layer radially within an inner surface of the second layer of cellular material and a layer of abradable material radially within an inner surface of the ductile layer, the ductile layer being axially shorter than the fan casing, the ductile layer having a higher yield stress than the layer of abradable material, the ductile layer having ductility which is greater than a crush initiation limit of the first and second layers of cellular material and the ductile layer being arranged to contain at least a portion of a detached blade without rupturing.