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AssigneeROLLS-ROYCE plc
InventorsSivasubramaniam K Sathianathan, Julian M Reed, Paul Hodgson, David Geary, Ian G Martindale
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A gas turbine engine fan blade containment assembly (38) comprising a generally cylindrical, or frustoconical, metal casing (40) which has an inner surface (62), an outer surface (64), an upstream flange (42) and a downstream flange (52). The outer surface (62) of the metal casing (40) is provided with a pattern of blind apertures (66) which extend radially inwardly from the outer surface (62) of the metal casing (40) between the flanges (42,52). The fan blade containment has reduced weight of the metal casing (40) of the fan blade containment assembly (38) for a large diameter turbofan gas turbine engine (10) but has unimpaired stiffness and penetration resistance.
A gas turbine engine rotor blade containment assembly comprising a generally cylindrical, or frustoconical, metal casing, to contain a gas turbine engine rotor blade in a gas turbine engine rotor blade containment region, the metal casing having an inner surface and an outer surface, at least a portion of the outer surface of the metal casing having a plurality of blind apertures extending into the casing from the surface of the casing to reduce the weight of the casing without impairing the stiffness and penetration resistance of the metal casing, wherein the depth of the blind apertures is in the range of 2.4 mm to 4 mm, the maximum diameter of the blind apertures is in the range 9 mm to 15 mm.
A gas turbine engine rotor blade containment assembly comprising a generally cylindrical, or frustoconical, metal casing, to contain a gas turbine engine rotor blade in a gas turbine engine rotor blade containment region, the metal casing having an inner surface and an outer surface, at least a portion of the outer surface of the metal casing having a plurality of blind apertures extending into the casing from the surface of the casing to reduce the weight of the casing without impairing the stiffness and penetration resistance of the metal casing, wherein the depth of the blind apertures is in the range of 2.4 mm to 4 mm, the maximum diameter of the blind apertures is in the range 9 mm to 15 mm.
A gas turbine engine rotor blade containment assembly comprising a generally cylindrical, or frustoconical, metal casing, to contain a gas turbine engine rotor blade in a gas turbine engine rotor blade containment region, the metal casing having an inner surface and an outer surface, at least a portion of the outer surface of the metal casing having a plurality of blind apertures extending into the casing from the surface of the casing to reduce the weight of the casing without impairing the stiffness and penetration resistance of the metal casing, wherein there is a first set of blind apertures having a first diameter, a second set of blind apertures having a second diameter and the second diameter is greater than the first diameter.
Dependencies are inferred from the claim text.