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US 2005/0238484 A1Published application
Gas turbine engine blade containment assembly
AssigneeROLLS-ROYCE plc
InventorsMichael Lawson, Sivasubramaniam Sathianathan
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AssigneeROLLS-ROYCE plc
InventorsMichael Lawson, Sivasubramaniam Sathianathan
Estimating the term…
A gas turbine engine rotor blade containment assembly (38) comprises a generally cylindrical, or frustoconical, metal casing (40). The metal casing (40) has at least one arched portion (62, 64, 66) and each arched portion (62, 64, 66) extends circumferentially around the metal casing (40). Each arched portion (62, 64, 66) comprises a radially inwardly extending arch (68) in which the trough (74) of the arch (68) is radially inwardly of a straight line (76) interconnecting the axial ends (70, 72) of the arch (68). The trough (74) of the arch (68) is radially inwardly of the at least one of the axial ends (70, 72) of the at least one arch (68). The arched portions (62, 64, 66) introduce compressive stresses into the metal casing (40) during a fan blade 34 impact and enable the metal casing (40) to withstand the impact. The fan blade containment assembly (38) is lighter for large diameter turbofan gas turbine engine (10).
A gas turbine engine rotor blade containment assembly comprising a generally cylindrical, or frustoconical, casing, the casing having at least one arched portion, the at least one arched portion extending circumferentially around the casing, the at least one arched portion having axial ends, the at least one arched portion comprising a radially inwardly extending arch in which the trough of the arch is radially inwardly of an imaginary cylinder, or imaginary frustocone interconnecting the axial ends of the arch, the at least one arched portion surrounding the rotor blades of the gas turbine engine a first axial end of the at least one arched portion being arranged substantially in a plane containing the leading edges of the rotor blades and a second axial end of the at least one arched portion being arranged substantially in a plane containing the trailing edges of the rotor blades.
Dependencies are inferred from the claim text.