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AssigneeGeneral Electric Company
InventorsAbhijeet Jayshingrao Yadav, Nicholas Joseph Kray, Nitesh Jain, Saurabh Sanjay Rasal
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A rotor assembly includes a fan rotor shaft coupled to a fan rotor, a low pressure turbine rotor shaft coupled to a low pressure turbine rotor, and a joint device configured to connect the fan rotor shaft to the low pressure turbine rotor shaft, to allow torsion, shear and bending to be transferred between the fan rotor shaft and the low pressure turbine rotor shaft under normal operation, and allow torsion and shear but prevent bending to be transferred between the fan rotor shaft and the low pressure turbine rotor shaft under a fan blade-out event.
A rotor assembly comprising:
A method for fabricating a rotor assembly for a gas turbine engine, the method comprising:
A method for reducing unbalanced bearing loading of a gas turbine engine under a fan blade out (FBO) event, the engine comprising a fan rotor shaft coupled to a fan rotor and a low pressure turbine rotor shaft coupled to a low pressure turbine rotor, the method comprising:
Dependencies are inferred from the claim text.