Patent ID: 7153091

Claim:
A gas turbine engine comprising a first rotor and at least a second rotor, the first rotor carrying a plurality of circumferentially spaced radially outwardly extending rotor blades, the second rotor carrying a plurality of circumferentially spaced radially outwardly extending rotor blades, the first rotor being mounted on a first shaft, the second rotor being mounted on a second shaft, the second shaft being arranged around the first shaft, the first rotor being rotatably mounted on a support structure by a first bearing, the second rotor being rotatably mounted on the support structure by a second bearing spaced axially from the first bearing, the first and second rotors being normally arranged coaxially with each other and with the support structure, the first bearing being connected to the support structure by a first frangible connection and the second bearing being connected to the support structure by a second frangible connection.