| 摘要 |
A turbofan gas turbine engine ( 10 ) comprises a fan rotor and a compressor rotor ( 62 ). The fan rotor ( 24 ) carries a plurality of circumferentially spaced radially outwardly extending fan blades ( 26 ). The compressor rotor carries a plurality of circumferentially spaced radially outwardly extending compressor blades ( 64 ). The fan rotor ( 24 ) is mounted on a fan shaft ( 38 ) and the compressor rotor ( 62 ) is mounted on a compressor shaft ( 68 ). The compressor shaft ( 68 ) is arranged around the fan shaft ( 38 ). The fan rotor ( 24 ) is rotatably mounted on a support structure ( 40 ) by a first bearing ( 50 ) and the compressor rotor ( 62 ) is rotatably mounted on the support structure ( 40 ) by a second bearing ( 58 ) spaced axially from the first bearing ( 50 ). The fan and compressor rotors ( 24, 62 ) are normally arranged coaxially with each other and with the support structure ( 40 ). The first bearing ( 50 ) is connected to the support structure ( 40 ) by a first frangible connection ( 54 ) and the second bearing ( 58 ) is connected to the support structure ( 40 ) by a second frangible connection ( 61 ).
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