a gas turbine engine having at least one spool assembly , the at least one spool assembly including a fan rotor , a compressor disposed downstream of the fan rotor , a turbine and a shaft connecting the fan rotor , compressor and turbine , a joint affixed to an upstream end of the shaft , and including a first link connecting the fan rotor to the shaft and a second link connecting the compressor to the shaft , the second link being less rigid then the first link .