component is made of metal while the second blade component is a light weight composite material application_number US 201313789794 A description fig1 schematically depicts a turbofan engine a which as an example illustrates the application of the described subject matter the turbofan engine a includes a nacelle 10 a low pressure spool assembly which includes at least a fan 12 and a low pressure turbine 14 connected by a low pressure shaft 16 and a high pressure spool which includes a high pressure compressor 18 and a high pressure turbine 20 connected by a tie shaft 22 and a high pressure shaft 24 the engine further comprises a combustor 26 advanced fans in turbofan engines are transonic with high rotor tip speeds these transonic fans have to be strong enough to take a certain size of foreign object damage without a significant performance loss at the same time the reduction of weight is a key requirement for aircraft engine design the fan 12 described in the following example combines the features of transonic rotor tip speed with relatively lower weight compared to fans with existing all titanium fan blades the fan 12 includes an array of circumferentially spaced dual rotor blades each made up of leading rotor blade 32 and trailing rotor blade 34 the leading.