INTEGRATED FAN/LOW PRESSURE COMPRESSOR ROTOR FOR GAS TURBINE ENGINE

摘要

This invention concerns a turbofan gas turbine engine with an integrated fan and low pressure compressor rotor which is mounted to a forward end of the shaft immediately upstream of a one piece engine support structure (20). The fan blade portion (30) and compressor blade portion (31) have aerodynamicall y aligned lateral airfoil surfaces and platforms enabling a single integrated rotor to replace prior art separate blades thereby simplifying the engine design and reducing the axial length of the engine.