MULTI-STAGE IMPELLER

摘要

A multi-stage compressor rotor (10) for a gas turbine engine comprises an axial-flow rotor (12) followed by a centrifugal rotor (14). The axial-flow rotor (12) and the centrifugal rotor (14) are diffusion bonded together to form a unitary dual flow impeller having blades (22, 96) with continuos axia l- flow and centrifugal stage sections. By eliminating the gap between the axia l flow and centrifugal stages, unsynchronized air deflection between the successive arrays of blades is prevented, thereby improving the aerodynamic performance of the compressor rotor (10).