| 摘要 |
<p>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 axial-flow and centrifugal stage sections. By eliminating the gap between the axial 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).</p> |
