| 摘要 |
A dual-entry radial compressor rotor (140) has two sets of alternating full length blades (152a, 154b) and partial length blades (152b, 154b) on a symmetrical hub (144), with the partial length blades (152b or 154b) on one hub side terminating at the rotor high velocity exit coincident with the full length blades (154a or 152a) on the other hub side, to smooth the gas velocity profile in the tangential direction. Aerodynamically shaped sawtooth-profiled reliefs (172) are provided in the hub radial portion between the blade tips to allow induced pressure differentials between the flow paths to smooth the axial velocity profile. |
