| 摘要 |
A stator vane assembly for a turbomachine comprising a plurality of circumferentially arranged stator vanes (32), the axial position of the stator vanes (32) and/or the pitch angle circumferentially between adjacent stator vanes (32) is varied circumferentially around the stator vane assembly. The stator vane assembly reduces the pressure distortion upstream of the fan outlet stator vanes (32), reduces the circumferential pressure variation and this reduces blade forced response excitation, noise generation and aerodynamic losses. |
