| 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. |
