A stator vane assembly for a turbomachine

摘要

A stator vane assembly for a gas turbine engine (10) compressor (16) comprises a plurality of circumferentially arranged stator vanes (44A) and a plurality of circumferentially arranged load bearing struts (46). The leading edges (45,47) of the stator vanes (44A) and the struts (46) are arranged in a common plane. The leading edges (45,47) of the stator vanes (44A) and the struts (46) have substantially the same profile. The spacing (B) between adjacent struts (44A) in any group is the same. The spacing (C) between the suction surface (50) of one of the struts (46A) of the adjacent pair of struts (46) and an adjacent stator vane (44A) is less than the spacing (B) between adjacent stator vanes (44A) and the spacing (D) between the pressure surface (52) of the other of the struts (46B) of the adjacent pair of struts (46) and an adjacent stator vane (44A) is greater than the spacing (B) between adjacent stator vanes (44A) to equalise aerodynamic loading of the stator vanes (44A) and to reduce the aerodynamic losses of the struts (46). <IMAGE>