| 摘要 |
An aerofoil blade (30), for use as one of a ring of similar blades arranged in an axial flow turbomachine having an annular path for working fluid, has a radially inner platform region (32), a radially outer tip region (34), an axially forward leading edge (35) and an axially rearward trailing edge (36) which is straight between the platform region (32) and the tip region (34) and oriented radially of the annular path. The aerofoil blade (30) has a pressure surface (38) which is convex in the radial direction between the radially inner platform region (32) and the radially outer tip region (34) and a suction surface (40) which is concave in the radial direction between the radially inner platform region (32) and the radially outer tip region (34). The axial width (W) of the aerofoil blade (30), being the axial distance between the leading edge (35) and the straight trailing edge (36), varies parabolically between a maximum axial width (W max) at the platform and tip regions (32, 34) and a minimum axial width (W min ) at a position between the platform region (32) and the tip region (34). |
