| 摘要 |
A transsonic or supersonic compressor stage is equipped with vanes 11 defining inter-vane channels for gas flow. The outer surface of each vane comprises an inlet area 12 connecting with an intermediate area 13 via a dihedral lying between + 2 DEG and - 3 DEG at a point placed in such a way that the oblique shock wave given off by the connection arrives at the leading edge of the following vane. The intermediate area is connected to a downstream area 19 via another dihedral situated at the neck, which is itself situated in the vicinity of the impact point of the oblique shock wave given off by the leading edge of the following vane. The downstream area of the outer surface and the area opposite the inner surface of the adjacent blade exhibit a slight divergence provided in order to stabilise the straight shock wave. <IMAGE> |
