| 摘要 |
A compressor aerofoil (70) for a turbine engine or an axial process compressor, the compressor aerofoil comprises a suction surface wall (88) having a suction surface (89) and a pressure surface wall (90) having a pressure surface (91), the suction surface wall and the pressure surface wall meet at a leading edge (76) and a trailing edge (78) and define a tip (80) having a tip surface (86), the aerofoil has a maximum thickness Tmax. A mean camber line (108) is defined as passing through the leading edge and the trailing edge. The compressor aerofoil further comprises a winglet (100) at the tip (80) and which extends from the suction surface (89), the winglet (100) has an overhang Wmax that has a perpendicular extent from the suction surface (89) in the range 0.1Tmax to 1.5Tmax. The winglet (100) has a maximum overhang Wmax that occurs within 50% of the length of the mean camber line (108) from the leading edge(76). |
