| 摘要 |
<p>A compressor aerofoil for a turbine engine, the compressor aerofoil comprises a suction surface wall and a pressure surface wall meeting at a leading edge and a trailing edge, a tip plate extends between the suction surface wall and the pressure surface wall and has a first tip rib and a second tip rib extending therefrom. At least one of the first tip rib and the second tip rib has a height R2 extending from the tip plate. A camber line is defined as passing through the leading edge and the trailing edge and the camber line length is from the leading edge to the trailing edge along the tip plate. The first tip rib and the second tip rib define a slot generally arranged along the camber line of the aerofoil. The first tip rib is located a distance L1 from the leading edge towards the trailing edge and the second tip rib is located a distance L2 from the leading edge, wherein The distances L1 and L2 are greater than 1% of the camber line length.</p> |
