| 摘要 |
A rotor blade for a gas turbine engine comprises an aerofoil projecting from a blade root 3 having a leading edge, a trailing edge 5, a concave pressure surface 2 and, a convex suction side 1. The aerofoil varies in section from root 3 to tip 4 such that: chord-wise convex curvature of the rear suction surface decreases, the tip 4 possibly being flat, or concaved, at its back surface, and blended into the lower portion of the aerofoil, which may have radial extents between 40%- 80% of the span; convex curvature of the early to mid suction surface increases; stagger of the aerofoil section increases, preferably resulting in convex curvature on the pressure surface 2, and; the trailing edge is a straight line, which may extend radially from the axis of blade rotation, or at an angle to this, and may comprise a row of chord-wise running cooling holes lying in a radial geometric plane. |
