| 摘要 |
A rotor blade for a gas turbine engine includes a blade root ( 3 ) and an aerofoil projecting therefrom, the aerofoil having a leading edge and a trailing edge ( 5 ), a generally concave pressure surface ( 2 ) and a generally convex suction surface ( 1 ). The aerofoil shape of the blade varies in section along the length thereof such that: the chord-wise convex curvature of the rear suction surface decreases towards the tip ( 4 ) of the blade; the convex curvature of the early to mid suction surface increases towards the tip; the stagger of the aerofoil section increases towards the tip; and the trailing edge ( 5 ) is a straight line.
|
