| 摘要 |
<p>A rotor blade (100) for a turbine engine (10) including a blade root section (104) and an airfoil section (102) which extends radially outward along a radial line RAS from the blade root section (104), is described. The radial line RAS extends at an angle relative to a plane extending across a top surface of a platform (106), rather than normal, or perpendicular, to such plane. As a result, and during a blade out event, an over turning moment is generated in a root of the airfoil section (102). The overturning moment facilitates bending the airfoil section (102) reducing damage to the stator. <IMAGE></p> |
