Patent ID: 7001150

Claim:
A rotor blade of a gas turbine engine, the rotor blade comprising: an airfoil extending from a root end to a tip end, the root end mounted to a connection apparatus for securing the blade to the engine, the airfoil having a leading edge, a trailing edge and an outer periphery, the outer periphery defined by a pressure side and a suction side each extending from the leading edge to the trailing edge; an open recess defined in the tip end of the airfoil extending from the tip end towards the root end, the recess having first and second sides corresponding to the airfoil pressure and suction sides; and at least one reinforcing element disposed in the recess and extending from the first side to the second side, the element disposed in the recess in a position adapted, in use, to minimize a trailing edge bending of the blade by reason of said position of the element in the recess.