Patent ID: 6672829
Filing Date: 2004-01-06
Classification: F01D,F05D

Abstract:
A turbine blade for a gas turbine engine including an airfoil and integral dovetail for mounting said airfoil along a radial axis to a rotor disk inboard of a turbine shroud, said airfoil comprising:(a) first and second sidewalls joined together at a leading edge and a trailing edge, said first and second sidewalls extending from a root disposed adjacent said dovetail to a tip plate for channeling combustion gases thereover; and (b) at least one tip rib extending outwardly from said tip plate, said tip rib being oriented so as to extend substantially between said leading and trailing edges; wherein said tip rib is oriented so that an axis extending longitudinally therethrough is at an angle with respect to said radial axis for at least a designated portion of an axial length of said turbine blade.