Patent ID: 6059530
Filing Date: 2000-05-09
Classification: F01D

Abstract:
A turbine blade comprising an airfoil and integral dovetail for mounting said airfoil to a rotor disk inboard of a turbine shroud, said airfoil including:first and second sidewalls joined together at a leading edge and a trailing edge, and extending from a root disposed adjacent said dovetail to a tip plate for channeling thereover combustion gases, and a cooling channel disposed in said airfoil for receiving cooling fluid through said dovetail;a first tip rib extending outwardly from said tip plate between said leading and trailing edges;a second tip rib extending outwardly from said tip plate between said leading and trailing edges, and spaced laterally from said first tip rib to define an open-top tip channel having a tip inlet near said leading edge for receiving said combustion gases, and a tip outlet near said trailing edge for discharging said combustion gases; andeach of said first and second tip ribs has an airfoil profile including opposite concave and convex sides extending from said tip inlet to said tip outlet for extracting energy from said combustion gases.