Patent ID: 6790005
Filing Date: 2004-09-14
Classification: F01D,F05D,Y02T

Abstract:
A gas turbine rotor blade comprising:an airfoil integrally joined with a mounting dovetail at a platform therebetween; said airfoil including opposite pressure and suction sidewalls extending chordally between opposite leading and trailing edges, and in span between a root adjoining said platform and an opposite tip; said tip including a floor bounded by integral, first and second ribs extending upwardly therefrom along said pressure and suction sidewalls, respectively, to define an open tip plenum therebetween; and said first rib being inclined outwardly from said tip plenum, and having a base offset inwardly from said pressure sidewall to form an outboard ramp inclined upwardly from a bullnose at said pressure sidewall to join said first rib at a fillet and define a notch extending chordally along said first rib between said leading and trailing edges.