Patent ID: 6779979
Filing Date: 2004-08-24
Classification: F01D,F05D,Y10S

Abstract:
A method for fabricating a rotor blade for a gas turbine engine, said method comprising:forming an airfoil including a first side wall and a second side wall that each extend in radial span between an airfoil root and an airfoil tip, and wherein the first and second side walls are connected at a leading edge and at a trailing edge; and forming a rib that extends outwardly from at least one of the airfoil first side wall and the airfoil second side wall, and extends in a chordwise direction from the airfoil leading edge to the airfoil trailing edge, such that a natural frequency of chordwise vibration of the airfoil is increased to a frequency that is not excited by any excitation frequencies during normal engine operations.