Patent ID: 7252481
Filing Date: 2007-08-07
Classification: F01D,F05D,Y10S

Abstract:
1. A gas turbine engine blade adapted to be mounted in a blade attachment slot, defined between a front face and a back face of a rotor disc mounted for rotation about an axis, the blade comprising: a platform having a top surface and a bottom surface, an airfoil extending upwardly from said top surface of said platform, a root extending downwardly from said bottom surface of said platform, said root having a disc engaging portion adapted to be received in the blade attachment slot, wherein said blade has a natural frequency, and wherein said natural frequency is tuned by a tuning notch defined in a back side of the root radially outwardly of said disc engaging portion and of the blade attachment slot when the blade is mounted therein, and wherein said tuning notch extends axially inwardly relative to the back face of the rotor disc and the blade attachment slot when the blade is operatively installed on the disc.