Patent ID: 7458779

Claim:
A gas turbine or compressor rotor blade, comprising a convex outer surface or suction side and a concave inner surface or pressure side, said suction and pressure sides being joined at their upstream ends by a leading edge and at their downstream ends by a trailing edge for gases and terminating on a platform, said platform being substantially rectangular and comprising an upstream fairing extending upstream from the leading edge and defining an upstream edge of the platform, and a downstream fairing extending downstream from the trailing edge and defining a downstream edge of the platform, said upstream and downstream edges of the platform being joined at their ends by two lateral edges of the platform, wherein said downstream fairing includes at least one through-notch that extends right through its thickness or dimension along the longitudinal axis of the blade, from the downstream edge of the platform towards a transverse line passing through the trailing edge, wherein the at least one notch is configured to divide the downstream fairing into two lateral portions.