Patent ID: 7416394
Filing Date: 2008-08-26
Classification: B23P,F01D

Abstract:
1. A rotor blade for an axial flow gas turbine engine, comprising: a blade root having a platform region; a curved main blade profile surface which extends from the platform region of the root, the blade profile having a suction side, a pressure side, a blade height, a leading edge, and a trailing edge where the trailing edge is located down-stream of the leading edge with respect to an operative working fluid flow direction; a first relief wall arranged parallel to a radial centerline of the blade and located in the main blade profile adjacent to the trailing edge, having a radially inner most edge and a radially outermost edge, and the first relief wall extends through the blade from the suction side to the pressure side of the main blade profile; a second relief wall parallel to the first relief wall having a radially inner most edge and a radially outermost edge, and extends through the blade from the suction side to the pressure side of the main blade profile; a third relief wall arranged between the radially inner most edges of the first and second relief walls extending through the blade from the suction side to the pressure side of the main blade profile; and a fourth relief wall arranged between the radially outer most edges of the first and second relief walls extending through the blade from the suction side to the pressure side of the main blade profile, wherein the first relief wall, second relief wall, third relief wall and fourth relief wall collectively define a relief slot arranged in the trailing edge region of the main blade profile.