| 摘要 |
The invention relates to a gas turbine blade. The invention starts from a gas turbine blade which comprises a blade platform having a blade trailing edge side, a blade convex side, a blade concave side and a blade leading edge side. A blade profile portion is connected to the blade platform. A groove is formed in the blade trailing edge side of the blade platform, wherein the groove runs form the blade concave side to the blade trailing edge side. The said groove begins on the blade concave side und exits on the blade trailing edge side. To allow a gas turbine blade with very high thermal and mechanical load capacities, it is proposed in accordance with the invention that the groove (17) comprises a first portion (19) which is curved with respect to a mean camber line (21) of a trailing edge (22) of the blade profile portion (16). |
