The present invention is related to a turbine blade (100) for gas turbines including an inner platform (110) having a suction side mate face (116) and a pressure side mate face (118) for being in contact with the corresponding mate faces of adjacent turbine blades. The mate faces (116, 118) are contoured such that a radial height of the suction side mate face (116) is different from the radial height of the pressure side mate face (118) at a certain axial position. Due to inherent manufacturing tolerances, adjacent turbine blade platforms will not provide a flush flow boundary introducing secondary flow structures. Therefore, the deliberate variation of a radial height disparity between adjacent turbine blade platforms reduces the negative impact of said secondary flow structures due to waterfall and/or damming conditions when fluid flow crosses the inter-blade platform gap improving the overall aerodynamic efficiency of the turbine rotor.
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