The invention relates to a modular blade or vane for a gas turbine, which includes the modular components of a platform element with a planar or contoured surface defining a platform level and a through-opening therein, and an airfoil, extending through the platform element. The airfoil includes a load carrying structure extending along a longitudinal axis of the airfoil, having a root portion for fastening on a blade or vane carrier of the gas turbine, having a tip portion, and having at least one interior passage, extending from the root portion to the tip portion of the airfoil. An aerodynamically shaped shell extends in a distance over the carrying structure and defining the outer contour of the airfoil. A longitudinally extending gap, is disposed between the carrying structure and the shell. A number of through-holes in the carrying structure direct a cooling medium from the interior passage into the gap. The shell is integrally joined to said carrying structure by a first joint in a region below the platform level of the platform element. The shell is joined to the carrying structure by at least one additional joint, wherein said at least one additional joint is a form-fit joint, allowing relative movement in longitudinal direction between shell and carrying structure.