The invention relates to a turbine blade (10) or turbine vane (20) for a gas turbine, comprising successively along a radial direction of said gas turbine, a root (12) for attaching the turbine blade (10) or turbine vane (20) to a carrier, a platform (14), an aerodynamically shaped hollow airfoil (15) comprising a suction side wall and a pressure side wall extending with respect to the direction of a hot gas flow (16) from a common leading edge (18) to common a trailing edge (22) and extending transversely thereof from said platform (14) to an airfoil tip (24), wherein the airfoil (15) comprises at least one cooling cavity (30) extending in accordance to a cooling fluid flow direction from a platform level (17) to said airfoil tip, said at least one cooling cavity (30) being in fluid connection with a number of cooling fluid outlets (38) distributed along the trailing edge (22) through an array (34) of impingement cooling features located there between. To provide a turbine blade or turbine vane which is easy to manufacture and which enables sufficient cooling of the fillet in the vicinity of the airfoil trailing edge it is proposed that, said array (34) extends into a region (37) which is located radially outside the airfoil (15) within the platform (14) comprising also said impingement cooling features.