PURPOSE: To provide a multi-outlet film cooling structure of a turbine airfoil for enhancing film cooling effect, expanding a convection cooling area in a film cooling hole and improving film covering.

CONSTITUTION: A plurality of multi-outlet holes 46 formed through opposite walls 28, 30 defining a pressure surface and an intake surface of a turbine airfoil having a hollow interior chamber 40 permit passage of cooling air flow from the hollow interior chamber 40 to an external surface 44 of the wall portion. Each multi-outlet hole 46 comprises at least one flow inlet 52 formed on an internal surface 42 of the walls 28, 30, at least a pair of flow outlets 58A, 58B formed on the external surface 44 of the wall portion, and at least a pair of flow branches 64A, 64B extending through the wall portion and between the flow inlet and the flow outlets. The flow branches merge and intersect with one another at the flow inlet. The flow outlets are displaced preferably downstream of the flaw inlet relative to the direction H of gas flow past the external surface 44 of the wall of the airfoil. The branches are slanting with respect to the external surface 44 of the wall portion and run through walls 28, 30.