A turbine airfoil (10) usable in a turbine engine (12) and having an internal cooling system (14) with a leading edge showerhead (16) having a plurality of film cooling holes (18) positioned for efficient film cooling is disclosed. The film cooling holes (18) of the showerhead (16) may be aligned in spawnwise and chordwise extending rows forming the leading edge showerhead (16). In addition, a middle row (24) of film cooling holes (18) may be in alternating alignment with pressure and suction side rows (26, 28) forming the chordwise extending rows (31). In particular, a first middle row (24) cooling hole may be aligned with a pressure side row film cooling hole (34) and a second middle row cooling hole (36) may be aligned with a suction side row film cooling hole (38). The film cooling holes (18) may also have an ejection angle (40) that is nonorthogonal and nonlinear with an axis defining the middle, pressure or suction side rows (24, 26, 28) to eliminate dead spots within the flow pattern.
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