Patent ID: 7137779

Claim:
A gas turbine airfoil comprising: a leading edge portion extending radially from a root of the airfoil to a tip of the airfoil; a cooling fluid supply chamber disposed within a first section of the leading edge portion and extending radially away from the root, the cooling fluid supply chamber receiving a cooling fluid; a first leading edge impingement chamber disposed against a backside of the leading edge portion in the first section and in fluid communication with the cooling fluid supply chamber, the first impingement chamber receiving the cooling fluid discharged from the cooling fluid supply chamber and discharging an impinged cooling fluid; a discharge chamber disposed radially outward of the first leading edge impingement chamber and in serial fluid communication with the first impingement chamber within a second section of the leading edge portion, the discharge chamber receiving the impinged cooling fluid discharged from the first impingement chamber; and a second leading edge impingement chamber disposed against a backside of the leading edge portion in the second section of the leading edge portion and in fluid communication with the discharge chamber, the second impingement chamber receiving the impinged cooling fluid discharged from the discharge chamber.