Patent ID: 7530789

Claim:
A turbine blade for use in a gas turbine engine, the blade comprising: an airfoil having a pressure side and a suction side; a first row of film cooling holes located on the suction side of the blade; a first impingement cavity located to provide impingement cooling on the suction side wall of the blade and in fluid communication with the first row of film cooling holes; a second row of film cooling holes located on the pressure side of the blade; a second impingement cavity located to provide impingement cooling on the pressure side wall of the blade and in fluid communication with the second row of film cooling holes; a serpentine flow cooling path comprising a first cooling supply channel located on the pressure side of the blade and opposed to the first impingement cavity; a first metering and impingement hole to connect the first cooling supply channel to the first impingement cavity; the serpentine flow cooling path further comprising a second cooling supply channel located on the suction side of the blade and opposed to the second impingement cavity; and, a second metering and impingement hole to connect the second cooling supply channel to the second impingement cavity.