Patent ID: 8292582

Claim:
An air-cooled turbine blade comprising: an airfoil with a leading edge with a leading edge impingement cavity and a showerhead arrangement of film cooling holes to discharge film cooling air from the leading edge impingement cavity; a trailing edge with a trailing edge cooling circuit and a row of trailing edge exit cooling holes to discharge cooling air from the blade; a first up-pass near wall cooling channel formed on a pressure side wall of the airfoil and located in an airfoil mid-chord region; a first down-pass near wall cooling channel formed on the pressure side wall of the airfoil and located adjacent to and forward of the first up-pass near wall cooling channel; a second up-pass near wall cooling channel formed on a suction side wall of the airfoil and located in the airfoil mid-chord region; a second down-pass near wall cooling channel formed on the suction side wall of the airfoil and located adjacent to and forward of the second up-pass near wall cooling channel; the first up-pass channel connected to the first down-pass channel through a first tip turn channel; the second up-pass channel connected to the second down-pass channel through a second tip turn channel; a first mid-chord chamber formed between the first down-pass channel and the second down-pass channel; a second mid-chord chamber formed between the first up-pass channel and the second up-pass channel; a trailing edge up-pass channel formed in the trailing edge region and extending across the pressure sidewall and the suction sidewall; the second mid-chord chamber being connected to the first mid-chord chamber at a tip turn channel; and, the second mid-chord chamber being connected to the trailing edge up-pass channel through a root turn channel.