Patent ID: 7572102

Claim:
A large turbine blade comprising: a serpentine flow cooling circuit with a first leg adjacent to a leading edge of the blade; a second leg of the serpentine flow cooling circuit located adjacent to and downstream from the first leg; a last leg of the serpentine flow cooling circuit located near a trailing edge of the blade; an impingement cooling channel located on an upper span of the trailing edge of the blade, the impingement cooling channel having a first plurality of exit holes spaced along the upper span of the trailing edge of the blade; a cooling supply channel located on a lower span of the trailing edge of the blade, the cooling supply channel having a second plurality of exit holes spaced along the lower span of the trailing edge of the blade; a first cooling air supply passage in a root of the blade to supply cooling air to the first leg of the serpentine flow cooling circuit; a second cooling supply channel in the root of the blade to supply cooling air to the cooling supply channel; and, a plurality of impingement holes to provide fluid communication between the last leg of the serpentine flow cooling circuit and the impingement cooling channel.