Patent ID: 8702391
Filing Date: 2014-04-22
Classification: F01D,F05D

Abstract:
1. A gas turbine blade, comprising: a root; an airfoil with a leading edge and a trailing edge and a tip; and a cooling air channel system extending from a cooling air opening in the root via a winding serpentine channel to a trailing edge channel at the trailing edge, the cooling air channel system including an air outlet at the trailing edge and an air bypass channel directly connecting the cooling air opening in the root with the trailing edge channel bypassing the serpentine channel, wherein the cooling air channel system comprises a radial channel opening into the serpentine flow channel as well as into a tip channel connecting the cooling air opening in the root via the radial channel with an air outlet in a trailing edge section of a radially outer blade tip surface on a top of the tip supplying the trailing edge section of the radially outer blade tip surface on the top of the tip with cooling air.