GAS TURBINE BLADE

摘要

In the cooling system for the gas turbine blade, the present invention ensures cooling of the trailing edge part of the blade for which machining is difficult, while aiming at improvement of the thermal efficiency. The steam cooling structure for carrying out heat recovery-type steam cooling is employed to the leading edge part and the central part of the blade where machining is easy because of its large thicknes, and the convection cooling and film cooling are employed for the trailing edge part of the blade where the thickness is small, using steam cooling and air cooling at the same time.