Patent ID: 6196798
Filing Date: 2001-03-06
Classification: F01D

Abstract:
A cooled blade of a gas turbine, comprising:a cooling air passage formed inside of the cooled blade through which cooling air is caused to flow for cooling the interior of the cooled blade;a number of air-transpiration holes formed at a leading edge portion of the cooled blade so that said leading edge portion is shower-head cooled by the cooling air blown out from said cooling air passages by way of said air-transpiration holes; andpreventing means operative to reduce concentration of thermal stress around inlet/outlet ports of said air-transpiration holes at said leading edge portion of said cooled blade, thereby preventing cracking of the cooled blade around the inlet/outlet ports,wherein said preventing means comprises said air-transpiration holes, each having an orthogonal orientation in which an axis through said air-transpiration hole is substantially orthogonal to a plane which is tangential to said blade surface at said leading edge portion, none of said air-transpiration holes in said leading edge portion of said cooled blade having an orientation other than said orthogonal orientation.