Patent ID: 6186740
Filing Date: 2001-02-13
Classification: F01D,F05D,Y02E

Abstract:
A gas turbine cooling blade comprising:a plurality of ribs defining a plurality of convection regions which are divided in a chord direction, the plurality of convection regions being designed to make a refrigerant jetted in the blade returns from a blade end and a blade root, and convect the refrigerant in the chord direction; andan insert inserted in a first convection region of the plurality of convection regions which is located on a front edge side of the blade, the insert having a plurality of nozzles formed therein, the insert being designed to jet the refrigerant onto a surface of the front edge side of the blade,wherein the refrigerant jetted out from the insert flows from a first passage in the first convection region, which is defined by the surface of the front edge side of the blade and a front edge of the insert, to a second passage in the first convection region, which is defined by a surface of a rear edge side of the blade and that rib of the plurality of ribs which defines the first convection region, and then all of the refrigerant flows through those convection regions of the plurality of convection regions which are subsequent to the first convection region, and in which no inserts are inserted.