GAS TURBINE COOLING BLADE, GAS TURBINE AND COOLING METHOD OF GAS TURBINE COOLING BLADE

摘要

PROBLEM TO BE SOLVED: To provide a gas turbine cooling blade, a gas turbine and a cooling method of the gas turbine cooling blade for restraining the occurrence of cooling nonuniformity, improving cooling side heat transfer performance, restraining consumption of a cooling medium, and improving efficiency of the gas turbine by uniformizing an inflow quantity of the cooling medium to respective passages when partitioned into a plurality of passages.;SOLUTION: This gas turbine has inside a plurality of partition walls 24a to 24e arranged in a zigzag shape, a serpentine-like cooling medium flowing passage 25 demarcated by these partition walls 24a to 24e and a partition wall 30 for partitioning the passage 26e into two parallel passages 29a and 29b in parallel and having an upstream side end part projecting to a folding-back part 27 more than the partition wall 24d for separating the passage 26d and the passage 26e just before folding back so that the cooling medium uniformly flows in these partitioned parallel passages 29a and 29b.;COPYRIGHT: (C)2004,JPO&NCIPI