Gas turbine rotor blade

摘要

In a gas turbine which is constructed such that there is provided a shroud at a terminal end of a blade and cooling air is led into the blade to flow through a multiplicity of cooling holes provided in the blade to be then led into the shroud and is flown out of a multiplicity of cooling passages provided in the shroud, a uniform flow of cooling air in both side portions of the shroud and thus a more uniform cooling of the shroud with a facilitated flow control of the cooling air is achieved by the following measures: The multiplicity of cooling holes of the blade (221) and the multiplicity of cooling passages (70-73,74-77) of the shroud (92) are sectioned into two groups, respectively. There are formed in the shroud (92) two cavities (80,81), each connecting to each one of the groups of cooling holes of the blade as well as connecting to each one of the groups of cooling passages of the shroud (92). The groups of the cooling passages of the shroud (92) are arranged so that the cooling air flowing therethrough is flown out of mutually opposing side portions of the shroud (92).