Patent ID: 6195979
Filing Date: 2001-03-06
Classification: F01D,F05D

Abstract:
A cooling apparatus for a moving blade of a gas turbine, which comprises:a rotor having a plurality of discs which are mounted with an interval between adjacent disc;a plurality of moving blades respectively mounted to an outer peripheral portion of each of the discs anda plurality of spacers respectively disposed in spaces between the respective discs at portions in proximity with said stationary blades wherein the moving blades are each formed with a cooling medium flow passage having inlet and outlet portions in communication with an interior of the rotor and wherein the discs and the spacers are arranged with spaces therebetween for passage of a cooling medium in a radial direction of the rotor so as to form a closed-loop cooling unit for supplying the cooling medium to the cooling medium passage formed in the moving blade and recovering the same therefrom,a passage assembly having a cooling medium supply passage and a cooling medium recovery passage running in parallel to each other in an axial direction of the turbine rotor, said passage assembly being provided at a central axis portion of the turbine rotor, said cooling medium supply passage including a cooling medium supply port in communication with a cooling medium inlet of the cooling medium flow passage formed in the moving blade through said space, said cooling medium recovery passage of the passage assembly including a cooling medium recovery port in communication with a cooling medium outlet of the cooling medium flow passage in the moving blade through said space, wherein at least one of the discs and the spacers of the turbine rotor extends to a central axis portion of the turbine rotor so as to form a portion of the passage assembly by using the extended portion and wherein the passage assembly is connected to said extended portion; anda spacer located on the downstream side of the disc forming the turbine rotor, said spacer including an implanted moving blade of a high-temperature and a high-pressure stage which includes a disc shape which extends to the central access portion of the turbine rotor wherein a space in the turbine rotor, in which the moving blade, of the high-temperature and high-pressure stage is disposed, is separated from other stages by said spacer so as to supply the air discharged from a compressor to the moving blade of the high temperature and high-pressure stage as a first cooling medium to perform open-loop cooling, and wherein the second medium is supplied to the moving blades of the other stages via the passage assembly so as to perform closed-loop cooling.