Patent ID: 6860110

Claim:
In a gas turbine comprising a turbine disc for constituting a turbine rotor and a rear portion shaft connected thereto in a downstream side of a gas path of said turbine disc and supported by bearing members having a bearing member metal in a main body stationary side, a cooling medium passage formed inside said turbine disc, a center hole for communicating a cooling medium formed in said rear portion shaft, said cooling medium is supplied from a rear portion side of said rear portion shaft to said center hole, said cooling medium is communicated in an axial direction from a rear portion side to a front portion side in said center hole and to said disc cooling medium passage, said cooling medium is communicated to turbine rotor blades which are cooled, a cooling medium recovery communication passage for recovering said cooling medium after cooling from a front portion side of the turbine, and a recovery means for recovering said cooling medium from said cooling medium recovery communication passage, the gas turbine further comprising: a heat shield pipe in which a heat shield pipe portion arranged in said center hole of said rear portion shaft and contacting an inner wall of said rear portion shaft at a first contact portion which is positioned in a front portion side within an axial direction range of said bearing member metal and for forming an air layer between said inner wall of said rear portion shaft and said heat shield pipe portion, a seal shaft portion positioned in a rear portion of said heat shield pipe portion for preventing leakage of said cooling medium between a face of said seal shaft portion opposed to said main body stationary side and said main body stationary side, and a flange portion positioned between said heat shield pipe portion and said seal shaft portion, are constructed as a single piece component.