Patent ID: 6077034
Filing Date: 2000-06-20
Classification: F01D,F05D

Abstract:
A blade cooling air supplying system of a gas turbine which comprises: a plurality of rotating blades each attached to a rotor through a blade root portion, and a plurality of stationary blades arranged alternatively with the rotating blades such that each stationary blade has outer and inner shrouds, a cavity for a respective seal in a lower portion of each inner shroud, and a respective seal box operatively associated with each of said stationary blades in a lower portion of each cavity for a seal; an air pipe extending through each of said stationary blades from the outer shroud to the inner shroud and inserted into each respective seal box; a plurality of rotating blade side cooling air introducing portions each being arranged in the blade root portion of a respective rotating blade and being adapted to guide cooling air to the respective rotating blade; and cooling air passages, each arranged in a respective one of said respective seal boxes and communicating with said air pipe of said respective seal box and opening toward an inlet of an adjacent one of said rotating blade side cooling air introducing portions; wherein the cooling air is sent to each of said air pipes and is blown out from said cooling air passages to the inlets of said rotating blade side cooling air introducing portions and is sent from the rotating blade side cooling air introducing portions to each rotating blade;wherein substantially all of the air supplied to said air pipes from an outer shroud side of the stationary blades is supplied to the rotating blades, and cooling air supplied to a leading edge portion passage out of each of said stationary blades is sent as air for sealing to the cavity of each stationary blade.