Patent ID: 7913495
Filing Date: 2011-03-29
Classification: F01K,F02C,F04D,Y02E,Y10T

Abstract:
1. A manufacturing process of a gas turbine system for use in manufacturing a gas turbine system from a base system comprising a gas turbine designed for one desired gas turbine system and including a compressor with a channel to compress a fluid flowing inside a casing to which stator vanes are fixed, said process comprising the steps of: forming said compressor channel for the fluid to have an inner surface defined by an outer circumferential surface of each of compressor rotor disks and an outer surface defined by an inner circumferential surface of said casing; reducing a distance between said inner surface and said outer surface in comparison with a corresponding distance in said base system; cutting off a root portion of said stator vanes by a length substantially equal to an amount by which a radius from the rotation shaft center of said compressor to said outer surface has been reduced; and using said stator vanes in which the root portion of each of the stator vanes at an outer side is cut off so as to decrease a length of a vane portion compared with said base system.