Patent ID: 7441410

Claim:
A manufacturing process of a gas turbine for use in manufacturing a gas turbine from a base plant comprising a gas turbine designed for one desired gas turbine cycle and including a compressor with a channel to compress a fluid flowing inside a casing to which stator vanes are fixed, said manufactured gas turbine having a different gas turbine cycle, 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, changing the distance between said inner surface and said outer surface in comparison with a corresponding distance in said base plant without deleting or adding stages of said compressor, and cutting a tip portion of a rotor blade or a root portion of said stator vane by a length substantially equal to an amount by which the radius from a rotation shaft center of said compressor to said outer surface has been reduced.