Gas turbine and manufacturing process of gas turbine
View Patent ↗The invention is intended to maintain turbine reliability when, based on a gas turbine designed for one desired cycle, a gas turbine for another different cycle is manufactured. A channel of a compressor is formed such that a mass flow of a fluid compressed by the compressor changes. Thus, when manufacturing, based on the gas turbine designed for one desired cycle, the gas turbine for another different cycle, turbine reliability can be maintained.
1. 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.
2. A manufacturing process of a gas turbine that is manufactured with respect to a first gas turbine from a base plant having one desired gas turbine cycle, said manufactured gas turbine including a compressor, the compressor having compressor rotor disks, a casing to which stator vanes are fixed and a channel for compressing a fluid flowing inside the casing, wherein the manufactured gas turbine has a gas turbine cycle that is different from said one gas turbine cycle, said processing 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 said 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 the corresponding distance in said base plant such that a mass flow of the fluid passing through said compressor channel is different from that of a comparable channel of a compressor of said one gas turbine cycle without deleting or adding stages for said compressor, and
cutting a tip portion of a roto blade or a root portion of said stator vane 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.