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 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.
2. 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 a casing;
reducing a distance between said inner surface and outer surface in comparison with a corresponding distance in said base system;
cutting off a tip portion of a rotor blade and a root portion of said stator vane by a length substantially equal to an amount by which the radius from the rotation shaft center of said compressor to said outer surface has been reduced; and
using said stator vanes in which a 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.
3. 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 without deleting or adding stages of said compressor;
cutting off a root portion of said stator vane by a length substantially equal to an amount by which the radius from the rotation shaft center of said compressor to said outer surface has been reduced; and
using said stator vanes in which a 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.