Patent ID: 10202982

Abstract:
An object is to reduce the compressor flow rate in comparison with the reference model while maintaining a compression ratio equivalent to that in the reference model. Annulus areas required of a compressor 38 of a derivative gas turbine 200 are determined based on a compressor flow rate and a compression ratio required of the compressor 38 of the derivative gas turbine 200. Under the condition that the annulus area of each stage of the compressor 38 becomes equal to the determined annulus area, an inner radius increment and an outer radius decrement of an initial stage 36a are determined, the inner radius increment and the outer radius decrement of each of intermediate stages 36b-36e are determined so that the inner radius increment is not more than the inner radius increment of the previous stage and the outer radius decrement is not less than the outer radius decrement of the previous stage, and the inner radius increment and the outer radius decrement of a final stage 36f are determined so that the outer radius decrement is not less than the inner radius increment. The compressor 38 is designed by updating design data of components of the reference compressor 15 that deviated from the specifications due to the determination of the inner radius increment and the outer radius decrement so that the updated design data fulfill the specifications in each of the stages 36a-36f.