ENGINEERING OF GAS TURBINE AND PROCESS OF MANUFACTURE OF GAS TURBINE

摘要

PROBLEM TO BE SOLVED: To reduce a flow rate of a compressor as compared with that of a standard machine while keeping a compression rate similar to that of the standard machine.SOLUTION: A compressor 38 is designed by a method in which an annular band area required for the compressor 38 for a derivation gas turbine 200 is determined on the basis of a flow rate and a compression ratio required for the compressor 38 of the derivation gas turbine 200; an inner diameter increasing amount and an outer diameter decreasing amount at an initial stage 36a are determined under a condition in which an annular band area at each of the stages of the compressor 38 becomes the determined annular band area; an inner diameter increased amount and an outer diameter reduction amount at each of the stages of intermediate stages 36b to 36e are determined in such a way that the inner diameter increased amount becomes equal to or less than the inner diameter increased amount of a previous stage; an outer diameter decreased amount is determined in such a way that it becomes more than the outer diameter decreased amount of the previous stage; the inner diameter increased amount and the outer diameter decreased amount at the final stage 36f are determined in such a way that the outer diameter decreased amount becomes more than the inner diameter increased amount; and engineering data out of specification about composing elements of the standard compressor 15 as the inner diameter increased amount and the outer diameter decreased amount are updated to coincide with the specification at each of the stages 36a to 36f.SELECTED DRAWING: Figure 3