DESIGNING METHOD OF COMBUSTOR TRANSITION PIECE

摘要

Provided is a designing method of a combustor transition piece (22) comprising setting an angle of a center line (s) of a combustor (2) relative to an axial center (R) of a rotor (4) of a gas turbine, setting a contraction ratio from a transition piece inlet (221) in which combustion gas flows to a transition piece outlet (222) from which the combustion gas flows out, forming an inner outline in a radial direction, by extending a straight line in parallel with the center line (s) from an inner end in a radial direction of the transition piece inlet (221) to a downstream side, while maintaining a cross-sectional area of the transition piece inlet (221), extending a straight line in parallel with the axial center (R) from an inner end in a radial direction of the transition piece outlet (222) to an upstream side, and connecting the straight lines by an arc, forming an outer outline in the radial direction by smoothly connecting an outer end in a radial direction on a tubular downstream side where the cross-sectional area of the transition piece inlet (221) is maintained, to an outer end in the radial direction of the transition piece inlet (221), and monotonously reducing a cross-sectional area from the tubular downstream side to the transition piece outlet (222), along the inner outline in the radial direction and the outer outline in the radial direction.