<p>In a gas turbine that generates rotational power by supplying fuel to compressed air compressed by a compressor and burning the fuel in a combustor and supplying resultant combustion gas to a turbine, a circumferential distance (S) starting from a leading edge (32c) of a turbine first stage nozzle (32) toward a trailing edge (32d) side of the first stage nozzle (32) and ending at center of transition pieces (22) of such combustors that are adjacent in a circumferential direction is set relative to a circumferential pitch (P) of such first stage nozzles (32) within a range of 0.05‰¤S/P‰¤0.15, and an axial distance (L) between a leading edge (32C) of the first stage nozzle (32) and a transition piece rear end (222) of the combustor is set relative to the circumferential pitch (P) of the first stage nozzles (32) within a range of 0.00‰¤L/P‰¤0.13. By improving the relative position of a transition piece (33) of the combustor and the first stage nozzle (32), both suppression of inner pressure fluctuations of the combustor and enhancement in aerodynamic efficiency can be achieved.</p>
