Combustor of a gas turbine

摘要

The present invention provides a combustor of a gas turbine engine, including: a fuel spray portion (3) configured to spray a fuel so as to create a diffusion combustion region (50) in a combustion chamber (12); a pre-mixture supply portion (4) configured to supply a pre-mixture gas including the fuel and an air so as to create a pre-mixture combustion region (51) in the combustion chamber, the pre-mixture supply portion being positioned concentrically with the fuel spray portion so as to surround the fuel spray portion; and an annular separation portion (43) disposed between a downstream end of the fuel spray portion and a downstream end of the pre-mixture supply portion so as to separate the diffusion combustion region and the pre-mixture combustion region from each other.