To provide a gas turbine combustor which maintains stable combustion and low NOX combustion performance in use of hydrogen-contained fuel.
The gas turbine combustor 9 includes a plurality of porous coaxial jet flow burners 50, 53 including a combustion chamber 1 supplied with fuel and air, an air hole plate 54 located at the upstream side of the combustor 1 and forming a plurality of air holes 55 in a shape of a concentric circle line, and a plurality of fuel nozzles 56 disposed at the upstream side of the respective air holes 55 of the air hole plate 54, and supplies the fuel to the air hole 55. In the gas turbine combustor 9 for combusting the hydrogen-contained fuel, a combustor chamber sidewall coaxial jet flow burner 62 includes a plurality of combustor chamber sidewall air holes 59 having a jet direction to be oriented toward a center axis of the combustor chamber 1 at the upstream sidewall of the combustor chamber 1 and a combustor chamber sidewall fuel nozzle 60 whioch is disposed coaxially with the combustion chamber sidewall air hole 59 supplies the fuel to the combustion chamber sidewall air hole 59. The plurality of combustor chamber sidewall coaxial jet flow burner 62 are disposed with a constant interval in a circumferential direction of the combustor chamber sidewall.
ASAI TOMOHIRO
AKIYAMA KYOTA
