Abstract: A gas turbine combustor, which can enable only a swirler and a heat shield to be readily taken out from the combustor upon the exchange the swirler and the heat shield. The gas turbine combustor includes: a combustion cylinder; a fuel injection unit for supplying fuel to a head portion of the combustion cylinder; a support member configured for allowing the fuel injection unit to be supported by the combustion cylinder; and a heat shield adapted for heat-insulating the support member from combustion gas in the combustion chamber, wherein the fuel injection unit includes a fuel injection valve for injecting the fuel, and a swirler for supplying compressed air to the fuel injected from the fuel injection valve while swirling the compressed air. The swirler and heat shield are connected together, constituting a swirler unit. This swirler unit is detachably attached to the support member via a fastening member.

Abstract: This invention provides a gas turbine combustor, which can enable only a swirler and a heat shield to be readily taken out from the combustor upon the exchange the swirler and the heat shield. The gas turbine combustor (1) includes: a combustion cylinder (8) constituting a combustion chamber (11); a fuel injection unit (12) adapted for supplying fuel (F) to a head portion of the combustion cylinder (8); a support member (27) configured for allowing the fuel injection unit (12) to be supported by the combustion cylinder (8); and a heat shield (28) adapted for heat-insulating the support member (27) from combustion gas in the combustion chamber (11), wherein the fuel injection unit (12) includes a fuel injection valve (13) adapted for injecting the fuel (F), and a swirler (14) adapted for supplying compressed air (CA) to the fuel (F) injected from the fuel injection valve (13) while swirling the compressed air (CA).