Gas turbine combustor

A gas turbine combustor comprising:

• a combustion cylinder that defines a combustion chamber;
• a combustor that supplies a fuel to the combustion chamber;
• and
• a two-stage combustion nozzle that is disposed on a downstream side of the combustor in a flow direction of a combustion gas in the combustion chamber,
• wherein the two-stage combustion nozzle includes
• a nozzle flow path forming portion that forms a nozzle flow path having a nozzle injection port formed in an inner peripheral surface of the combustion cylinder, and
• a seal air flow path forming portion that forms a seal air flow path having a seal air injection port at least a portion of which is disposed on an upstream side of a nozzle central axis, which is a center line of the two-stage combustion nozzle, in the flow direction of the combustion gas.
• the nozzle flow path forming portion has a nozzle flow path wall that is continuous with the inner peripheral surface of the combustion cylinder,
• the seal air flow path forming portion further includes
• the nozzle flow path wall, and
• an inner flow path wall that is disposed inside the nozzle flow path wall and forms a fuel channel through which the fuel flows,
• the two-stage combustion nozzle further includes a partition wall that is connected to the nozzle flow path wall and the inner flow path wall in the seal air flow path.
• the partition wall has a tip portion which is a downstream-side end portion in a flow direction of seal air in the seal air flow path and a rear end portion which is an end portion opposite to the tip portion, and
• at least one of the tip portion or the rear end portion has a streamlined shape.