Gas Turbine Combustor

A deviation of fuel injection amounts among a plurality of fuel nozzles connected to one fuel header is suppressed while suppressing increases in a manufacturing man-hour count and a pressure loss of a fuel. A gas turbine combustor includes: a liner forming a combustion chamber; a plurality of fuel nozzles; a fuel header to which the plurality of fuel nozzles are connected; and a fuel supply flow passage connected to the fuel header, the fuel header including a first chamber to which the fuel supply flow passage is connected and a second chamber to which the plurality of fuel nozzles are connected. An outlet of the fuel supply flow passage is opened in the first chamber, and at least one communication opening communicating with the first chamber is opened in the second chamber. The outlet of the fuel supply flow passage faces an inner wall surface of the first chamber. The second chamber includes a region spreading from the communication opening toward the combustion chamber, and inlets of the fuel nozzles are disposed closer to the combustion chamber than entirety of the communication opening.