Gas turbine combustor

A gas turbine combustor (3) includes: multiple gaseous fuel nozzles (9) to inject gaseous fuel; a manifold (17) to distribute gaseous fuel to the multiple gaseous fuel nozzles; a burner flange (11) to secure a burner (200) to an end cover (6); and a burner body (10) to connect the manifold and the burner flange. Gaseous fuel passages (15, 18) are provided in the end cover, the burner flange, and the burner body. The gaseous fuel passage communicates with the manifold. A second manifold (16) is provided in the burner flange. The gaseous fuel passage is provided in the burner body to make the second manifold communicate with the first mentioned manifold.