To effectually achieve cooling when low calorie combustion is used, and securely protect a combustor liner and hence effectually reduce NOx by providing a cooling passage for closing in the form of a blind alley a downstream end side along a primary combustion region of the combustor liner and opening an upstream end side.

A gas turbine combustor 1 includes a flow sleeve 2 and a combustor liner 3 accomodated axially in the former, and further a combustion chamber 4 formed in the liner 3. It further includes a combustion nozzle 5 mounted on a head of the liner 3, from which a fuel is injected toward a primary combustion region 4a. A combustion air passage 6 is formed between the sleeve 2 and the liner 3 for guiding high pressure air from a compressor. In this case, a cooling passage 7 is provided which closes in the form of a blind alley a downstream end side along the primary combustion region 4a and opens an upstream end side. The passage 7 extends up to a drawing part 4b to derive the combustion air to the secondary combustion region 4c from there. Hereby, the liner 3 is effectually cooled.