| 摘要 |
PROBLEM TO BE SOLVED: To provide a gas turbine combustor capable of evenly supplying compressed air from a bypass passage into a combustor tail pipe and capable of reducing deviation of temperature distribution at a cross section of the combustor tail pipe. SOLUTION: This combustor for burning fuel is equipped with the bypass passage connected to one side of the combustor in order to supply the air to the combustor, and a circular passage provided around the combustor and communicating with the bypass passage. The air supplied from the bypass passage passes through an opening part communicating the combustor with the circular passage and is supplied into the combustor evenly along a peripheral direction while following through the circular passage along the peripheral direction. |
