| 摘要 |
PROBLEM TO BE SOLVED: To provide a gas turbine combustor reducing cooling air flow rate while maintaining metal temperature of a combustion chamber liner within an appropriate range. SOLUTION: This gas turbine combustor is constituted by connecting a plurality of can type combustors with cross fire pipes. The can type combustor has the combustion chamber liner 20 on which a connection part of the cross fire pipe is arranged. A plurality of combustion holes 30a, 30b and cooling holes 40a, 40b, 40c for cooling the combustion chamber liner are arranged on the combustion chamber liner 20, and the combustion holes 30a, 30b are circumferentially dispersedly arranged thereon at axial positions approximately at the same position as the cross fire pipe connection parts 101. In addition to the cooling holes 40a, 40b, 40c, cooling hole columns 50a, 50b are also provided, and the cooling holes are more densely arranged on the axial area in the vicinity of the cross fire pipe connection part 101 of the combustion chamber liner 20 than other portions. COPYRIGHT: (C)2004,JPO
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