| 摘要 |
PROBLEM TO BE SOLVED: To provide a method and a device for performing satisfactory and uniform cooling in a transition area between a combustion section and a discharge section of a turbine. SOLUTION: This device for cooling a combustor liner 112 and a transition component of the gas turbine is provided with the combustor liner 112 arrayed axial-directionally along a length determining a length of the combustor liner 112, and having a plurality of circular ring turbulators 140 positioned on an outer face 223, the first flow sleeve 128 having a plurality of cooling holes 34 formed around a circumferential part, the transition component 10 connected to the combustor liner 112, and the second flow sleeve having a line with a plurality of second cooling openings 120 to guide the cooling air to the second flow annulus 24 between the second flow sleeve 128 and the transition component 10. COPYRIGHT: (C)2006,JPO&NCIPI
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