| 摘要 |
<p>A gas turbine combustor, wherein a ring (100) forming a cooling air layer is fitted to a combustion chamber inner tube (11), cooling air fed from a compressor through a cooling air supply hole (41) is supplied to the ring, and the cooling air flows out from a space (51) formed of the ring (100) and the inner wall surface of the combustion chamber inner tube (11) during the operation of a gas turbine to form the cooling air layer on the inner wall surface of the combustion chamber inner tube (11).</p> |
