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).
申请公布号
WO03002913(A1)
申请公布日期
2003.01.09
申请号
WO2002JP06318
申请日期
2002.06.25
申请人
MITSUBISHI HEAVY INDUSTRIES, LTD.;MANDAI, SHIGEMI;TANAKA, KATSUNORI;KATAOKA, MASAHITO;SAITOH, KEIJIROU;AKIZUKI, WATARU