| 摘要 |
A gas turbine combustor 1 of the present invention comprises a fuel injector 13 for injecting a fuel F toward a combustion chamber 11; a swirler 14 which takes-in compressed air CA generated in a compressor and swirl the compressed air CA, in the vicinity of the fuel injector 13; a tubular guide member 34 for guiding the compressed air CA taken-in from the swirler 14, to the combustion chamber 11; and a heat shield 23 having a cylindrical portion 23b located outward relative to the guide member 34; wherein the cylindrical portion 23b has a purge hole 40; and air is introduced through the purge hole 40 and is supplied to a space 39 formed between the guide member 34 and the cylindrical portion 23b.
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