FIELD: machine engineering.
SUBSTANCE: fuel injector for an axial flow gas turbine includes annular channels for delivery to the combustion products. An annular air passage 62 for receiving the compressor discharge air. Adjacent to the axial end of the annular channel 62 of the air swirl vane channels 64 are disposed. The next first annular channel 66 is located radially within the annular air channel 62 and has a first opening 68 is disposed adjacent the first axial end of the annular channel 66 and downstream of the swirl blade 64 channels. The next second annular channel 70 is disposed radially inwardly of the first annular channel 66 and has a second opening 72 is disposed adjacent the second axial end of the annular channel 70 and downstream of the first holes 68.
EFFECT: provision of simple design with a more efficient spraying of liquid fuel in the pre-mixing channel for reducing emissions along with optimal use of the air curtain.
18 cl, 3 dwg
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