Dual-fuel combustion chamber nozzle of combustion gas turbine
A gas turbine and dual-fuel technology, applied in combustion chambers, continuous combustion chambers, combustion methods, etc., can solve problems such as unfavorable flame stability, difficulty in maintaining high-efficiency combustion, and disturbing the flow field of the combustion chamber, so as to avoid the phenomenon of uneven dilution, Protects against burnout and improves combustion stability
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[0018] The principle, structure and specific implementation of the present invention will be further described below in conjunction with the accompanying drawings.
[0019] figure 1 A schematic diagram of the structural principle of a gas turbine dual-fuel combustor nozzle provided by the present invention, the nozzle includes an axial central fuel passage 1 and a peripheral axial annular fuel passage 2 coaxially arranged with the axial central fuel passage 1, and its characteristics In that: outside the peripheral axial annular fuel passage 2, a peripheral axial annular dilution gas passage 3 coaxially arranged with the axial central fuel passage 1 is also arranged; the air passage of the nozzle is also arranged coaxially with the axial central fuel passage 1, and It is divided into a first-level peripheral radial annular air channel 4 and a second-level peripheral radial annular air channel 5 .
[0020] There are dense small holes 6 on the wall surface of the outlet end of ...
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