The invention relates to a dual-fuel
combustion chamber
nozzle of a
combustion gas
turbine, and belongs to the technical field of
combustion gas turbines. The dual-fuel
combustion chamber nozzle comprises an axial center fuel channel, a
peripheral axial annular fuel channel, a
peripheral axial annular
diluent gas channel, a first-level
peripheral radial-direction annular
air channel and a second-level peripheral radial-direction annular
air channel, wherein the peripheral axial annular fuel channel, the peripheral axial annular
diluent gas channel, the first-level peripheral radial-direction annular
air channel and the second-level peripheral radial-direction annular air channel are arranged to be coaxial with the axial center fuel channel. The
nozzle supplies
fresh air to the head of a
combustion chamber in a two-stage mode, meanwhile a
diluent is divided into three plumes, one plume is supplied to fuel, one plume is supplied to first-level air, and another plume is supplied to second-level air; the ratio of the three plumes of the diluents can be adjusted according to the result of optimizing the performance of the
combustion chamber, so that the sufficient air is supplied to the fuel for supporting combustion, and the good balance of efficient combustion and reduction of
flame temperature is obtained; secondly, the diluents, the fuel and the air are mixed well and then enter a
flame tube to take part in combustion, so that addition of the diluents does not disturb a inner flow field in the combustion chamber, and stability of combustion and good outlet temperature distribution are ensured.