Coaxially staged burner for low-emission combustion chamber of dual-fuel gas turbine utilizing gaseous and liquid fuels

A coaxially staged burner for a low-emission combustion chamber of a dual-fuel gas turbine utilizing gaseous and liquid fuels, comprising:

• a mounting flange (1), a main fuel sleeve (2), and a swirler (3), wherein the mounting flange (1), the main fuel sleeve (2), and the swirler (3) are connected in a sealed manner;
• the swirler (3) comprises a first-stage hub (4), a plurality of first-stage full blades (7), a pilot-stage bluff body (10), a plurality of second-stage full blades (8), a second-stage hub (5), and a plurality of second-stage split blades (9);
• the pilot-stage bluff body (10) is connected to a rear end of the main fuel sleeve (2);
• a liquid fuel nozzle (6) is disposed inside the pilot-stage bluff body (10);
• an inner periphery of the first-stage hub (4) and an outer wall of the pilot-stage bluff body (10) are connected via the plurality of first-stage full blades (7);
• an inner periphery of the second-stage hub (5) and an outer wall of the first-stage hub (4) are connected via the plurality of second-stage full blades (8);
• and the inner periphery of the second-stage hub (5) and the outer wall of the first-stage hub (4) are connected via the plurality of second-stage split blades (9);
• and
• the pilot-stage bluff body (10) and the liquid fuel nozzle (6) form a center pilot stage;
• the pilot-stage bluff body (10), the first-stage hub (4), and the plurality of first-stage full blades (7) form a first premix stage;
• and the first-stage hub (4), the second-stage hub (5), the plurality of second-stage full blades (8), and the plurality of second-stage split blades (9) form a second premix stage;
• wherein the plurality of second-stage full blades (8) are arranged at equal intervals around an axis of the pilot-stage bluff body (10);
• each of the plurality of second-stage full blades (8) is internally provided with a second-stage blade gaseous fuel cavity (82);
• and an outer wall of the second-stage blade gaseous fuel cavity (82) is provided with a plurality of second-stage blade gaseous fuel holes (81);
• wherein the plurality of second-stage split blades (9) are arranged at equal intervals around the axis of the pilot-stage bluff body (10);
• one second-stage split blade (9) is disposed between any two adjacent second-stage full blades (8);
• each of the plurality of second-stage split blades (9) is internally provided with a second-stage blade liquid fuel cavity (92);
• and an outer wall of the second-stage blade liquid fuel cavity (92) is provided with a plurality of second-stage blade liquid fuel holes (91).