| 摘要 |
<p>An air fuel assembly (30, 32) for a combustor (10) in a gas turbine (12), the assembly comprising: a gaseous fuel nozzle (35) having a center axis and extending along the center axis, the fuel injection nozzle including a gaseous fuel passage and a fuel nozzle (50) at a distal end of the passage; an air tube (48) concentric with the fuel nozzle and defining an air passage between the air tube and the fuel nozzle (35), wherein the air tube includes a distal section (52) extending axially beyond the fuel injection nozzle; a first fuel-air mixing zone defined by and inside the distal section of the air tube, wherein said first fuel-air mixing zone is downstream of the fuel injection nozzle, and a flame holder (56) comprising a porous structure and defining a downstream end of the first fuel-air mixing zone, wherein fuel and air from the first fuel-air mixing zone pass through the porous structure of the flame holder and into a combustion zone of the combustor.</p> |
