| 摘要 |
In accordance with one embodiment, the present technique provides a combustor assembly (34) for use in a gas-turbine device. The combustor assembly (34) includes a first combustion zone (66) and a second combustion zone (46). The combustor assembly (34) further includes a first premix chamber (38) configured to receive a fuel (24) and air (58) to facilitate a first fuel-air mixture (62) having a first fuel-to-air ratio, wherein the first premix chamber (38) is fluidiclly coupled to the combustion chamber (42) at the first combustion zone (66). The combustor assembly also includes a second premix chamber (40) configured to receive a fuel (24) and air (60) to facilitate a second fuel-air mixture (72) having a second fuel-to-air ratio, wherein the second premix chamber (40) is fluidiclly coupled to the combustion chamber (42) at the second combustion zone (46), wherein the second combustion zone (46) is radially outboard of the first combustion zone (66).
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