| 摘要 |
A multi-point injector (10) for use in a gas turbine engine or other types of combustors comprises a plurality of nozzles (12) arranged in at least two arrays such as concentric rings (12, 14, 16, 18). The injector further has different fuel circuits (22) for independently controlling the fuel flow rate for the nozzles (12) in each of the arrays (12, 14, 16, 18). Each of the nozzles (12) include a fluid channel (47) and one or more swirler vanes (44) in the fluid channel for creating a swirling flow within the fluid channel. A method for injecting a fuel/air mixture into a combustor stage of a gas turbine engine is also described in which at least one zone has a flame hot enough to stabilize the entire combustor flame. <IMAGE> <IMAGE> |
