| 摘要 |
A gas turbine combustor assembly has a fuel/air mixer assembly (204) with a plurality of fuel/air mixer elements (206a-f). Each fuel/ air mixer element defines an air flow passage therethrough. A fuel injector (202) is coupled to the fuel/air mixer assembly. The fuel injector has a tip portion (218) with a plurality of fuel outlets (220a-f) arranged to direct fuel into the air flow passages of the air/fuel mixer elements. Each of the fuel/air mixer elements has at least one fuel outlet arranged to supply fuel to the element. |
