| 主权项 |
1. A turbine combustor assembly, comprising:
a fuel/air mixer assembly comprising a plurality of fuel/air mixer elements, each of the fuel/air mixer elements comprising:
a fuel/air mixer body having an internal cavity extending axially between an air inlet and an air outlet; anda prefilmer residing within an interior cavity of the fuel/air mixer body, the prefilmer comprising an axial inner air flow passage extending coaxially with an axial centerline of the internal cavity of the fuel/air mixer body and a radial fuel injection port into the air flow passage; and a fuel injector coupled to the fuel/air mixer assembly, the fuel injector arranged to direct fuel into a plurality of the fuel/air mixer elements via the fuel injection port of the prefilmer of each fuel/air mixer element. |
