Fuel / air premixer for a combustor system of a gas turbine with an air inlet and at least two fuel nozzles.

摘要

A fuel / air premixer for use in a burner in a burner system of a gas turbine includes an air inlet (1) a fixed nozzle geometry (4) and an annular mixing passage (3). The fuel / air premixer mixing fuel and air in the annular mixing passage for injection into a combustor reaction zone (5). A plurality of fuel sources (21, 22) is connected to the fixed nozzle geometry and each of the fuel sources can cooperate with the fixed nozzle geometry to effect a plurality of fuel flow variations, including variations in the type of fuel, the fuel mixture, volume flow and pressure conditions.