Patent ID: 10443855

Abstract:
A fuel burner system (10) configured to inject a liquid fuel and a gas fuel into a combustor (12) of a turbine engine (14) such that the engine (14) may operate on the combustion of both fuel sources (20, 24) is disclosed. The fuel burner system (10) may be formed from a nozzle cap (16) including one or more first fuel injection ports (18) in fluid communication with a first fuel source (20) of syngas and one or more second fuel injection ports (22) in fluid communication with a second fuel source (24) of natural gas. The fuel burner system (10) may also include an oil lance (26) with one or more oil injection passages (28) that is in fluid communication with at least one oil source (30) and is configured to emit oil into the combustor (12). The oil lance (26) may include one or more fluid injection passages (32) configured to emit air to break up the oil spray and water to cool the combustor (12), or both.