MULTI-FUEL INJECTOR HAVING SEPERATE AIR-PREMIXING STRUCTURES FOR THE PLURALITY OF FUELS AND A CONSEQUENT COMMON MIXING STRUCTURE BEFORE THE NOZZLE OUTLET

摘要

A system includes a turbine engine having a fuel injector. The fuel injector includes fluid ducts, each having a fuel inlet coupled to a distinct fuel source. The system includes a compressed air source that provides compressed air simultaneously to the fluid ducts, and a convergence point where combined fuel and air streams from the ducts are mixed. The fuel inlets are in a parallel flow arrangement such that no fuel from one fuel injector is present at another fuel injector.