Patent ID: 9212609
Filing Date: 2015-12-15
Classification: F02C,F05D,F23D,F23R

Abstract:
1. A turbine engine, comprising: a combined pilot gaseous fuel and air assist manifold; an air assist source coupled to the combined pilot gaseous fuel and air assist manifold; a pilot gaseous fuel source coupled to the combined pilot gaseous fuel and air assist manifold; a compressor system, the compressor system configured to discharge compressed gas into an enclosure; and a plurality of fuel injectors, wherein each fuel injector comprises: a pilot injector barrel, a combined pilot gaseous fuel and air assist tube, the tube connected to the combined pilot gaseous fuel and air assist manifold, terminating in a restricting outlet, and configured to direct a fluid supplied to the combined pilot gaseous fuel and air assist tube into a first end of the pilot injector barrel, the restricting outlet being positioned with respect to the pilot injector barrel to draw additional gas from the enclosure into the first end of the pilot injector barrel, a pilot liquid fuel circuit configured to distribute pilot liquid fuel at a second end of the pilot injector barrel; a first valve positioned between the air assist source and the combined pilot gaseous fuel and air assist manifold; a second valve positioned between the pilot gaseous fuel source and the combined pilot gaseous fuel and air assist manifold; and a controller configured to adjust the first valve and the second valve.