Symmetric fuel injection for turbine combustor

摘要

A fuel injection system comprises a combustor liner, an air tube, a fuel manifold and a fuel injector. The combustor liner defines primary and secondary combustion zones. The air tube extends through the combustor liner along an axis to an exit aperture inside the combustor. The fuel manifold is positioned proximate the combustor line to deliver fuel through the air tube to the primary and secondary combustion zones. The fuel injector is coupled to the fuel manifold and positioned to inject the fuel along an axis of the air tube, such that the fuel has a substantially symmetric distribution at the exit aperture.

主权项

1. A fuel injection system comprising:
a combustor liner defining primary and secondary combustion zones; an air tube extending through the combustor liner along an axis to an exit aperture inside the combustor, and comprising a fuel tube formed along an inner axial surface of the air tube which forms a boundary for air flow, the fuel tube offset from the axis of the air tube; a fuel manifold positioned proximate the combustor liner to deliver fuel through the air tube to the primary and secondary combustion zones; and a fuel injector coupled to the fuel manifold and positioned to inject the fuel from the fuel tube substantially in a direction parallel to the axis of the air tube, such that the fuel has a substantially symmetric distribution about the axis of the air tube, at the exit aperture.