Patent ID: 6178751
Filing Date: 2001-01-30
Classification: F02C,F05D,F23D,F23R

Abstract:
A liquid fuel injector system for a gas turbine engine, comprising;an annular combustor having an outer wall, an inner wall, a closed upstream end, and an open discharge end; anda plurality of liquid fuel injectors spaced around the periphery of said closed end of said combustor to direct liquid fuel/air into the closed end of said combustor, each of said plurality of liquid fuel injectors comprising a straight cylindrical liquid fuel tube having a reduced diameter discharge end and a straight cylindrical air assist tube concentrically disposed around said straight cylindrical liquid fuel tube and having a reduced diameter discharge end disposed around the reduced diameter discharge end of said straight cylindrical liquid fuel tube, and generally directing fuel/air tangentially towards the inner wall of said combustor.