Patent ID: 8893500

Claim:
A dual fuel injector for a gas turbine engine comprising: a central cavity extending along a longitudinal axis from a first end to a second end; a first fuel discharge outlet configured to direct a first fuel into the central cavity at the first end; a first air discharge opening circumferentially disposed about the first fuel discharge outlet and configured to direct a first quantity of air into the central cavity; a second air discharge opening circumferentially disposed about the central cavity and configured to discharge a second quantity of air into the central cavity downstream of the first air discharge outlet; a second fuel discharge outlet circumferentially disposed about the central cavity and configured to discharge a second fuel therethrough, the second fuel being different from the first fuel; and a second fuel discharge passage extending along the longitudinal axis to fluidly couple an annular cavity containing the second fuel at the second end to the second fuel discharge outlet, the second fuel discharge passage including a portion proximate the second fuel discharge outlet that converges towards the longitudinal axis.