Patent ID: 6286298
Filing Date: 2001-09-11
Classification: F23R

Abstract:
A fuel injection system for a gas turbine engine combustor, said combustor including a dome inlet module having a plurality of flow passages formed therein by a plurality of vanes positioned circumferentially therein, a combustion chamber, and at least one trapped vortex cavity formed in a liner downstream of said dome inlet module by an aft wall, a forward wall, and a third wall therebetween, said fuel injection system comprising:(a) a fuel supply;(b) a plurality of radially disposed fuel injector bars positioned circumferentially around and interfacing with said inlet dome module, said fuel injector bars being in flow communication with said fuel supply, each of said fuel injector bars further comprising(1) a body portion having an upstream end, a downstream end, and a pair of sides; and(2) at least one injector formed in the downstream end of said body portion and in flow communication with said fuel supply and said forward wall of said trapped vortex cavity;wherein fuel is provided to said trapped vortex cavity through said fuel injector bars.