Patent ID: 6295801
Filing Date: 2001-10-02
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 and said forward wall, 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;(2) a plurality of injectors formed in said body portion sides and in flow passages; and(3) at least one injector located on said body portion downstream end of said fuel injector bars in flow communication with said fuel supply to provide fuel into each trapped vortex cavity formed in said liner through said forward wall;wherein fuel is provided to said dome inlet module flow passages and each said cavity through said fuel injector bars.