Patent ID: 6983600
Filing Date: 2006-01-10
Classification: F23R

Abstract:
1. A combustor for a gas turbine comprising a combustor housing including a flow liner for receiving compressor discharge air; a main fuel injector downstream of said flow liner for receiving the compressor discharge air and mixing air and fuel; a catalytic section downstream of said main fuel injector for receiving a mix of air and fuel from the main fuel injector; said main fuel injector including (i) an array of venturis each including a convergent inlet, a throat and a diffuser for flowing a fuel/air mixture therethrough in a generally axial direction for exit from said diffuser, (ii) a front plate and (iii) an aft plate surrounded by an enclosure defining a fuel supply plenum between said plates; each said plate having a plurality of openings for receiving the venturis; and each said venturi inlet having at least one fuel supply hole for supplying fuel from said fuel supply plenum into said venturi inlet at a location axially upstream from said throat.