Patent ID: 7578130
Filing Date: 2009-08-25
Classification: F23C,F23R

Abstract:
1. A combustion chamber for a gas turbine engine, comprising: a first premixer and a second premixer oriented about an axis defined between an upstream end and a downstream end of a combustor, each premixer comprising at least one fuel injector, at least one air inlet duct, and at least one vane pack downstream of the at least one fuel injector for at least partially mixing air from the at least one air inlet duct and fuel from the at least one fuel injector; wherein each of the vane packs comprises a plurality of fuel orifices through which at least a portion of the fuel and at least a portion of the air pass; wherein the at least one vane pack of the first premixer is positioned at a first axial position relative to the axis and the at least one vane pack of the second premixer is positioned at a second axial position relative to the axis, wherein the second axial position is axially staggered with respect to the first axial position.