Patent ID: 6282904
Filing Date: 2001-09-04
Classification: F23D,F23R

Abstract:
An improved dual-mode, dual-stage gas turbine combustor comprising:a primary combustion chamber;one or more primary fuel nozzles positioned to deliver fuel to said primary combustion chamber;a secondary combustion chamber adjacent to and downstream of said primary combustion chamber;a venturi passage separating said primary and secondary chambers;a secondary fuel distribution system situated near said secondary combustion chamber and surrounded by said plurality of said primary fuel nozzles, wherein said secondary fuel distribution system comprises;an elongated housing having opposing ends;a diffusion nozzle located proximate one end of said elongated housing;a plurality of fuel transfer tubes situated within said elongated housing to supply transfer fuel to said diffusion nozzle;a central fuel distribution conduit connected directly to said diffusion nozzle to deliver fuel to said diffusion nozzle;a plurality of air flow channels situated within said elongated housing such that said fuel transfer tubes surround said air flow channels and wherein said air flow channels supply air to said diffusion nozzle;a sleeve affixed to said elongated housing;a plurality of support members affixed to said sleeve and extending radially outward therefrom; anda premix fuel nozzle comprising an annular tubular manifold circumferentially disposed around said elongated housing, said manifold affixed to said plurality of support members away from said elongated housing and having a plurality of fuel dispersion apertures situated about its periphery and facing in a downstream direction for emitting fuel such that an air stream flowing around the outside of said premix fuel nozzle mixes with said emitted fuel,wherein at least one of said apertures is circumferentially offset from said support members.