Patent ID: 6996990
Filing Date: 2006-02-14
Classification: F23C,F23R

Abstract:
1. A combustor for a gas turbine comprising: a preburner section for receiving fuel and air for combustion therein; a main fuel injector; a catalyst section downstream of the preburner section and in a flow stream including fuel from the main fuel injector and air and products of combustion from the preburner section; a flow liner encompassing the flow stream between the preburner section and the catalyst section; a flow controller disposed intermediate the preburner section and the catalyst section for obtaining a substantial uniform flow distribution at an inlet to the catalyst section; said flow controller including a flow splitter disposed in the flow stream and including first and second elements at least in part defining first and second annular flow areas through the splitter, said first element including a generally radially outwardly directed frustoconical wall in the downstream direction of the flow stream defining with said liner said first annular flow area to substantially eliminate or minimize separation of the flow stream downstream of the flow controller and relative to the liner.