Patent ID: 7874138
Filing Date: 2011-01-25
Classification: F23M,F23R

Abstract:
1. A combustor for use in a turbine engine comprising a compressor section, a combustion section downstream from the compressor section, a turbine section downstream from the combustion section, and defining an axis of rotation, the combustor comprising: an inner annulus wall extending from a burner end of the combustor to an outlet end of the combustor adjacent the turbine section of the engine; an outer annulus wall disposed outwardly from said inner annulus wall and extending from said burner end of the combustor to said outlet end of the combustor adjacent the turbine section of the engine; a combustion zone defined by said inner annulus wall and said outer annulus wall and extending continuously from said inner annulus wall to said outer annulus wall, said combustion zone defining an area adjacent to said burner end of the combustor where air transported from the compressor section of the engine is mixed with a fuel and ignited; a passageway formed between said inner annulus wall and said outer annulus wall extending from said combustion zone to said outlet end of the combustor for conveying an ignited air and fuel mixture from said combustion zone to said outlet end of the combustor; a plurality of burners associated with said burner end of the combustor for distributing the fuel to said combustion zone; and a plurality of section walls symmetrically distributed about the axis of rotation of the turbine engine, the section walls extending radially from said inner annulus wall to said outer annulus wall and extending from said burner end of the combustor toward to said outlet end of the combustor, said section walls dividing said combustion zone into a plurality of segments.