Patent ID: 7185497

Claim:
A combustor for a gas turbine engine, comprising: a combustor inlet end longitudinally separated from a combustor outlet end along a combustor centerline; a premix chamber disposed at said combustor inlet end, said premix chamber in fluid communication with a primary combustion chamber, said primary combustion chamber in fluid communication with a secondary combustion chamber disposed at said combustor outlet end, said premix chamber comprising a cylindrical chamber having a premix chamber wall coaxially disposed about said combustor centerline, said cylindrical chamber having a chamber inlet end longitudinally separated from a chamber outlet end along said combustor centerline by a chamber length; a chamber inlet plate in communication with said premix chamber wall at said chamber inlet end; a fuel nozzle inlet hole disposed through said chamber inlet plate; a plurality of swirler passages disposed through said chamber inlet plate; and a fuel nozzle engaged with said chamber inlet plate within said fuel nozzle inlet hole, said chamber outlet end comprising a flair outlet opening expanding radially away from said combustor centerline into said primary combustion chamber, said primary combustion chamber comprising a combustor liner having a first frustoconical portion attached to a cylindrical portion, said cylindrical portion attached to a second frustoconical portion serially disposed along said combustor central axis, wherein a radius of said first frustoconical portion increases in an axial direction from said combustor inlet end to said combustor outlet end, wherein a radius of said cylindrical portion remains constant longitudinally along said combustor centerline, wherein a radius of said second frustoconical portion decreases in an axial direction along said combustor centerline from said combustor inlet end to said combustor outlet end, said secondary combustor disposed within said combustor liner, wherein a radius of said secondary combustor remains constant in an axial direction, wherein said primary combustor comprises a frustoconical heat shield disposed between said first frustoconical portion and said combustor centerline, wherein said secondary combustor comprises a plurality of intermediate jets disposed through said combustor liner, wherein said secondary combustor comprises a plurality of dilution holes disposed through said combustor liner, and wherein said plurality of dilution holes are located between said intermediate jets and said combustor outlet end.