Patent ID: 6715292
Filing Date: 2004-04-06
Classification: F23D

Abstract:
A fuel injector for a turbine engine combustor module, comprising:a pressure atomizing core nozzle disposed about an injector centerline, the core nozzle having a discharge orifice for injecting a stream of primary fuel into a combustion zone of the module; first and second partitions circumscribing the core nozzle to define radially inner and outer extremities of an annular inner air passage for injecting a stream of inner air into the combustion zone; a third partition circumscribing the second partition and cooperating therewith to define a secondary fuel passage having an outlet oriented to direct a stream of secondary fuel into the combustion zone toward the injector centerline; an outer wall circumscribing the third partition and forming the radially outermost border of an annular outer air passage having an outlet oriented to direct a stream of outer air into the combustion zone toward the injector centerline; and an air distribution baffle having a cap that extends radially across the inner air passage, the cap having an outer edge radially spaced from the second partition to define an air injection annulus and also being penetrated by a radially and circumferentially distributed plurality of all injection orifices.