Methods and systems to facilitate reducing flashback/flame holding in combustion systems

A gas turbine combustor system (10) includes a combustion liner (28) and a premixing injector (26) coupled to the combustion liner. The premixing injector includes a centerbody (38) including a center axis and a radially outer surface. An inlet flow conditioner (32) is coupled to the centerbody such that a inlet flow conditioner substantially circumscribes the centerbody. The inlet flow conditioner includes a radially outer wall (50) including a plurality of openings (52) defined therein, the outer wall is substantially parallel to the center axis. A radially inner wall (76) extends substantially parallel to the outer wall, and the inner wall is spaced from the outer wall such that a first passage (58) is defined therebetween. The inner wall is spaced from the centerbody outer surface such that a second passage (66) is defined therebetween, and an end wall (54) extends substantially perpendicularly between the outer and inner walls. The end wall includes a plurality of openings (56) defined therein.