for conducting straight line air fuel mixture 16 and swirling air fuel mixture 18 to combustion chamber 14 where mixtures 16 18 cooperate with auxiliary fluid stream 23 to define combustible mixture 19 in an illustrative embodiment shown in fig5 and 6 straight line air fuel mixture 16 flows into combustion chamber 14 through a small diameter inner annular zone 41 defined by small dimension 141 located in air fuel transfer channel 40 and swirling air fuel mixture 18 flows into combustion chamber 14 through a large diameter outer annular zone 42 defined by larger dimension 142 surrounding small diameter inner annular zone 41 and lying in air fuel transfer channel 40 a somewhat u201c cylindrical u201d shear layer stabilization boundary 43 is created between inner and outer annular zones 41 42 in air fuel transfer channel 40 and an inlet region 44 provided in combustion chamber 14 as suggested diagrammatically in fig6 and illustratively in fig5 ignition of straight line and swirling air fuel mixtures 16 18 and auxiliary fluid stream 23 in combustion chamber 14 using ignitor 24 produces a stable flame 12 flame attachment of flame 12 is provided by reacting boundary layers along shear layer stabilization boundary 43 located between inner and outer annular zones 41 42 to define a u201c zero velocity u201d flow zone containing at least the root of flame 12 in other words flame 12 is attached by reacting swirling air fuel mixture 18 and annular straight line air.