| 主权项 |
1. A fuel nozzle for use with a turbine engine, said fuel nozzle comprising:
a housing coupled to a combustor liner defining a combustion chamber, said housing comprising an endwall that at least partially defines the combustion chamber; and a plurality of mixing tubes extending through said housing for channeling a fuel to the combustion chamber, each mixing tube of said plurality of mixing tubes comprising an inner surface extending between an inlet portion and an outlet portion, wherein a fuel aperture extends through said inner surface proximate said inlet portion and is configured to channel a flow of fuel to said mixing tube said outlet portion oriented adjacent said housing endwall, at least one mixing tube of said plurality of mixing tubes comprising:
a plurality of projections extending outwardly from a distal end of said outlet portion, wherein adjacent said projections are spaced a circumferential distance apart such that a groove is defined between each of said pairs of circumferentially-apart projections to facilitate enhanced mixing of fuel in the combustion chamber, and wherein each projection of said plurality of projections comprises one of the following:(i) a tip surface substantially perpendicular to said inner surface, the tip surface having a substantially trapezoidal shape;(ii) a tip surface that extends obliquely between said inner surface and an outer surface of said at least one of said plurality of mixing tubes; and(iii) a tip surface that extends between said inner surface and an outer surface of said at least one of said plurality of mixing tubes and has an arcuate shape. |
