Flame disgorging two stream tangential entry nozzle

A fuel nozzle assembly for use in a gas turbine engine, comprising:

• a centerbody including
• a longitudinal axis,
• a base, and
• a radially outer surface including a frustum portion defining the outer surface of a frustum that is coaxial with the longitudinal axis and flares toward the base;
• a scroll swirler having
• first and second endplates, said first endplate in spaced relation to said second endplate, said second endplate having a combustor inlet port extending therethrough, said inlet port coaxial with said axis and including a convergent surface, a discharge surface, and a throat therebetween,
• at least two cylindrical-arc scroll members, each scroll member defining a body of partial revolution about a centerline, each of said scroll members extending from said first endplate to said second endplate and spaced uniformly about the axis thereby defining a mixing zone therebetween, each of said scroll members in spaced relation to each of the other scroll members, each of said centerlines located within said mixing zone, each of said centerlines in spaced relation to, equidistant from, and parallel to said axis, thereby defining inlet slots extending parallel to said axis between each pair of adjacent scroll members for introducing combustion air into said mixing zone, each of said scroll members including a fuel conduit for introducing fuel into combustion air introduced through one of said inlet slots;
• wherein said base is connected to said first endplate and said frustum portion extends into said combustor inlet port.