Patent ID: 9360221
Filing Date: 2016-06-07
CPC Classification: F23C,F23D,F23R

Claim Text:
1. A burner in a gas turbine, comprising: a. an inner shroud extending axially along at least a portion of the burner; b. an outer shroud radially separated from the inner shroud and extending axially along at least a portion of the burner; c. a plurality of stator vanes located at an axial position extending radially between the inner shroud and the outer shroud, the plurality of stator vanes having an inner end proximate the inner shroud and an outer end proximate the outer shroud; d. a fuel port on each of the plurality of stator vanes, the fuel port in fluid communication with a fuel plenum; and e. a plurality of vortex tips, the plurality of vortex tips portioned in alternating sequence on the inner end or the outer end of each adjacent stator vanes of the plurality of stator vanes, wherein a gap exists between each of the plurality of vortex tips and the outer shroud when those ones of the plurality of stator vanes are connected to the inner shroud and a gap exists between each of the plurality of vortex tips and the inner shroud when those ones of the plurality of stator vanes are connected to the outer shroud.