General Electric Company
Fuel nozzle with improved swirler vane structure

Abstract:

A fuel nozzle for a turbomachine includes a centerbody that extends axially with respect to a centerline of the fuel nozzle. A confining tube is positioned radially outward of the centerbody. A plurality of swirler vanes is disposed between the centerbody and the confining tube. Each of the plurality of swirler vanes includes a radially inner base and a radially outer tip. Each of the swirler vanes further includes an upstream portion that extends generally axially from a leading edge. A downstream portion extends from the upstream portion to a trailing edge. The downstream portion defines a bend length between the upstream portion and the trailing edge. The bend length at the radially outer tip is greater than the bend length at the radially inner base.