Patent ID: 9371998
Filing Date: 2016-06-21
CPC Classification: F23D,F23R

Claim Text:
1. A pilot liquid tube for use in a gas turbine engine, the pilot liquid tube comprising: a pilot liquid fuel conduit having a first end, and a second end opposite the first end, the first end and the second end being in fluid communication; a pilot liquid fuel inlet fluidly coupled to the pilot liquid fuel conduit at the first end; a shroud assembly including a tube interface, a pilot liquid fuel nozzle, a tube extension extending between the tube interface and the pilot liquid fuel nozzle, a shroud circumscribing the pilot liquid fuel nozzle and the tube extension forming a portion of a secondary pilot air duct of an injector, and an integrated conduit support extending from the tube extension to the shroud and connecting the shroud to the tube extension forming an integrated unit, the shroud assembly coupled to the pilot liquid fuel conduit at the second end via the tube interface, the pilot liquid fuel nozzle fluidly coupled to the pilot liquid fuel conduit via the tube extension; and a swirler extending from the tube extension to the shroud connecting the shroud to the tube extension adjacent to the pilot liquid fuel nozzle, the swirler forming part of the integrated unit, wherein the swirler is configured to swirl compressed air passing through the shroud assembly; wherein the integrated conduit support is located between the swirler and the tube interface; and wherein the shroud includes an upstream portion that circumscribes the integrated conduit support, the upstream portion including a first tubular shape with a first diameter, a downstream portion that circumscribes the swirler, the downstream portion including a second tubular shape with a second diameter smaller than the first diameter, and an intermediate portion that transitions from the upstream portion to the downstream portion.