Patent ID: 6886346

Claim:
A pilot fuel nozzle for a gas turbine combustor comprising: an elongated housing of generally circular cross section extending from a first end to a second end, having a center axis, and a length, said elongated housing comprising: a first inner diameter extending from said first end to said second end; a first portion and a second portion, each having a first outer diameter, thereby forming a first wall thickness between said first inner diameter and said first outer diameter; a third portion having a second outer diameter, thereby forming a second wall thickness between said first inner diameter and said second outer diameter; a first flange fixed to said elongated housing at said first end; a second flange fixed to said elongated housing along said third portion; a nozzle tip containing a plurality of fuel injection holes, said nozzle tip located at said second end; and, wherein said third portion is located between said first portion and said second portion.