Patent ID: 7658339
Filing Date: 2010-02-09
Classification: B05B,F23R

Abstract:
1. A modular fuel nozzle air swirler for a gas turbine engine, the nozzle comprising: a body defining a fuel passage extending axially between an inlet end and a discharge end of the body, the discharge end having a peripheral end surface, the body having at least one first interlocking member; and an annular cap having a shoulder surface interfacing with the peripheral end surface of the body, the annular cap having at least one second interlocking member cooperating with the at least one first interlocking member, the second interlocking member surrounding the first interlocking member and defining a radial slot in which the first interlocking member is axially captively received, thereby axially retaining the annular cap on the body, the peripheral end surface of the body and the shoulder surface defining a plurality of through air channels.