Patent ID: 7581402

Claim:
A fuel swirler assembly for a turbine engine combustor comprising: an elongated swirler body having an inlet end and an outlet end, the swirler body defining a longitudinal axis, the swirler body having an outer peripheral surface and an inner peripheral surface; a plurality of swirler vanes extending radially inward from the inner peripheral surface of the swirler body, the vanes being arrayed about the inner peripheral surface of the swirler proximate the inlet end; and a bracket secured to the outer peripheral surface of the swirler body and projecting outward from the swirler body in a direction that is substantially radial to the longitudinal axis, the bracket having a radially distal end, the bracket including a hole adapted for removably receiving a fastener, such that the fastener is attached within the hole the hole extending inward from the radially distal end of the bracket in a direction that is substantially radial to the longitudinal axis, the hole opening to the radially distal end of the bracket, wherein the bracket is located on the swirler body in a region defined between the inlet end and an axially central region of the swirler body.