Patent ID: 7900872

Claim:
An anti-icing system for a nacelle inlet of an aircraft engine, the system comprising: a generally ring-shaped hollow spray tube for directing hot gasses toward a portion of the nacelle inlet, the spray tube including two closed ends which define a thermal expansion gap therebetween to accommodate thermal expansion of the spray tube caused by the hot gasses; a plurality of fasteners for attaching the spray tube to a support structure of the aircraft engine wherein each of the fasteners comprises: a support bracket for attachment to the support structure of the aircraft; and a guide assembly for supporting the spray tube to the support bracket, the guide assembly including— a generally ring-shaped block for encircling the spray tube, a bushing positioned within the block for contact with the bearing sleeve of the spray tube, and a pair of bushing retainers positioned on opposite sides of the block for retaining the bushing within the block; and a supply duct for delivering the hot gasses from the aircraft engine to the spray tube.