| 摘要 |
A fuel shield (68) is configured for use in the afterburner (34) of a turbof an aircraft engine (10). The shield (68) includes wings (72,74) obliquely joined togethe r at a nose (76), with each of the wings (72,74) including an offset mounting tab (78) at a proximal end thereof. The wings (72,74) and tabs (78) are configured to complement a flameholder vane (42) around its leading edge (52), with the tabs (78) contacting the vane sidewalls (48,50) to offset the wings (72,74) outwardly therefrom and form a thermally insulating gap (70) therebetween.
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