| 摘要 |
A gas turbine engine fuel nozzle assembly 12 includes a pilot fuel injector tip 57 on a centerline 120 in an annular pilot inlet 54 of a pilot mixer 102, with a cross over arm 56 extending across inlet 54 to tip 57, and a pilot nose cap 53 at an upstream end 55 of tip 57. Arm 56 includes an fairing 62 surrounding fuel transfer tubes 64, 66 to tip 57. The cross over arm 56 and/or the pilot nose cap 53 has a rounded forebody 46 followed by a straight afterbody 48. Rounded forebody 46 of pilot nose cap 53 includes a substantially rounded dome 78 extending forwardly from a rounded nose base 77 and straight afterbody 48 includes a substantially cylindrical nose afterbody 92 parallel to a pilot nose centerline 111 normal to nose base 77. An arm fairing 62 surrounding fuel transfer tubes 64, 66 to tip 57 includes rounded leading and trailing edges 80, 82 and a rectangular middle section 76 therebetween having flat first and second sides 67, 68.
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