| 主权项 |
1. An internal fuel manifold assembly for a gas turbine engine comprising:
a fuel manifold ring defining at least one fuel conveying passage therethrough in fluid flow communication with a plurality of fuel injection nozzles adapted for spraying fuel into a combustor of the gas turbine engine, the manifold ring having an inlet port in fluid flow communication with the at least one fuel conveying passage; an elongate inlet member defining at least one inlet passage extending therethrough between first and second ands of the inlet member, the first end being mounted to the inlet port of the manifold ring for communication therewith and the inlet member extending from the manifold ring, the at least one inlet passage being in fluid flow communication with the at least one fuel conveying passage, the inlet member defining a fuel drainage passage, the fuel drainage passage having an entry on a peripheral surface of the inlet member and an exit on an end surface of the second end of the inlet member; a heat shield surrounding the inlet member and being attached to the manifold ring proximate a first end of the heat shield and allowing the inlet member to extend outwardly from a second end of the heat shield, the heat shield and the inlet member being spaced apart so as to define an annulus therebetween, the annulus having substantially closed ends and being in fluid flow communication with the fuel drainage passage of the inlet member; and at least one transfer tube having first and second ends, the first end of the transfer tube being connected to the inlet member proximate the second end thereof and being in fluid flow communication with the at least one inlet passage. |
