Patent ID: 8096131
Filing Date: 2012-01-17
Classification: F02C,F05D,F16L

Abstract:
1. A fuel inlet tube to an internal fuel manifold ring of a fuel injection system in a gas turbine engine, the internal fuel manifold ring being concentric with a longitudinal axis of the gas turbine engine and having at least two fuel conveying passages therein in fluid flow communication with a plurality of fuel injection nozzles adapted for spraying fuel into a combustor of the gas turbine engine, the fuel inlet tube comprising a solid cylindrical tube body having only two fuel channels formed therein, the two fuel channels being a primary and a secondary fuel channel, the primary and secondary fuel channels of the fuel inlet tube being connected in fluid flow communication with said at least two fuel conveying passages within the internal fuel manifold ring, the secondary fuel channel of the fuel inlet tube having a substantially crescent shaped cross-sectional area, the primary and secondary fuel channels intersecting at least a first transverse axis of the tube body which is substantially parallel to the longitudinal axis of the gas turbine engine, the secondary fuel channel being complementary in shape to the primary fuel channel such as to maximize a combined fuel flow area through the primary and secondary fuel channels relative to an outer diameter of the cylindrical tube body.