Patent ID: 7624576
Filing Date: 2009-12-01
Classification: F02C,F23R

Abstract:
1. A gas turbine engine fuel nozzle comprising: a fuel conveying member having a stem defining at least one fuel passage, a spray tip connected in fluid flow communication with said at least one fuel passage, said spray tip having an air swirler, a sheath provided about said stem, an annular air passage defined between said stem and said sheath, said air passage leading to air openings defined through said air swirler, an air inlet defined through a side wall of said sheath for connecting said annular air passage in fluid flow communication with a source of air, and at least one wing-like projection extending longitudinally along the stem into the annular air passage for redirecting air entering the annular air passage towards the air swirler of the spray tip, the at least one wing-like projection extending axially from an inlet end of the stem beyond the air inlet towards said spray tip.