Patent ID: 7093419
Filing Date: 2006-08-22
Classification: F23D,F23R

Abstract:
1. A primer nozzle for a gas turbine engine combustor including a centerline axis, said primer nozzle comprising: an inlet coupled to a source of pressurized air; an injection tip for discharging fuel into said combustor in a direction that is substantially parallel to the gas turbine engine centerline axis; a body extending between said inlet and said injection tip, said body comprising at least one annular projection for coupling said nozzle to said body such that said primer nozzle is positioned relative to the combustor; and a shroud extending around said injection tip and around at least a portion of said body such that a gap is defined between said shroud and at least one of said body and said injection tip, said shroud comprising a shroud tip extending around said injection tip, said shroud tip comprising a plurality of cooling openings extending therethrough to facilitate film cooling said injection tip, said shroud comprising a plurality of circumferentially-spaced openings extending through the shroud for metering cooling air supplied to said injection tip, wherein said plurality of circumferentially-spaced openings are coupled in flow communication to a recuperator for receiving cooling air therefrom.