Abstract: A gas turbine engine fuel supply assembly which includes a fuel manifold mounted to a casing surrounding a combustor of the engine, and a plurality of fuel nozzles mounted to the fuel manifold. A mating interface between the fuel nozzles and the fuel manifold has at least one sealing element, and at least one aperture defined in the fuel nozzle proximate to the mating interface. The aperture is a non fuel conveying passage, and reduces conductive heat transfer to the sealing element by preventing a direct conductive heat transfer path between a hot region of the fuel nozzle and the sealing element.

Abstract: A fuel nozzle for a gas turbine engine comprises a nozzle body defining a passage extending therethrough and a flange around the nozzle body extending radially and outwardly from the nozzle body. The flange defines a mounting face thereof and a plurality of mounting holes in the mounting face extending through the flange. The mounting face includes a contacting land protruding from the mounting face for abutting a mounting surface of a support structure of the engine when the fuel nozzle is mounted to the support structure.

Abstract: A gas turbine engine fuel supply assembly which includes a fuel manifold mounted to a casing surrounding a combustor of the engine, and a plurality of fuel nozzles mounted to the fuel manifold. A mating interface between the fuel nozzles and the fuel manifold has at least one sealing element, and at least one aperture defined in the fuel nozzle proximate to the mating interface. The aperture is a non fuel conveying passage, and reduces conductive heat transfer to the sealing element by preventing a direct conductive heat transfer path between a hot region of the fuel nozzle and the sealing element.

Abstract: A fuel nozzle having a fuel conveying member surrounded by a sheath. An air passage is defined between the fuel conveying member and the sheath for directing air to an air swirler provided at one end of the fuel conveying member. At one flow director is provided in the air passage for promoting air and fuel uniformity and distribution at a spray tip of the fuel nozzle.

Abstract: A fuel nozzle for a gas turbine engine comprises a nozzle body defining a passage extending therethrough and a flange around the nozzle body extending radially and outwardly from the nozzle body. The flange defines a mounting face thereof and a plurality of mounting holes in the mounting face extending through the flange. The mounting face includes a contacting land protruding from the mounting face for abutting a mounting surface of a support structure of the engine when the fuel nozzle is mounted to the support structure.

Abstract: A fuel nozzle having a fuel conveying member surrounded by a sheath. An air passage is defined between the fuel conveying member and the sheath for directing air to an air swirler provided at one end of the fuel conveying member. At one flow director is provided in the air passage for promoting air and fuel uniformity and distribution at a spray tip of the fuel nozzle.

Abstract: Thermal stress relief in a nozzle head of a gas turbine fuel nozzle is provided by forming a slit through each selected air passages of the nozzle head. The strategic location of stress-relief slits contributes to extend the fatigue life of the nozzle with minimal cost and impact on the nozzle aerodynamics.

Abstract: Thermal stress relief in a nozzle head of a gas turbine fuel nozzle is provided by forming a slit through each selected air passages of the nozzle head. The strategic location of stress-relief slits contributes to extend the fatigue life of the nozzle with minimal cost and impact on the nozzle aerodynamics.