Patent ID: 8393154
Filing Date: 2013-03-12
Classification: F02C,F23R

Abstract:
1. A fuel supply assembly for a gas turbine engine, comprising: a fuel manifold mounted to a casing surrounding a combustor of the gas turbine engine; and a plurality of fuel nozzles mounted to the fuel manifold in fuel flow communication therewith, an axially extending mating interface between the fuel nozzles and the fuel manifold, the axially extending mating interface extending from a first axial position to a second axial position, at least one sealing element disposed between each of the fuel nozzles and the fuel manifold at a third axial position, the third axial position being axially disposed between the first and second axial positions, at least one aperture defined in each of said fuel nozzles proximate to said mating interface with the fuel manifold, the aperture being a non fuel conveying aperture and defining a radial air gap, the aperture extending axially and having a length defined between a first open aperture end and a second closed aperture end, the first open aperture end being open to atmosphere surrounding the fuel nozzle and proximate the first axial position of the mating interface, the length of the aperture axially spanning the first, second and third axial positions, wherein an axial overlap is provided between said at least one sealing element and the radial air gap defined by the aperture to reduce conductive heat transfer to said sealing element by preventing a direct conductive heat transfer path between a hot region of the fuel nozzle disposed within said casing and said sealing elements.