Abstract: A combustor for a gas turbine engine includes an inner liner and an outer liner circumscribing the inner liner and forming a combustion chamber with the inner liner. The outer liner is a dual walled liner with a first wall and a second wall. The combustor includes a fuel igniter comprising a tip portion configured to ignite an air and fuel mixture in the combustion chamber and an igniter tube positioning the fuel igniter relative to the combustion chamber. The igniter tube includes a plurality of holes configured to direct cooling air toward the tip portion of the fuel igniter.

Abstract: A cylindrical test specimen is provided. The test specimen comprises a metallic sheet curved to form a cylindrical shape, an adhesive layer contacting the metallic sheet, and a thermal barrier coating coupled to the metallic sheet with the adhesive layer, the thermal barrier coating adapted to inhibit thermal transfer.

Abstract: A fuel manifold assembly for a gas turbine engine comprises an annular fuel manifold and a plurality of fuel nozzles circumferentially distributed about the fuel manifold. The fuel manifold has at least one fuel conveying passage in fluid flow communication with the plurality of fuel nozzles and defines at least one location susceptible to overheating between two of the plurality of fuel nozzles. A slot extends through the fuel manifold in the susceptible location to reduce heat transfer in the fuel manifold while maintaining the fuel manifold assembly dynamically balanced.

Abstract: A fuel manifold assembly for a gas turbine engine comprises an annular fuel manifold and a plurality of fuel nozzles circumferentially distributed about the fuel manifold. The fuel manifold has at least one fuel conveying passage in fluid flow communication with the plurality of fuel nozzles and defines at least one location susceptible to overheating between two of the plurality of fuel nozzles. A slot extends through the fuel manifold in the susceptible location to reduce heat transfer in the fuel manifold while maintaining the fuel manifold assembly dynamically balanced.

Abstract: A method of manufacturing a heat shield for a manifold ring of a gas turbine engine, comprising forming a tubular portion of heat shield material with an arcuate longitudinal axis, deforming the tubular portion such that a cross-section thereof defines a profile corresponding to at least two complementary heat shield portions configured to cooperate to significantly surround at least a circumferential portion of the manifold ring, and cutting the tubular portion to divide the tubular portion into each of the heat shield portions.

Abstract: A fuel injection system comprises a fuel conveying member and a nozzle tip assembly threadably engaged thereto. A pair of sealing elements is engaged in a fuel passage between the fuel conveying member and the nozzle tip for sealing the junction therebetween. The pair of sealing elements includes a first and a second sealing element located proximate each other and having different cross-sectional shape.

Abstract: A method of producing a plurality of effusion holes in a wall of a combustor of a gas turbine engine comprises: determining a hole pattern definition which provides a functional relationship of the spacing between each adjacent hole within the row of holes; using the hole pattern definition to identify individual positions of the effusion holes to be produced; and using a hole producing system to produce the effusion holes at the identified positions.

Abstract: A fuel nozzle sheath has a lateral opening for admitting air about a nozzle stem. The stress distribution along the perimeter of the window is smoothed out by increasing the corner radius of the window corner presenting higher stress concentration.

Abstract: A reverse flow combustor for a gas turbine engine having an outer combustor liner and an inner combustor liner defining an annular combustion chamber, and a compound-angle frustoconical portion in the outer liner having a first and second conical slopes towards an engine centreline.

Abstract: A method of manufacturing a heat shield for a manifold ring of a gas turbine engine, comprising forming a tubular portion of heat shield material with an arcuate longitudinal axis, deforming the tubular portion such that a cross-section thereof defines a profile corresponding to at least two complementary heat shield portions configured to cooperate to significantly surround at least a circumferential portion of the manifold ring, and cutting the tubular portion to divide the tubular portion into each of the heat shield portions.

Abstract: A fuel injection system for a gas turbine engine having a manifold ring, a plurality of spray tip assemblies and a heat shield including at least two heat shield segments cooperating to at least substantially surround a cross-section of the manifold ring around a circumference of the manifold ring, and detachably retained around the manifold ring through a plurality of removable fasteners.

Abstract: A fuel injection system comprises a fuel conveying member and a nozzle tip assembly threadedly engaged thereto. A sealing element is engaged in a first fuel passage between the fuel conveying member and the nozzle tip for sealing a first junction therebetween.