Abstract: A gas turbine engine having a gas relief means which is operable to open when the engine is inactive such that hot gases accumulated therein are released.

Abstract: A fuel conveying member for an engine, the fuel conveying member having heating means integrated therein to permit pyrolysis of carbonaceous deposits.

Abstract: The manifold includes supports which slidably engage a heat shield to floatingly suspend it around the manifold.

Abstract: A method and a pre-shaped workpiece for making at least a portion of a gas turbine fuel nozzle are disclosed having opposed gripping tabs which can be secured to machine tool holders during manufacturing by a machine tool.

Abstract: A heat shield comprises a flexible inner jacket configured and disposed to be fitted around at least a portion of a component, and a flexible outer jacket configured and disposed to be fitted around the inner jacket.

Abstract: Fuel conduit systems for internal installation in a gas turbine engine are provided which are low cost and easy to manufacture. First and second members co-operate to provide a channel to define a discrete fuel carrying conduit. The direction of fuel flow can be adapted to provide desired cooling effect.

Abstract: The present invention includes a fuel distributor for a fuel nozzle in a gas turbine engine comprising an inner tubular body and an outer tubular body respectively having an outer body inner surface and an inner body outer surface adapted to be in sealing contact one with the other, at least two helical fuel channels defined in at least one of the inner and outer surfaces and being in fluid communication with a fuel inlet, and a channel exit port for each helical fuel channel. The present invention also includes a method of distributing fuel in a fuel nozzle comprising the steps of providing at least two helical channels in the fuel nozzle, each having a channel exit port, providing a fuel inlet cavity in fluid communication with the helical channels, and flowing fuel in the fuel inlet cavity, the helical channels and the channel exit ports.

Abstract: A method of manufacturing a composite wall with an open cell metal foam core layer bonded to an inner cladding layer and an outer cladding layer. The method involves: creating a core substrate of open cell gas permeable foam in a chosen shape; impregnating the open cell foam substrate with metal vapour and depositing a porous layer of metal on exposed internal and external surfaces of the substrate thereby forming the open cell metal foam core through metal vapour deposition; and forming the inner and outer cladding layers upon the metal foam core through spray application of metal or ceramic.

Abstract: A fuel nozzle (18) for a gas turbine engine comprises a nozzle stem (55), a nozzle tip assembly (60) and a nozzle sheath (50). A plurality of inlets (82) allow air to flow into the interior (90) of the sheath (50); fuel is flowed into the nozzle (18) through a fuel passage (135) in fluid communication with a fuel manifold. The fuel enters a fuel channel (140) defined by the stem (55) and tip assembly (60), and then passes into a fuel gallery (185) through a plurality of metering holes (190). Fuel swirls out of the tip assembly (60), where it is caught between, and squeezed by, first and second streams of air passing out of radially spaced apart air passages (145) and (220).