Abstract: A heat shield for a fuel member of a gas turbine engine having at least one heat shield segment having a connection edge with at least one joint receiving portion defined therealong for receiving a welded joint attaching the heat shield segment to a fuel member, each joint receiving portion including a stress relieving feature defined along at least one end thereof.

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 mounting system for an annular internal fuel manifold disposed within a gas generator case of a gas turbine engine including at least one fastener support assembly and at least one receiving element, each fastener support assembly including a primary fastener engaging the receiving element to constrain a relative movement between the fuel manifold and the gas generator case in an axial direction while allowing the relative movement in a radial direction and a secondary fastener in position to passively and automatically engage the receiving element upon failure of the primary fastener.

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 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 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 multiple conduit system for a gas turbine engine, the multiple conduit system extending between a plurality of conduit inlet and outlets. A channel, adapted for conveying fuel flow, is formed in a surface of a gas turbine engine component. The channel includes at least a first discrete conduit and a second discrete conduit. The first and second discrete conduits are each adapted to direct an independent fluid flow from respective inlets to respective outlets.

Abstract: A fuel manifold assembly for a gas turbine engine includes an annular fuel manifold having at least one fuel conveying passage and defining at least one slow fuel flowing location. A heat shield at least partly encloses the fuel manifold and a plurality of intermittent joints attach the heat shield to the fuel manifold. The joints are circumferentially distributed about the fuel manifold as far away from the slow flowing location as possible while maintaining the fuel manifold dynamically balanced.

Abstract: A system for mounting an internal fuel manifold within a gas generator case of a gas turbine engine includes at least one fastener support assembly having a fastener pin and at least one receiving element, respectively engaged to either the internal fuel manifold or the gas generator case. A biasing member is located between the fastener pin and the receiving element to axially preload the joint between the fastener pin and the receiving element, such as to constrain relative movement between the two parts in an axial direction while allowing relative movement in a radial direction.

Abstract: A fuel manifold assembly for a gas turbine engine is described and includes an annular manifold body and an annular heat shield assembly mounted to and surrounding the manifold body. The heat shield assembly has an inner surface facing the manifold body and spaced apart therefrom by an inner air gap, which substantially surrounds the manifold body, defined therebetween. The heat shield assembly has an outer surface facing away from the manifold body and spaced apart from the inner surface by an outer air gap substantially surrounding the inner air gap. At least the outer air gap is formed by a double wall configuration of the heat shield assembly.

Abstract: An assembly of a combustor and fuel manifold comprises a fuel manifold having at least an annular portion with a plurality of fuel outlets facing at least partially radially inward. A combustor comprises an annular inner liner and an annular outer liner spaced apart from the inner liner, the inner liner and outer liner concurrently forming an annular combustor chamber therebetween. The inner and outer liners concurrently define an annular receptacle in the annular combustor chamber for receiving the fuel manifold. The inner liner and outer liners are shaped to define an annular gas path in the annular combustor chamber having an upstream portion that is substantially radial and oriented toward a center when the combustor is in a gas turbine engine.

Abstract: A mounting system for an annular internal fuel manifold disposed within a gas turbine engine includes a fuel inlet assembly having a heat shield extending about at least a portion of an inner fuel inlet tube. The heat shield has a distal end engaged with the fuel manifold and has a radially outwardly projecting shoulder proximate an opposed proximal end thereof. The proximal end of the heat shield is received within a bushing disposed within a corresponding opening of a supporting casing. The shoulder of the heat shield retains the bushing in place.

Abstract: A fuel conveying member of a gas turbine engine is described and includes a fuel manifold defining an annular fuel flow passage through a body of the fuel manifold. A plurality of fuel nozzles extend from the manifold in fluid flow communication with the annular fuel flow passage. The fuel manifold includes integral attachment lugs thereon for mounting the fuel manifold within the gas turbine engine. The attachment lugs are adapted to receive pins therein and provide a mounting mechanism which allows for thermal expansion of the fuel manifold relative to a surrounding support structure to which the fuel manifold is mounted via the attachment lugs.

Abstract: A mounting system for an annular internal fuel manifold of a gas turbine engine includes three supports equally spaced apart about the annular fuel manifold, the three supports having at least two pin supports disposed between the fuel manifold and a surrounding gas generator casing. Each pin support includes a radially extending pin co-operating with an aligned ring slidingly disposed around the pin for relative sliding displacement therebetween. The pin supports providing axial constraint while permitting the fuel manifold to radially displace relative to the surrounding gas generator casing due to thermal size change.

Abstract: A fuel manifold for a gas turbine engine comprises manifold adaptors each supporting a nozzle for outputting fuel from a fuel supply. The manifold adaptors have a primary conduit and a secondary conduit extending between connection ends of the manifold adaptor. The primary conduit and the secondary conduit are in fluid communication with the nozzle to supply fuel thereto. Transfer units are between adjacent manifold adaptors, and each comprises a primary transfer tube matingly connected at opposite ends to the primary conduits of the adjacent manifold adaptors for fuel circulation between the primary conduits. A secondary transfer tube in each transfer unit is matingly connected at opposite ends to the secondary conduits of the adjacent manifold adaptors for fuel circulation between the secondary conduits. A drain sleeve in each transfer unit is connected at opposite ends to the adjacent manifold adaptors.

Abstract: In a gas turbine engine, a fuel inlet tube comprising a body, a channel defined in the body and in fluid communication with a manifold, and a side inlet in fluid communication with the channel, such that fuel entering the side inlet is delivered to the manifold through the channel with a pressure generally directed along a radial axis of the body. Also, a fuel inlet tube comprising a heat shield surrounding at least part of a body, a chamber defined between the heat shield and the body and in fluid communication with fuel leak sources, a drain channel defined in the body in fluid communication with the chamber, and a drain hole defined in the body in fluid communication with the drain channel, such that a leak produces fuel received in the chamber and safely directed through the channel and the hole to allow detection of the leak.

Abstract: A fuel supply assembly for a gas turbine engine comprises a plurality of fuel injectors configured for mounting circumferentially to an engine casing of the gas turbine engine and to be serially interconnected. At least one pair of the plurality of the fuel injectors has a first fuel injector including a first manifold adapter having a first outlet defined around a first outlet axis, and a first stem connected to the first manifold adapter at the first outlet and extending longitudinally along a first stem axis; and a second fuel injector including a second manifold adapter having a second outlet defined around a second outlet axis, and a second stem connected to the second manifold adapter at the second outlet, the first and second outlet axes being disposed circumferentially between the first and second stem axes.

Abstract: A manifold is provided surrounding the casing of a combustion chamber for a gas turbine engine, and the manifold is mounted in spaced aligned segments with couplings between the segments. Each coupling includes a removable tube connector extending between passageways forming the fuel line in the manifold. The tube connector is provided with a radial collar thereon, and a sleeve which is adapted to enclose the space between ends of respective manifold segments is also provided with a mating collar adapted to receive the radial collar on the tube connector. The sleeve is retractable over the ends of the manifold segments, and movement of the sleeve in one direction or the other will also move the tube connector by virtue of the interlocking collars. The manifold segments are provided with a second passageway for draining leaked fuel. The space defined by the sleeve is sealed, and fuel can communicate through to the second passageway for drainage outboard of the engine.