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: An access conduit for access to the interior of a combustor for the washing of the turbine components of a gas turbine engine. The access conduit is secured between a gas generator case and a combustion chamber liner of the combustor. The access conduit has an open outer end accessible from an outer face of the gas generator case and an open inner end exiting in a combustion chamber through the liner. The access conduit has one or more openings disposed in a combustor gap between the gas generator case and the liner of the combustor. A plug is removably secured in the open outer end and extends into the access conduit to obstruct the one or more openings.

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 method of manufacturing an internal manifold of a gas turbine engine including machining an annular channel in a ring by a turning process, and varying a position of a tool bit relative to the surface of the ring as a function of a relative circumferential location of the tool bit around the ring such that the channel has a cross-sectional area that varies around a circumference of the ring.

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

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 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: An inlet tube supplies fuel to a manifold of a combustor in a gas turbine engine, the manifold defining a manifold plane. The inlet tube comprises a tube body having a channel providing fluid flow communication between first and second ends of the tube body. At least a portion of the channel defines a tube body plane which is spaced apart from the manifold plane.

Abstract: A mounting system supporting and positioning an internal fuel manifold of a gas turbine engine includes at least a heat shield surrounding a fuel inlet of the fuel manifold, the heat shield bearing at least a portion of a load to support the fuel manifold.

Abstract: The method comprises flowforming at least one section of the preform and then welding at least one additional element to the at least one flowformed section.

Abstract: A fuel manifold assembly for a gas turbine engine fuel system comprises a fuel manifold at least partly enclosed by a heat shield, the internal manifold being made of a first material having a first coefficient of thermal expansion, and the heat shield being made of a second material having a second coefficient of thermal expansion that is lower than the first coefficient of thermal expansion.

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 manifold assembly for a gas turbine engine comprises 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 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: 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, the side inlet being sealingly isolated by at least two annular sealing members concentric with each other and disposed about the tube body at longitudinally spaced part points thereon.

Abstract: A combustor wall louver for ducting a flow of compressed air through an inlet opening in the combustor wall from a source of compressed air outside the combustor where the louver is a circumferentially extending member, mounted to an interior surface of the combustor wall and covering the inlet opening with outlet openings fed by a channel in flow communication between each outlet opening and the inlet opening. Preferably, the circumferential member is made of arcuate segments of cast metal removably mounted to the interior surface of the combustor wall with threaded studs.

Abstract: A gas turbine engine fuel nozzle system having a fuel conveying member with a channel formed in a surface thereof defined between a pair of facing spaced apart walls, and at least one sealing member disposed within the channel and sealingly fastened to the spaced apart walls.

Abstract: A method of manufacturing an internal manifold of a gas turbine engine including machining an annular channel in a ring by a turning process, and varying a position of a tool bit relative to the surface of the ring as a function of a relative circumferential location of the tool bit around the ring such that the channel has a cross-sectional area that varies around a circumference of the ring.

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, the side inlet being sealingly isolated by at least two annular sealing members concentric with each other and disposed about the tube body at longitudinally spaced part points thereon.

Abstract: An inlet tube supplies fuel to a manifold of a combustor in a gas turbine engine, the manifold defining a manifold plane. The inlet tube comprises a tube body having a channel providing fluid flow communication between first and second ends of the tube body. At least a portion of the channel defines a tube body plane which is spaced apart from the manifold plane.