Abstract: An acoustic structure for a gas turbine engine comprising a noise reduction layer and a fire protector layer connected to the noise reduction layer. The noise reduction includes a perforated inner wall adapted to be in contact with a first fluidic environment, and a noise reduction adjacent to the inner wall. The fire protector layer includes a non-perforated outer wall adapted to be in contact with a second fluidic environment having potentially a fire, a fire protector adjacent to the outer wall, and a pressure resisting wall disposed between the fire protector and the noise reduction. The second fluidic environment is under a pressure lower than a pressure of the first fluidic environment. The inner and outer walls are load-bearing walls of the acoustic structure.

Abstract: The described method of supplying fuel to an internal fuel manifold of a bypass gas turbine engine includes directing a fuel flow through a fuel fairing having an outer surface exposed to a cool bypass airflow, directing the fuel flow in the fuel fairing through a heat exchanging structure on the outer surface of the fuel fairing to cool the fuel flow being below a coking temperature of the fuel, and then feeding the cooled fuel flow from the fuel fairing to the internal fuel manifold.

Abstract: A gas turbine engine with a rear mount assembly including link rods interconnecting the bypass duct wall and the core portion and connecting assemblies connected to the bypass duct wall. Each connecting assembly has inner and outer surfaces bordering an opening through which an outer end of a respective link rod extends. The outer surface is accessible from outside the bypass duct wall. A first locking member is engaged to the outer end in a first locked position, and includes an abutment portion located radially inwardly of the inner surface and abutting the inner surface, and an outer portion protruding radially outwardly through the opening beyond the outer surface. A second locking member is engaged the outer end in a second locked position, and has an abutment portion located radially outwardly of the outer surface and abutting the outer surface. A method of supporting a core portion is also discussed.

Abstract: A gas turbine engine with a rear mount assembly including link rods interconnecting the bypass duct wall and the core portion and connecting assemblies connected to the bypass duct wall. Each connecting assembly has inner and outer surfaces bordering an opening through which an outer end of a respective link rod extends. The outer surface is accessible from outside the bypass duct wall. A first locking member is engaged to the outer end in a first locked position, and includes an abutment portion located radially inwardly of the inner surface and abutting the inner surface, and an outer portion protruding radially outwardly through the opening beyond the outer surface. A second locking member is engaged the outer end in a second locked position, and has an abutment portion located radially outwardly of the outer surface and abutting the outer surface. A method of supporting a core portion is also discussed.

Abstract: The described method of supplying fuel to an internal fuel manifold of a bypass gas turbine engine includes directing a fuel flow through a fuel fairing having an outer surface exposed to a cool bypass airflow, directing the fuel flow in the fuel fairing through a heat exchanging structure on the outer surface of the fuel fairing to cool the fuel flow being below a coking temperature of the fuel, and then feeding the cooled fuel flow from the fuel fairing to the internal fuel manifold.

Abstract: A mounting method and system for supporting and positioning an internal fuel manifold relative to a combustor in a fuel injection system for a gas turbine engine. The method includes positioning the fuel manifold within a gas generator casing, applying a heat shield around a radially extending fuel inlet connected to the fuel manifold, and using the heat shield to at least partially support the fuel manifold within the gas generator casing.

Abstract: The link rod can have a core portion supported inside an annular bypass duct with a bypass air passage extending radially therebetween, the link rod comprising a hot end fitting, a cold end, and an elongated and hollow strut body of composite material and having an aerodynamic cross-sectional shape, the strut body being secured to the hot end fitting and extending between the hot end fitting and the cold end, the hot end fitting having a metal body housing a spherical bearing mountable to the core portion, and the cold end housing a spherical bearing mountable to the bypass duct wall.

Abstract: An acoustic structure for a gas turbine engine comprising an noise reduction layer and a fire protector layer connected to the noise reduction layer. The noise reduction includes a perforated inner wall adapted to be in contact with a first fluidic environment, and an noise reduction adjacent to the inner wall. The fire protector layer includes a non-perforated outer wall adapted to be in contact with a second fluidic environment having potentially a fire, a fire protector adjacent to the outer wall, and a pressure resisting wall disposed between the fire protector and the noise reduction. The second fluidic environment is under a pressure lower than a pressure of the first fluidic environment.

Abstract: A gas turbine engine has a rear mounting structure incorporating a mounting apparatus attached to a bypass duct wall with a link device of six rods for transferring core portion related inertia-induced loads, from an inner case of the core portion in a short circuit across an annular bypass air passage to the bypass duct wall.

Abstract: The link rod can have a core portion supported inside an annular bypass duct with a bypass air passage extending radially therebetween, the link rod comprising a hot end fitting, a cold end, and an elongated and hollow strut body of composite material and having an aerodynamic cross-sectional shape, the strut body being secured to the hot end fitting and extending between the hot end fitting and the cold end, the hot end fitting having a metal body housing a spherical bearing mountable to the core portion, and the cold end housing a spherical bearing mountable to the bypass duct wall.

Abstract: A mounting method and system for supporting and positioning an internal fuel manifold relative to a combustor in a fuel injection system for a gas turbine engine. The method includes positioning the fuel manifold within a gas generator casing, applying a heat shield around a radially extending fuel inlet connected to the fuel manifold, and using the heat shield to at least partially support the fuel manifold within the gas generator casing.

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: A gas turbine engine has a rear mounting structure incorporating a mounting apparatus attached to a bypass duct wall with a link device of six rods for transferring core portion related inertia-induced loads, from an inner case of the core portion in a short circuit across an annular bypass air passage to the bypass duct wall.

Abstract: A cooling apparatus for cooling a fluid in a bypass gas turbine engine comprises a heat exchanger disposed within a bypass duct and accommodated by a sub-passage defined by a flow divider affixed to an annular wall of the bypass duct. The sub-passage defines an open upstream end and an open downstream end to direct a portion of the bypass air flow to pass therethrough.

Abstract: A cooling apparatus for cooling a fluid in a bypass gas turbine engine comprises a heat exchanger disposed within a bypass duct and accommodated by a sub-passage defined by a flow divider affixed to an annular wall of the bypass duct. The sub-passage defines an open upstream end and an open downstream end to direct a portion of the bypass air flow to pass therethrough. A sealing assembly for the bypass duct is also provided.

Abstract: A fuel conveying member of a gas turbine engine fuel system conducting pressurized fluid flow is provided. The fuel conveying member comprises a body defining an L-shaped fuel flow passage therein, the L-shaped passage including an elbow. The elbow portion provides a substantially smooth fluid-dynamic transition between portions of the passage upstream and downstream thereof.

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 method and apparatus for cooling a fluid in a bypass gas turbine engine involves directing the fluid to the bypass duct of the engine to allow for heat exchange from the fluid to bypass air passing through the bypass air duct.

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: 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.