Abstract: A heat exchanger and heat exchanger core are provided. The heat exchanger core includes a plurality of columnar passages extending between an inlet plenum of the heat exchanger core and an outlet plenum of the heat exchanger core, the columnar passages formed monolithically in a single fabrication process.

Abstract: A integrated fluid conduit is provided having two or more internal conduits, the size and shape of the internal conduits is designed to optimize the hydraulic diameter of each conduit based on the needs of the system. The integrated fluid conduit is advantageously manufactured according to additive manufacturing techniques which enable formation of off-center and/or non-concentric internal conduits adapted to specific applications requiring turns such as the fuel delivery system or the hydraulic system of/on a gas turbine engine for an airplane.

Abstract: A heat exchanger and heat exchanger core are provided. The heat exchanger core includes a plurality of columnar passages extending between an inlet plenum of the heat exchanger core and an outlet plenum of the heat exchanger core, the columnar passages formed monolithically in a single fabrication process.

Abstract: A heat exchanger is provided having an integrally and seamlessly formed return manifold connecting multiple supply tubes and return tubes. The heat exchanger may also include a return manifold having one or more structures providing a flow restriction within or proximate the return manifold.

Abstract: A heat exchanger and heat exchanger core are provided. The heat exchanger core includes a plurality of columnar passages extending between an inlet plenum of the heat exchanger core and an outlet plenum of the heat exchanger core, the columnar passages formed monolithically in a single fabrication process.

Abstract: A integrated fluid conduit is provided having two or more internal conduits, the size and shape of the internal conduits is designed to optimize the hydraulic diameter of each conduit based on the needs of the system. The integrated fluid conduit is advantageously manufactured according to additive manufacturing techniques which enable formation of off-center and/or non-concentric internal conduits adapted to specific applications requiring turns such as the fuel delivery system or the hydraulic system of/on a gas turbine engine for an airplane.

Abstract: A valve assembly and a method of additively manufacturing the same are provided. The valve assembly includes a valve housing defining first and second mounting features, such as recessed dimples or protruding bumps, positioned on opposite sides of a substantially cylindrical channel to define a hinge axis. One or more valve flaps are positioned within the cylindrical channel, each valve flap including a hinge member extending along the hinge axis and defining two or more complementary features or coupling members for engaging either the mounting features of the valve housing or an adjacent hinge member.

Abstract: A heat exchanger assembly for a gas turbine engine that includes an outer engine case. The heat exchanger assembly includes at least one cooling channel, the at least one cooling channel is configured to receive a flow of fluid to be cooled. At least one first coolant flow duct that is configured to receive a flow of a first coolant, wherein the at least one cooling channel is disposed between a first inlet and a first outlet. The heat exchanger assembly further include at least one second coolant flow duct that is configured to receive a flow of a second coolant, wherein the at least one cooling channel is disposed between a second inlet and a second outlet.

Abstract: A heat exchanger and heat exchanger core are provided. The heat exchanger core includes a plurality of columnar passages extending between an inlet plenum of the heat exchanger core and an outlet plenum of the heat exchanger core, the columnar passages formed monolithically in a single fabrication process.

Abstract: A ducted cowl support includes an annular structure configured to be mounted to an annular turbine engine frame and including one or more bypass ducts integrally formed therein.

Abstract: A valve assembly and a method of additively manufacturing the same are provided. The valve assembly includes a valve housing defining first and second mounting features, such as recessed dimples or protruding bumps, positioned on opposite sides of a substantially cylindrical channel to define a hinge axis. One or more valve flaps are positioned within the cylindrical channel, each valve flap including a hinge member extending along the hinge axis and defining two or more complementary features or coupling members for engaging either the mounting features of the valve housing or an adjacent hinge member.

Abstract: The heat exchanger assembly includes a heat exchanger body and a plurality of columns of fluid passages arranged in a first direction within the heat exchanger body. The plurality of columns of fluid passages includes at least one first fluid column of fluid passages and at least two second fluid columns of fluid passages. The first fluid column is interspersed between two second fluid columns. The first fluid column includes a plurality of first fluid passages configured to channel a first fluid through the heat exchanger body. The at least two second fluid columns includes a plurality of second fluid passages configured to channel a second fluid through the heat exchanger body. The plurality of first fluid passages is offset with respect to the plurality of second fluid passages.

Abstract: A heat exchanger assembly for a gas turbine engine that includes an outer engine case. The heat exchanger assembly includes at least one cooling channel, the at least one cooling channel is configured to receive a flow of fluid to be cooled. At least one first coolant flow duct that is configured to receive a flow of a first coolant, wherein the at least one cooling channel is disposed between a first inlet and a first outlet. The heat exchanger assembly further include at least one second coolant flow duct that is configured to receive a flow of a second coolant, wherein the at least one cooling channel is disposed between a second inlet and a second outlet.

Abstract: A fuel manifold apparatus includes an annular array of fuel nozzles interconnected by a plurality of manifold tubes, wherein each manifold tube includes at least two fuel passages integrally formed therein, the fuel passages being configured for conduction heat transfer therebetween.

Abstract: A gas turbine engine is provided. The gas turbine engine includes a compressor assembly and a combustion assembly in flow communication with the compressor assembly. The combustion assembly includes a plurality of fuel nozzles and a fluid conduit for delivering fuel to the fuel nozzles. The fluid conduit has a plurality of first outlet ports that are spaced apart from one another along the fluid conduit, and the fluid conduit also has a plurality of second outlet ports that are spaced apart from one another along the fluid conduit. The fluid conduit further has a first flow path extending along the fluid conduit in flow communication with the first outlet ports, and the fluid conduit also has a second flow path extending along the fluid conduit in flow communication with the second outlet ports. At least a portion of the first flow path is circumscribed by the second flow path.

Abstract: A heat exchanger is provided having an integrally and seamlessly formed return manifold connecting multiple supply tubes and return tubes. The heat exchanger may also include a return manifold having one or more structures providing a flow restriction within or proximate the return manifold.

Abstract: A fuel manifold apparatus includes an annular array of fuel nozzles interconnected by a plurality of manifold tubes, wherein each manifold tube includes at least two fuel passages integrally formed therein, the fuel passages being configured for conduction heat transfer therebetween.

Abstract: A ducted cowl support includes an annular structure configured to be mounted to an annular turbine engine frame and including one or more bypass ducts integrally formed therein.

Abstract: Load-bearing structures constructed from polymer matrix composite (PMC) materials, and processes for their production. The structures are produced from at least one shaped panel formed of a continuous fiber reinforcement in a thermoplastic resin matrix. The shaped panel has been thermoformed to have a substantially constant cross-sectional thickness and portions that lie in different planes and are interconnected by one or more bends. The shaped panel is machined to alter its shape, and optionally to produce multiple separate subcomponents therefrom. The machined shaped panel can constitute the entire structure, or the structure can be formed by joining the machined shaped panel with other shaped panels or by joining two or more of the subcomponents. The structure can be installed on an aircraft engine to secure components to the engine.

Abstract: A gas turbine engine is provided. The gas turbine engine includes a compressor assembly and a combustion assembly in flow communication with the compressor assembly. The combustion assembly includes a plurality of fuel nozzles and a fluid conduit for delivering fuel to the fuel nozzles. The fluid conduit has a plurality of first outlet ports that are spaced apart from one another along the fluid conduit, and the fluid conduit also has a plurality of second outlet ports that are spaced apart from one another along the fluid conduit. The fluid conduit further has a first flow path extending along the fluid conduit in flow communication with the first outlet ports, and the fluid conduit also has a second flow path extending along the fluid conduit in flow communication with the second outlet ports. At least a portion of the first flow path is circumscribed by the second flow path.