Abstract: A flexible joint assembly for a joint between a first duct and a second duct for providing a flow of fluid, such as bleed air in an aviation implementation. The flexible joint includes a bellows supported by a mounting assembly having a first support and a second support, provided within the interior of the bellows. A rod assembly can operably couple the first support and the second support.

Abstract: A flexible joint assembly for a joint between a first duct and a second duct for providing a flow of fluid, such as bleed air in an aviation implementation. The flexible joint includes a bellows supported by a mounting assembly having a first support and a second support, each surrounding a portion of the bellows. A set of rod assemblies can operably couple the first support and the second support.

Abstract: A flexible joint assembly for a joint between a first duct and a second duct for providing a flow of fluid, such as bleed air in an aviation implementation. The flexible joint includes a bellows supported by a mounting assembly having a first support and a second support, each surrounding a portion of the bellows. A gimbal ring assembly of the joint assemblies can operably couple the first support and the second support.

Abstract: A turbine engine duct assembly including a joint assembly having an outer shroud, a bellows, a flared tube, a backing ring, and a kinematic ring. The joint assembly provides for dynamic movement of the duct assembly during operation of the engine. Such dynamic movement can be resultant of vibrational forces or thermal expansion of the engine. The joint assembly permits such dynamic movement without excessive system stiffness.

Abstract: A flexible joint assembly for a joint between a first duct and a second duct for providing a flow of fluid, such as bleed air in an aviation implementation. The flexible joint includes a bellows supported by a mounting assembly having a first support and a second support, each surrounding a portion of the bellows. A set of flexures provided on a joint ring of the joint assemblies can operably couple the first support and the second support.

Abstract: A turbine engine duct assembly and joint assembly having an outer shroud at least partially defining an interior of the joint assembly, an inner shroud at least partially received within the outer shroud and forming an interface therewith and defining a remainder of the interior of the joint assembly and having a flexible portion for dynamic movement of the duct assembly during operation of the engine.

Abstract: A manufacturing process for making aircraft engine parts utilizes reusable reconfigurable smart memory polymer mandrel tooling, low temperature metal deposition, and composite part lay-up with resin coated conformable braided carbon fiber sleeves, to fabricate both metal internal engine parts and non-metal external parts for turbine engines.

Abstract: An igniter assembly for an engine, including a gas turbine engine, includes a shell comprising a tip end defining an opening and a sidewall extending away from the tip end where the sidewall surrounds a cavity within the shell and a tip insert assembly operably coupled to the tip end within the opening and having an insert body and a set of pins recessed within the insert body.

Abstract: A heat exchanger for a turbine engine having a body including a first surface, a second surface opposite the first surface, and at least one fluid passage configured to carry a flow of heated fluid proximal to the second surface and where the body is arranged to transfer heat from the heated fluid to a cooling fluid passing by the second surface.

Abstract: An apparatus and method for cooling a fluid within a turbine engine. A fan casing assembly for the turbine engine can include an annular fan casing with a peripheral wall having a flow path defined through the casing. A fan casing cooler includes a body to confront the peripheral wall with at least one conduit configured to carry a flow of heated fluid to convectively cool the heated fluid with a flow of air through the flow path.

Abstract: A method for manufacturing a heat exchanger including forming a heat exchanger with walls using direct metal laser melting. The walls include defects formed during the direct metal laser melting process. The defects can cause leaking within the heat exchanger. The method includes healing the defects.

Abstract: An apparatus and method for cooling a fluid within a turbine engine. A fan casing assembly for the turbine engine can include an annular fan casing with a peripheral wall having a flow path defined through the casing. A fan casing cooler includes a body to confront the peripheral wall with at least one conduit configured to carry a flow of heated fluid to convectively cool the heated fluid with a flow of air through the flow path.

Abstract: A heat exchanger apparatus including a surface cooler and a passive automatic retraction and extension system coupled to the surface cooler. The surface cooler having disposed therein one or more fluid flow channels configured for the passage therethrough of a heat transfer fluid to be cooled. The heat transfer fluid in a heat transfer relation on an interior side of said one or more fluid flow channels. The surface cooler including a plurality of fins projecting from an outer surface thereof. The passive automatic retraction and extension system including a thermal actuation component responsive to a change in temperature of at least one of the heat transfer fluid and a cooling fluid flow so as to actuate a change in a geometry of the surface cooler. Further disclosed is an engine including the heat exchanger apparatus.

Abstract: A valve and a heat exchanger apparatus for a gas turbine engine include a valve body having a valve seat and an actuation component including a plate formed from a set of metal layers and responsive to a change in at least one of a thermal condition and a pressure exerted thereon such that the plate moves and the valve moves between an opened and a closed position where a portion of the plate engages with the valve seat.

Abstract: A heat exchanger includes a core defining a first passageway and a second passageway. The core includes a plurality of unit cells coupled together. Each unit cell of the plurality of unit cells includes a first wall and a second wall. The second wall is spaced from the first wall. The first wall at least partially defines a first passageway portion and a second passageway portion. The second wall at least partially defines the second passageway portion. The second wall extends about the first wall such that the first passageway portion is nested within the second passageway portion.

Abstract: A heat exchanger includes a cooling air conduit having multiple baffles, a hot air conduit having multiple passes through the cooling air conduit and forming multiple intersections with the baffles, and multiple perforations extending through the baffles. A cooling air flow passes through the baffles, rather than strictly between the baffles, and improves heat-transfer characteristics of the heat exchanger.

Abstract: A heat exchanger is provided. The heat exchanger is formed of a spiral wound flow body (70) having a plurality of passages (76) ending therethrough for passage of a first fluid. The flow body is positioned within a housing (42) and a cross-flow of a second fluid passes between or across successive layers of the spiral wound flow body. The intermixing of the thermal energy of the cross-flowing second fluid and the first fluid provide improved heat exchange.

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: The present innovation relates to a gas turbine engine comprising an engine core with a combustion section, a fuel circuit fluidly coupled to the combustion section, an oil circuit fluidly coupled to the engine core, and an oil heat exchanger comprising a portion of the fuel circuit forming part of the oil circuit.

Abstract: A heat exchanger includes a core defining a first passageway configured for a first fluid to flow through and a second passageway configured for a second fluid to flow through. The core includes a plurality of unit cells coupled together. Each unit cell of the plurality of unit cells includes a sidewall at least partly defining a first passageway portion, a second passageway portion, a plurality of first openings for the first fluid to flow through, and a plurality of second openings for the second fluid to flow through. Each unit cell of the plurality of unit cells is configured to enable the first fluid to combine and divide in the first passageway portion. Each unit cell is further configured to enable the second fluid to combine and divide in the second passageway portion.