Abstract: A heat exchanger is provided that can include furcating unit cells coupled with each other. Each of the unit cells can be elongated along an axis and include a sidewall that defines annular ring openings on opposite ends of the unit cell along the axis. The sidewall also can define undulating annular rings between the annular ring openings and axially separated from each other along the axis. The sidewall can further define angled openings into the unit cell both above and below each of the undulating annular rings. At least a first opening of the annular ring openings and the angled openings can be configured to be an inlet to receive a first fluid into the unit cell and at least a second opening of the annular ring openings and the angled openings configured to be an outlet through which the first fluid exits the unit cell.

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 method of forming a heat exchanger, for example a heat exchanger used in an aircraft, the method comprising extruding a metal body with at least one fluid passage in the metal body, forming a set of fins that are attached to the metal body and forming a set of heat transfer augmentation structures on the metal body.

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 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 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.

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: 3-D build jobs having surrogate supports, 3-D printers using surrogate supports, and techniques to support vulnerable regions of build pieces using surrogate supports are disclosed. The surrogate supports are generated in a first material configuration and are offset via a gap from the vulnerable regions. The gap comprises a second material configuration, such as loose or partially fused powder on which the build piece can be supported during 3-D printing. In alternative embodiments, the gap instead includes thin manual ties or a solid body using material that is stronger but more amenable to breaking off without damaging the build piece. Post-processing steps are dramatically reduced as the surrogate supports and gaps facilitate virtually error-free separation from the build piece. In an embodiment, the surrogate supports include a support structure extending to a fixed base underneath, the fixed base being a build plate or a global surrogate.

Abstract: A buffer block apparatus for securing a node may be described. The buffer block apparatus may include a first surface having disposed thereon at least one first zero-point feature configured for a first zero-point interface with a robotic assembly apparatus; and a second surface, different from the first surface, configured to connect with a first surface of a node and form a first rigid connection between the buffer block apparatus and the node, wherein the buffer block apparatus provides at least one reference coordinate system with respect to the node.

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: 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 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 can include a cooling air conduit having at least one baffle, as well as a hot air conduit having at least two passes through the cooling air conduit. The heat exchanger can further include at least one perforation extending into the least one baffle. The perforation can have a passage connecting an inlet to an outlet.

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 method of forming a heat exchanger, for example a heat exchanger used in an aircraft, the method comprising extruding a metal body with at least one fluid passage in the metal body, forming a set of fins that are attached to the metal body and forming a set of heat transfer augmentation structures on the metal body.

Abstract: A fan casing assembly, connection assembly and method for moving a fan casing cooler. The 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 can mount along the peripheral wall in order to confront a cooling fluid flow within the flow path in order to cool a fluid through the fan casing cooler.

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 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: 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 duct for a turbine engine, such as a gas turbine engine, can be utilized to carry a fluid from one portion of the engine to another. The duct can include a metallic tubular element having one of a varying wall thickness, a varying cross section, or a tight bend. Such a duct can be formed utilizing additive manufacturing or metal deposition on an additively manufactured mandrel.