Abstract: A noise attenuation panel for a structure within a propulsion system includes a first plurality of unit cells; and a second plurality of unit cells, the second plurality of unit cells merged within the first plurality of unit cells, the first plurality of unit cells including a first periodic structure having a first unit cell, a second unit cell, a third unit cell and a fourth unit cell, each of the first unit cell, the second unit cell, the third unit cell and the fourth unit cell including a central body interconnected via a plurality of lateral tubes extending from the central body, the first periodic structure forming a first lateral layer of unit cells.

Abstract: A heat exchanger for providing thermal energy transfer between a first flow along a first flowpath and a second flow along a second flowpath has at least one plate bank having a plurality of plates, each plate having: a first face and a second face opposite the first face; a leading edge along the second flowpath and a trailing edge along the second flowpath; a proximal edge having at least one inlet port along the first flowpath and at least one outlet port along the first flowpath; and at least one passageway along the first flowpath. An inlet manifold has a first face to which the plurality of plates are mounted along their respective proximal edges. An inlet plenum has at least one inlet port and at least one outlet port. An outlet plenum has at least one outlet port and at least one inlet port.

Abstract: A turbine engine heat exchanger has: a manifold having a first face and a second face opposite the first face; a plurality of first plates along the first face, each first plate having an interior passageway; and a plurality of second plates along the second face, each second plate having an interior passageway. A first flowpath passing through the interior passageways of the first plates, the manifold, and the interior passageways of the second plates.

Abstract: A method for forming a reinforced metallic structure includes providing a tool having a formation surface corresponding to a desired structure shape of the reinforced metallic structure. The method also includes positioning a plurality of fibers on the formation surface of the tool. The method also includes depositing a layer of material on the plurality of fibers using a cold-spray technique. The method also includes removing the layer of material with the plurality of fibers from the tool to create the reinforced metallic structure.

Abstract: A vane arc segment includes a platform and an airfoil section that extends in a radial direction from the platform. The airfoil section has a pressure side and a suction side. The platform defines fore and aft axial sides, a core gaspath side, a non-core gaspath side, and first and second flanges that project from the non-core gaspath side. The first and second flanges define, respectively, first and second circumferential mate faces. The first and second flanges each are formed of upturned fiber plies from the platform such that the fiber plies in the first and second flanges are radially-oriented. The first and second circumferential mate faces have, respectively, first and second seal slots that each extend in a ply through-thickness direction across two or more of the fiber plies.

Abstract: An assembly for mounting an auxiliary component to an engine case of a gas turbine engine includes a support bracket, the support bracket having a first end configured for attachment to a first flange of the engine case, a second end configured for attachment to a second flange of the engine case, and an intermediate portion located intermediate the first end and the second end; a bearing member disposed within the intermediate portion; a locator disposed within the bearing member; a first plurality of bolts configured to attach the first end of the support bracket to the first flange; a second plurality of bolts configured to attach the second end of the support bracket to the second flange; and a mechanical fuse.

Abstract: A gas turbine engine includes a fan section, a compressor section, and a turbine section. The fan section has a plurality of vane assemblies spaced circumferentially about an engine axis. The vane assemblies each include an airfoil extending between a leading edge and a trailing edge, a control rod extending through the airfoil, and a mechanism driven by the control rod to change the shape of the airfoil. A vane system for a gas turbine engine is also disclosed.

Abstract: An assembly includes first and second core gaspath walls. Each of the core gaspath walls defines a core gas path side and a non-core gas path side. The first and second core gaspath walls are arranged next to each other and define a gap therebetween. There is a seal arranged on the non-core gas path side that bridges over the gap to seal the gap. A spring device has a plurality of spring elements. The spring elements bias the seal against the non-core gas path sides of the first and second core gaspath walls.

Abstract: A case for a gas turbine engine includes a cast case section cast case section configured to be welded between a forward case section and an aft case section.

Abstract: Airfoils bodies having a first core cavity and a second core cavity located within the airfoil body that is adjacent the first core cavity. The second core cavity is defined by a first cavity wall, a second cavity wall, a first exterior wall, and a second exterior wall, wherein the first cavity wall is located between the second core cavity and the first core cavity and the first and second exterior walls are exterior walls of the airfoil body. The first cavity wall includes a first surface angled toward the first exterior wall and a second surface angled toward the second exterior wall. At least one first cavity impingement hole is formed within the first surface and a central ridge extends into the second core cavity from at least one of the first cavity wall and the second wall and divides the second core cavity into a two-vortex chamber.

Abstract: An apparatus is provided for a turbine engine. This turbine engine apparatus includes a monolithic body. The monolithic body includes a splash plate and a fuel nozzle. The splash plate includes a splash plate surface. The fuel nozzle includes a nozzle orifice. The fuel nozzle is configured to direct fuel out of the nozzle orifice to impinge against the splash plate surface.

Abstract: A node of a radio frequency waveguide system can include a waveguide interface, a signal splitter, a power rectifier and conditioner, a communication filter, and a network processor. The waveguide interface is configured to communicate through a waveguide in the radio frequency waveguide system. The signal splitter is configured to split a radio frequency transmission received at the waveguide interface between a power path and a communications path within the node. The power rectifier and conditioner are configured to produce a conditioned power signal based on power received through the power path. The communication filter of the communications path is configured to produce a filtered communication signal. The network processor is powered by the conditioned power signal and configured to extract encoded information from the filtered communication signal.

Abstract: Techniques for determining a fan spool speed value associated with a hybrid electric gas engine (“engine”) are described herein. For example, a method includes generating a first fan spool speed value based on a base extraction amount. The method further includes generating a change in the first fan spool speed value based on a flight condition and a change in extraction amount. The method further includes generating a second fan spool speed value based on the extraction amount and an augmentation value for intersection of a combustion instability and burner pressure limit. The method further includes generating a second change in the second fan spool speed value based on the flight condition and the change in extraction amount. The method further includes determining a final fan spool speed value and operating the engine at the final fan spool speed value.

Abstract: An anti-vortex tube (AVT) retaining ring and bore basket is provided and includes a unitary body having an inboard portion, an outboard portion and an intermediate portion. The inboard portion includes a first ring-shaped body with an outer diameter. The outboard portion is configured to support an array of AVTs and includes a second ring-shaped body with an inner diameter larger than the outer diameter of the first ring-shaped body. The intermediate portion includes a flange extending between the outer and inner diameters of the first and second ring-shaped bodies, respectively.

Abstract: A heat exchanger duct includes a wall having ends spaced along a central axis. An inlet manifold is positioned within a downstream portion of the duct at a radially outward location. An outlet manifold is positioned within an upstream portion of the duct at a radially outward location. At least one of the inlet and outlet manifolds extend at least 10 degrees around the circumference of the duct. A central manifold is disposed between the inlet and outlet manifolds, and radially inwardly of the inlet and outlet manifolds. Heat exchanger entrance elements extend radially inward from the inlet manifold to the central manifold, and heat exchanger exit elements extend radially outward from the central manifold to the outlet manifold. A gas turbine engine is also disclosed.

Abstract: A method for smoothing surface roughness within an internal passageway is disclosed. In various embodiments, the method comprises developing a first sphere progression through a length of the internal passageway, each sphere within the first sphere progression having a first sphere diameter greater than or equal to a diameter of the internal passageway; and developing a second sphere progression through the length of the internal passageway, each sphere within the second sphere progression having a second sphere diameter greater than the first sphere diameter, whereby the inner surface of the internal passageway is smoothed, first by the first sphere progression and then by the second sphere progression.

Abstract: A gas turbine engine includes a compressor section, a turbine section and an intermediate combustor. The compressor section has a plurality of rotating compressor blades rotating about an axis of rotation, and static stator vanes positioned axially intermediate the rotating compressor blades. There are a plurality of bleed holes extending through a compressor outer housing positioned radially outwardly of the rotating compressor blades, and allowing air compressed by the compressor blades to move into a bleed chamber. There is a bleed chamber outer housing positioned radially outwardly of the compressor outer housing, and defining the bleed chamber in part in combination with the compressor outer housing. A flow discourager is positioned radially intermediate the bleed holes and the bleed outer housing, such that air leaving the bleed hole impacts upon the flow discourager before reaching the bleed chamber outer housing.

Abstract: A heat exchanger has: a first manifold assembly having a stack of plates; a second manifold assembly having a stack of plates; and a plurality of tubes extending from the first manifold assembly to the second manifold assembly. The plurality of tubes is a plurality groups of tubes. For each of the groups of the tubes: the tubes of the group have first ends mounted between plates of the first manifold assembly; and the tubes of the group have second ends mounted between plates of the second manifold assembly.

Abstract: The present disclosure provides methods and systems for composite-to-metal hybrid bonded structures compromising the laser surface treatment on titanium alloys to promote adhesive bond performance. For example, a computer may be programmed to set a laser path corresponding to a predetermined geometric pattern. A laser may be coupled to the computer and apply a pulsed laser beam to a contact surface of the titanium alloy along the predefined geometric pattern. The laser may generate an open pore oxide layer on the contact surface of the substrate with a thickness of 100 and 500 nm. The open pore oxide layer may have a topography corresponding to the predefined geometric pattern. The topography may contain high degree of open pore structure and promote adhesive bond performance. Adhesive, primer or composite resin matrix may fully infiltrate into the open pore structures. Adhesive and composite laminate may co-cure to form composite-to-titanium hybrid bonded structures.

Abstract: A system for bleeding air from a core flow path of a gas turbine engine is disclosed. In various embodiments, the system includes a bleed valve having a bleed valve inlet configured to receive a bleed air from a first access point to the core flow path and a bleed valve outlet; and an air motor having a first air motor inlet configured to receive the bleed air from the bleed valve outlet and a first air motor outlet configured to exhaust the bleed air, the air motor configured to pump the bleed air from the core flow path of the gas turbine engine.