Abstract: A process of treating a carbon-carbon composite material including modifying a surface of the carbon-carbon composite material to increase a hydrophilic surface functionality; applying a plasma surface treatment to the carbon-carbon composite material; infiltrating the carbon-carbon composite with an oxidation inhibiting composition; and heating the carbon-carbon composite at a predetermined temperature sufficient to form a deposit from the oxidation inhibiting composition in at least some pores of the carbon-carbon composite.

Abstract: A pin-guided spring is used for mounting a ceramic matrix composite (CMC) component of a turbine engine, wherein the CMC component having a hot side configured for exposure to a hot gaspath of the turbine engine and an opposing non-gaspath side having a first flange and a second flange extending radially outward therefrom, the first and second flanges each including axial holes disposed therethrough. The pin-guided spring has a first end with first axial holes in registration with the axial holes in the first flange and dimensioned to engage a plurality of pins, a second end with second axial holes in registration with the axial holes in the first flange and dimensioned to engage the plurality of pins, and a compressible central section dimensioned for an interference fit between a support and the second flange. The interference fit on the pin-guided spring can protect the CMC component from damage.

Abstract: A seal ring has a substrate having: an inner diameter surface; an outer diameter surface; a first zone representing a by-weight majority of the substrate and having Co as a largest by-weight constituent element and at least 18.0 weight percent Cr; and a second zone, radially outward of the first zone, and having Cr2O3 and Cr2CoO4.

Abstract: A hollow fan blade comprises a sheath, an airfoil and a cover. The sheath forms a pressure side wall and has an exterior surface. The airfoil forms a suction side wall and has an exterior surface. There are a plurality of ribs extending between the pressure side wall and the suction side wall, where the plurality of ribs partition the hollow airfoil into one or more cavities. The cover is disposed in the one or more cavities to protect the plurality of ribs. The cavities are filled with a polymeric foam.

Abstract: An engine core includes a compressor section and a core flowpath. The compressor section includes first and second compressor rotors. The core flowpath extends across the first compressor rotor and the second compressor rotor between an inlet into the core flowpath and an exhaust from the core flowpath. An air system includes an eductor, a first bleed port, a second bleed port, a first passage and a second passage. The eductor includes a nozzle disposed in the second passage. The first bleed port is disposed along the core flowpath at a downstream end of the first compressor rotor. The first bleed port fluidly couples the core flowpath to the first passage and the second passage in parallel. The second bleed port is disposed along the core flowpath at a downstream end of the second compressor rotor. The second bleed port fluidly couples the core flowpath to the nozzle.

Abstract: A vane arm has: a first end and a second end; a shank extending between the first end and the second end and having a first face and a second face; a first hole in the shank proximate the first end; a second hole in the shank proximate the second end; and a transverse groove in the first face intersecting the second hole. The transverse groove has: a base; a first open end and a second open end; a first side face and a second side face. The transverse groove first side face and second side face converge toward each other from the first open end to the second open end.

Abstract: An integrally bladed disk is provided that includes a disk and a plurality of rotor blades. The disk has an outer radial hub and is configured for rotation around a rotational axis. Each rotor blade of the plurality of rotor blades has an airfoil that extends chordwise between a leading edge and a trailing edge, and extends spanwise between a base end and a blade tip. Each rotor blade includes a damper pocket, a damper body, and a plug. The damper pocket extends into the airfoil from the base end and has a first tapered configuration. The damper body is disposed within the damper pocket, and has a second tapered configuration. The second tapered configuration of the damper body mates with the first tapered configuration of the damper pocket. The plug is disposed to retain the damper body within the damper pocket.

Abstract: A system for monitoring operation of a gas turbine engine comprises a plurality of expert networks each configured to generate a separate gas path parameter responsive to a separate actuator position. A router network configured to generate a weighting vector responsive to at least one ambient condition parameter. The weighting vector includes a plurality of weighting values each associated with one of the plurality of expert networks. Summing circuitry configured to apply the plurality of weighting values to each of the associated separate gas path parameters from the plurality of expert networks and sum each of the plurality of weighted separate gas path parameters from the plurality of expert networks to a weighted sum value.

Abstract: Disclosed are methods of anodizing a metal component. In the methods an anodization bath includes an organic acid.

Abstract: An assembly is provided for an aerial vehicle. This assembly includes a vehicle body, a gas turbine engine and a support structure. The vehicle body includes a body section. The gas turbine engine includes a stationary structure. The gas turbine engine is housed within the vehicle body. The support structure extends between and is connected to the body section and the stationary structure. The support structure supports the gas turbine engine within the vehicle body. The body section, the stationary structure and the support structure are included in a monolithic body.

Abstract: According to an embodiment, a method includes receiving engine data associated with an engine. The method further includes analyzing the engine data to determine a number of engine on-wing performance analyses to perform and a number of engine shop visit performance analyses to perform. The method further includes performing an engine on-wing performance analysis. The method further includes performing an engine shop visit performance analysis. The method further includes performing a workscope analysis to generate a recommendation. The method further includes causing the recommendation to be implemented to service the engine.

Abstract: An aircraft propulsion system includes a plurality of condenser pairs where water is condensed from the exhaust gas flow received through a corresponding one of the plurality of exhaust ducts. Each of the condenser pairs are angled relative to each other and the corresponding one of the plurality of exhaust ducts and each condenser of the plurality of condenser pairs comprises an inward facing side and an outward facing side through which a cooling air flow is communicated for cooling the exhaust gas flow.

Abstract: A hybrid ignitor including an ignitor body with an ignitor wall defining an ignitor interior and an ignitor exterior, the ignitor body having an electrode end opposite a discharge end; a central electrode disposed within the ignitor interior, the central electrode including a spark end; a ground electrode disposed within the ignitor interior and electrically coupled with the central electrode near the spark end; an air inlet formed in the ignitor wall near the spark end; and a solid fuel disposed within the ignitor interior near the discharge end and near the spark end of the central electrode and downstream of the air inlet.

Abstract: A fabric reinforced seal assembly, comprising a substrate; a seal comprising a fabric having a first side facing the substrate, a second side facing away from the substrate and a thickness defined between the first side and the second side, and an elastomer infiltrated into the fabric from the second side toward the first side, wherein the elastomer extends into the fabric from the second side for a distance of less than or equal to 50% of the thickness of the fabric.

Abstract: A turbine engine airfoil element has an airfoil having: a pressure side and a suction side; and a plurality of spanwise passageway legs. The passageway legs include: a leading edge impingement cavity; and a plurality of main body feed passageway legs along a camber line. A wall separates the leading edge impingement cavity from a leading one of the main body feed passageway legs, the wall having a suction side section and a pressure side section joining at a junction, the junction forming a vertex of an angle of transverse cross-section of the wall; and a plurality of impingement feed holes through the wall. The plurality of impingement feed holes are larger thickness-wise than span-wise.

Abstract: A method of coating a component includes attaching the component to a support that is configured to hold a plurality of components and placing a base of the support in a holder that is attached to rotatable member of a fixture, wherein an axis of the holder is parallel to an axis of rotation of the rotatable member. The method also includes transporting the fixture into a coating chamber wherein a direction of an exit stream of a coater in oriented perpendicularly to the axis of rotation, exposing the fixture and the component to a reverse transfer arc cleaning/pre-heating procedure, and exposing the fixture and the component to a coating procedure during which a coating is directed at the component in a direction perpendicular to the axis of rotation while the rotatable member is rotating. The method further includes transporting the fixture and removing the component from the support fixture.

Abstract: A gas turbine engine has: a core flowpath sequentially through one or more fan sections, one or more compressor sections, a combustor section, and one or more turbine sections; a bypass flowpath extending through the one or more fan sections and bypassing the combustion section; a heat exchanger in the bypass flowpath placing a portion of the bypass flowpath in heat exchange relation with a second fluid flowpath; a first thermoelectric generator having a first side upstream of the heat exchanger along the bypass flowpath and a second side away from the bypass flowpath; and a second thermoelectric generator having a first side downstream of the heat exchanger along the bypass flowpath and a second side away from the bypass flowpath.

Abstract: A chemical vapor infiltration (CVI) system comprises a reactor with an inlet for receiving a flow of reactive gas and an outlet for exhausting the flow of reactive gas, and plurality of acoustic wave generators disposed to generate acoustic waves within the reactor.

Abstract: An assembly is provided for an aircraft powerplant. This assembly includes a first powerplant component, a second powerplant component, a third powerplant component and a fluid system. The fluid system includes a first fluid circuit, a second fluid circuit, a third fluid circuit and a heat exchanger. The first fluid circuit extends through the heat exchanger and is configured to service the first powerplant component. The second fluid circuit extends through the heat exchanger and is configured to service the second powerplant component. The third fluid circuit extends through the heat exchanger and is configured to service the third powerplant component. The heat exchanger is configured as or otherwise includes a radiator.

Abstract: A propulsion system assembly includes an open propulsor rotor and an open guide vane structure. The open guide vane structure is axially next to the open propulsor rotor. The open guide vane structure includes a plurality of open guide vanes arranged circumferentially about a rotational axis in an array. An airfoil of a first of the open guide vanes includes a base, a tip, a first side surface, a second side surface, a leading edge, a trailing edge and a mean line. The airfoil projects spanwise out from the base to the tip. The airfoil extends laterally between the first side surface and the second side surface. The airfoil extends longitudinally along the mean line between the leading edge and the trailing edge. The first open guide vane is configured to pivot about a pivot axis which is axially offset along the rotational axis from the airfoil at the base.