Abstract: An alloy composition includes, by weight: 20% to 23% of Cr; 8% to 10% of Mo; 3.15% to 4.15% of Nb+Ta; 0.25% to 1.5% of B; 0.35% to 1.75% of N; and a balance of Ni.

Abstract: An encapsulated polymeric article is disclosed. The encapsulated polymeric article may include a polymer substrate and a metallic outer shell at least partially encapsulating the polymer substrate. The encapsulated polymeric article may be fabricated by a method comprising: 1) providing a mandrel in a shape of the encapsulated polymeric article, 2) shaping the metallic outer shell on the mandrel, 3) removing the mandrel from the metallic outer shell, and 4) molding the polymeric substrate into the metallic outer shell through a port formed in the metallic outer shell to provide the encapsulated polymeric article.

Abstract: A gas turbine engine includes a fan rotor driven by a fan drive turbine about an axis through a gear reduction to reduce a speed of the fan rotor relative to a speed of the fan drive turbine. A fan case surrounds the fan rotor, and a core engine with a compressor section, including a low pressure compressor. The fan rotor delivers air into a bypass duct defined between the fan case and the core engine. A rigid connection between the fan case and the core engine includes a plurality of H-frame connecting members rigidly connected to the fan case, and to the core engine. The H-frame connecting members each are defined by two rigid legs which extend between the fan case and to the core engine, along directions which are generally parallel to each other. A plurality of non-structural fan exit guide vanes and the non-structural fan exit guide vanes are provided with an acoustic feature to reduce noise. The non-structural fan exit guide vanes are rigidly mounted to at least one of the fan case and the core engine.

Abstract: A method of constructing an additive manufactured article with erodible support. The method includes computing a length of an overhanging geometry that extends from an inner surface of an additively manufactured article; determining points along the overhanging geometry determining an outside point and an inside point from the multiple of overhanging geometry points; determining an anchor point by moving from the inside point I antiparallel to the build direction by a distance sufficient to form an angle greater than a critical angle of the additive process; connecting the anchor point to the overhanging geometry points to form ligament segments; thickening the ligament segments to form a solid ligament to form the erodible support; and additively manufacturing the overhanging geometry from the inner surface of the additively manufactured article via the erodible support, the erodible support erodible during operation of the additively manufactured article.

Abstract: A heat exchanger system is provided and includes a heat sink, fins arrayed on a central region of the heat sink to form channels between adjacent fins and an integrated blower. Each of the fins extends radially outwardly from the central region and has a height that increases with increasing distance from the central region. The integrated blower is disposed at the central region to generate flows of coolant directed into and through the channels.

Abstract: A ducted heat exchanger system for a gas turbine engine includes an additive manufactured heat exchanger core with a contoured external and/or internal geometry. A method of additively manufacturing a heat exchanger for a gas turbine engine includes additively manufacturing a core of a heat exchanger to set a ratio of local surface area to flow area to control a pressure drop per unit length along the core.

Abstract: An angled face cap probe includes a housing having a radially inner end and a radially outer end, defining a cavity, and configured to be located radially outward from an airfoil. The angled face cap probe further includes a sensor located in the cavity at the radially inner end of the housing, having a sensor body with a sensing face that is angled to match or substantially match an angle of a radially outward face the airfoil, and having a sensor flat that is elongated in a first direction. The angled face cap probe further includes an outer cap located in the cavity, coupled to the housing, and having an outer cap main body and cap legs that extend radially inward from the outer cap main body to interface with the sensor flat to resist rotation of the sensor relative to the housing.

Abstract: An epicyclic gear assembly includes a carrier that includes a first plate axially spaced from a second plate. At least one epicyclic gear set is located between the first plate and the second plate. The first plate is configured to rotate with an output of the epicyclic gear assembly. A first bearing race is attached to the first plate for supporting a first bearing. A second bearing race is attached to the second plate for supporting a second bearing.

Abstract: An engine component is configured with a component fluid passage and a receptacle. The component fluid passage extends within the engine component to the receptacle. The receptacle extends through the engine component between a receptacle first end and a receptacle second end. A fluid diverter is configured with a diverter fluid passage and a port. The fluid diverter extends between a diverter first end and a diverter second end. The diverter fluid passage extends partially into the fluid diverter from the diverter first end. The fluid diverter is mated with the receptacle. The diverter first end is disposed at the receptacle first end. The diverter plugs a portion of the receptacle at the diverter second end. The port fluidly couples the component fluid passage to the diverter fluid passage. Fluid is directed through the component fluid passage into the diverter fluid passage to remove debris from the engine component.

Abstract: An additive manufactured multi-portion article includes a first portion of an article manufactured by a first additive manufacturing process; and a second portion of the article manufactured by a second additive manufacturing process different than the first additive manufacturing process, the second portion attached to the first portion.

Abstract: A heat exchanger has a plurality of plates having opposed surfaces and side walls extending beyond the opposed surfaces to a height (h); and a fin pack extending from one opposed surface toward an opposed surface of an adjacent plate, and having a fin height (f), wherein the fin height (f) is equal to or less than the height (h). The plates can be stacked to form a heat exchanger assembly with a gap between adjacent fin packs.

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor section including a propulsor supported on a propulsor shaft, a turbine section including a turbine shaft, a compressor section, and an epicyclic gear train interconnecting the propulsor shaft and the turbine shaft. The gear train includes a sun gear coupled to the turbine shaft, intermediary gears arranged circumferentially about and meshing with the sun gear, a carrier supporting the intermediary gears, and a ring gear including first and second portions each having an inner periphery with teeth intermeshing with the intermediate gears. The first and second portions have axially opposed faces abutting one another at a radial interface. The first and second portions have grooves at the radial interface that form a hole that expels oil through the ring gear.

Abstract: An aspect includes a system for a gas turbine engine. The system includes one or more bleeds of the gas turbine engine and a control system configured to check one or more activation conditions of a dirt rejection mode in the gas turbine engine. A bleed control schedule of the gas turbine engine is adjusted to extend a time to hold the one or more bleeds of the gas turbine engine partially open at a power setting above a threshold based on the one or more activation conditions. One or more deactivation conditions of the dirt rejection mode in the gas turbine engine are checked. The dirt rejection mode is deactivated to fully close the one or more bleeds based on the one or more deactivation conditions.

Abstract: A compression fitting is provided. The compression fitting may include a body, a follower, and a pin, and a cap nut. The follower may be disposed within an axial cavity of the body. The pin may be coupled with the follower. The cap nut may be coupled with the body. An internal edge of the cap nut radially overlaps at least a portion of a forward edge of the pin.

Abstract: A vane arm connection system for a gas turbine engine includes a vane stem having a head with flat contact surfaces; a vane arm having a claw, the claw having opposed arms having inwardly facing surfaces engaging the flat contact surfaces of the head; and a torque transfer member having a body defining an opening for engaging the flat contact surfaces of the head of the vane stem, and at least one arm extending from the body to contact the claw, whereby load from torque is transferred away from the inwardly facing surfaces.

Abstract: A method of fabricating a ceramic component includes hot pressing a composite component with a glass powder / filler cover mixture to form a consolidated glass-based coating on the composite component.

Abstract: A dirt blocker including a support structure disposed within a gas turbine engine, the support structure defining an upstream control volume proximate a forward portion of the gas turbine engine and a downstream control volume proximate an aft portion of the gas turbine engine, the downstream control volume being opposite the upstream control volume relative to the support structure, a flow passage formed through the support structure, the flow passage configured to fluidly couple the upstream control volume with the downstream control volume; a radial contact wall formed from the support structure in fluid communication with the upstream control volume, the radial contact wall configured to intercept debris entrained within cooling air within the gas turbine engine; and a stagnation zone fluidly coupled with the flow passage, the stagnation zone configured to reduce momentum of the debris.

Abstract: A system for controlling blade tip clearances in a gas turbine engine may comprise an active clearance control system and a controller in operable communication with the active clearance control system. The controller may be configured to identify a cruise condition, reduce a thrust limit of the gas turbine engine to a de-rated maximum climb thrust, determine a first target tip clearance based on the de-rated maximum climb thrust, and send a command signal correlating to the first target tip clearance to the active clearance control system.

Abstract: A system of a machine includes a network of a plurality of nodes distributed throughout the machine. Each of the nodes is operable to communicate through one or more radio frequencies, where the machine includes a cooler portion and a hotter portion. The system includes a means for communicating with the network of nodes using a higher frequency to communicate with one or more of the nodes in the cooler portion of the machine and a lower frequency to communicate with one or more of the nodes in the hotter portion of the machine.

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan and a braking system. The braking system is configured to selectively engage the fan during ground windmilling to apply a first level of braking to slow rotation of the fan. Further, when the rotation of the fan sufficiently slows, the braking system is further configured to apply a second level of braking more restrictive than the first level of braking.