Abstract: A turbine engine having a disk and a composite airfoil assembly. The disk having a slot. The composite airfoil assembly having an airfoil portion, a dovetail portion, and a roll snubber. The dovetail portion having a radially inner surface. The roll snubber being provided on the radially inner surface. The radially inner surface spaced from the slot to define a gap therebetween.

Abstract: A method of forming a composite airfoil assembly. The method includes forming an inner support structure with at least a first core and a second core each having a core material with at least one of fibers, yarns, braids, or tows. The method includes applying a laminate overlay to surround at least a portion of the inner support structure.

Abstract: A turbine engine with an engine core defining an engine centerline and comprising a rotor assembly and a stator assembly. The turbine engine including a primary stage of airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor assembly. A subsidiary stage of airfoils located upstream of the primary stage of airfoils and circumferentially arranged about the engine centerline.

Abstract: An automated fiber placement assembly forms a component by the placement of separate or multiple layers of fiber tows. The automated fiber placement assembly comprises a cutter assembly defining a cut shape. A backplate is spaced from the first cutter assembly against which cutter assembly can cut the fiber tows. The fiber tows define a longitudinal axis and are fed between the first cutter assembly and the backplate in a feed direction. The cutter head assembly is rotatable and movable to vary the orientation of the cutter assembly in order to define different cut shapes non-orthogonal to the longitudinal axis.

Abstract: An aircraft engine assembly includes a gas turbine engine having an intake channel configured to receive an incoming flow of air and form an intake flow of air, the intake channel configured to turn the received incoming flow of air from an incoming flow direction to a first axial direction of the gas turbine engine, the incoming flow direction reverse of the first axial direction, and an electric machine coupled with the low pressure shaft and located at the aft end of the gas turbine engine proximate the intake channel, the electric machine in heat exchange communication with the intake flow of air such that the electric machine transfers heat to the incoming flow of air within the intake channel when the electric machine is operated.

Abstract: An aircraft engine assembly includes a gas turbine engine having an intake channel configured to receive an incoming flow of air and form an intake flow of air, the intake channel configured to turn the received incoming flow of air from an incoming flow direction to a first axial direction of the gas turbine engine, the incoming flow direction reverse of the first axial direction, and an electric machine coupled with the low pressure shaft and located at the aft end of the gas turbine engine proximate the intake channel, the electric machine in heat exchange communication with the intake flow of air such that the electric machine transfers heat to the incoming flow of air within the intake channel when the electric machine is operated.

Abstract: An automated fiber placement assembly forms a component by the placement of separate or multiple layers of fiber tows. The automated fiber placement assembly comprises a cutter assembly defining a cut shape. A backplate is spaced from the first cutter assembly against which cutter assembly can cut the fiber tows. The fiber tows define a longitudinal axis and are fed between the first cutter assembly and the backplate in a feed direction. The cutter head assembly is rotatable and movable to vary the orientation of the cutter assembly in order to define different cut shapes non-orthogonal to the longitudinal axis.

Abstract: An aircraft engine assembly includes a gas turbine engine having an intake channel configured to receive an incoming flow of air and form an intake flow of air, the intake channel configured to turn the received incoming flow of air from an incoming flow direction to a first axial direction of the gas turbine engine, the incoming flow direction reverse of the first axial direction, and an electric machine coupled with the low pressure shaft and located at the aft end of the gas turbine engine proximate the intake channel, the electric machine in heat exchange communication with the intake flow of air such that the electric machine transfers heat to the incoming flow of air within the intake channel when the electric machine is operated.

Abstract: A gas turbine engine oil flow control system can include a variable flow oil pump useful to provide oil at varying rates to a variety of oil consumers, such as, power gearboxes, engine shaft bearings, electrical generators, etc. Oil flow control valves that have an ability to provide a variable flow of oil can be used in conjunction with the variable flow oil pump. Flow sensors can be used along with an oil flow controller to measure a flow of oil at various points in the gas turbine engine oil flow control system. The oil flow controller can use information from the flow sensors along with a variable consumption demand association with one or more of the oil consumers (either provided to the oil controller or calculated based upon an operational need of the oil consumer) to change operation of the variable flow oil pump and/or oil flow control valve.

Abstract: Methods, network traffic management apparatuses, non-transitory computer readable media, and network traffic management systems that control network traffic with a subscriber-aware disaggregator include mapping a network address in a network packet received from a client to one of a plurality of subscribers in a subscriber database. A master network address for the one of the subscribers is identified from the mapped network address, where the subscriber has at least one other network address associated with the one of the subscribers. The network packet is routed to a determined one of a plurality of processing nodes and processing threads based on the master network address for the one of the subscribers.

Abstract: A gas turbine engine includes a fan section, a compressor section, a combustion section, and a turbine section in serial flow arrangement, and defining an engine centerline extending between a forward direction and an aft direction. A disk includes a slot for mounting a composite airfoil to the disk. An axial retainer couples to the disk and secures the composite airfoil to the disk. A compliant portion positioned at the composite airfoil abuts the composite airfoil during operation of the gas turbine engine to secure the composite airfoil to the disk.

Abstract: A liquid fuel system for a turbine engine may include one or more sensors configured to generate sensor outputs corresponding to one or more phase properties of a fuel supplied to the turbine engine through a fuel pathway, and a controller configured to generate control commands configured to control one or more controllable components of the liquid fuel system based at least in part on the sensor outputs. The one or more sensors may include one or more phase detection sensors. The fuel may include hydrogen. The fuel may have a liquid phase state.

Abstract: A gas turbine engine is provided having a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (ADTExit) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine; wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) in degrees Celsius, a maximum drive turbine shaft torque (TOUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows: ( T OUT A DTExit ) 2 * EGT A HPCExit * 1 ? 0 - 1 ? 1 ; wherein CSP is greater than 0.0001194×EGT2?0.103×EGT+22.14 and less than 0.0003294×EGT2?0.306×EGT+77.

Abstract: An aircraft engine assembly includes a gas turbine engine having an intake channel configured to receive an incoming flow of air and thereby form an intake flow of air, the intake channel configured to turn the received incoming flow of air from an incoming flow direction to a first axial direction of the gas turbine engine, the incoming flow direction reverse of the first axial direction, and an electric machine coupled with the low pressure shaft and located at the aft end of the gas turbine engine proximate the intake channel, the electric machine in heat exchange communication with the intake flow of air such that the electric machine transfers heat to the incoming flow of air within the intake channel when the electric machine is operated.

Abstract: A turbine engine comprising a compressor section, combustor section, and turbine section in serial flow arrangement, and defining an engine longitudinal axis. The turbine engine includes an airfoil with an outer wall having a pressure side and a suction side, extending between a root and a tip in a span-wise direction, and extending between a leading edge and a trailing edge in a chord-wise direction. The airfoil includes a woven core, a first bonding layer including a toughened region, and a laminate skin provided exterior of the first bonding layer and bonded to the woven core by the first bonding layer.

Abstract: A gas turbine engine includes a fan section having a fan rotatable with a fan shaft, a turbomachinery section having a turbine and a turbomachine shaft rotatable with the turbine, a power gearbox mechanically coupled to the fan shaft and the turbomachine shaft such that the fan shaft is rotatable by the turbomachine shaft across the power gearbox, a grounded structure coupled to and supporting the power gearbox, and a torque monitoring system. The torque monitoring system includes a gearbox sensor. The gearbox sensor is coupled to the grounded structure and the torque monitoring system configured to determine a torque across the power gearbox using the gearbox sensor.

Abstract: A heat exchanger positioned within an annular duct of a gas turbine engine is provided. The heat exchanger extends substantially continuously along the circumferential direction and defining a heat exchanger height equal to at least 10% of a duct height. An effective transmission loss (ETL) for the heat exchanger positioned within the annular duct is between 5 decibels and 1 decibels for an operating condition of the gas turbine engine. The heat exchanger includes a heat transfer section defining an acoustic length (Li), and wherein an Operational Acoustic Reduction Ratio (OARR) is greater than or equal to 0.75 to achieve the ETL at the operating condition.

Abstract: A turbine engine having a disk, a composite airfoil assembly and a pitch snubber. The disk having a slot. The composite airfoil assembly having an airfoil portion and a dovetail portion. The dovetail portion having a radially inner surface spaced from the slot to define a gap therebetween. The pitch snubber being provided on one of the slot or the radially inner surface of the dovetail portion.

Abstract: An electric propulsor is provided. The electric propulsor includes a core cowl and an outer cowl. A first air flowpath is defined radially outward of the outer cowl and a second air flowpath is defined between the core cowl and the outer cowl. The electric propulsor also includes one or more electric machines, a fan rotatably drivable by at least one electric machine, and a booster having a plurality of airfoils disposed at least in part in the second air flowpath, the booster being rotatably drivable by at least one electric machine for compressing air flowing along the second air flowpath. The electric propulsor further includes a heat exchanger disposed within the second air flowpath downstream of the booster, the heat exchanger being in thermal communication with at least one of the one or more electric machines and/or a gearbox mechanically coupled with the fan.

Abstract: A gas turbine engine includes a compressor section, combustor section, and turbine section in serial flow arrangement, and defining an engine longitudinal axis. Sets of blades can be rotatably driven about the longitudinal axis in the compressor section and the turbine section, with adjacent vanes provided between sets of blades. The airfoil structure defining one or more of the blades or vanes can include a core structure which includes a woven or foam core, with an exterior woven layer.