Abstract: A turbine engine including a fan section, a compressor section, a combustion section, a turbine section, and an airfoil assembly. The airfoil assembly comprising a spar, a trunnion and a stress relief. The trunnion having an upper edge with an open top, and a socket extending from the open top. The spar extending through the open top and into the socket. A junction being formed between the spar and a portion of the upper edge defining the open top.

Abstract: A composite airfoil assembly for a turbine engine. The composite airfoil assembly includes a woven core having a core exterior. The woven core includes a first region, a second region, and a transition region. A skin is applied to at least a portion of the woven core at the core exterior.

Abstract: A cooking appliance includes a cooking cavity having first and second sidewalls that are spaced-apart from one another. A housing includes first and second sidewalls that are spaced-apart from one another and an upper wall. The first and second sidewalls of the housing are spaced-apart from the first and second sidewalls of the cooking cavity to define first and second side channels therebetween, respectively. A duct assembly includes first and second sidewalls spaced-apart from one another and an upper wall. The duct assembly is positioned on the upper wall of the housing and includes an interior cavity having a front opening and a rear opening. A blower assembly includes an inlet operably coupled to the rear opening of the duct assembly and is fluidically coupled to the first and second channels. The blower assembly includes an upwardly opening rear outlet having a plurality of baffles and deflectors positioned therein.

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: Aspects of subject technology provide systems and methods for generation and distribution of a stable identifier associated with multiple aliases of a user account. The stable identifier may be provided to various electronic devices by a server, responsive to requests associated with communications to those devices from one of the associated aliases. In this way, messaging applications can utilize the stable identifier to merge conversations from a single user having multiple aliases, and secure access to a secure device can be provided to an authorized user, even if the authorized user attempts access from an unauthorized account alias.

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: 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 component for a gas turbine engine. The component includes a continuous fiber blade including an airfoil extending radially between a root and a tip and a blade attachment feature positioned at or adjacent to the root. The component further includes a platform coupled to the root of the continuous fiber blade. The platform includes a plurality of chopped fibers. Additionally, the component includes a thermoplastic polymer contained in both the continuous fiber blade and the platform. Moreover, the continuous fiber blade and platform are coupled together such that the continuous fiber blade and platform form a monolithic composite body.

Abstract: Assemblies of stacked layers of materials are described. The assemblies include functional and structural layers. Functional layers include binderless ceramic materials on woven or non-woven substrates of natural, synthetic, or metallic materials. The layers of functional and structural materials may be configured to transport moisture or heat from an inner surface to an outer surface that is exposed to an ambient environment.

Abstract: A fan assembly for an engine has a fan blade, a disk having a disk segment, a trunnion mechanism having a trunnion extending at least partially through the disk segment, and first and second attachment systems. The trunnion has a platform and a shaft. The fan blade is adjacent to the platform of the trunnion. The trunnion is attached to the disk segment using the first attachment system along a preload path. The first and second attachment systems further include first and second retention features, respectively, separate from the preload path. During normal operation of the fan assembly, the first attachment system retains the trunnion within the disk along a first load path. Upon a failure in the trunnion, the first and second retention features together retain the trunnion within the disk segment along a second load path, the first load path being different than the second load path.

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 composite blade assembly for a turbine engine. The composite blade assembly having a core, a first skin and a second skin. The core having a composite structure. The first skin having at least one composite ply. The second skin having at least one composite ply. The first skin having a first radius. The second skin having a second radius.

Abstract: A turbine engine comprising a fan section, a compressor section, a combustion section, and a turbine section in serial flow arrangement and defining a stator portion and a rotor portion, which rotates about an engine centerline. The rotor portion comprising a variable pitch airfoil assembly. The variable pitch airfoil assembly having an airfoil and a balancing insert.

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: 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.

Abstract: An airfoil assembly for a turbine engine, the airfoil assembly including a platform defining an inner surface and an outer surface, a variable pitch airfoil extending radially from the outer surface of the platform from a root to a tip to define a span length and a mounting structure connected to the platform.

Abstract: A turbine engine including a fan section, a compressor section, a combustion section, and a turbine section in serial flow arrangement. The turbine engine further including a composite airfoil assembly. The composite airfoil assembly having an outer wall, a composite body at least partially defining the outer wall, and a tip cap at least partially defining the outer wall.