Abstract: A turbine engine includes a fan and a turbomachine defining an engine centerline. The turbomachine includes a compressor section, a combustion section, and a turbine section in serial flow order. The turbine engine also includes a set of composite airfoils circumferentially arranged about the engine centerline. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.

Abstract: A turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. The turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.

Abstract: A turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. The turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.

Abstract: A system and method for converting a common hydrogen-based input fluid into an output fluid comprising an overabundance of hydrogen H1 atoms is disclosed. This conversion occurs in the absence of elevated temperatures or pressures, so that the resulting output fluid is suitable for shipping or storage at Standard Temperature and Pressure (STP). A vaporizer system and method for transforming the output fluid into H2 gas is also disclosed.

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 system and method for converting a common hydrogen-based input fluid into an output fluid comprising an overabundance of hydrogen H1 atoms is disclosed. This conversion occurs in the absence of elevated temperatures or pressures, so that the resulting output fluid is suitable for shipping or storage at Standard Temperature and Pressure (STP). A vaporizer system and method for transforming the output fluid into H2 gas is also disclosed.

Abstract: Aspects of this technical solution can determine, based on power applied to a vehicle from a source of power and power consumed by the vehicle, an emission metric corresponding to the vehicle, and send a request to a second system, the request to link with an asset based on the emission metric.

Abstract: A composite airfoil with an airfoil core and a wall surrounding the airfoil core. The wall including a first set of stacked plies including a first type of ply having directional fibers extending in a first direction, and defining at least a portion of an exterior surface, the exterior surface extending between a leading edge and a trailing edge to define a chordwise direction and between a root and a tip to define a spanwise direction. At least one stiffener located between the airfoil core and the wall, the at least one stiffener having a second set of stacked plies.

Abstract: A turbine engine includes a fan and a turbomachine defining an engine centerline. The turbomachine includes a compressor section, a combustion section, and a turbine section in serial flow order. The turbine engine also includes a set of composite airfoils circumferentially arranged about the engine centerline. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.

Abstract: An airfoil for a turbofan engine includes a first contoured sidewall, a second contoured sidewall, a leading edge, and a trailing edge with each extending in a spanwise direction defined between a root and a tip portion of the airfoil. The first contoured sidewall and the second contoured sidewall define an outer surface of the airfoil. The airfoil further includes a plurality of protrusions where each protrusion of the plurality of protrusions has a curvilinear shape and extends outwardly from the outer surface along at least one of the first contoured sidewall or the second contoured sidewall. The plurality of protrusions is defined downstream from a mid-point of a chord length of the airfoil and terminates upstream of the trailing edge.

Abstract: A turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. The turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.

Abstract: A turbine engine includes a fan and a turbomachine defining an engine centerline. The turbomachine includes a compressor section, a combustion section, and a turbine section in serial flow order. The turbine engine also includes a set of composite airfoils circumferentially arranged about the engine centerline. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion. The leading edge protector includes at least one projection extended past a base of the airfoil to a root of the airfoil.

Abstract: An airfoil assembly having a trunnion and a spar. The trunnion having an interior surface defining a flared socket with an open top. The spar extending from the flared socket and through the open top.

Abstract: The disclosure relates to a roller crusher having two generally parallel rollers arranged to rotate in opposite directions, towards each other, and separated by a gap, each roller having two ends, the roller crusher comprising: a flange attached to at least one of the ends of one of the rollers, the flange extending in a radial direction of the roller, the flange having a height above an outer surface of the roller, wherein the roller crusher further comprises at least one scraper arranged at an end of the roller with a flange for at least partially removing material accumulated on the flange and/or on the outer surface at the end of the roller. According to the invention, the at least one scraper comprises a scraping element having a scraping surface which scraping surface comprises a polycrystalline diamond (PCD).

Abstract: A composite blade assembly for a turbine engine, the composite blade assembly having a core and a laminate skin. The core having a composite structure. The laminate skin having at least one composite ply. The laminate skin having a first portion forming a first angle relative to a horizontal plane, and a second portion forming a second angle relative to the horizontal plane.

Abstract: A gas turbine engine is provided. The gas turbine engine includes: a turbomachine; a fan including a plurality of fan blades rotatably driven by the turbomachine; a nacelle surrounding at least in part the plurality of fan blades of the fan; and a clearance control system including a control ring positioned at least partially within the nacelle, coupled to the nacelle, or both for control of a clearance gap between the plurality of fan blades and the nacelle.

Abstract: A rotor assembly is provided, along with gas turbine engines for its use. The rotor assembly may include a spool defining a plurality of apertures arranged in a first row and spaced circumferentially around the spool, wherein each aperture of the plurality of apertures extends through the spool from a radially inward-facing surface to a radially outward-facing surface; and a blade assembly comprising at least two blades connected to each other via a platform, wherein each blade extends through a respective aperture.

Abstract: Composite airfoils and methods for forming composite airfoils are provided. For example, a composite airfoil of a gas turbine engine comprises opposite pressure and suction sides extending radially along a span from a root to a tip, which define opposite radial extremities of the airfoil. The composite airfoil further comprises a body section and a tip section, which includes the tip, that each extend radially along the span. The composite airfoil is formed from a composite material comprising fibers disposed in a matrix material. The tip section has a tip fiber volume, and the body section has a body fiber volume that is greater than the tip fiber volume. Another composite airfoil comprises a tip cap applied over the tip that tapers from a first end to a second end such that each of the pressure and suction side walls of the tip cap narrows from a first thickness to a second thickness.

Abstract: Methods, apparatus, systems and articles of manufacture corresponding to a fan blade with intrinsic damping characteristics are disclosed. An example fan blade comprises an exterior body including a first side and a second side; a first hairpin structure in contact with (a) the first side of the exterior body and (b) the second side of the exterior body; and a second hairpin structure in contact with (a) the first side and (b) the second side, wherein the first hairpin structure corresponds to a first stiffness and the second hairpin structure corresponds to a second stiffness different than the first stiffness.

Abstract: Systems and methods for generating personalized and structured content using a collaborative generator provide a user interface to a user computing system and receive a prompt from the user computing system via the user interface. The systems and methods provide the prompt to a generative model, with the generative model being a machine-learned model trained to process language input prompts to generate a language output. The systems and methods receive a generative output generated by the generative model in response to the prompt. Additionally, the systems and methods generate a modified output by modifying the generative output based at least in part on historical user data for a user associated with the prompt, and then provide the modified output via the user interface.