Abstract: This application discloses an intent recognition optimization processing method, apparatus, device and storage medium, and relates to the field of internet technology. The implementation scheme of specific method includes: acquiring a first intent set and at least one original corpus; acquiring a first recognition result of each original corpus, where the first recognition result of any one of the original corpus includes a first intent corresponding to the original corpus recognized by the intent recognition model; acquiring a second recognition result of each original corpus, where the second recognition result of any one of the original corpus includes a second intent corresponding to the original corpus obtained through artificial recognition; and performing optimization processing on the first intent set to obtain a second intent set according to the first recognition result and the second recognition result of each original corpus.

Abstract: A gas turbine engine component includes a structural component having a surface, the structural component having an organic matrix composite material; and a cured thermal barrier layer on the surface, wherein the cured thermal barrier layer is a pre-ceramic layer including inorganic matrix containing silicon oxides reinforced with glass or quartz fibers.

Abstract: A steerable arm for use in endoscopic surgical procedures. The steerable arm cut from a tube of nitinol to provide flexibility and resilience by the structure into which the tube is cut. Typically, the cut tube comprises a spiralling coil, the loops of which are in contact on one lateral side of the tube and the tube is bent to open apart the loops on the other lateral side. The material which the tube is made of is capable of retaining memory of the bend. This provides a bias for restoring the tube to the bend whenever a force causing the tube to flex is removed.

Abstract: A gas turbine engine article includes a substrate that has a pre-bond surface that includes a serpentine groove. A coating is disposed on the pre-bond surface and mechanically interlocks with the serpentine groove.

Abstract: A gas turbine engine article includes a substrate that has a pre-bond surface that includes a serpentine groove. A coating is disposed on the pre-bond surface and mechanically interlocks with the serpentine groove.

Abstract: The present disclosure provides methods and systems for composite-to-metal hybrid bonded structures compromising the laser surface treatment on titanium alloys to promote adhesive bond performance. For example, a computer may be programmed to set a laser path corresponding to a predetermined geometric pattern. A laser may be coupled to the computer and apply a pulsed laser beam to a contact surface of the titanium alloy along the predefined geometric pattern. The laser may generate an open pore oxide layer on the contact surface of the substrate with a thickness of 100 and 500 nm. The open pore oxide layer may have a topography corresponding to the predefined geometric pattern. The topography may contain high degree of open pore structure and promote adhesive bond performance. Adhesive, primer or composite resin matrix may fully infiltrate into the open pore structures. Adhesive and composite laminate may co-cure to form composite-to-titanium hybrid bonded structures.

Abstract: The present disclosure provides methods and systems for composite-to-metal hybrid bonded structures compromising the laser surface treatment on titanium alloys to promote adhesive bond performance. For example, a computer may be programmed to set a laser path corresponding to a predetermined geometric pattern. A laser may be coupled to the computer and apply a pulsed laser beam to a contact surface of the titanium alloy along the predefined geometric pattern. The laser may generate an open pore oxide layer on the contact surface of the substrate with a thickness of 100 and 500 nm. The open pore oxide layer may have a topography corresponding to the predefined geometric pattern. The topography may contain high degree of open pore structure and promote adhesive bond performance. Adhesive, primer or composite resin matrix may fully infiltrate into the open pore structures. Adhesive and composite laminate may co-cure to form composite-to-titanium hybrid bonded structures.

Abstract: A method for treating a surface of a contoured titanium substrate used for adhesively bonded engine components. The method including applying energy from a fiber laser system to a contoured surface of a titanium substrate, the laser energy is distributed to the contoured titanium surface by at least one of direct light of sight, reflection, or scattering of one or more laser beam.

Abstract: The present disclosure provides methods and systems for composite-to-metal hybrid bonded structures compromising the laser surface treatment on titanium alloys to promote adhesive bond performance. For example, a computer may be programmed to set a laser path corresponding to a predetermined geometric pattern. A laser may be coupled to the computer and apply a pulsed laser beam to a contact surface of the titanium alloy along the predefined geometric pattern. The laser may generate an open pore oxide layer on the contact surface of the substrate with a thickness of 100 and 500 nm. The open pore oxide layer may have a topography corresponding to the predefined geometric pattern. The topography may contain high degree of open pore structure and promote adhesive bond performance. Adhesive, primer or composite resin matrix may fully infiltrate into the open pore structures. Adhesive and composite laminate may co-cure to form composite-to-titanium hybrid bonded structures.

Abstract: Methods and systems for the laser surface treatment on stainless steel alloys and nickel alloys may include a computer may be programmed to set a laser path corresponding to a predetermined geometric pattern. A laser may be coupled to the computer and apply a pulsed laser beam to a contact surface of the substrate along the predefined geometric pattern. The pulsed laser beam may have a laser power between 0.1 W and 100 W, single pulse fluence 1 mJ/mm2 and 1025 mJ/mm2 and a laser speed between 25.4 cm/s and 127 cm/s. The laser may generate an open pore oxide layer on the contact surface of the substrate with a thickness of 0.1-1 ?m, an open pore distance of 0.05-1 ?m. The open pore oxide layer may have a topography corresponding to the predefined geometric pattern. The topography may contain open pore structures and promote adhesive bond performance.

Abstract: A method for treating a surface of a contoured titanium substrate used for adhesively bonded engine components. The method including applying energy from a fiber laser system to a contoured surface of a titanium substrate, the laser energy is distributed to the contoured titanium surface by at least one of direct light of sight, reflection, or scattering of one or more laser beam.

Abstract: A gas turbine engine composite article having a composite article airfoil extending outwardly to an article root to an article airfoil tip. Within the article airfoil is a core including a core airfoil attached to a core root including a core dovetail. A continuous outer three-dimensional braided layer including braided composite material tows are braided on the core and the braided layer covers the entire core airfoil and the core root. The core may be an inflatable mandrel or a composite core made of a composite material. The core may include stiffeners such as an I beam or hollow rectangular cross-section box beams. A method for making such an article includes braiding a continuous outer three-dimensional braided layer including braided composite material tows on the core including covering the entire core airfoil and the core root with the continuous outer three-dimensional braided layer.

Abstract: A confinement article for containing a fluid includes a wall and a nano-aligned barrier. The wall is constructed and arranged to contain the fluid. The nano-aligned barrier co-extends with the wall, and is constructed and arranged to restrict permeation of the fluid.

Abstract: A UV-IR combination curing system and method for manufacture and repair of composite parts, such as for use in wind blade manufacture and repair. The system and method utilize UV and IR dual radiation sources to cure glass fiber reinforced laminates containing a photo initiator. The UV and IR dual radiation sources can be configured as discrete stand-alone UV and IR lamps used in a side by side configuration, a plurality of UV lamps with thermal IR radiation, a combined UV/IR lamp, or other forms of light sources providing both UV and IR radiation. To achieve high glass transition and complete curing of thick laminates, the IR radiation source is initially turned on to heat the laminate to close to 40° C.-100° C. before the UV radiation source is turned on. The IR radiation source can be turned off after UV radiation source is activated.

Abstract: A slot liner for a rotor assembly in one embodiment includes a metallic support member and a coating. The coating is disposed on at least one side of the metallic support member, and includes a mixture of a filler and a polyimide resin. The filler is a high thermal conductivity electrical insulating (HTCEI) filler, and includes particles of at least one of boron nitride, aluminum nitride, or a diamond material.

Abstract: A slot liner for a stator assembly in one embodiment includes a mesh structural member and a coating. The coating is disposed on at least one side of the mesh structural member, and includes a mixture of a filler and a polyimide resin. The filler is a high thermal conductivity electrical insulating (HTCEI) filler, and includes particles of at least one of boron nitride, aluminum nitride, or a diamond material.

Abstract: A gas barrier fabric is disclosed. The barrier fabric includes a fabric substrate. A heat-resistant coating layer disposed over a first side of the fabric substrate. A first gas barrier layer (also referred to herein as simply as a barrier layer) including a polymer is disposed over a second side of the fabric substrate. A second gas barrier layer is disposed over the first air barrier coating layer of the fabric substrate. The second barrier layer has a thickness of 5 nm to 1000 nm and includes aligned nanoplatelets.

Abstract: An electric machine includes a housing, a stator core positioned within the housing, a wire wound about the stator core to form a plurality of end-turns that extend from an end of the stator core, and a thermal conductor positioned between the plurality of end-turns and the housing. The thermal conductor includes a substrate and a thermally conductive coating formed on a surface of the substrate. The thermally conductive coating includes a thermally conductive, dielectric material configured to transfer heat from the plurality of end-turns to the substrate.

Abstract: A slot liner for a stator and/or a rotor of an electric machine includes a body configured to be received within a stator slot and/or within a rotor slot. The body extends from a first end to an opposite second end and from a first edge to an opposite second edge. The body includes an inner segment and first and second outer segments that extend along the body. The first and second outer segments flank the inner segment such that the inner segment extends between the first and second outer segments along the body. The inner segment includes at least one different material such that a thermal conductivity of the inner segment is greater than a thermal conductivity of the first and second outer segments.

Abstract: A gas turbine engine composite article having a composite article airfoil extending outwardly to an article root to an article airfoil tip. Within the article airfoil is a core including a core airfoil attached to a core root including a core dovetail. A continuous outer three-dimensional braided layer including braided composite material tows are braided on the core and the braided layer covers the entire core airfoil and the core root. The core may be an inflatable mandrel or a composite core made of a composite material. The core may include stiffeners such as an I beam or hollow rectangular cross-section box beams. A method for making such an article includes braiding a continuous outer three-dimensional braided layer including braided composite material tows on the core including covering the entire core airfoil and the core root with the continuous outer three-dimensional braided layer.