Abstract: A control method for a water diversion device, a water diversion device and a dishwasher. The control method for a water diversion device includes: acquiring a target state position to be reached by a water diversion piece; acquiring the current state position of the water diversion piece; controlling a driving component to operate, and counting the number of signals actually received; on the basis of the target state position, the current state position and the number of signals actually received, determining whether the water diversion piece has reached the target state position; and when the water diversion piece has reached the target state position, controlling the driving component to stop rotating.

Abstract: The present disclosure generally provides uses of certain mixed hydroxy- and methoxy-substituted flavones (HMFs) to reduce bitterness, astringency, or sourness, or to enhance sweetness of a ingestible composition, such as a flavored food or beverage product. In some embodiments, the disclosure provides uses of the HMFs disclosed herein to reduce the unpleasant taste of limonin, nomelin, or naringin, which can be present at elevated levels in certain citrus products.

Abstract: Techniques are described with respect to a system, method, and computer product for visualizing viewpoints. An associated method includes receiving access to a multi-party discussion occurring via a telecommunication system and analyzing the multi-party discussion using natural language processing. The method further includes extracting a plurality of viewpoints of the multi-party discussion based on the analysis, synthesizing a subset of the plurality of viewpoints based on the content of each viewpoint of the plurality of viewpoints, and transmitting a rendered synthesized visualization of the subset.

Abstract: The present disclosure generally provides uses of certain mixed hydroxy- and methoxy-substituted flavanones (HMFs) to reduce bitterness, astringency, or sourness, or to enhance sweetness of a ingestible composition, such as a flavored food or beverage product. In some embodiments, the disclosure provides uses of the HMFs disclosed herein to reduce the unpleasant taste of limonin, nomelin, or naringin, which can be present at elevated levels in certain citrus products.

Abstract: A system that can be used for suturing implants includes a first automated fixture that can comprise an articulation arm and a target device holder and a second automated fixture configured to operate as a sewing machine to sew material onto the implant. The second automated fixture uses a curved needle to form a stitch without having to release the needle in the process. The second automated fixture can also include a stitch looper that moves in coordination with the curved needle to perform a single-suture or single-thread stitch.

Abstract: A computer-based method for managing a dataflow pipeline across a plurality of environments, includes the steps of: receiving, for a first environment, a check-in comprising source code, a task definition, a configuration, and a flow definition; receiving a definition of an application secret and an associated credential; storing the application secret and credential in a dataflow pipeline deployer data store; creating a data flow pipeline package, further comprising the steps of: merging the source code, the configuration, and the secrets; and defining a pipeline graph in the first environment pipeline flow registry.

Abstract: An intelligent moving basketball shooting frame includes a slide track and a backboard with a basket, a groove is provided on the slide track; a PCBA board is provided in an interior of the backboard; a rear face of the backboard is provided with a bracket which is in matching projection-and-recess engagement with the groove, and a power wheel is driven by the PCBA board; when the backboard is hung on the slide track through the bracket, the power wheel is in contact with a surface of the slide track, and drives the backboard to move back and forth along the slide track. The intelligent moving basketball shooting frame is simple in structure, light in weight, convenient to carry, easy to assemble/disassemble, and the installation position is not restricted by venues; at the same time, the basket is movable and is more entertaining.

Abstract: Gas turbine engines generally comprise a first-stage nozzle guide vane. Temperatures in a trailing-edge area of the suction-side wall of such vanes can exceed material and coating limits. While an insert can be used to form passages for cooling air to flow along the inner surfaces of the vane walls, design constraints prevent the insert from extending beyond a certain point into the trailing edge of the vane. Accordingly, a fin is disclosed for insertion downstream of the insert. By eliminating sudden expansion beyond the downstream end of the insert and maintaining the speed of the cooling air across the trailing-edge area of the suction-side wall, the fin improves the cooling coefficient for the trailing-edge area, so as to prevent or reduce excessive temperatures in the trailing-edge area.

Abstract: Gas turbine engines generally comprise a first-stage nozzle guide vane. Temperatures in a trailing-edge area of the suction-side wall of such vanes can exceed material and coating limits. While an insert can be used to form passages for cooling air to flow along the inner surfaces of the vane walls, design constraints prevent the insert from extending beyond a certain point into the trailing edge of the vane. Accordingly, a fin is disclosed for insertion downstream of the insert. By eliminating sudden expansion beyond the downstream end of the insert and maintaining the speed of the cooling air across the trailing-edge area of the suction-side wall, the fin improves the cooling coefficient for the trailing-edge area, so as to prevent or reduce excessive temperatures in the trailing-edge area.

Abstract: An airfoil for a turbomachine such as a gas turbine engine includes a pressure side and a suction side, a flow-distributing forward wall and an inner cooling wall. A switchbacked passage extends through the airfoil, and the flow-distributing forward wall has a plurality of jetting orifices formed therein and connecting the switchbacked passage to a forward cavity. The jetting orifices are oriented to produce wall jets of cooling fluid directed in an upstream direction toward a back side of the leading edge. A second passage extends between the forward cavity and outlets of the airfoil, so as to convey cooling fluid in a downstream direction toward the outlets.

Abstract: An airfoil for a turbomachine such as a gas turbine engine includes a switchbacked passage for conveying cooling fluid, and flow-distribution passages in a forward wall so as to direct cooling fluid from the internal passage for back side impingement upon a leading edge of the airfoil. An inner cooling wall forms a passage for discharging the spent cooling air from a trailing edge of the airfoil after impingement, and cools one of a pressure side and a suction side of the airfoil by way of conduction. The switchbacked passage may have a serpentine form.

Abstract: A turbine blade for a gas turbine engine may include an outer, peripheral wall extending along a suction side and a pressure side of the blade from a leading edge to a trailing edge of the blade and from a root end to a tip end of the blade, a substantially vertical bifurcating internal wall extending between the leading edge and the trailing edge of the blade in between the suction side and the pressure side of the blade, a plurality of pressure side cooling fluid passages defined between the peripheral wall on the pressure side of the blade and the bifurcating internal wall and extending at least part way from the root end to the tip end of the blade, and a plurality of suction side cooling fluid passages defined between the peripheral wall on the suction side of the blade and the bifurcating internal wall and extending at least part way from the tip end to the root end of the blade.

Abstract: A turbine blade for a gas turbine engine may include at least two wrapped, serpentine-shaped internal cooling paths. A first one of the serpentine-shaped internal cooling paths may include a first passage that extends radially along a leading edge of the turbine blade from adjacent a root end of the turbine blade to adjacent a tip end of the turbine blade. The first passage may be configured to provide fresh cooling fluid to the leading edge. A second passage downstream of the first passage may be configured to discharge spent cooling fluid from the first passage of the first one of the serpentine-shaped internal cooling paths across a plurality of flow disrupters positioned along an upper span of a trailing edge of the turbine blade before exiting from the trailing edge of the turbine blade. A second one of the serpentine-shaped internal cooling paths may be configured to supply fresh cooling fluid to a lower span of the trailing edge of the turbine blade.

Abstract: Inclusion complexes are provided containing a targeted carrier non-covalently associated with an active agent. The targeted carrier includes an inclusion host that binds the active agent or a binding partner attached to the active agent. The targeted carrier includes a targeting moiety attached to the inclusion host or to a polymer or linker attached thereto. Pharmaceutical formulations of the inclusion complexes are provided. Methods of making the inclusion complexes and formulations thereof are provided. Methods of using the inclusion complexes and formulations are provided. In some embodiments the inclusion complex includes a progesterone or estrogen targeting moiety that targets the inclusion complex to cancer cells. The targeting can cause internalization of the active agent in the target cells. In some embodiments the active agent is an anthracycline such as doxorubicin and the target cells are cancer cells.

Abstract: A turbine blade for a gas turbine engine may include an outer, peripheral wall extending along a suction side and a pressure side of the blade from a leading edge to a trailing edge of the blade and from a root end to a tip end of the blade, a substantially vertical bifurcating internal wall extending between the leading edge and the trailing edge of the blade in between the suction side and the pressure side of the blade, a plurality of pressure side cooling fluid passages defined between the peripheral wall on the pressure side of the blade and the bifurcating internal wall and extending at least part way from the root end to the tip end of the blade, and a plurality of suction side cooling fluid passages defined between the peripheral wall on the suction side of the blade and the bifurcating internal wall and extending at least part way from the tip end to the root end of the blade.

Abstract: A turbine blade for a gas turbine engine may include at least two wrapped, serpentine-shaped internal cooling paths. A first one of the serpentine-shaped internal cooling paths may include a first passage that extends radially along a leading edge of the turbine blade from adjacent a root end of the turbine blade to adjacent a tip end of the turbine blade. The first passage may be configured to provide fresh cooling fluid to the leading edge. A second passage downstream of the first passage may be configured to discharge spent cooling fluid from the first passage of the first one of the serpentine-shaped internal cooling paths across a plurality of flow disrupters positioned along an upper span of a trailing edge of the turbine blade before exiting from the trailing edge of the turbine blade. A second one of the serpentine-shaped internal cooling paths may be configured to supply fresh cooling fluid to a lower span of the trailing edge of the turbine blade.

Abstract: An airfoil for a turbomachine such as a gas turbine engine includes a pressure side and a suction side, a flow-distributing forward wall and an inner cooling wall. A switchbacked passage extends through the airfoil, and the flow-distributing forward wall has a plurality of jetting orifices formed therein and connecting the switchbacked passage to a forward cavity. The jetting orifices are oriented to produce wall jets of cooling fluid directed in an upstream direction toward a back side of the leading edge. A second passage extends between the forward cavity and outlets of the airfoil, so as to convey cooling fluid in a downstream direction toward the outlets.

Abstract: An airfoil for a turbomachine such as a gas turbine engine includes a switchbacked passage for conveying cooling fluid, and flow-distribution passages in a forward wall so as to direct cooling fluid from the internal passage for back side impingement upon a leading edge of the airfoil. An inner cooling wall forms a passage for discharging the spent cooling air from a trailing edge of the airfoil after impingement, and cools one of a pressure side and a suction side of the airfoil by way of conduction. The switchbacked passage may have a serpentine form.

Abstract: A nozzle segment for a nozzle ring of a gas turbine engine is disclosed. The nozzle segment includes an upper endwall, a lower endwall, and an airfoil extending between the upper endwall and the lower endwall. The airfoil includes a pressure side wall, a plurality of inner cooling apertures, and a plurality of outer cooling apertures. The plurality of inner cooling apertures extends through a pressure side wall and is arranged in a first row adjacent the lower endwall. The plurality of outer cooling apertures extends through the pressure side wall and is arranged in a second row adjacent the upper endwall.

Abstract: A turbine blade for a gas turbine engine. The turbine blade includes a base having a blade root, a platform, a cooling air inlet, and a base air passageway. The turbine blade also includes an airfoil section adjoined to the base and having an outer wall, an airfoil air passageway, a plurality of trailing edge slots in fluid communication with the airfoil air passageway and a plurality of directional film holes through the outer wall in fluid communication with the airfoil air passageway. The plurality of directional film holes includes a first portion configured to discharge the cooling air toward a tip end, and a second portion configured to discharge the cooling air toward the platform.