Abstract: Disclosed herein is a method of trapping arthropods by providing a substantially planar, flexible insert having a LED-facing surface having an adhesive for trapping the arthropods disposed thereon. Then, bending the insert into a curved configuration and inserting the insert into an arthropod trapping device. The device includes a housing having a base and a curved shade. The curved shade is configured to receive the insert and comprises a LED-facing surface. A first LED having a peak wavelength of from about 400 nm to about 500 nm is mounted on the base and is configured to emit light in a direction substantially perpendicular to the LED-facing surface of the shade. A second LED having a peak wavelength of from about 350 nm to about 400 nm is mounted on the base and is configured to emit light in a direction substantially parallel to the LED-facing surface of the shade.

Abstract: In one embodiment, a computer-implemented method comprises using a script automation processor that is hosted using a virtual compute instance and a virtual storage instance associated with one or more second non-transitory computer-readable storage media storing one or more second sequences of instructions defining an API implementation of the API, a graph server, and one or more programming language runtime interpreters, receiving a user pipeline automation script comprising one or more first sequences of instructions specifying one or more API calls to an application programming interface (API), and a user application; using the script automation processor, creating and storing one or more programmatic containers in memory of the script automation processor, the containers corresponding to functions that user pipeline automation script and user application invoke; using the script automation processor, creating and storing a directed acyclic graph (DAG) in the memory of the script processor, the DAG compri

Abstract: Methods, systems, and devices for circuitry borrowing in memory arrays are described. In one example, a host device may transmit an access command associated with data for a first memory section to a memory device. The first memory section may be located between a second memory section and a third memory section. A first set of circuitry shared by the first memory section and the second memory section may be operated using drivers associated with the first memory section and drivers associated with the second memory section. A second set of circuitry shared by the first memory section and the third memory section may be operated using drivers associated with the first memory section and drivers associated with the third memory section. An access operation may be performed based on operating the first set of circuitry and the second set of circuitry.

Abstract: Pituitary tumors may be reduced in size by administration of relacorilant. Pituitary tumors include, without limitation, non-secreting tumors, hormone-secreting tumors, adenomas, and carcinomas. Relacorilant administration may be effective to reduce hormone secretion from a hormone-secreting pituitary tumor, e.g., to reduce adrenocorticotrophic hormone (ACTH) secretion. A pituitary tumor may be imaged before and/or after relacorilant administration. Relacorilant may be administered independent of surgery, and before, during, or after surgery to treat a pituitary tumor. Relacorilant may aid or improve surgical outcomes, and may reduce the size or growth of pituitary tumor tissue before surgery, and any tumor tissue remaining following surgical treatment. Relacorilant may be orally administered for the treatment of pituitary tumors. Relacorilant may be orally administered to a fasted patient, or to a fed patient.

Abstract: An engine protection cover device for airtight sealing an engine of an aircraft or spacecraft includes an air intake cover being inflatable to correspond to the internal dimension of the air intake for airtight sealing the same, wherein the air intake cover includes an airtight sealable access opening for attaching or passing through an air dryer for drying the air inside the engine. An aircraft or spacecraft is disclosed with such an engine protection cover device.

Abstract: Methods of depositing silicon-containing layers in the formation of semiconductor devices are described. The methods include a thermal chemical vapor deposition (CVD) process or a thermal atomic layer deposition (ALD) process without the use of plasma. Some methods include exposing a semiconductor substrate to a silicon-containing precursor, an oxygen-containing reactant, and an initiator compound to deposit a silicon oxide layer. Some methods include exposing a semiconductor substrate to a silicon-containing precursor, a nitrogen-containing reactant, and an initiator compound to deposit a silicon nitride layer. Some methods include exposing a semiconductor substrate to a silicon-containing precursor, an oxygen-containing reactant, a nitrogen-containing reactant, and an initiator compound to deposit a silicon oxynitride layer.

Abstract: A method for the production of a zigzag-shaped protection element formed from multiple individual profiles includes the following steps: providing the individual profiles, welding the individual profiles to form a zigzag-shaped preform of the protection element such as to form at least one weld seam, wherein the individual profiles are welded to each another at an angle of 30° to 120°, inserting the preform into a hot molding tool, molding the preform into the zigzag-shaped protection element in the hot molding tool, and mold hardening of the zigzag-shaped protection element in the hot molding tool.

Abstract: A liquid pharmaceutical formulation comprising a CNP compound, a buffering agent, an isotonicity agent, a preservative and optionally an antioxidant and methods for making and using such formulation.

Abstract: The present invention relates to novel silanes, curable compositions containing the silanes and a curable polyorganosiloxane endcapped with such silanes, wherein said silanes having the formula Si(R1)m(R2)4-m, in which each R1 independently stands for a substituted or unsubstituted alkyl, alkenyl, or alkynyl group; a substituted or unsubstituted cycloaliphatic group or aryl group; a substituted or unsubstituted heteroalicyclic group or heteroaryl group; each R2 independently stands for a group of the general formula —O—CHR3—C(?O)—O—R4, wherein R3 independently stands for: a substituted or unsubstituted alkenyl group; R4 stands for: a substituted or unsubstituted alkyl, alkenyl, alkynyl, cycloalkyl, aryl, heterocyclyl or heteroaryl group; and m independently stands for 0 or 1.

Abstract: A dispensing device that intermittently dispenses a cooling medium onto a cast strand in a continuous casting installation. The dispensing device has a housing with at least one inlet opening for letting the cooling medium into the housing and a dispensing opening for dispensing the cooling medium out of the housing. A switching valve is arranged in the housing and is designed to open and close the dispensing opening. The switching valve has a sleeve, which is filled with a working fluid and which, on the dispensing opening side, is closed with a closure in a fluid-tight manner. The closure has a switching element, which, by controlling the pressure in the working fluid, is displaceable relative to the sleeve into a closing position in which the switching element closes the dispensing opening.

Abstract: A gas turbine engine for an aircraft includes an engine core including a turbine, a combustor, a compressor, and a core shaft connecting the turbine to the compressor. The engine includes a fan located upstream of the engine core and arranged to be driven by the core shaft. The engine includes a nacelle surrounding the fan and the engine core and defining a bypass duct located radially outside of the engine core, where the bypass ratio, defined as the ratio of the mass flow rate of the flow through the bypass duct to the mass flow rate of the flow through the core at cruise conditions, is at least 4. The engine includes a plurality of actuators and a fuel supply system arranged to supply fuel to fueldraulically drive at least one actuator of the plurality of actuators. The engine includes two fuel-oil heat exchangers.

Abstract: The invention relates to an apparatus and a method for investigating chemical processes in plate-like reaction cells which can be fixed flexibly and independently in the apparatus. an investigation of stacks of plate-like reaction cells also being possible. The plate-like reaction cells are positioned with an outer plate surface in a receiving unit and are then pressed against one another by one or more piston tensioners, the pistons of the piston tensioners acting on the outer plate surface of the plate-like reaction cells, more specifically in each case on the plate surface that is opposite the receiving unit, and sealing the reaction cells tightly and detachably by the action of the pressing force.

Abstract: A gas turbine engine for an aircraft, comprising: a combustor; a fuel-oil heat exchanger arranged to receive fuel from a fuel tank onboard the aircraft and transfer heat from the oil to the fuel; a fuel return line arranged to return at least some fuel that has passed through the heat exchanger to the fuel tank; and a modulator valve arranged to modulate the flow of fuel along the fuel return line, wherein the modulator valve is arranged to initiate return of fuel to the fuel tank when fuel having passed through the heat exchanger is at a temperature of at least 120° C. A method of operating a gas turbine engine is also disclosed.

Abstract: A gas turbine engine for an aircraft includes an engine core with a turbine, a combustor, a compressor, and a core shaft connecting the turbine to the compressor. The engine includes a fan upstream of the engine core driven by the core shaft. The engine includes a nacelle surrounding the fan and engine core and defining a bypass duct located radially outside of the engine core, where the bypass ratio of the mass flow rate through the bypass duct to the mass flow rate through the core at cruise conditions, is at least 4. The engine includes an engine heat management system and an actuator configured to actuate at least one valve within that system. The engine includes a fuel supply system to supply fuel to fueldraulically drive the actuator. The actuator is configured to actuate said valve to enable non-binary position adjustment between an open and closed valve positions.

Abstract: The invention relates to a multi-component system for producing a dental impression material, comprising in two or more separate components: i) one or more crosslinkable (co)polymers, ii) one or more components of a crosslinker system for crosslinking the crosslinkable (co)polymers, and iii) one or more fillers, wherein the multi-component system comprises at least one platelet-shaped filler, wherein the platelet-shaped filler has a first form factor F1=Dortho/Dmax in the range of 0.3 to 1.0 and a second form factor F2=Dmax/H of 3 or more, wherein Dmax is the maximum platelet diameter in the platelet plane, wherein Dortho is the largest platelet diameter orthogonal to Dmax in the platelet plane, and wherein H is the average platelet thickness orthogonal to the platelet plane.

Abstract: A method of operating a gas turbine engine includes an engine core with a turbine, compressor, fuel combustor, and core shaft; a fan upstream of the engine core; a gearbox that receives an input from the core shaft and outputs drive to the fan; an oil loop system supplying oil to the gearbox; and a heat exchange system including: air-oil and fuel-oil heat exchangers, and wherein the oil loop system branches such that part of the oil flows along each branch and the air-oil and fuel-oil heat exchangers are parallel on different branches; and a modulation valve allows the oil sent via each branch to be varied, the method including controlling the heat exchange system wherein, under cruise conditions, a heat transfer ratio of: rate ? of ? heat ? transfer ? from ? oil ? to ? air rate ? of ? heat ? transfer ? from ? oil ? to ? fuel is in the range from 0 to 0.67.

Abstract: A gas turbine engine for an aircraft, comprising: a combustor; a fuel-oil heat exchanger arranged to receive fuel and transfer heat from the oil to the fuel so as to raise the fuel temperature to at least 120° C. on entry to the combustor; a fuel recirculation line arranged to recirculate at least some fuel on a fuel flow path from a first point on the fuel flow path to a second point on the fuel flow path, the second point upstream of the first point; and a modulator valve arranged to modulate the flow of fuel along the fuel recirculation line. A method of operating a gas turbine engine is also disclosed.

Abstract: A method of operating an aircraft gas turbine engine including: a core including a turbine, a compressor, a combustor, and a core shaft connecting the turbine to the compressor; a fan upstream of the core; a fan shaft; at least one bearing supporting the fan shaft; at least one auxiliary system using some of the fuel; an oil loop system to supply oil to the bearing; and a heat exchange system including: a primary fuel-oil heat exchanger through which oil in the oil loop system and substantially all the fuel flow to transfer heat between the oil and the fuel; and a secondary fuel-oil heat exchanger through which oil in the oil loop system and a portion of the fuel flow, to transfer heat between the oil and the fuel; and a fuel pump; wherein, under cruise conditions, fuel temperature on leaving the second heat exchanger is 120° C. to 200° C.

Abstract: A method for preparing a sterilised drug delivery device (1) comprising a fluid medication, the method comprising the steps of: providing a prefilled barrel (10) containing the fluid medication, the barrel being sealed with a stopper; placing the prefilled barrel, a plunger rod (20) and a finger grip (30) in a package such that the prefilled barrel, the plunger rod and the finger grip are separated from each other, wherein one side of the package is formed by a gas-permeable sheet (40); closing and sealing the package; and exposing the sealed package to a sterilant gas under conditions such that external surfaces of the prefilled barrel, the plunger rod and the finger grip are sterilised, wherein the package is a tray (50) comprising a cavity (51) formed therein wherein the cavity comprises at least three separate compartments (51a, 51b, 51c) adapted to the respective shapes of the components of the device for placement therein, and wherein the each of the prefilled barrel, the plunger rod and the finger grip

Abstract: The present disclosure provides methods and compositions useful for treating metastatic breast cancer in a subject in need thereof. The methods include measuring gene expression in breast cancer cells obtained from the subject, and administering an anticancer therapeutic to the subject.