Abstract: The present invention relates to methods, devices and systems for associating consumable data with an assay consumable used in a biological assay. Provided are assay systems and associated consumables, wherein the assay system adjusts one or more steps of an assay protocol based on consumable data specific for that consumable. Various types of consumable data are described, as well as methods of using such data in the conduct of an assay by an assay system. The present invention also relates to consumables (e.g., kits and reagent containers), software, data deployable bundles, computer-readable media, loading carts, instruments, systems, and methods, for performing automated biological assays.

Abstract: An integral resistance heater is disclosed. The heater includes a beryllium oxide (BeO) ceramic body having a first surface and a second surface. A heating element is formed from a metal foil or metallizing paint and is printed onto the top or second surface of the beryllium oxide ceramic body.

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: 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: 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 comprises an engine core comprising a turbine, a combustor, a compressor, and a core shaft connecting the turbine to the compressor. The engine comprises a fan located upstream of the engine core and arranged to be driven by the core shaft. The engine comprises 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 greater than or equal to 4. The engine comprises a plurality of actuators and a fuel supply system. The fuel supply system is arranged to supply fuel for combustion in the combustor, and to supply fuel to fueldraulically drive at least ten of the plurality of actuators.

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 the engine core and defining a bypass duct located radially outside 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 greater than or equal to 4. The engine includes a plurality of actuated engine systems, including a heat management system and a turbine case cooling system. The engine includes a fuel supply system arranged to supply fuel for combustion in the combustor, and to supply fuel to fueldraulically drive at least three of the plurality of actuated engine systems.

Abstract: A gas turbine engine includes engine core, combustor, compressor, and core shaft. The engine includes fan located upstream of engine core and arranged to be driven by core shaft. The engine includes a nacelle surrounding fan and engine core and defining a bypass duct located radially outside of engine core, where a bypass ratio, defined as ratio of mass flow rate of flow through bypass duct to mass flow rate of flow through core at cruise conditions, is at least 4. The engine includes plurality of actuators and fuel supply system arranged to supply fuel for combustion in combustor, and to supply fuel to fueldraulically drive at least one actuator of plurality of actuators. The fuel supply system is arranged to select between: causing fuel to actuate at least one actuator; and causing fuel to bypass the at least one actuator, based on sustainable aviation fuel—SAF—content of fuel.

Abstract: A method of operating a gas turbine engine comprising an engine core comprising a turbine, a compressor, a core shaft connecting the turbine to the compressor, and a combustor arranged to combust a fuel; a fan located upstream of the engine core; an oil system arranged to circulate oil; and a heat exchange system comprising at least one fuel-oil heat exchanger arranged to transfer heat from the oil to the fuel, wherein the method comprises: determining at least one fuel characteristic of the fuel arranged to be provided to the combustor; and modulating the heat exchange system so as to adjust the fuel temperature on entry to the combustor at cruise to a set level, the set level being based on the at least one fuel characteristic.

Abstract: A method of operating a gas turbine engine includes an engine core with a turbine, compressor, fuel combustor, and core shaft connecting the turbine and compressor; a fan located 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 includes a bypass pipe allowing oil to bypass a heat exchanger; and a bypass valve allowing the oil sent via the bypass pipe to be varied, the method including controlling the bypass valve 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 method of operating a gas turbine engine of an aircraft with an engine core including a turbine, compressor, combustor, and core shaft connecting the turbine to the compressor; 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 to supply oil to the gearbox; and a heat exchange system with an air-oil heat exchanger through which the oil flows; and a fuel-oil heat exchanger through which the oil and fuel flow; and a modulation valve to allow the oil sent via each heat exchanger to be varied, the method including determining a fuel characteristic of the fuel to be combusted by the combustor; and controlling the modulation valve based on the at least one fuel characteristic to adjust the proportion of the oil sent via each heat exchanger at cruise conditions.

Abstract: A gas turbine engine for an aircraft includes an engine core including a turbine, combustor, compressor, and core shaft connecting the turbine to the compressor. The engine includes a fan located upstream of engine core and arranged to be driven by core shaft. The engine includes a nacelle surrounding the fan and engine core and defining bypass duct located radially outside of engine core, where bypass ratio, defined as the ratio of the mass flow rate of the flow through bypass duct to the mass flow rate of the flow through the core at cruise conditions, is at least 4. The engine includes plurality of actuators and fuel supply system arranged to supply fuel to fueldraulically drive at least one actuator of the plurality of actuators. At cruise, fuel temperature on entry into the at least one actuator is at least 5° C. greater than fuel temperature on entry to combustor.

Abstract: A therapy system includes a patient support apparatus and a pneumatic therapy device that is coupleable to the patient support apparatus. The therapy device may receive power and air flow from the patient support apparatus.

Abstract: A charting system is provided for use in a healthcare facility having a network. The charting system includes a microphone to receive voice inputs from a caregiver. A vital sign monitor obtains a vital sign from a patient and displays it. The system includes a communication device having a voice-to-text module that includes a processor coupled to the microphone. The processor operates a voice-to-text algorithm that converts the vital sign into text in response to the caregiver dictating the vital sign into the microphone. The processor initiates transmission of the vital sign to an EMR computer via the network after conversion of the at least one vital sign to text.

Abstract: A method of simultaneously testing catalytic activity and/or selectivity of a plurality of catalyst includes coating a substrate having the plurality of catalyst with a polymer thin film having one or more reactive probes, subjecting the coated substrate to catalysis conditions corresponding to the target catalytic activity and/or selectivity, and imaging the coated substrate for the optical signal. Each reactive probe has a signaling component that generates an optical signal upon reaction of the probes with a product of the target catalytic activity and/or selectivity, thereby allowing sensing and signaling of the product of the target catalytic activity and/or selectivity. The presence of an optical signal in one or more regions of the coated substrate is indicative of catalysts of the plurality of catalyst in the one or more regions being active for the target catalytic activity and/or selectivity.

Abstract: A cable management drive system for extending and retracting cable bundles is provided. The cable management drive system includes a cable bundle configured to provide power signals or data signals to an industrial robot configured to perform a service. The cable bundle is configured to couple to the industrial robot. The cable management drive system includes a plurality of drive wheels coupled to a drive mechanism and configured to cause the cable bundle to be extended to facilitate a deployment of the industrial robot to perform the service and to be retracted to facilitate a withdrawal of the industrial robot upon performance of the service, and a driver system coupled to the plurality of drive wheels and the drive mechanism. The driver system is configured to power the drive wheels and the drive mechanism to cause the cable bundle to be extended and retracted.

Abstract: A head-mounted device may include optical assemblies for presenting images to a user. The optical assemblies may be mounted in a head-mounted device housing. The head-mounted device housing may be supported at the front of the head of a user in front of the user's eyes using head-mounted support structures such as straps. The straps may include a rear strap and an overhead strap. A counterweight may be provided at the rear of the user's head to counterbalance the weight of the head-mounted device housing. The counterweight may be coupled to a rigid portion of the head-mounted housing at a connection. A clutch may be provided to allow the rotational orientation of the counterweight to be adjusted about the connection. A sliding mass in the counterweight may also be adjusted. These adjustments alter the amount of counterbalancing created by the counterweight to counterbalance the head-mounted device housing.

Abstract: A computer-implemented neurocognitive training game is provided. The game comprises first presenting, in a user interface, a number of questions regarding different health parameters of a user within a previous 24 hour period. Responsive to entry of answers to all of the questions, a number of trials are presented in the user interface. Each trial has a specified response time window and comprises a number of images displayed within spatially distinct contexts. A user score is generated based on the correct identification of the images in the trials by the user. The difficulty and the response time window is adjusted for the trials according to the user score.

Abstract: Automatic removal of AI bias associated with an AI model. A computing device accesses an AI model. The computing device executes two or more independent bias mitigation algorithms, each of the two or more independent bias mitigation algorithms designed to independently remove AI bias from the AI model. Results of execution of the two or more independent bias mitigation algorithms are displayed to the user. A selection is received from the user of one or more bias mitigation algorithms for use with the AI model. The selected one or more bias mitigation algorithms are executed to correct bias in the AI model.

Abstract: An optoelectronic assembly includes: (i) a substrate having a cavity, (ii) an optoelectronic device, which is disposed over the cavity and includes an array of multiple emitters configured to emit a predefined number of light beams in response to receiving one or more electrical signals, and (iii) an integrated circuit (IC), which is mounted within the cavity, between the substrate and the optoelectronic device, and is configured to drive the one or more electrical signals to the optoelectronic device.