Abstract: Disclosed are monoclonal antibodies, antigen binding fragments, and bi-specific antibodies that specifically bind a coronavirus spike protein, such as SARS-CoV-2. Also disclosed is the use of these antibodies for inhibiting a coronavirus infection, such as a SARS-CoV-2 infection. In addition, disclosed are methods for detecting a coronavirus, such as SARS-CoV-2, in a biological sample, using the disclosed antibodies.

Abstract: Methods and devices for implementation of a health care prescription. Some devices may dynamically monitor information from a patient device. Some embodiments may dynamically provide instructions to patient devices to treat and for treating patients through the use of medical devices based on the information from a patient device. Some embodiments treat musculoskeletal conditions by providing for alignment of bones by use of bone alignment devices in accordance with instructions provided through a prescription. Other embodiments may facilitate or provide revised prescriptions in response to treatment conditions. Embodiments may also provide effective ways of communicating prescription and compliance information between patients and health care providers.

Abstract: A gas turbine engine for an aircraft including a unit supplied with oil from a first oil circuit and a second oil circuit. The first oil circuit and the second oil circuit each are fluidly coupled with at least one inlet and with at least one outlet of the unit and with at least one inlet and with at least one outlet of an oil tank. The first oil circuit and the second oil circuit are configured to receive oil from the oil tank and to direct the received oil to the unit. The oil tank is incorporating offset outlets to each of the oil circuits. The offset outlet of the second oil circuit is positioned higher in the oil tank than the offset outlet of the first oil circuit.

Abstract: A gas turbine engine includes a gearbox receiving input from a core shaft and driving a fan at a lower speed than the core shaft. First and second oil circuits fluidly couple with an inlet and outlet of the gearbox. A third oil circuit fluidly couples with an inlet and outlet of the gearbox. The outlet of the gearbox includes a device directing oil from the gearbox to the first oil circuit, to the second oil circuit and to the third oil circuit when feeding to the gearbox exceeds a predefined oil flow rate, or deviates an operational value corresponding with that oil flow rate, and directs oil from the gearbox to the third oil circuit when feeding to the gearbox is ? the predefined flow rate or is ? a corresponding operational value or is greater than or equal to a further corresponding operational value.

Abstract: A method (500) and apparatus (50, 60) for lubrication of a gearbox (30) of an aircraft engine comprise provision (502) of oil to the gearbox (30) through a primary oil system (50) driven by a core (11) of the engine (10) in normal conditions; detection (504) of windmilling conditions and/or failure of the primary oil system (50); and in response to the detected condition or failure, activation (506) of an electric pump (61) of an auxiliary oil system (60), to provide oil to the gearbox (30).

Abstract: Methods and devices for implementation of a health care prescription. Some devices may dynamically monitor information from a patient device. Some embodiments may dynamically provide instructions to patient devices to treat and for treating patients through the use of medical devices based on the information from a patient device. Some embodiments treat musculoskeletal conditions by providing for alignment of bones by use of bone alignment devices in accordance with instructions provided through a prescription. Other embodiments may facilitate or provide revised prescriptions in response to treatment conditions. Embodiments may also provide effective ways of communicating prescription and compliance information between patients and health care providers.

Abstract: A turbine arrangement for a gas turbine engine comprising a turbine shaft. An axial array of turbine rotors, having a first axial end and a second axial end. A drive arm coupled between the turbine shaft and the first axial end. A measurement system arranged to measure a parameter of the turbine arrangement, the measurement system positioned at the second axial end. The parameter may be rotational speed.

Abstract: A gas turbine engine (10) comprising: an engine core (11), comprising a compressor (14, 15); an outer casing (25A) separating the engine core (11) from a bypass airflow; a compressor bleed valve (50) in communication with the compressor (14, 15) and configured to release bleed air from the compressor (14, 15); a bleed air duct (51) connected to the compressor bleed valve (50) and configured to eject the bleed air released by the compressor bleed valve (50) into an airflow at a location radially inward of the outer casing (25A).

Abstract: A gas turbine engine for an aircraft including a unit supplied with oil from a first oil circuit and a second oil circuit. The first oil circuit and the second oil circuit each are fluidly coupled with at least one inlet and with at least one outlet of the unit and with at least one inlet and with at least one outlet of an oil tank. The first oil circuit and the second oil circuit are configured to receive oil from the oil tank and to direct the received oil to the unit. The oil tank is incorporating offset outlets to each of the oil circuits. The offset outlet of the second oil circuit is positioned higher in the oil tank than the offset outlet of the first oil circuit.

Abstract: A gas turbine engine includes a gearbox receiving input from a core shaft and driving a fan at a lower speed than the core shaft. First and second oil circuits fluidly couple with an inlet and outlet of the gearbox. A third oil circuit fluidly couples with an inlet and outlet of the gearbox. The outlet of the gearbox includes a device directing oil from the gearbox to the first oil circuit, to the second oil circuit and to the third oil circuit when feeding to the gearbox exceeds a predefined oil flow rate, or deviates an operational value corresponding with that oil flow rate, and directs oil from the gearbox to the third oil circuit when feeding to the gearbox is the predefined flow rate or is a corresponding operational value or is greater than or equal to a further corresponding operational value.

Abstract: A method (500) and apparatus (50, 60) for lubrication of a gearbox (30) of an aircraft engine comprise provision (502) of oil to the gearbox (30) through a primary oil system (50) driven by a core (11) of the engine (10) in normal conditions; detection (504) of windmilling conditions and/or failure of the primary oil system (50); and in response to the detected condition or failure, activation (506) of an electric pump (61) of an auxiliary oil system (60), to provide oil to the gearbox (30).

Abstract: The present disclosure relates to an oil/fuel pump system for an accessory gear box of a gas turbine engine. The system comprises an oil pump, the oil pump having an oil pump shaft that can be operatively coupled to the drive shaft, and a fuel pump, the fuel pump having a fuel pump shaft. The fuel pump shaft is operatively coupled to the oil pump shaft such that the fuel pump is only operational when the oil pump is operational.

Abstract: A turbine arrangement for a gas turbine engine comprising a turbine shaft. An axial array of turbine rotors, having a first axial end and a second axial end. A drive arm coupled between the turbine shaft and the first axial end. A measurement system arranged to measure a parameter of the turbine arrangement, the measurement system positioned at the second axial end. The parameter may be rotational speed.

Abstract: Methods and devices for providing instructions to treat and for treating patients through the use of medical devices are provided. Some embodiments treat musculoskeletal conditions by providing for alignment of bones by use of bone alignment devices in accordance with instructions provided through a prescription. Other embodiments may facilitate or provide revised prescriptions in response to treatment conditions. Embodiments may also provide effective ways of communicating prescription and compliance information between patients and health care providers.

Abstract: A phase change material (PCM) switch is disclosed that includes a resistive heater element, and a PCM element proximate the resistive heater element. A thermally conductive electrical insulating barrier layer positioned between the PCM heating element and the resistive heating element, and conductive lines extend from ends of the PCM element and control lines extend from ends of the resistive heater element.

Abstract: A phase change material (PCM) switch is disclosed that includes a resistive heater element, and a PCM element proximate the resistive heater element.

Abstract: A presence registration and routing node receives a message indicative of a telephony-related action performed by a user. In response to the message, the presence registration and routing node sends a message to a presence server for updating presence information regarding the user in a presence server database.

Abstract: A presence registration and routing node receives a message indicative of a telephony-related action performed by a user. In response to the message, the presence registration and routing node sends a message to a presence server for updating presence information regarding the user in a presence server database.

Abstract: A presence registration and routing node receives a message indicative of a telephony-related action performed by a user. In response to the message, the presence registration and routing node sends a message to a presence server for updating presence information regarding the user in a presence server database.

Abstract: A two-phase liquid cooling system includes an active venting system for regulating an amount of non-condensable gas within the cooling system. Various venting structures may be used to remove gases from the cooling system, some of which are designed to remove the non-condensable gases and avoid removing the vapor-phase coolant. A control system activates the venting system to achieve a desired pressure, which may be based on measured process conditions within the cooling system. A venting and refilling system may serve multiple cooling systems in a parallel arrangement. A return path of the cooling system can be tested for coolant leaks by increasing the pressure in the return path and placing a coolant detector near the path.