Abstract: An engine includes a first turbine fluidically coupled to a first group of adjacent cylinders, and a second turbine fluidically coupled to a second group of adjacent cylinders. In this engine, the cylinders of the first and second groups are arranged along a line. The engine also includes a variable valve-lift system configured to admit at least air to the first group of cylinders during reduced engine-load conditions, but to stop admitting air to the second group of cylinders during the reduced engine-load conditions.

Abstract: Embodiments for cooling a turbine of an engine are provided. In one example embodiment, an internal combustion engine comprises a turbocharger including a turbine having a coolant jacket integrated in a housing of the turbine, and an oil circuit coupled to the coolant jacket of the turbine. By cooling the turbine with the oil circuit, the turbine may be constructed from less-heat resistant materials.

Abstract: The present invention concerns a method and a device for determining mechanical stress load, and optionally interface effects, on particles dispersed in a fluid. According to the invention, fluid comprising dispersed particles such as biomolecules is fed into a sample space of a device comprising a jacket which encloses a sample chamber and at least two rolls arranged within said jacket such that said sample space is defined between said rolls, said rolls being independently rotatable with respect to each other, wherein said jacket has an inner surface which is essentially adapted to the outer surface of the rolls, rotational movement is imparted to at least one of the rolls of said device, and changes in the state of said particles are determined from which mechanical stress load acting on the particles can be determined.

Abstract: Embodiments for a supercharged engine are presented. In one example, a supercharged engine includes a cylinder head having at least two cylinders, each cylinder having at least one outlet opening for discharging exhaust gases and each outlet opening being adjoined by an exhaust line, with exhaust lines of at least two cylinders merging to form an overall exhaust line within the cylinder head so as to form an integrated exhaust manifold, at least two turbines arranged in series, the two turbines being of different size and arranged downstream of the exhaust manifold in the overall exhaust line, a distributor housing in which the overall exhaust line downstream of the manifold enters into and leads through to a small turbine of the two turbines, and a first turbine housing which accommodates the small turbine including at least one coolant jacket in order to form a liquid cooling arrangement.

Abstract: The invention provides a liquid aqueous pharmaceutical formulation comprising a human anti-TNFa antibody, or antigen-binding portion thereof, which reduces pain associated with injection in a subject by at least about 50% when compared to injecting an otherwise identical formulation comprising at least one salt and/or at least one buffer. The invention also provides a liquid aqueous pharmaceutical formulation comprising a human anti-TNFa antibody, or antigen-binding portion thereof, having increased bioavailability upon subcutaneous administration into a subject. The formulation may comprise a therapeutic protein, such as a human anti-TNF-alpha antibody, or an antigen-binding portion thereof, or a biosimilar thereof.

Abstract: An adjustable, or all-moving, horizontal stabiliser for an aircraft, the stabiliser having a leading edge, a trailing edge, a root and a tip, and a strake fixed with respect to the stabiliser and attached to, or integrally formed with, the stabiliser leading edge adjacent the root.

Abstract: This disclosure relates to a cooler for an aircraft cooling system. The cooler includes a matrix body in which a plurality of coolant channels are designed and extend from a first surface of the matrix body to a second surface of the matrix body, allowing a coolant to flow through the matrix body. The matrix body of the cooler is designed to form a section of the outer skin of the aircraft.

Abstract: A hybrid cooling system for an engine is provided. The system comprises a block oil cooling circuit, a head coolant cooling circuit, the head and block circuits having a common heat exchanger. The system also includes a flow device in the head cooling circuit for preventing coolant flow in the head cooling circuit at least during a first phase of a warm-up phase of the internal combustion engine, a delivery device in the block cooling circuit which delivers engine oil constantly under pressure through the block cooling circuit to bearing points in a cylinder block and to bearing points in a cylinder head, and a control element arranged in a control line to reduce the delivery capacity of the delivery device through the block cooling circuit at least during the first phase of the warm-up phase. In this way, heat transfer in the common heat exchanger may be substantially prevented.

Abstract: An aircraft including a device for influencing the directional stability of the aircraft is provided. The device includes a control-input device; a flight control device; a sensor device for acquiring the rotation rates, including the yaw rates, of the aircraft; and at least one actuator, which is coupled with ailerons, spoilers, an elevator and a rudder. The flight control device includes a control function generating adjusting commands for the actuators for controlling the aircraft according to control commands. The aircraft includes two tail-mounted flaps, each including an actuator connected with the flight control device, situated symmetrically to each other and on opposite sides of the fuselage, and movable between retracted and extended positions. The control function is designed such that the adjusting commands that are generated on the basis of the control commands depending on the acquired rotation rates include adjusting commands to the actuators of the tail-mounted flaps.

Abstract: Embodiments for cooling a turbine of an engine are provided. In one example embodiment, an internal combustion engine comprises a turbocharger including a turbine having a coolant jacket integrated in a housing of the turbine, and an oil circuit coupled to the coolant jacket of the turbine. By cooling the turbine with the oil circuit, the turbine may be constructed from less-heat resistant materials.

Abstract: A method for partial cylinder cutoff is provided. The method comprises operating a multi-cylinder internal combustion engine with applied ignition, in which an odd number n of cylinders is arranged in line, and during partial-load operation when engine load is below threshold, enabling a partial cutoff of the cylinders, the partial cutoff comprising operating each cylinder only intermittently such that each cylinder is fired and cut off in turn at an interval of (2*720° CA)/n.

Abstract: The present invention concerns a method and a device for determining mechanical stress load, and optionally interface effects, on particles dispersed in a fluid.