Abstract: A light metal material having a tensile strength of >180 MPa at room temperature is provided, as well as a method for producing such a light metal material and the use of such a light metal material as a piston component in a rotary piston engine.

Abstract: A contact element for high voltage direct current switches includes a matrix made of a first material selected from the group comprising copper, silver, palladium, platinum, tungsten, molybdenum, rhenium, nickel, gold, and alloys thereof. The contact element also includes a foreign phase, which is dispersed in the matrix and is made of a second material selected from the group comprising carbon, tin(II) oxide, tin(IV) oxide, zinc(II) oxide, tungsten, nickel and mixtures thereof. The contact element has a porosity of ?1.0% by volume, based on a total volume of the contact element.

Abstract: A gas turbine engine, especially a turbojet or turbofan for an aircraft, includes a combustion section and an exhaust section produces an exhaust gas. The emission products can be reduced by using a gas treatment device with a reactor and an injection device. The reactor produces a nitrogeneous substance such as ammonia. This reducing agent is injected in the gas phase in the exhaust section of the gas turbine engine. By selective non catalytic reaction the Nitrogen oxides of the exhaust gas can be reduced. Furthermore the injection device is arranged such that the temperature window of this reduction process is ranging from 850° C. to 1100° C. The reactor for producing gaseous ammonia can either be a thermal reactor or a high pressure plasma device.

Abstract: The invention relates to a method for plasma reformation of fuel, in particular kerosene, which method comprises the steps of: feeding fuel through a line to the inlet of an expansion nozzle; supplying energy from an energy source by way of a hollow waveguide to generate a plasma state in the expansion nozzle; injecting further fuel through nozzles into the arising plasma flame in order to decompose the fuel in the heat into components such as CO, C and H; and expanding the plasma flame at high speed into the combustion chamber.

Abstract: An induction heating system and a method for controlling a process temperature for induction heating of a workpiece. The induction heating system comprises an inductor configured to generate an alternating magnetic field in response to an alternating current supplied thereto, a magnetic load comprising a magnetic material, the magnetic material having a Curie temperature and being configured to generate heat in response to the alternating magnetic field being applied thereto, the magnetic load being connectable to the workpiece in a heat-conducting manner so as to transfer the generated heat to the workpiece, and a control unit configured to control the process temperature for manufacturing the workpiece by adjusting the alternating magnetic field when the temperature of the magnetic material is in a temperature control range around or below the Curie temperature of the magnetic material, the temperature control range being dependent on the magnetic material of the magnetic load.

Abstract: An ion dosage apparatus for an energy storage apparatus includes a first energy guiding device with a first energy supply device and a separating device. The separating device is configured to control, via supplied energy, a number of ions that are transported around the first energy guiding device and/or blocked.

Abstract: A structural component for a vehicle has a surface with a riblet structure. The riblet structure includes a plurality of grooves, including a first groove having a first longitudinal section forming a first angle with a main longitudinal direction of the structural component. The first angle is larger than 0° and the main longitudinal direction corresponds to a flow direction of a fluid along the surface of the structural component.

Abstract: A gas turbine includes a combustion chamber and a microwave source to produce microwave radiation. The gas turbine is arranged to guide the microwave radiation into a cavity of the combustion chamber. Due to the microwave radiation, in the cavity of the combustion chamber, combustion in the cavity may be supported and thus lean operation of the gas turbine is made possible.

Abstract: An aircraft includes a propulsion unit with a compressor and a bleed air device for providing bleed air from the propulsion unit, a fuel tank for a fuel, at least one fuel cell, a reactor for reforming fuel from the fuel tank to a hydrogen-containing fuel gas, and at least one feed unit with a bleed air inlet, a fuel inlet, an oxidizing agent outlet, and a fuel outlet. The feed unit can selectively and not simultaneously feed an oxidizing agent by means of the oxidizing agent outlet or fuel by means of the fuel outlet into the reactor. The feed unit is connected to the bleed air device and designed to provide the oxidizing agent based on bleed air.

Abstract: A method for producing a surface structure with a lightning strike protective system involves providing a support structure based on a fiber-reinforced composite material. At least one arrangement of a lightning strike protective material made from or with a conductive material is applied onto the support structure so that the lightning strike protective material arrangement adheres to the support structure in such a way that it is held securely in its position. A cover material is applied in such a way that it embeds the at least one arrangement of a lightning strike protective material that is held securely in its position on the support structure, and the cover material is solidified.

Abstract: An ice protection system for de-icing an aircraft and/or for keeping the aircraft free of ice includes a composite structure for an aircraft component and a structural element of an aircraft with an ice protection system that is integrated in the composite structure. The ice protection system includes a flat surface-like electric heating element that is embedded in the composite structure below an outer layer of an outer surface of the aircraft component.

Abstract: An aircraft fuel cell system is provided. The system includes a fuel tank, a reactor for generating hydrogen gas from a fuel, a heating apparatus and a fuel cell. The reactor can process a synthetic fuel produced from biomass. The use, in an aircraft, of a synthetic fuel, produced from biomass, for generating a gas that contains hydrogen is also provided.

Abstract: A method for manufacturing a solid oxide fuel cell element by layer-wise buildup wherein at least one section of the element is built up by carrying out a step that at least includes the following at least once: applying a layer section of a particulate ceramic material with predefined dimensions onto a base layer in a predefined area and heating the layer section by means of a heat source such that the particles of the ceramic material connect to one another within the predefined dimensions. The solid oxide fuel cell element manufactured with the method is realized in one piece, as well as highly compact, and has a low weight.

Abstract: A drive unit includes a combustion chamber for combusting a fuel/air mixture, and a fuel cell device, wherein the fuel cell device includes at least one fuel cell, which in each case includes an anode that is couplable to a fuel line, a cathode that is couplable to an air source, and a fluid outlet and is arranged upstream of the combustion chamber. The combustion chamber further includes a combustion chamber inlet for supplying the fuel/air mixture, and a combustion chamber outlet for discharging exhaust gas, and the combustion chamber inlet is connected to the fluid outlet of the fuel cell device. In this way a hybrid drive unit can be provided which apart from mechanical power also generates electrical power at high efficiency.

Abstract: A method and device for surface peening, particularly ultrasonic shot peening, of a component in the region of a passage opening is disclosed. A vibration device impinging the blasting material is disposed on one side and a counter-element is disposed on an opposite side relative to a component region having the passage opening. The counter-element is disposed at a distance relative to the corresponding side of the component region.

Abstract: A fuel cell supply device that generates hydrogen for fuel cells in an aircraft includes a reaction chamber which reacts hydrogenated polysilanes or mixtures thereof with water; a feed device that feeds at least one reactant into the reaction chamber; and a discharge device that leads hydrogen formed in the reaction to a fuel cell.

Abstract: A method for machining workpieces provides a machining electrode, which is guided at a specific distance to the workpiece. An electrolyte is provided between the workpiece and the machining electrode, through which an operating current flows between the machining electrode and the workpiece. The operating current results from an operating voltage (UA), which is produced at the machining electrode, the workpiece being connected to ground. To perform the machining procedure, the distance between the machining electrode and the workpiece is regulated and the operating voltage (UA) is determined in such a way that the resulting operating current is a DC current or a pulsed DC current—i.e., the operating voltage is a DC voltage of fixed or specific dimension. A measuring voltage (UM) is superimposed on the operating voltage (UA) for producing the operating current.

Abstract: A corrosion detection apparatus for permanently and integrally monitoring a state of corrosion of a component is provided. The corrosion detection apparatus makes it possible to use the change in electrical conductivity to detect corrosion of a component to be monitored. A corrosion-sensitive bridging element that establishes an electrical connection between a first electrical line section and a second electrical line section of a sensor circuit is used to change certain electrical properties of the sensor circuit. On account of the corrosion-sensitive property of the bridging element, the latter changes its electrical conductivity when corrosion starts. This makes it possible to use the sensor circuit to detect corrosion of the bridging element and thus of the component to be monitored.

Abstract: The invention relates to a method for the production of aero-dynamic structures during the production of integrally bladed gas turbine rotors. Aerodynamic structures of an integrally bladed gas turbine rotor are produced on a rotor disk base body, whereon the end contours are precise, by removing material according to an electrochemical removal process, i.e. by means of an electrochemical machining (ECM)-process. The method comprises the following steps: a) preparing a rotor disk base body which is made of a material which is difficult to machine; b) removing the material which is between the blade wings until a specific dimension is obtained, according to a removal process; c) preparing at least one working electrode in order to finish at least one aerodynamic structure of an integrally bladed gas turbine rotor.

Abstract: A method for manufacturing integrally bladed rotors (preferably gas turbine rotors) is provided. The method includes the steps of a) providing a basic rotor body; b) placing the basic rotor body into an electrolyte; c) electrochemically machining the basic rotor body by simultaneously manufacturing a plurality of unmachined blades; and d) subsequently machining the unmachined blades to provide hydrodynamic surfaces, in particular a suction side and a pressure side, in the area of each unmachined blade.