Abstract: The invention relates to a planetary gear box in a gas turbine engine, characterized by at least one protective device in the interior of a casing of the planetary gear box, wherein the protective device is designed and configured to divert at least one particle which is moving in the casing, in particular in an event of damage, and/or to extract kinetic energy from the moving at least one particle, in particular by deformation of the protective device, wherein the protective device is coupled to the casing of the planetary gear box, to a planet gear and/or to a planet carrier. The invention also relates to a gas turbine engine.

Abstract: A pre-swirl nozzle carrier for a gas turbine engine, includes: a wall having front and rear sides, and a multiplicity of pre-swirl nozzles formed in the wall and which each have a flow passage, wherein the flow passage has an inlet opening at the front side and an outlet opening at the rear side. The flow passages are provided and designed to discharge air, which has flowed in via the inlet opening, with swirl from the outlet opening. It is provided that the inlet opening is surrounded by a periphery which, at least in certain sections, has a region with a convex curvature adjacent to the flow passage and has a region with a concave curvature adjacent to said region with a convex curvature. The invention furthermore relates to a method for producing a pre-swirl nozzle in a pre-swirl nozzle carrier.

Abstract: A stator pole for a stator of a transverse flux machine is provided. The stator includes a stator winding arranged in a winding space, and the winding space being formed circumferentially in a circumferential direction in relation to an axis of rotation of a rotor. The stator pole has a body element made of a ferromagnetic material, which has at least one pole head which, in the installation position, may be arranged opposite the one rotor, and a magnetic return path region, which may be arranged facing away from the one rotor, wherein a number of the pole heads of the stator pole correspond to a number of the rotors. The stator pole is configured to occupy only a portion of a circumference of the winding space in the circumferential direction, and the magnetic return path region has a curved shape which adjoins the at least one pole head, as a result of which the magnetic return path region is designed to define the winding space in part transversely to the circumferential direction.

Abstract: An electric machine includes a rotor, a stator, and an air gap formed between a magnetic device of the rotor and the stator. For the selective setting of the air gap, movement devices implemented by piezoelectric stacks are provided on the rotor and/or on the stator. The movement devices may influence radial positions of the respective magnetic device and thus set the radial air gap width. It is thereby possible to exert open-loop and/or closed-loop control over a power or torque of the electric machine without adjusting stator currents. Vibration or unbalance of the rotor may also be counteracted quickly and effectively during operation of the machine.

Abstract: A planetary gear mechanism for a gas turbine engine includes a planet carrier and a planet pin rotationally fixedly connected thereto and on which a planet gear is rotatably mounted via a planet bearing. The planet pin is at least approximately hollow cylindrical in regions. A sleeve in the planet pin comprises an oil feed region through which the bearing is supplied with oil. An outer side region of the sleeve and an inner side region of the planet pin are press fit together. The sleeve has a web radially inside the outer side region. The web extends radially through the sleeve and is fixedly connected to the outer side region in an end region of a main load zone of the bearing, and at the other end is fixedly connected to the outer side region on the opposite side thereof in the radial direction of the sleeve.

Abstract: A lean burn combustor includes a plurality of lean burn fuel injectors, each including a fuel feed arm and a lean burn fuel injector head with a lean burn fuel injector head tip, wherein the lean burn fuel injector head tip has a lean burn fuel injector head tip diameter, the lean burn fuel injector head including a pilot fuel injector and a main fuel injector, the main fuel injector being arranged coaxially and radially outwards of the pilot fuel injector; and a combustor chamber extending along an axial direction for a length and including a radially inner annular wall, a radially outer annular wall, and a meter panel defining the size and shape of the combustor chamber, wherein the combustor chamber includes primary and secondary combustion zones. A ratio of the combustor chamber length to the lean burn fuel injector head tip diameter is less than 5.

Abstract: The electric machine comprises at least one winding (30) having at least one conductor (20) and electrical insulation for insulating one or more of the windings (30) and/or conductors (20), wherein the insulation is formed by a metal oxide. The method for producing such an electric machine having at least one winding (30) having at least one conductor (20) comprises the steps of metallizing the at least one winding (30) and/or conductor (20) with metal and oxidizing the metal. The aircraft is in particular an electric or hybrid-electric aircraft and has such an electric machine (10).

Abstract: A state of charge of a battery is estimated by a battery model specific to the battery. The battery model provides a section-wise defined correlation of terminal voltage values depending on state of charge values. Each of sections of the battery model delimits a monotonic dependence of the correlation from others of the sections. By segmenting the correlation of terminal voltage values depending on a state of charge value into sections, each segment within such the section-wise defined correlation of terminal voltage values depending on state of charge values is mathematically spoken a bi-unique function suitable for transformation into an inverse function defined within the section. The estimated state of charge may be continuously refined by an iterative feedback loop including coulomb counting for estimating a battery charge value, where refined estimated battery charge values state of charge values at a previous cycle are projected forward to the current cycle.

Abstract: The disclosure relates to a method for determining an incorrect operating state of an electrical machine with the aid of an electronic circuit having at least one comparator. The electrical machine is controlled with a pulse width modulation signal. The pulse width modulation signal is demodulated. A first signal, which represents the demodulated pulse width modulation signal, is compared with a second signal. The second signal represents a rotational speed or a rotational angle of the electrical machine and/or a current intensity of the electrical machine. This comparison is carried out with the aid of the at least one comparator. An error signal is generated based on the comparison in order to determine the incorrect operating state of the electrical machine.

Abstract: An electric machine includes at least one stator having at least one individual-tooth winding carrier that has at least one spacer configured to space apart turns of an individual-tooth winding mounted on the individual-tooth winding carrier. A hybrid electric aircraft has an electric machine of this kind.

Abstract: The disclosure relates to a hybrid-electrical drive system for an aircraft having two subsystems that are largely independent of each other. A stator winding of a common electrical machine is assigned to each of the subsystems such that both subsystems may be supplied with electrical energy from the common electrical machine. If a defect occurs in one of the subsystems, the drive system may be configured such that electrical energy from a battery of the non-defective subsystem may be transferred into the defective subsystem by utilizing the two stator winding systems.

Abstract: The invention relates to a circuit arrangement of a converter (1) for the electrical supply of a multi-phase electric motor (2). The arrangement comprises multiple DC-voltage-supplied (+DC, ?DC) phase intermediate circuits (13) and multiple inverter circuits (5) that are electrically connected to each phase intermediate circuit (13), wherein a respective phase intermediate circuit (13) and inverter circuit (5) are provided for each phase, together forming a commutation cell (14). The invention also relates to an aircraft having a circuit arrangement of this type, and an operating method with a circuit arrangement of this type.

Abstract: A sensor device determines measured values of a property of a fluid, in particular of a gas, in a cavity of a gas turbine engine having a duct for carrying the fluid from the cavity to a sensor element. A data processing device is coupled to the sensor element and processes the measured values. The data processing device has a device for detecting changes in the measured values with respect to time, and an evaluation device, by which the changes in the measured values with respect to time can be detected. If there is a deviation in the changes in the measured values with respect to time from a predefined criterion, a signal relating to an at least partial blockage of the at least one inlet duct can be output. A measurement method is also disclosed.

Abstract: In the method for propelling an aircraft, to obtain electric energy, a fuel is combusted, and an electric machine is used, wherein the fuel is used to cool at least one part of the electric machine and contains natural gas. The propulsion system is configured to propel an aircraft, in particular according to the above-mentioned method. The propulsion system has an electric machine configured to obtain electric energy by combusting a fuel. The propulsion system further includes a natural gas tank configured to supply the fuel formed with natural gas, and a cooling device configured to cool at least one part of the electric machine. The aircraft has such a propulsion system.

Abstract: The invention relates to a circuit arrangement, comprising at least one wiring carrier plate (1), characterized by at least one separating element (2) formed in the wiring carrier plate (1), which separating element divides the wiring carrier plate (1) into sections separated by the separating element (2), wherein the transfer of vibrations from one section to another section is at least partially decoupled and/or damped by the separating element (2). The invention further relates to a converter having such a circuit arrangement, and to an aircraft having a converter. The converter can comprise capacitor stacks (3) arranged on the wiring carrier plate (1), and power semiconductors (6).

Abstract: The invention relates to a rotating electrical flux-switching machine, comprising a rotatable tubular rotor (2), an inner first stator (3), and an outer second stator (4) that is concentric and spaced apart relative to the first stator (3), wherein the rotor (2) is arranged concentrically relative to the first and second stator (3, 4) and is arranged between the first and the second stator (3, 4) in such a way that a first air gap (10) is formed between the first stator (3) and the rotor (2), and a second air gap (11) is formed between the second stator (4) and the rotor (2). The invention also relates to an aircraft comprising a rotating electrical machine of this type.

Abstract: A lean burn fuel spray nozzle comprises: a lean burn fuel spray nozzle head comprising a pilot fuel injector with a pilot fuel injector outlet and a main fuel injector with a main fuel injector outlet; a feed arm adapted to feed pilot fuel from pilots pipework to the pilot fuel injector through a pilot fuel circuit and feed main fuel from mains pipework to the main fuel injector through a main fuel circuit; and a switching device comprising a switching valve adapted to switch between a Main On position, wherein the main fuel injector is in fluid communication with the mains pipework such that main fuel is sprayed through the main fuel injector outlet, and a Main Off position, wherein the main fuel injector outlet is not in fluid communication with the mains pipework such that main fuel is prevented to flow through the main fuel injector.

Abstract: A measuring device with at least one fluid channel for conveying a measuring fluid, wherein the fluid channel includes at least one inlet for the entry of the measuring fluid into the fluid channel and at least one outlet for the exit of the measuring fluid from the fluid channel. The fluid channel includes a diamond-shaped cross-section and includes a course from the at least one inlet to the at least one outlet over which the measuring fluid entering the fluid channel is deflected by at least 90° before the measuring fluid exits the fluid channel at the at least one outlet.

Abstract: An oil system of a gas turbine engine, has first and second oil circuits. The oil circuits include. Respectively, first and second oil reservoirs, first and second oil consumers of the engine, and first and second heat exchangers for temperature control. The first oil consumer is impinged with oil from the first oil reservoir. The second oil consumer is impinged with oil from the second oil reservoir. The first oil consumer is connected to the first oil reservoir, and the second oil consumer is connected to the second oil reservoir. The operating temperature of oil in the first oil circuit is lower than in the second oil circuit. The first oil reservoir is connected to the second oil reservoir. Oil from each oil reservoir can be guided into the other oil reservoir via the connection.

Abstract: The invention relates to a processing, i.e. storing and analyzing, of measurement data. In order to store the measurement data, respective data units or data sets are created for sampling points, a plurality of measurement data temporally adjacent to the sampling-point measurement datum being stored within the data unit. A time interval between time values of the sampling-point measurement data of two consecutive data units at least is set approximately to a multiple of a sampling time interval, i.e. of a reciprocal of the measurement-value recording rate or sampling rate. The method according to the invention reduces the provision of data units because an individual data unit contains, in addition to a sampling-point measurement date, further measurement data temporally adjacent to the sampling-point measurement date.