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: 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 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: 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 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: 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: 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.

Abstract: A gas turbine engine, includes: an engine core including a turbine, compressor, and shaft system connecting the turbine to the compressor, and forming a torque path therebetween. The shaft system is axially located by a thrust bearing located forward of the turbine, and the engine is configured, in the event of a shaft break which divides the shaft system into a front portion located by the thrust bearing and a rear portion unlocated by the thrust bearing, the rear portion is free to move axially rearwardly under a gas load. The engine further includes a shaft break detector having a forward speed sensor configured to measure a rotational speed of the front portion of the shaft system, and a rear microwave sensor configured to measure a rotational speed of the rear portion of the shaft system, wherein a shaft break can be detected based on differences in the measured speeds.

Abstract: A coupling device for rotably coupling a shaft with a gearbox in a geared turbo fan aircraft engine, wherein the coupling device includes a connection to the shaft at a first end and a connection to the gearbox at a second end, the first and the second ends being axially separated and at least one curved shape between the first end and the second end extending from the gearbox radially inwards to the shaft and the at least one curved shape including at least one cross-section in the axial direction of the engine with a logarithmic profile or a power profile.

Abstract: The disclosure relates to a modular arrangement of a converter for the electrical supply of a multi-phase electric motor. The modular arrangement includes multiple output stage modules, each module having a separate first housing. An output stage module is provided for each phase of the electric motor, wherein the output stage module has a phase intermediate circuit and an inverter circuit, together forming a commutation cell. The phase intermediate circuit supplies DC voltage and is electrically connected to the inverter circuit. The disclosure also relates to a motor arrangement and an aircraft having a motor arrangement of this type.

Abstract: An insert fixture has a base, a plurality of mounting brackets, and a plurality of separators. The plurality of separators extends vertically from the base and includes a plurality of grid portions extending the length of the insert fixture and a plurality of divider portions, which connect to the plurality of grid portions to form a plurality of individual component holders around one of the plurality of mounting brackets. Each individual component holder has two separated grid portion sections positioned on either side of the bracket. These grid portions have two divider portions which are also separated and positioned either side of the bracket at an angle relative to the two grid portions. The individual component holder forms a cell around the mounting bracket. The insert fixture may be constructed from a molybdenum alloy, lanthanum oxide and/or titanium zirconium molybdenum.

Abstract: The invention relates to an electrical machine (10), comprising at least one first coil (12), which is surrounded by a first electrical insulation element (24) at least in a partial region, and at least one second coil (14), which is surrounded by a second electrical insulation element (26) at least in a partial region, wherein at least one electrically conductive layer (28) provided in addition to the coils (12, 14) and in addition to the electrical insulation elements (24, 26) is arranged between the coils (12, 14).