Abstract: Embodiments of the invention are shown in the figures, where a gas turbine engine for an aircraft includes: an engine core including a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan including a plurality of fan blades; and a gearbox that receives an input from the core shaft and outputs drive to the fan so as to drive the fan about a rotational axis at a lower rotational speed than the core shaft, wherein the gearbox is an epicyclic gearbox with a plurality of planet gears arranged in first and second sets of planet gears, the planet gears of the first set being positioned displaced relative to the planet gears of the second set in a direction parallel to the rotational axis.

Abstract: The invention relates to a torque limiting device in a torque bearing connecting structure between a gearbox and a stationary structure in a gas turbine engine, wherein the torque limiting device comprises a mechanical fuse in the connection structure comprising an at least partially circumferential weakening of the material. The invention also relates to a gas turbine engine.

Abstract: A device includes a circuit carrier board and a conductor element that is configured to transfer an electric current from and/or to the circuit carrier board. The device includes an electrically conductive, elastically deformable, contoured, plate-like connection element that connects the circuit carrier board to the conductor element and is configured to create a local, dynamic resilience. As a result of this, a force transmission front the conductor element to the circuit carrier board may be reduced. A plate thickness of the connection element is at least 2 cm. A power converter and an aircraft having such a device are also provided.

Abstract: A planetary gear arrangement including a sun gear configured to rotate about an axis of rotation, a plurality of planet gears driven by the sun gear, a ring gear engaged with the plurality of planet gears and a plurality of journal pins arranged in the plurality of planet gears forming a converging gap and a diverging gap therebetween. Each journal pin has at least one longitudinal groove along an outer surface thereof, configured to guide oil on the outer surface when the oil is carried from the converging gap towards the diverging gap due to a revolving movement between a planet gear around a corresponding journal pin. A journal pin for supporting a gear and a gas turbine engine.

Abstract: The invention relates to a planetary gear box, which has a sun gear, a plurality of planet gears, a ring gear, a plurality of plain bearing pins and an axially front carrier plate and an axially rear carrier plate. The plain bearing pin and the planet gear here configure a lubricated plain bearing which includes a plain bearing gap. Furthermore, the plain bearing pin, on the contact face thereof, configures a feed pocket which is provided and configured to receive oil and during the operation deliver oil in the circumferential direction to the plain bearing by way of a delivery edge. It is provided that the feed pocket is configured in the contact face of the plain bearing pin in such a manner that the delivery edge has a profile that deviates from a straight profile parallel to the longitudinal axis of the plain bearing pin.

Abstract: A gas turbine engine has an accessory gearbox disposed outside of a bypass channel and connected to a housing part, which radially delimits the bypass channel, in a connection region near the housing part and in a connection region far from the housing part. A connecting element is provided between the housing part and the connection region far from the housing part. A longitudinal axis of the connecting element includes an angle in the range of 75° to 115° with a vertical axis of the accessory gearbox. The connecting element can vary a distance between the far connection region and a connection point of the connecting element on the housing part such that deformation of the housing part and a resulting position change of the connection point cause a lesser deflection of the accessory gearbox than a deflection with an unchanged length of the connecting element.

Abstract: A power electronics converter includes a multi-layer planar carrier substrate having a plurality of electrically conductive layers, at least one electrical connection, and a converter commutation cell comprising a power circuit and a gate driver circuit. The power circuit includes at least one power semiconductor switching element and at least one capacitor. Each power semiconductor switching element is included in a power semiconductor prepackage having one or more power semiconductor switching elements embedded in a solid insulating material. The power electronics converter includes a heat sink configured to remove heat from the power semiconductor prepackage. A converter parameter ? is greater than or 20 equal to 100 kW/m3K, ? being defined as a heat transfer coefficient between the heat removal side of the power semiconductor prepackage and a cooling medium of the heat sink divided by the size of a gap between the power semiconductor prepackage and the heat sink.

Abstract: The invention concerns a planetary gear box with a flow guidance device for a planet gear lubricant stream in the planetary gear box, which is directed at least partially along a planet gear after an engagement with a sun gear, characterized by a collecting region of the flow guidance device in which the planet gear lubricant stream between the planet gear and the flow guidance device can be at least partially captured, and wherein the collecting region has an outlet region between the flow guidance device and the tooth face of the planet gear for at least a part of the planet gear lubricant stream, and an edge is arranged at the outlet region for defined constriction of the passage for the planet gear lubricant stream.

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 invention relates to a drive device (1) for an aircraft, comprising: an electric machine (2) with a stator (3) and a rotor (4) and a cooling device (10) for cooling the electric machine (2), the cooling device (10) having an encapsulated first cooling region (12), in which a first cooling liquid for cooling the stator (3) and/or the rotor (4) is disposed, the cooling device (10) having a second cooling region (15), which is separate from the first cooling region (12) and in which the second liquid is disposed, and the cooling device (10) having an internal heat exchanger (11) for transmitting heat from the first cooling liquid to the second cooling liquid.

Abstract: The disclosure relates to a device for cooling components. The device includes a main body and cylindrical and/or conical cooling fins which are formed in the main body and around which a coolant may flow, wherein the cooling fins are formed in parallel first rows and equally spaced apart from one another. Neighboring first rows are arranged offset from one another in the row direction in such a way that the axes of neighboring cooling fins of the neighboring first rows are offset by at least 25% of the hydraulic diameter of the cooling fins. The disclosure also relates to a converter and an aircraft including a device of this type.

Abstract: A power electronics converter includes a carrier substrate, and a converter commutation cell including a power circuit. The power circuit includes a power semiconductor switching element included in a power semiconductor prepackage. The power semiconductor prepackage includes a power semiconductor switching element and an electrical connection extending from a terminal of the power semiconductor switching element to an electrical connection side of the power semiconductor prepackage. The power electronics converter includes a heat sink arranged to remove heat from the power semiconductor prepackage, a thermal interface layer arranged between the heat removal side of the power semiconductor prepackage and the heat sink, and an electrical isolation layer arranged between the power semiconductor switching element and the heat sink. A product of a thermal conductivity of the thermal interface layer and a breakdown electric field strength of the electrical isolation layer is greater than or equal to 5 MVW/m2K.

Abstract: An electric drive system includes at least one electric drive unit. The at least one electric drive unit includes an electric motor and inverters that are each supplied with DC voltage via a high-voltage bus. The electric drive system includes a main battery system that has a plurality of battery modules that supply DC voltage to each of the high-voltage buses. The electric device system includes a plurality of reserve batteries. A separate reserve battery is provided for each high-voltage bus. The drive system is configured to make a change to the supply of DC voltage when a corresponding control signal is present for each of the high-voltage buses. A change is made from a supply of DC voltage of the battery module of the main battery system that is assigned to the high-voltage bus to a supply of DC voltage of the reserve battery assigned to the high-voltage bus.

Abstract: An electrical power system for an aircraft includes a DC:AC power electronics converter and a transverse flux electrical machine. The transverse flux electrical machine includes a rotor that is coupleable to a rotating shaft of a propulsor of the aircraft, wherein the rotor includes a plurality of permanent magnets defining a number, NP, of evenly distributed rotor poles. The transverse flux electrical machine further includes a stator arranged to interact with the rotor, such that a torque is produced. The stator includes a plurality of coils.

Abstract: The proposed solution relates in particular to a method for assembling an engine assembly having a first engine component and a second engine component, wherein at least one fastening element is first of all arranged on an assembly aid, the at least one fastening element is arranged on the first engine component via the assembly aid and is held in an assembly position under the action of at least one magnetic element of the assembly aid, the at least one fastening element is fixed to the second engine component, and the assembly aid is removed again from the first engine component.

Abstract: An electrical propulsion unit (EPU) for a vertical take-off and landing (VTOL) aircraft is provided. The EPU includes a propeller or a fan and an electric motor. The electric motor includes a stator comprising coils configured to carry current and a rotor arranged to interact with the stator. The rotor is configured to generate a torque for driving rotation of the propeller or the fan. The coils of the stator have a cumulated conductor volume Vconductor The stator, the rotor, or the stator and the rotor include a flux guiding iron material configured to guide magnetic flux generated by the coils of the stator, wherein the flux guiding iron material has a cumulated iron volume Viron, and wherein the electric motor has a machine parameter ? that is greater than or equal to 0.25, ? being defined as: ?=Vconductor/Viron.

Abstract: A power electronics converter includes a multi-layer planar carrier substrate, and a converter commutation cell including a power circuit. The power circuit includes at least one power semiconductor switching element, each of which is comprised in a power semiconductor prepackage. Each power semiconductor prepackage includes one or more power semiconductor switching elements embedded in a solid insulating material. A heat sink is arranged to remove heat from the respective power semiconductor prepackage. A thermal interface layer is arranged between a heat removal side of the respective power semiconductor prepackage and the heat sink. The thermal interface layer has a thermal conductivity and a mechanical compressibility. A converter parameter, which is defined as the mechanical compressibility of the thermal interface layer divided by the thermal conductivity of the thermal interface layer, satisfies 0.1 MNK/Wm<?<1 GNK/Wm.

Abstract: A planetary gear arrangement for carrying load including a sun gear configured to rotate about an axis of rotation of the planetary gear and defines an axial direction of the planetary gear, a plurality of planet gears driven by the sun gear, a ring gear engaged with the plurality of planet gears and a plurality of elliptical pins, each having a longitudinal axis and an outside contact surface, wherein the plurality of elliptical pins are arranged in the plurality of planet gears forming a convergent gap and a divergent gap therebetween, and wherein plurality of elliptical pins are configured to conform to elliptically deformed plurality of planet gears when subjected to the load and form an effective area therebetween to bear the load. An elliptical pin for supporting a gear and a gas turbine engine.

Abstract: The invention regards a structural assembly for a gas turbine engine which includes a bearing with a statically arranged outer ring and a rotatably arranged inner ring, the bearing outer ring including a radially outer surface. The assembly further includes a housing structure supporting the statically arranged outer ring. It is provided that the housing structure forms a housing ring against which the radially outer surface of the bearing outer ring lies and which supports the bearing outer ring radially outwards.

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.