Abstract: The coil winding has an electrical conductor for an electrical machine and includes at least two layers. The electrical conductor, following its longitudinal extension, runs inwardly wound in a first of the at least two layers, and then extends to a second of the at least two layers and runs outwardly wound in the second layer. The electrical machine includes at least one such coil winding. The hybrid electric aircraft is in particular an airplane and includes such an electrical machine and/or at least one such coil winding.

Abstract: A power electronics converter may include a converter commutation cell having 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, each prepackage including one or more power semiconductor switching elements embedded in a solid insulating material, each power semiconductor switching element having at least three terminals including a gate terminal. The gate driver circuit is electrically connected to and configured to provide switching signals to the gate terminal of each of the at least one power semiconductor switching element. A peak rated power output of the power electronics converter is greater than 25 kW and a value of a converter parameter ? is greater than or equal to 0.5 PV/FH.

Abstract: A planetary gear box (and method of assembly), where the gear box includes a sun gear, a plurality of planet gears, a ring gear, a plurality of planet pins, an axially forward carrier plate and an axially rearward carrier plate. Each planet pin is fixed respectively at its axially forward end on the axially forward carrier plate and at its axially rearward end on the axially rearward carrier plate of the planetary gear box. The planet pin is of two-part design and forms a radially outer pin part and a radially inner pin part, which are connected to one another in a manner precluding relative rotation therebetween, wherein the radially outer pin part forms a bearing with the planet gear, and only the radially inner pin part is fixed at its axial ends to the forward and rearward carrier plates.

Abstract: A method and system for detecting a functional failure in a power gearbox, includes a) measuring operational data in a gas turbine engine of operational parameters dependent on power generation and power consumption of the engine or the gearbox, b) obtaining analyzed operational data including time data, angular data of rotation, frequency data and/or phase data, c) using the analyzed operational data in a comparison with stored baseline operational data to determine deviation data, d) determining time dependent trend data from the deviation data or determining a first state measured dependent on the power generation, power consumption or power regulation of the engine and measuring a second state dependent on vibrational data of the engine, e) generating a signal and/or a protocol for controlling the gearbox, and/or the engine based on the time dependent trend data, if a threshold is exceeded or based on the first or second states.

Abstract: A vertical take-off and landing (VTOL) aircraft is provided. The VTOL aircraft includes at least one electrical propulsion unit (EPU), wherein an EPU of the at least one EPU includes a propeller or a fan. The EPU further includes an electric motor including a stator having insulated coils for carrying current and a rotor arranged to interact with the stator, such that a torque for driving rotation of the propeller or the fan is produced.

Abstract: A combustion chamber assembly includes a through hole on the combustion chamber wall bounded on an outer side of the wall by a hole edge and a combustion chamber shingle having a collar bounding a mixing air hole on the outer side of the wall and protruding with a first collar portion beyond the hole edge on the outer side of the wall. A cooling air opening is formed on an inner circumferential surface of a duct portion of the mixing air hole adjoining the first collar portion and extending in the direction of a combustion space, the cooling air opening leading into a cooling air duct which extends through the duct portion and via which cooling air is guided out of the mixing air hole in a direction of a hot side of the shingle facing the combustion space.

Abstract: The present invention relates to a method for producing an engine component having a cooling duct arrangement which has a plurality of cooling ducts, each having an inflow opening, the inflow openings being arranged according to a predefined pattern in an inflow surface of the engine component, and each cooling duct opening into a recess in a wall of the engine component, along which wall a cooling film is to be formed. According to the invention, the pattern is formed in at least one subregion of defined size of the inflow surface, from a plurality of identical isosceles triangles, which are defined by a minimum spacing (k) and by a mean diameter (a) of the inflow openings correlating to the minimum spacing (k). This procedure reduces the complexity of the design process.

Abstract: The proposed solution relates, in particular, to an engine component having at least one first loading zone, which is designed for dynamic loads arising at the engine component when the engine component is correctly built into an engine and when the engine is operating, and a second loading zone, which is provided spaced at a distance from the first loading zone on the engine component and likewise is designed for dynamic loads arising at the engine component when the engine component is correctly built into an engine and when the engine is operating. The proposal is, in particular, that at least one spatially delimited modification zone with introduced internal tensile stress is formed on the engine component, via which zone a crack propagating in the engine component is guided to the and/or within the second loading zone.

Abstract: An apparatus for oil lubrication of a rotationally fixed connection between two shafts. A first shaft engages with a hollow region of the second shaft. The shafts are operatively connected to each other in a form-fitting manner in the overlapping region. Oil is introduced into a first chamber in the hollow region, which chamber is connected to a second chamber in the hollow region. The second chamber is connectable to a third chamber is arranged in the overlapping region. The fluidic connection between the second chamber and the third chamber is separated above a defined oil volume in the second chamber and above a rotational speed threshold of the shafts via a sealing element. The sealing element is reversibly deformable by the oil volume in the second chamber and the centrifugal force acting thereon and, in the deformed state, seals the connection between the second and third chambers.

Abstract: A device for detecting a thermal runaway of a battery module with a number of cells includes a current acquisition module that is configured to capture a set of currents, and a temperature acquisition module that is configured to capture a set of temperatures. The device includes a state of charge capturing module that is configured to capture a set of states, and a resistance calculation module that is configured to derive a set of resistances. The device includes a temperature prediction module that is configured to calculate a set of temperature predictors, and a runaway prediction module that is configured to calculate a set of runaway predictors. A warning module that is configured to set a warning indicator when at least one runaway predictor value of the set of runaway predictors exceeds a predefined threshold value.

Abstract: A system for finishing a surface of a workpiece. The system includes a laser unit configured to emit a laser radiation. The system further includes an attenuator disposed within the laser unit and configured to adjust optical parameters of the laser radiation. The system further includes a cavitation chamber storing a liquid medium. The workpiece is mounted within the cavitation chamber and is in contact with the liquid medium. The system further includes at least one lens configured to focus at least a portion of the laser radiation and transmit at least one laser beam towards the workpiece.

Abstract: A stator winding system for a stator of an electric machine is provided. The stator has a number of windings to be positioned on stator teeth of the stator. At least two windings that follow one another in a current flow direction of an electric current and are thus arranged in series are formed from an electric conductor that is continuous in the current flow direction, forming a winding chain.

Abstract: The disclosure relates to an electric machine of an electrical system, (e.g., a drive system), and in particular to the electrical insulation of a coil of the machine. A coil arrangement includes a coil, formed by an electrical coil conductor, and also an insulating arrangement. The coil is arranged at an electrically conductive element of the machine, for example, at or on a corresponding tooth of a stator or of a rotor of the machine, which is formed by a laminated core. The insulating arrangement is configured to insulate the coil from the electrically conductive element, (e.g., from the laminated core forming the tooth). The insulating arrangement has a first, electrically conductive layer, which is at least partly arranged between the coil and the metallic component. Furthermore, the first layer is electrically connected to the metallic component, in order to prevent partial discharges between the insulating arrangement and the metallic component.

Abstract: An example system includes a throttle control for managing power in a hybrid propulsion system that includes an electrical propulsion unit configured to operate using electrical energy sourced from an electrical energy storage system (ESS) and/or one or more electrical generators, the throttle control comprising: a control lever movable through a plurality of positions, the plurality of positions including: a regeneration position; an off position; a maximum electric only position; a maximum continuous dual source position; and a maximum non-continuous dual source position.

Abstract: An arrangement for detecting a direction of rotation of a multi-phase electric motor includes a plurality of single-phase converters. Each single-phase converter of the plurality of single-phase converters supplies one phase of the multi-phase electric motor with current. The arrangement also includes two sensor units that are configured to determine actual values of the phase currents of the multi-phase electric motor and to transmit the actual values to the plurality of single-phase converters. The arrangement also includes a monitoring and control unit in each converter of the plurality of single-phase converters. The monitoring and control unit is configured and programmed to determine the direction of rotation and a speed of rotation of the multi-phase electric motor from the actual values.

Abstract: A gas turbine engine for an aircraft. The engine including: an engine core with a turbine, a compressor, a fan located upstream of the compressor and including a plurality of fan blades, and a core shaft connecting the turbine to the compressor; a gearbox which receives an input from the core shaft and outputs drive, via a driveshaft, to the fan so as to drive the fan at a lower rotational speed than the turbine, the drive shaft and core shaft forming a shaft system.

Abstract: Embodiments of the invention are shown in the figures, where a method for manufacturing a gearbox, the method comprising: providing a predefined interval around an integer; providing a gearbox setup; determining a speed ratio of at least two components of the gearbox setup; comparing the speed ratio with the predefined interval around the integer; and manufacturing a gearbox in accordance with the gearbox setup in dependence on the comparison.

Abstract: An aircraft hybrid propulsion system (5) comprises an internal combustion engine (10) comprising a main drive shaft (24), an electric machine (28) comprising an electric machine rotor (78), a propulsor (12) mounted to a propulsor shaft (62), and a clutch arrangement configured to selectively couple each of the gas turbine engine main drive shaft (24) and electric machine rotor (78) to the propulsor drive shaft (62). The electric machine rotor (78) is mounted coaxially with the main drive shaft (24) and the clutch arrangement comprises a first overrunning clutch (52) configured to couple the main drive shaft (24) to the propulsor drive shaft (62), and a second overrunning clutch (54) configured to couple the electric machine rotor (78) to the propulsor drive shaft (62).

Abstract: An automated method for influencing a gust load of an aircraft is provided. A torque at least of an electromotive thrust generating unit arranged on a wing of the aircraft is modified such that a root bending torque of the wing generated by the gust load is reduced. An associated apparatus, an aircraft, a computer program product, and a computer-readable medium for carrying out the method are also provided.

Abstract: The invention concerns a planetary gear box, which has a sun gear, a plurality of planet gears, a ring gear and a plurality of plain bearing pins. Here, a plain bearing pin is arranged in each planet gear, wherein the plain bearing pin and the planet gear form a lubricated plain bearing, and the plain bearing pin forms a crowning at its contact face, wherein the outer diameter of the contact face decreases from a maximum outer diameter towards at least one axial end of the contact face. The crowning of the contact face is configured such that the contact face is concavely shaped adjacent to at least one axial end of the contact face or to a cylindrical region adjoining the axial end.