Abstract: A nozzle device for feeding fuel into a combustion chamber of a gas turbine assembly, includes: a nozzle main body having nozzle openings for injecting the fuel into the combustion chamber; a nozzle bracket having a fuel line for fluidic connection between a manifold fuel line and the main body, wherein at least a portion of the fuel line is aligned along, a central longitudinal axis; and a throttle element disposed downstream of the manifold fuel line for throttling the fuel flow to a pre-specified target quantity. The throttle element includes two stages which are fluidically disposed in series, each stage having a line portion aligned along a central longitudinal axis and a flow cross section. A relaxation chamber is disposed between the stages, the flow cross section of the relaxation chamber being larger than the flow cross section of the upstream stage.

Abstract: A power electronics converter includes a substrate and a converter commutation cell including a power circuit. The power circuit includes at least one power semiconductor switching element and at least one capacitor. Each power semiconductor switching element is comprised in a power semiconductor prepackage. An electrical connection side of the respective power semiconductor prepackage is spaced apart in a z direction from the substrate so as to define a prepackage gap between the substrate and the electrical connection side. At least a portion of the prepackage gap is filled with an electrically insulating material having voids. A converter parameter ? defined as an insulation fill factor divided by a maximum void size is greater than or equal to 10/mm. The insulation fill factor is defined as a cumulated volume of the voids subtracted from a volume of the electrically insulating material divided by the volume of the electrically insulating material.

Abstract: The invention relates to a planetary gearbox in a gas turbine engine wherein a plurality of planetary gears are each mounted on a planetary gear bearing journal by a slide bearing, characterized in that a bushing is arranged in an inner bore of at least one planetary gear, which bushing spatially separates the sliding surface of the slide bearing from the inner bore of the planetary gear and the bushing is designed as a replacement part, in particular as a sacrificial part. The invention also relates to a gas turbine engine.

Abstract: The invention relates to a gear wheel for a transmission, comprising: including: a rim on which a toothing with a plurality of teeth is provided; a support point; and a web via which the rim is connected to the support point; wherein, on a side of the rim opposite the toothing and next to the web, a periodic variation of the geometry is formed that is aligned with the teeth of the toothing.

Abstract: A gas turbine engine for an aircraft that includes a nacelle, a fan, an engine core, a bypass duct extending between the engine core and the nacelle and guiding a bypass airflow through the bypass duct, and at least one non-structural strut extending in the radial direction within the bypass duct, wherein the non-structural strut includes an outside wall acting as a heat exchanger, and wherein the outside wall includes first transport means configured to transport in the outside wall at least one fluid to be cooled. It is provided that the non-structural strut further includes second transport means configured to transport a fluid to be heated, wherein the first transport means and the second transport means are configured such that the fluid to be heated is heated by the at least one fluid to be cooled and the at least one fluid to be cooled is cooled both by the bypass airflow and the fluid to be heated.

Abstract: A power Converter having power semiconductor components is disclosed herein, wherein a DC-link capacitor has a capacitance of less than 3 ?F and is not designed as a separate electrical device of the power converter, and wherein the clock frequency is greater than 1 MHz. A vehicle, (e.g., an aircraft), including a power Converter of this kind is also described.

Abstract: A vertical take-off and landing (VTOL) aircraft includes at least one electrical propulsion unit (EPU). An EPU of the at least one EPU includes a propeller or a fan and a transverse flux electric motor. The electric motor includes a stator having coils configured to carry current and a rotor arranged to interact with the stator, such that a torque for driving rotation of the propeller or the fan is generated. The rotor is configured to supply a flow of air to the coils, such that heat is removed from the coils. The coils are directly exposed to the flow of air, such that heat is exchanged directly from the coils to the flow of air. Each coil includes an effective cooling surface area directly exposed to the flow of air. An effective cooling surface area is at least 20% of a total surface area of the respective coil.

Abstract: A planetary gearbox for a gas turbine engine has a planet gear rotatably mounted on a carrier element, which is connected in a rotationally fixed manner to a planet carrier. An oil feed pocket is in a region of an external side of the carrier element, via which oil is passed into a bearing gap between the carrier element and the planet gear. The carrier element has a duct carrying oil. The duct in is provided radially within an external side of the carrier element, having a cross section which is closed in relation to the bearing gap. The duct in the flow direction of the oil has at least two sequential duct portions. The flow cross section of the duct in a transition region between an upstream duct portion and a next downstream duct portion decreases in an at least approximately step-shaped manner.

Abstract: A fan of a gas turbine engine, which has a fan disk with a multiplicity of fastening elements which are spaced apart in a circumferential direction and which project axially forwardly from the fan disk, and a nose cone which is arranged upstream of the fan disk and which is connected by means of the fastening elements to the fan disk. On an axially front side of the fan disk, there is formed a periphery which runs in encircling fashion in the circumferential direction and which runs radially at the inside in relation to the axially rear end region of the nose cone, wherein the periphery which runs in encircling fashion in the circumferential direction forms a concave indentation, in such a way that water which ingresses into a gap between the axially rear edge of the nose cone and the fan disk passes into the concave indentation.

Abstract: The electric machine includes a rotor and a stator, wherein the stator has stator coils, each with a coil core. The electric machine additionally includes an error-recovery device configured to change a magnetic flux coupling of coil cores with one another by a flux conducting element. The hybrid electric aircraft is a hybrid electric airplane, in particular, and the hybrid electric aircraft has such an electric machine.

Abstract: A guide vane wheel of a turbomachine, has a plurality of guide vanes, forming a blade row extending radially inward in a flow path of the turbomachine, and two borescope accesses. The guide vanes form two segments each with a plurality of guide vanes circumferentially spaced apart, with the two segments having the same, constant cascade pitch and the two segments spaced such that the respective outermost guide vane adjacent to the respective other segment has an enlarged spacing in the circumferential direction from the adjacent guide vane of the other segment equal to 1.3 to 1.7 times the cascade pitch, the sum of the increased spacings being equal to 3 times the cascade pitch. The increased distance between the respective two adjacent outermost guide vanes of the two segments creates an enlarged vane passage between these guide vanes where the borescope accesses are formed.

Abstract: A gear wheel of a transmission, in particular of a transmission of a gas turbine engine is described, which is designed with a groove which extends in the circumferential direction on the outer periphery of a base body of the gear wheel and in which fibers running at least in the circumferential direction are arranged. The fibers surround the base body in the circumferential direction, wherein the fibers at least partially support the operating loads on the gear wheel only on a breakage of the base body.

Abstract: A pilot arrangement for a nozzle of a gas turbine, includes a cavity extending along a longitudinal axis for conducting fuel, the narrowest flow cross section of which is larger than a flow cross section of a pilot fuel nozzle, and the pilot fuel nozzle, which adjoins the cavity downstream and includes a pilot line and a pilot fuel outlet arranged downstream of the pilot line, the narrowest flow cross section of which is smaller than that of the cavity. A compact configuration is achieved in that the cavity is arranged in a central body arranged on the longitudinal axis, a swirling element is arranged in a circumferential manner around the central body, wherein the central body and the swirling element form a swirling arrangement, and the swirling element, the central body and the pilot fuel nozzle are configured as a continuous, integral component.

Abstract: A system for monitoring and/or controlling a treatment process includes a treatment apparatus for carrying out the treatment process. The treatment apparatus includes a vibratory trough for receiving and retaining treatment media and a component support fixedly attached to the vibratory trough. The system includes a plurality of sensor devices respectively and fixedly disposed at a plurality of heights relative to the vibratory trough and configured to respectively measure a plurality of movement parameters of the treatment media at the plurality of heights and generate a plurality of movement signals corresponding to the plurality of movement parameters. The system includes a central controller configured to determine a plurality of process variables corresponding to the plurality of movement signals and control the treatment apparatus based at least on the plurality of process variables.

Abstract: A transverse flux electric motor includes a stator including coils configured to carry current and a rotor arranged to interact with the stator. The rotor is configured to produce a torque for driving rotation of the rotor. The transverse flux electric motor has an active parts mass, mact, equal to a cumulated mass of components of the transverse flux electric motor that contribute to the production of the torque. The transverse flux electric motor has an active parts torque density, ?act, defined as a peak rated torque, ?peak, divided by the active parts mass, mact. The transverse flux electric motor has a power factor equal to cos(?), wherein ? is a steady-state phase difference between a stator coil current and a stator coil voltage, and wherein the transverse flux electric motor has a machine parameter ? that is greater than or equal to 65 Nmkg?1, where ? equals ?act/cos(?).

Abstract: The disclosure relates to an electric drive system for an aircraft and to a corresponding operating method. The electric drive system includes a multiplicity of electric thrust generators, wherein each electric thrust generator has an electric motor, and a subsystem group including a multiplicity of subsystems. The thrust generators are apportioned unambiguously between the subsystems so that each subsystem includes two or more of the thrust generators. Furthermore, a control system for operating the drive system is provided, wherein the control system is configured to operate the drive system in such a way that, at least in the event that one of the subsystems of the subsystem group is faulty, an overall yawing moment which is composed of the sum of the yawing moments of the thrust generators of each non-faulty subsystem of the subsystem group essentially disappears.

Abstract: A power plant assembly, including—a turbine for driving at least one rotor shaft; —a combustion chamber for generating drive energy for the turbine; —at least one electric machine which is coupled to the rotor shaft and can be operated both in a generator mode and in a motor mode; —and at least one energy storage system which is connected to the electric machine and can store energy generated by the electric machine when the electric machine is in generator mode. A set of control electronics of the power plant assembly is configured to operate the combustion chamber using a lean fuel-air mixture and, for this purpose, to selectively operate the at least one electric machine in generator mode or in motor mode, depending on the power to be applied by the power plant assembly.

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: 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 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.