Abstract: A system (1) for vibration management comprises a stator (24, 45); a rotor (26) being mounted rotatably with respect to the stator (24, 45) about a rotational axis (9); one or more active devices (41A-41C) adapted to apply forces and/or moments on the rotor (26) and/or on the stator (24, 45); at least two sensors (42) for measuring vibrational parameter values with respect to two or more different positions, particularly along the rotational axis (9); and a controller (44) adapted to provide control signals to the one or more active devices (41A-41C) based on the vibrational parameter values of the at least two sensors (42) and on the respective position.

Abstract: A pressure regulating valve assembly includes: a valve having an upstream side receiving an input flow and a downstream side providing an output flow, an actuator for opening and closing the valve, including partially opening the valve, and a regulator controlling the actuator to open, close or partially open the valve. The regulator includes a sense pressure port, wherein pressure at the port is maintained constant by the regulator. A chamber has a first entry orifice, a second entry orifice and an exit orifice. The first entry orifice is connected to the upstream side, the second entry orifice is connected to the downstream side, and the exit orifice is connected to the port. The exit orifice provides that the pressure at the exit orifice lies between the pressure at the first entry orifice and the pressure at the second entry orifice.

Abstract: Embodiments of the invention are shown in the figures, where a system for vibration detection is shown, the system comprising: one or more drivelines including a rotatable component rotatable about a rotational axis relative to another component; an electrical machine having a rotor and a stator rotatable with respect to one another, the rotor being arranged to at least one of drive and be driven by a part of the driveline, the electrical machine being adapted to provide signals indicative for at least one of a motion and a force between the rotor and the stator and a torque applied on the rotor; and an analysis unit adapted to receive the signals and to detect a vibration signature of the rotatable component with respect to the other component based on the signals.

Abstract: A planetary gearbox includes a planet carrier, with a planetary gear rotatably disposed on the planet carrier, and a gear that meshes with the planetary gear, as well as a gas turbine engine having such a planetary gearbox. The planet carrier has an oil supply installation including a supply line for oil to an opening. The oil is directed out of the opening in the direction of the planetary gear and/or the gear. The oil supply installation in relation to a primary rotating direction of the planetary gear and/or the gear in front of the opening includes a shielding region which protrudes from an external side of the oil supply installation and which by way of the external side of the oil supply installation on a side that faces the primary rotating direction of the planetary gear and/or the gear, delimits an oil collection groove.

Abstract: A system including: a journal bearing having a carrier, a rotor arranged rotatable about a rotational axis relative to the carrier, and a fluid in a clearance between the rotor and the carrier. A sensor measures a vibration signal of the rotor. A control system is adapted to determine a pressure set point for the fluid in the clearance based on the vibration signal, and to provide control signals generated based on the pressure set point. An active device is adapted to modify the pressure of the fluid in the clearance based on the control signals.

Abstract: A structural subassembly which has a bearing which comprises a statically arranged outer ring and a rotatably arranged inner ring, wherein the inner ring is connected for conjoint rotation to a component that is rotatable about a longitudinal axis or said inner ring forms part of such a component, and wherein the longitudinal axis defines an axial direction of the bearing. The structural subassembly furthermore comprises a housing flange of a support structure, to which flange the statically arranged outer ring is connected. Provision is made for the outer ring to be of two-part design, wherein each part of the outer ring has a connecting element which is connected to the housing flange, wherein the housing flange is arranged between the two connecting elements in the axial direction.

Abstract: An electrical vertical take-off and landing (eVTOL) aircraft includes a plurality of electrical propulsion units (EPUs), each EPU having a propeller or a fan configured to be driven to rotate by an electrical motor arranged to receive electrical power from a respective power electronics converter. Each power electronics converter includes a converter commutation cell having a power circuit and a gate driver circuit, the power circuit including at least one power semiconductor switching element and at least one capacitor. At least one terminal of each power conducting switching element is connected to at least one electrically conductive layer of a multi-layer planar carrier substrate at an electrical connection side of a power semiconductor prepackage, which includes at least one electrically conductive layer located on an opposite side of the power semiconductor switching element to the electrical connection side of the power semiconductor prepackage.

Abstract: A gas turbine engine has an engine core, a fan arranged upstream of the engine core, and a hollow low-pressure shaft. The low-pressure shaft includes axially front and rear ends, wherein hot compressor air is applied to the axially rear end during operation. A valve is integrated into the interior of the low-pressure shaft, configured to open or close in accordance with the rotational speed of the low-pressure shaft, wherein the valve is closed from a predefined rotational speed and is open below this rotational speed, and wherein the valve, in the open state, allows hot compressor air to flow from the axially rear end of the low-pressure shaft to the axially front end of the low-pressure shaft and, in the closed state, prevents hot compressor air from flowing through the low-pressure shaft. A mechanism, when the valve is open, feeds hot compressor air outside of the fan disk.

Abstract: The invention relates to a circuit arrangement (12) for monitoring and triggering an igniter (5) of an active electrical fuse (6). The arrangement comprises: a control and evaluation unit (1), an alternating current generating unit (2) activated by the control and evaluation unit (1), an alternating current transmission unit arranged between the igniter (5) and the alternating current generating unit (2), the control and evaluation unit (1) being designed and programmed, in a first operational state, to determine the electrical resistance of the igniter (5) from a current detected on the primary side and a voltage detected on the primary side, the value of the resistance being a measure for tripping of the igniter (5), and, in a second operational state, to trigger the igniter (5) by means of the alternating current generating unit (2).

Abstract: A planetary gear box for a gas turbine engine, has a planet carrier with a carrier element and a planet gear. The planet gear is mounted rotatably via a plain bearing on the carrier element. An oil feed pocket is provided in the region of an outer side of the carrier element, via which feed pocket oil can be passed into a bearing gap between the outer side of the carrier element and an inner side of the planet gear. In the circumferential region of a main load direction of the plain bearing, the carrier element is formed with at least one channel carrying transmission oil. The channel extends in the carrier element radially inside the outer side of the carrier element, extending in the axial direction of the carrier element, and includes a cross section closed with respect to the bearing gap.

Abstract: Embodiments of the invention are shown in the figures, where a method is presented for designing a component, including designing or receiving a model of the component; determining at least one mode shape of at least a portion of the model; redesigning the model based on the determined at least one mode shape to obtain a redesigned model of the component; and manufacturing the component in accordance with the redesigned model.

Abstract: The invention relates to a bleed air extraction device for a turbomachine, which has: an axial compressor, formed in a flow path and having at least one compressor stage, which comprises a rotor and a stator, and a bleed air duct, which is provided and designed to guide a bleed air flow branched off from the flow path of the axial compressor. In this case, the bleed air duct comprises an inlet opening, which is formed downstream of a stator of the axial compressor in the radially outer flow path boundary, an axially forward wall adjoining the inlet opening, and an axially rearward wall adjoining the inlet opening. Guide means are provided, which are provided and designed for the purpose of guiding at least a portion of the bleed air flow branched off from the flow path in the direction of the axially forward wall of the bleed air duct.

Abstract: Aspects of the disclosure regard a fan case assembly for a gas turbine engine, the fan case assembly comprising a fan case having an inner surface and an outer surface, a front acoustic panel having an outer surface, and attachment means attaching the front acoustic panel outer surface to the fan case inner surface. The attachment means comprise a sliding arrangement allowing the front acoustic panel to be slid axially into the fan case. The sliding arrangement comprises a first longitudinal member and a second longitudinal member, one of the members being attached to the fan case inner surface and the other member being attached to the front acoustic panel outer surface. The attachment means further comprise removable fastening means fixing the first longitudinal member and the second longitudinal member in the axial direction.

Abstract: A power electronics converter includes 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. The gate driver circuit is configured to provide switching signals to a gate terminal of each power semiconductor switching element, and a peak rated power output of the power electronics converter is greater than 25 kW and a value of a converter parameter ? is less than or equal to 150 fFs/W, where the converter parameter ? is a total rated capacitance of the at least one capacitor of the power circuit divided by a product of the peak rated power output of the power electronics converter and a maximum switching frequency of the switching signals.

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. The power semiconductor switching element is comprised in a power semiconductor prepackage. The power semiconductor prepackage includes a power semiconductor switching element embedded in a solid insulating material, and an electrical connection extending from a terminal of the power semiconductor switching element through the solid insulating material 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. The power electronics converter includes a thermal interface layer arranged between the heat removal side of the power semiconductor prepackage and the heat sink.

Abstract: An assembly includes a plurality of electrically interconnected battery cells in a housing. An electrically insulating coolant fluid that directly surrounds the plurality of electrically interconnected battery cells flows around the plurality of electrically interconnected battery cells in the housing. An aircraft having an assembly of this type is also provided.

Abstract: A gas turbine engine, and an aircraft including the gas turbine engine. The gas turbine engine comprising: an engine core comprising a turbine, a compressor, and a shaft system connecting the turbine to the compressor. The shaft system is axially located by a thrust bearing located forward of the turbine, and the engine is configured such that, 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; and the engine further comprises an axial movement sensor configured to register a shaft break when it detects the axial movement of the rear portion of the shaft system.

Abstract: A device has two components that delimit a space containing oil. A rotationally fixed component is moved axially to press against an axial sealing surface of a rotatable component by an actuating force to seal the space in a region of another axial sealing surface. An air flow between the two sealing surfaces results in a further actuating force, acting on the fixed component in the axial direction to counteract the actuating force and move the fixed component away from the rotatable component once a defined speed of rotation of the rotatable component is reached. The rotatable component and the fixed component are supplied with oil close to the sealing surfaces. In the installed position of the fixed component, oil is passed from an upper region of the fixed component in the circumferential direction of the fixed component in the direction of a lower region of the fixed component.

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.