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).

Abstract: Arrangements and methods for identifying a phase-to-ground inverter short circuit in an IT (isolé-terre or isolated ground) network are provided. In the method, AC current values of all three phases and DC current values are measured and evaluated at a frequency that is higher than the clock frequency of the inverter. An AC short-circuit current is also identified by subtracting the fundamental wave from the AC current sensor values. An AC component of the DC current sensor value is also identified, and it is identified whether this component is higher than a value predefined for regular operation. The AC short-circuit current and the AC component of the DC current sensor value are also compared. A short circuit is identified for the phase if the two values of the AC short-circuit current and the AC component of the DC current sensor value are approximately equal.

Abstract: A method for monitoring at least one journal bearing for a shaft in respect to at least one acoustic event is provided. The at least one journal bearing is coupled with a gearbox, wherein a time dependent solid borne sound signal is detected by at least one solid borne sound signal sensor, the output signal of the at least one solid borne sound signal sensor is transmitted to a signal pre-processing device, frequency components of the solid borne sound signal with of more than 250 kHz are amplified in the signal pre-processing device and/or with a frequency of less than 50 kHz are attenuated in the signal pre-processing device, and the output signal of the signal pre-processing device is wirelessly transmitted via an antenna device to a signal evaluation device for the detection and/or location of the at least one acoustic event.

Abstract: A reduction gearbox which has: an input, which can be coupled to an input shaft, which has an input speed; an output, which rotates at an output speed that is lower than the input speed; and at least one statically arranged component. It is envisaged that an electric generator is integrated into the reduction gearbox, said generator comprising a rotor and a stator, wherein the rotor of the electric generator is coupled to the output of the reduction gearbox, and the stator of the electric generator is coupled to a statically arranged component of the reduction gearbox.

Abstract: A stator for an electric alternating current machine includes a stator winding arranged about a central axis and including conductor windings. The conductor windings are grouped to form electrical phases. The stator winding has winding layers. The conductor windings of a phase each have axially oriented conductor limbs that are connected to one another in two axial end regions in pairs by two winding heads. Individual coils are thus formed for each phase. As viewed in a circumferential direction, the axial conductor limbs of the individual phases follow one another in alternation in a uniform order. The winding heads of a given individual coil extend within a winding layer. A sequence of the axial conductor limbs of the respective phases and the distribution of the individual coils on the individual winding layers are chosen to avoid crossovers within the individual winding layers in the region of the winding heads.

Abstract: A rotor blade airfoil of a turbomachine, which rotor blade airfoil has: a leading edge, a trailing edge, and a profile chord length which is dependent on the height of the blade airfoil. In a side view of the blade airfoil, a maximum projected chord length his defined as the axial spacing between the axially foremost point of the leading edge and the axially rearmost point of the trailing edge of the blade airfoil in the side view under consideration. Here, the axial position of the leading edge varies in a manner dependent on the height of the blade airfoil above a front axial region.

Abstract: The disclosure relates to a stator for a rotating electrical machine. The stator includes: a laminated core which provides stator teeth with respect to an air gap of the rotating electrical machine, and a stator winding which has a plurality of tooth windings, wherein a respective one of the tooth windings is arranged on a respective one of the stator teeth and has a respective first electrical conductor arranged in a plurality of turns running around the respective stator tooth. The disclosure is based on the object of improving the electrical safety with respect to short circuits in the region of the stator winding. It is proposed that the respective tooth winding has a respective second electrical conductor which is electrically insulated from the first electrical conductor and has a plurality of turns arranged in a manner running around the respective stator tooth, wherein the respective turns of the first and second electrical conductors are arranged in a bifilar manner.

Abstract: A roller element device, in particular for a gas turbine engine, comprises an outer ring with an inner raceway, an inner ring with an outer raceway, and roller elements which are arranged between the raceways so as to roll thereon, wherein the outer ring and the inner ring are each connected via a connecting portion to a respective fixing portion for fixing to one of two components which are rotatable relative to each other about a rotation axis, and the connecting portions are formed such that the two raceways can be jointly tilted at least in portions relative to the rotation axis.

Abstract: The disclosure relates to an electric machine including a stator having a plurality of teeth and on which a winding of the electric machine is arranged, wherein a respective intermediate space is formed between neighboring teeth. The electric machine further includes a rotor that may rotate relative to the stator, wherein an air gap is formed between the stator and the rotor. The electric machine further includes a plurality of closing devices for closing the respective intermediate spaces in relation to the air gap, and wherein a respective closing device of the plurality of closing devices is arranged between neighboring teeth of the stator.

Abstract: Disclosed is an arrangement for coupling a fairing panel to an engine casing. The arrangement includes a pair of rigid brackets having a specific stiffness, wherein the pair of rigid brackets couple a first side of the fairing panel to a first side of the engine casing. The arrangement further includes a pair of flexible brackets comprising a first flexible bracket having a first stiffness and a second flexible bracket having a second stiffness more than the first stiffness. Moreover, the first stiffness and the second stiffness are less than the specific stiffness of the pair of rigid brackets. Furthermore, the pair of flexible brackets couple a second side opposite to the first side of the fairing panel to a second side opposite to the first side of the engine casing.

Abstract: Aspects of the invention regard an aircraft including: a gas turbine engine, the gas turbine engine including an intake, a nacelle, and gas turbine engine components located radially inside the nacelle; and an aircraft structure. The intake of the gas turbine engine is mounted to the aircraft structure in a manner such that its position can be adjusted. The nacelle and the gas turbine engine components located radially inside the nacelle are rigidly mounted to the aircraft structure. Other aspects of the invention regard a gas turbine engine and a method for adjusting the input of air flowing into a gas turbine engine.

Abstract: A turboshaft gas turbine engine comprises, in fluid flow series, a gas-generator compressor, a combustor, a gas-generator turbine, and a free power turbine. The expansion ratios of the turbines are dependent upon an outlet temperature of the combustor, and an expansion relationship between the turbines is defined as the ratio of expansion ratios of the turbines over a running range of non-dimensional power outputs of the gas turbine engine. A second derivative of the expansion relationship is from 0.6 to 1.0.

Abstract: The disclosure relates to a redundant electric machine for driving a propulsion means with increased operational safety. The machine may include two systems, with each system including a stator winding system and a rotor assigned thereto with permanent magnets, wherein the rotors are fastened on a common shaft for driving the propulsion means. If a fault occurs in one of the stator winding systems, the rotor, which continues to rotate, has to be prevented from inducing electric voltages in the stator winding system because this may lead to a fire in the machine. A demagnetization apparatus is therefore provided which, in a targeted manner, demagnetizes the permanent magnets of the rotor assigned to the faulty stator winding system such that the inducing of electric voltages is prevented.

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 housing is provided for an output stage with power semiconductors of a modular converter. The housing includes a stretchable hood arranged on the base plate. The housing further includes a metallic lattice formed in or on the hood and forming a Faraday cage, wherein the hood is configured to be stretchable so as to enlarge the volume enclosed by the hood in the event of an explosion of a power semiconductor as a result of the explosion energy, without destroying the hood. An output stage, a converter, and an aircraft are also provided.

Abstract: The invention relates to a propelling nozzle for a turbofan engine on a supersonic aircraft, the propelling nozzle including: a propelling nozzle wall, a duct, which is radially outwardly bounded by the propelling nozzle wall, and a central body arranged in the duct. According to the invention, the central body is connected to the propelling nozzle wall via at least one brace.

Abstract: A supporting structure arrangement for fastening an aircraft gas turbine engine to an aircraft, including: a supporting structural element of the aircraft engine and a supporting structure with at least one support and at least one bearing, by means of which the support can be connected or is connected to the aircraft, wherein the support can be connected or is connected rigidly to the supporting structural element of the aircraft engine by means of a connecting device.