A shaft failure detection apparatus for a rotating shaft of a gas turbine engine, wherein the rotating shaft transmits a torque and has a rotational speed and wherein an electric generator is connected to the rotating shaft. The shaft failure detection apparatus comprises measuring means configured to measure at least one parameter of the electric generator and/or of a power electronics device coupled to the electric generator, wherein the at least one parameter is dependent on the shaft torque, first determining means configured to determine a value representative of the shaft torque based on the measured at least one parameter, and second determining means configured to determine a shaft failure, wherein the second determining means evaluate a change in the value representative of the shaft torque determined by the first determining means.
An injector assembly for a gas turbine for introducing a gaseous fuel, liquid fuel and air into a combustion chamber, includes an injector shaft and an injector main body aligned along an injector longitudinal axis. The injector main body includes a first gas duct arranged centrally on the injector longitudinal axis, for introducing a gas flow into the combustion chamber; an air duct arranged radially around the outside of the first gas duct, and a liquid fuel injection arranged radially around the first gas duct for introducing the liquid fuel into the combustion chamber. The injector assembly introduces the gaseous fuel. The injector assembly is switchable between two configurations during operation: in a first configuration, air flows through the first gas duct, as an air injection; in a second configuration, the gaseous fuel flows through, as a gas fuel injection.
A noise filtering assembly include at least one core ring partially surrounding an insulator and a plurality of positioning rings disposed on an outer surface of the insulator. Each core ring defines a pair of opposing axial ends along a longitudinal axis and has an inner diameter within a predetermined tolerance range. Each axial end of each core ring is disposed adjacent to an adjacent positioning ring. Each positioning ring includes at least one inclined outer surface inclined at an oblique angle relative to the longitudinal axis. Within the predetermined tolerance range of the inner diameter of each core ring, each axial end of each core ring partially and slidably contacts the at least one inclined outer surface of the adjacent positioning ring.
The invention relates to a method for operating an aircraft with a gaseous fuel, in particular hydrogen, and a liquid fuel, in particular a sustainable alternative fuel and/or kerosene, wherein the gaseous fuel and the liquid fuel are supplied in parallel or alternatively to each other to a combustion chamber of at least one engine of the aircraft. An optimized method with regard to efficiency and pollutant emissions is provided in that the aircraft is operated at least temporarily with a constant flow of gaseous fuel, while the liquid fuel flow is varied.
A valve unit includes a in a housing which is subdivided, by an adjustable obturator in a fluid-tight manner in the valve space into first and second chambers separated from one another and through which fuel flows. The valve space has a first inlet for main fuel, a second inlet for pilot fuel, a first outlet for supplying fuel to an engine main stage, and a second outlet, for supplying fuel to an engine pilot stage. An elastic restoring element interacting with a fuel pressure difference between the chambers supplies an adjustment force, for positioning the obturator such that the obturator is adjustable into a closing position blocking the second outlet. The second chamber includes a further inlet for feeding a further fuel portion and a further outlet for discharging fuel from the second chamber and which remains open when the obturator is in the closing position.
A nozzle assembly for a combustion chamber of an engine has a nozzle for injecting fuel into a combustion space of the combustion chamber. The nozzle includes a main body, extending along a nozzle longitudinal axis, a nozzle head, and a nozzle bracket, connected to the main body and having a fuel feed line. The main body includes a central fuel pipe, extending along the longitudinal axis and a fuel outlet opening, and at the nozzle head, at least one air-guiding duct, spaced apart radially from the fuel pipe, with an air outlet opening. The nozzle assembly has a burner seal for sealing with respect to a combustion chamber head, the burner seal formed separately from the main body. The air-guiding duct is formed in the burner seal.
F23D 14/24 - Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone with separate air and gas feed ducts, e.g. with ducts running parallel or crossing each other at least one of the fluids being submitted to a swirling motion
F23D 14/58 - Nozzles characterised by the shape or arrangement of the outlet or outlets from the nozzle, e.g. of annular configuration
The invention relates to a method for producing a sintered hybrid component, having the steps of: producing the component in a green, brown, or sintered state, said production process including the process of producing a green body of the component in an injection molding process using an injection moldable powder-binder mixture; modifying the component by applying material onto the component using an additive manufacturing process, wherein the material applied by means of the additive manufacturing process consists of a powder-binder mixture, from which the binder can be removed and which can be sintered; removing the binder from the modified component; and sintering the modified component in order to provide a sintered hybrid component.
B22F 7/02 - Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting of composite layers
B22F 3/22 - Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sinteringApparatus specially adapted therefor for producing castings from a slip
B22F 10/18 - Formation of a green body by mixing binder with metal in filament form, e.g. fused filament fabrication [FFF]
B22F 10/64 - Treatment of workpieces or articles after build-up by thermal means
A circuit board assembly includes: a circuit board having an upper side and a lower side; at least one electrical component arranged on the lower side of the circuit board; a heat sink; and a hold-down device, wherein the hold-down device presses the circuit board against the heat sink. Furthermore, the hold-down device is configured to be spring-loaded and exert a spring force on the circuit board.
A printed circuit board (1) that has a plurality of layers (11-18), the layers (11-18) including a top circuitry layer (11), the top circuitry layer (11) configured to contact a sensor chip (2), an analog ground layer (13) arranged below the top layer (11), the analog ground layer (13) configured to be connected to an analog ground or combined with the top layer (11) in a single layer (110), and a plurality of current carrying layers (15-18) arranged below the top circuitry layer (11) and the analog ground layer (13) and configured to carry alternating currents. At protective earth layer (14) is further provided which is configured to be connected to a chassis ground, an earth ground or a protective ground, wherein the protective earth layer (14) is arranged between the analog ground layer (13) and the uppermost (15) of the current carrying layers (15-18). A printed circuit board assembly with such a printed circuit board is also provided.
G01R 15/20 - Adaptations providing voltage or current isolation, e.g. for high-voltage or high-current networks using galvano-magnetic devices, e.g. Hall-effect devices
CALIBRATION DEVICE FOR CALIBRATING VOLTAGES OF A FAULT MONITORING DEVICE, FAULT MONITORING DEVICE AND METHOD OF CALIBRATING VOLTAGES OF A FAULT MONITORING DEVICE
HLHLERRHmERRHbERRHb) are determined from the determined voltage values using linear regression. The invention further provides for a fault monitoring device and a method of calibrating voltages of a fault monitoring device.
The invention relates to a nozzle assembly for a combustor (103) of an engine (T), comprising at least one nozzle (D) for injecting fuel into a combustion chamber (1030) of the combustor (103), wherein the nozzle (D) comprises a nozzle main body (DR) extending along a nozzle longitudinal axis (L) and having a nozzle head (DK), and a nozzle holder (DH) connected to the nozzle main body (DR) and having at least one fuel supply line (1). The nozzle main body (DR) comprises a central fuel pipe (3) extending along the nozzle longitudinal axis (L) and at least two radially spaced-apart air guide channels (4, 5) on the nozzle head with a respective at least one air outlet opening.
F23D 14/58 - Nozzles characterised by the shape or arrangement of the outlet or outlets from the nozzle, e.g. of annular configuration
F23D 14/24 - Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone with separate air and gas feed ducts, e.g. with ducts running parallel or crossing each other at least one of the fluids being submitted to a swirling motion
F23R 3/14 - Air inlet arrangements for primary air inducing a vortex by using swirl vanes
13.
NOZZLE ASSEMBLY WITH A CENTRAL FUEL PIPE THAT IS SEALED AGAINST AN IN-FLOW OF AIR
The invention relates to a nozzle assembly for a combustor of an engine, including at least one nozzle for injecting fuel into a combustion chamber of the combustor, wherein the nozzle has a nozzle main body which extends along a nozzle longitudinal axis and a nozzle holder connected to the nozzle main body and having at least one fuel supply line. The nozzle main body comprises a central fuel pipe extending along the nozzle longitudinal axis and sealed against an in-flow of air, in which fuel supplied via the at least one fuel supply line can be guided within the nozzle main body up to a fuel outlet opening of the fuel pipe provided at a nozzle end of the nozzle, via which the fuel can be introduced into the combustion chamber.
The proposed solution relates to a nozzle assembly for a combustor of an engine, having at least one nozzle for injecting hydrogen into a combustion chamber of the combustor, wherein the nozzle has a nozzle main body which extends along a nozzle longitudinal axis and a nozzle head at one end of the nozzle main body and comprises a first air conduit, a fuel duct for the hydrogen to be injected, and a second air conduit. The fuel duct is arranged with a fuel exit opening for the hydrogen to be injected into the combustion chamber between the first and second air conduits with their first and second air exit openings, in relation to a radial direction running perpendicularly to the nozzle longitudinal axis. Also according to the invention, at least the second air conduit, which is situated radially further outwards, is designed and provided to provide an non-swirled air flow into the combustion chamber and the fuel duct is designed and provided to provide a non-swirled flow of hydrogen into the combustion chamber.
An electric drive system (1A-1D) comprises an electric motor (10; 10A, 10B) having a rotor (100) and a plurality of lanes (101A-101D) which are electrically isolated from one another and to which electric current can be applied independently of one another in order to drive the rotor (100); a respective supply unit (11) for each of the lanes (101A-101D); and a control system (12) which is designed to simultaneously operate at least one of the lanes (101A-101D) in a motor mode in which electric current is applied to the lane (101A-101D) via the corresponding supply unit (11) in order to convert electrical energy into kinetic energy of the rotor (100) and operate at least one of the lanes (101A-101D) in a generator mode in which electric current is provided by means of the lane (101A-101D) via the corresponding supply unit (11).
H02P 5/74 - Arrangements specially adapted for regulating or controlling the speed or torque of two or more electric motors controlling two or more AC dynamo-electric motors
B60L 3/00 - Electric devices on electrically-propelled vehicles for safety purposesMonitoring operating variables, e.g. speed, deceleration or energy consumption
B60L 58/21 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries of two or more battery modules having the same nominal voltage
A printed circuit board assembly includes a printed circuit board having an upper side and a lower side, an electrical module having an upper side and a lower side, and a holding down construction. The upper side of the electrical module is arranged on the lower side of the printed circuit board. The holding down construction includes screwing posts that are configured to be screwed against the printed circuit board. The holding down construction is arranged on the upper side of the printed circuit board and includes contact structures that are at a distance from the screwing posts and configured to rest or press on the printed circuit board at specific contact points only. The printed circuit board includes dedicated support points that correspond to the specific contact points of the holding down construction and are contacted by the specific contact points. The dedicated support points are mechanically reinforced.
The invention relates to a printed circuit board assembly having: a printed circuit board (1) which has a topside (11) and an underside (12), at least one electrical module (2) which has a topside (21) and an underside (22) and is arranged with its topside (21) against the underside (12) of the printed circuit board (1), and a heat sink (3) against which the underside (22) of the electrical module (2) rests via a heat-conducting material (4). The underside (22) of the electrical module (2) has a height profile (25), and a gap (5), in which the heat-conducting material (4) is arranged, is formed between the topside (31) of the heat sink (3) and the underside (22) of the electrical module (2). According to the invention, the heat sink (3) is structured in the area of its surface (31) in which the electrical module (2) rests with its underside (22) via the heat conducting material (4), and the structuring (35) compensates the height profile (25) of the underside (22) of the electrical module (2), such that the gap (5) is of constant height. The invention further relates to a method for producing such a printed circuit board assembly.
A combustion chamber assembly for an engine includes a combustion chamber defining a combustion space delineated by a combustion chamber wall and extending in a main flow direction from a combustion chamber head to a combustion chamber outlet. A fuel injection system is joined to the wall at the combustion chamber head and has a fuel feed for fuel and a nozzle head for injecting the fuel into the combustion space. The wall also has an integrated heat exchanger duct via which the fuel is routed within a first duct section of the heat exchanger duct which is connected to the fuel line from the combustion chamber head in the direction of the combustion chamber outlet and, after flowing through a deflection region, in a second duct section of the heat exchanger duct, back in the direction of the combustion chamber head and of the nozzle head.
The invention relates to an electric machine (1; 1′), comprising: a stator (10); a rotor (11) that can be rotated relative to the stator (10); a shaft (12) that can be rotated relative to the stator (10); and a flexible coupling element (13; 13′; 13″) having a first connecting section (130; 130′) fixed to the rotor (11) and a second connecting section (131; 131′; 131″) fixed to the shaft (12). which connecting sections have different diameters (D1, D2) and are connected to one another via an alternately curved connecting surface (132; 132′).
H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
B64D 27/30 - Aircraft characterised by electric power plants
F16D 3/76 - Yielding couplings, i.e. with means permitting movement between the connected parts during the drive with the coupling parts connected by one or more intermediate members shaped as an elastic ring centered on the axis, surrounding a portion of one coupling part and surrounded by a sleeve of the other coupling part
20.
METHOD FOR PRODUCING A COMPONENT OF AN ELECTRIC MACHINE, COMPONENT OF AN ELECTRIC MACHINE, AND ELECTRIC MOTOR IN AN AIRCRAFT PROPULSION SYSTEM INCLUDING A COMPONENT OF THIS TYPE
The invention relates to a method for producing a component (10) of an electric machine, wherein at least one permanent magnet means (1) of the component (10) is arranged on or at the component (10), together with at least one mechanical restraining means (2) for spatially fixing the at least one permanent magnet means (1), and the at least one mechanical restraining means (2) consists of a composite material or contains same, characterised in that, at least during a thermal treatment of the component (10), a means (3, F) is used for the targeted control of the magnetic field of the permanent magnet means (1).
H01F 13/00 - Apparatus or processes for magnetising or demagnetising
H02K 1/02 - Details of the magnetic circuit characterised by the magnetic material
H02K 15/035 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets on the rotor
H02K 15/121 - Impregnating, moulding insulation, heating or drying of windings, stators, rotors or machines of cores
A power distribution system includes a plurality of energy supply systems, a plurality of first electric propulsion units, and a second electric propulsion unit different from the plurality of first electric propulsion units. Each energy supply system is configured to power at least two of the first electric propulsion units and each first electric propulsion unit is configured to be powered by at least two of the energy supply systems. Further, at least a subset of the energy supply systems is configured to power the second electric propulsion unit.
B64D 35/04 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 35/02 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants
A method for controlling a drive system (1, 1') of an aircraft (2, 2'), comprising the following steps carried out by a control system (12) of the drive system (1, 1'): detecting (S10) at least one parameter which describes the operation of the drive system (1, 1'), and detecting at least one blade position of at least one blade (103, 210) of the aircraft (2, 2'); determining (S11) an operating state of the aircraft (2) using the at least one detected parameter and the at least one detected blade position; and operating (S12) at least one electric drive unit (10) of the drive system (1, 1') on the basis of a maximum value, predefined for the determined operating state, of a thrust and/or a power output of the at least one electric drive unit (10) of the drive system (1, 1').
A DC power distribution and protection system comprising: a first DC power source (21), a first load (R1), a first power bus (31, 41) connecting the first power source (21) and the first load (R01), the first power bus (31, 41) comprising a high side voltage rail (31) and a low side voltage rail (41), a first solid state power controller (SSPC_A) arranged in the high side voltage rail (31) or low side voltage rail (41) at a DC power source side (61) of the voltage rail, and a second solid state power controller (SSPC_B) arranged in the same voltage rail (31, 41) as the first solid state power controller (SSPC_A) at a load side (62) of that voltage rail (31, 41) A first bypass line (51) is provided that connects the first DC power source (21) with the first load (R1) under bypassing of the first and second solid state power controllers (SSPC_A, SSPC_B), wherein the first bypass line (51) comprises a third solid state power controller (SSPC_R), and wherein the third solid state power controller (SSPC_R) is configured to be switched on only if the first and second solid state power controllers (SSPC_A, SSPC_B) are switched off.
H02H 7/26 - Sectionalised protection of cable or line systems, e.g. for disconnecting a section on which a short-circuit, earth fault, or arc discharge has occurred
A DC power distribution and protection system comprising: a first DC power source (21) having a positive terminal (211) and a negative terminal (212), a first load (R1), a first power bus (31, 41) connecting the first power source (21) and the first load (R01), a first solid state power controller (SSPC_A) integrated into the first power bus (31, 41) at a power source side (61) of the first power bus, and a second solid state power controller (SSPC_B) integrated into the first power bus (31, 41) at a load side (62) of the first power bus A first bypass line (51) is provided that extends between an upstream switching device (SSPC_A1) of the first solid state power controller (SSPC_A) and a downstream switching device (SSPC_B2) of the second solid state power controller (SSPC_B), the first bypass line (51) bypassing a downstream switching device (SSPC_A2) of the first solid state power controller (SSPC_A) and an upstream switching device (SSPC_B1) of the second solid state power controller (SSPC_B). The first bypass line (51) comprises at least one bypass switching device (SSPC_R1, SSCP_R2, CT), and is configured to be switched on only if the downstream switching device (SSPC_A2) of the first solid state power controller (SSPC_A) and the upstream switching device (SSPC_B1) of the second solid state power controller (SSPC_B) are switched off.
H02J 1/08 - Three-wire systemsSystems having more than three wires
H02J 13/00 - Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the networkCircuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network
H02H 7/26 - Sectionalised protection of cable or line systems, e.g. for disconnecting a section on which a short-circuit, earth fault, or arc discharge has occurred
H02H 3/087 - Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition, with or without subsequent reconnection responsive to excess current for DC applications
A power distribution system that comprises a first and second energy supply systems (11, 12), first and second electric drives (21, 22) associated with first and second input protections units (31, 32), and a power network connecting the first and second energy supply systems (11, 12) with the first and second electric drives (21, 22) The power network comprises a first and second power bus (41, 42) connecting the first and second energy supply systems (11, 21) with the first and second electric drives (21, 22), a first switching unit (51) associated with the first electric drive (21), and a second switching unit (52) associated with the second electric drive (22). The first switching unit (51) comprises a first input (511) from the first power bus (41), a first output (512) to the first power bus (41) or the first electric drive (21), and a second output (513) to the second switching unit (52). The second switching unit (52) comprises a first input (521) from the second power bus (42), a first output (522) to the second power bus (42) or the second electric drive (22), and a second input (524) from the first switching unit (51). The first switching unit (51) is configured to couple its first input (511) with its first output (512) when the input protection unit (31) of first electric drive (21) is switched off and configured to couple its input (511) with its second output (513) when the input protection unit (31) of the first electric drive (21) is switched on. The second switching unit (52) is configured to couple its second input (524) with its first output (522) to receive through its second input (524) power from the first power bus (41) and to couple the received power into the second power bus (42) or the second electric drive (21).
H02J 1/08 - Three-wire systemsSystems having more than three wires
B60L 3/00 - Electric devices on electrically-propelled vehicles for safety purposesMonitoring operating variables, e.g. speed, deceleration or energy consumption
H02J 4/00 - Circuit arrangements for mains or distribution networks not specified as ac or dc
26.
ELECTRIC MACHINE HAVING AN ADDITIONAL COOLING SYSTEM
The invention relates to an electric machine (1, 1') comprising: a stator (10, 10'), a rotor (11, 11') which can be rotated relative to the stator (10, 10'), a machine controller (16) which is configured to set a power of the electric machine (1, 1') and in which a threshold value (T) is stored which determines an output which can be set as the maximum in a normal operation of the electric machine (1, 1'), a cooling system (12) for cooling the stator (10, 10') and/or the rotor (11, 11'), wherein the cooling system (12) is designed to continuously discharge at least a maximum normal-operation heat output which can be maximally delivered in normal operation of the electric machine (1, 1'), and an additional cooling system (13) with a reservoir (130) for receiving a consumable fluid (131) which can be delivered to the stator (10, 10') and/or the rotor (11, 11') in order to cool the stator (10, 10') and/or the rotor (11, 11').
H02K 9/06 - Arrangements for cooling or ventilating by ambient air flowing through the machine having means for generating a flow of cooling medium with fans or impellers driven by the machine shaft
H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
H02K 9/193 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil with provision for replenishing the cooling mediumArrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil with means for preventing leakage of the cooling medium
H02K 16/00 - Machines with more than one rotor or stator
H02K 1/04 - Details of the magnetic circuit characterised by the material used for insulating the magnetic circuit or parts thereof
H02K 3/30 - Windings characterised by the insulating material
H02K 11/33 - Drive circuits, e.g. power electronics
H02K 9/20 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil wherein the cooling medium vaporises within the machine casing
A method for gathering inflight data during operation of an electric or hybrid-electric aircraft. The aircraft includes: a swappable battery pack, connected to an electrical system of the aircraft, the swappable battery pack including a data storage module accessible via a data interface of the swappable battery pack; and a control unit, connected to the swappable battery pack via the data interface. The method includes, while the aircraft is in flight, gathering, by the control unit, the inflight data from the aircraft and saving the gathered inflight data to the data storage module of the swappable battery pack.
The invention relates to a fluid supply assembly having a line assembly from a fluid reservoir to a target location for supplying a fluid mass flow in a variable supply quantity, in particular for supplying fuel from a fuel reservoir to a combustion chamber, having a primary mass flow supplied or able to be supplied via a primary line and a secondary mass flow supplied or able to be supplied via a secondary line. An advantageous adaptation of the fluid mass flow, in particular fuel mass flow, to variable operating conditions is achieved in that disposed in the primary line and/or the secondary line is a passively operating restrictor which is invariable in its geometry and is without moving parts, by which the mass flow ratio of primary mass flow and secondary mass flow is altered as a function of the fluid mass flow supplied via the line assembly.
A multilane power distribution system includes a plurality of DC power sources and a plurality of load devices. Each DC power source powers at least two of the load devices, and each load device is powered by at least two DC power sources. The system further includes a DC connection network including power buses for connecting the DC power sources and the load devices. The power buses having a high side voltage rail for the positive voltage and a low side voltage rail for the negative voltage. At least two power buses are connectable by switchable elements, namely, a first switchable element for the high side voltage rails and a second switchable element for the low side voltage rails. One of the switchable elements is a pulse-width modulated switch that electrically connects the respective voltage rails in accordance with the pulse-width modulation.
H02M 3/158 - Conversion of DC power input into DC power output without intermediate conversion into AC by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only with automatic control of output voltage or current, e.g. switching regulators including plural semiconductor devices as final control devices for a single load
H02M 3/157 - Conversion of DC power input into DC power output without intermediate conversion into AC by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only with automatic control of output voltage or current, e.g. switching regulators with digital control
A multilane power distribution system includes a plurality of DC power sources and a plurality of load devices. Each DC power source powers at least two load devices, and each load device is powered by at least two of the DC power sources. The system further includes a DC connection network including power buses for connecting the DC power sources and the load devices. The power buses have a high side voltage rail for the positive voltage and a low side voltage rail for the negative voltage. At least two power buses are connectable by switchable elements, namely, a first switchable element for the positive voltage rails and a second switchable element for the negative voltage rails. The switchable elements, when switched on, electrically connect the terminals of two of the DC power sources connected by the respective power buses. A bypass path is provided that bypasses a switchable element.
A solid state power controller includes at least one semiconductor switch with a control terminal, a controller for generating a pulsed signal, and a gate driver circuit for receiving the pulsed signal and generating a pulsed driver signal. The gate driver circuit includes a gate driver for receiving the pulsed signal and providing a pulsed output signal, and driver signal generating device operable in a first state and a second state. The driver signal generating device receives the gate driver pulsed output signal and generates in the first state a first pulsed driver signal that operates a semiconductor switch in an active region and generates in the second state a second pulsed driver signal that operates the semiconductor switch in a saturated region. The controller is configured to set the driver signal generating device in the first or second state depending on a voltage level signal received by the controller.
A power protection system includes a first DC power source, a first load, a first power bus connecting the first power source and the first load, and a first solid state circuit breaker circuit integrated in the first power bus. The first solid state circuit breaker circuit includes a first semiconductor switch, a first capacitor arranged between the high side voltage rail and the low side voltage rail closer to the power source or to the load than the semiconductor switch, and a first inductor located such that current generated by the first capacitor when unloading in case of a short circuit at the power source or at the load passes the first inductor. The controller is configured to measure a voltage change over the first inductor and trigger an actuation signal for the first semiconductor switch if a voltage change surpasses a predetermined threshold voltage.
H02H 3/26 - Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition, with or without subsequent reconnection responsive to difference between voltages or between currentsEmergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition, with or without subsequent reconnection responsive to phase angle between voltages or between currents
H02H 1/00 - Details of emergency protective circuit arrangements
33.
METHOD FOR PRODUCING A COIL DEVICE FOR AN ELECTRIC MACHINE, COIL DEVICE FOR AN ELECTRIC MACHINE, AND ELECTRIC MACHINE
The invention relates to a method for producing a coil device (1), in particular a multi-layer coil device for an electric machine (10), wherein a) at least one electrically non-conductive fastening element (2) combined with an adhesive in the form of a wrappable tape is placed in and/or on a coil body (3) having Litz wires (5), b) at least one electrical insulating means (4) is placed on the outside of the coil body (3), in particular also on the fastening element (2), and c) the entirety of fastening element (2), coil body (3) and electrical insulating means (4) is integrally joined together as a result of pressure action (P) and/or thermal action (T), by adhesive bonding or melting of the adhesive, so as to form the coil device (1). The invention also relates to a coil device (1) produced by means of said method and to an electric machine (10) having corresponding coil devices (1).
H02K 3/34 - Windings characterised by the shape, form or construction of the insulation between conductors or between conductor and core, e.g. slot insulation
H02K 15/04 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of windings prior to their mounting into the machines
H02K 15/10 - Applying solid insulation to windings, stators or rotors, e.g. applying insulating tapes
H02K 15/12 - Impregnating, moulding insulation, heating or drying of windings, stators, rotors or machines
An electrical system (1A-1C) for an electric machine (2) comprises: at least three connections (A1-A3) for electrical connection to in each case one phase of an at least three-phase AC voltage; a first star circuit (10A-10C) with three strands (100A-100C) via each of which one of the at least three connections (A1-A3) is electrically connected to a common star point (101) of the first star circuit (10A-10C) and which each have at least (11A-11C) with three strands (110A-110C) via each of which one of the at least three connections (A1-A3) is electrically connected to a common star point (111) of the second star circuit (11A-11C) and which each have at least two tooth windings (Z) which are connected in series; and a measuring device (12), which is electrically connected between the first star circuit (10A-10C) and the second star circuit (11A-11C), for measuring an electrical variable.
H02P 25/16 - Arrangements or methods for the control of AC motors characterised by the kind of AC motor or by structural details characterised by the circuit arrangement or by the kind of wiring
B64D 27/32 - Aircraft characterised by electric power plants within, or attached to, fuselages
35.
BEARING HOLDING DEVICE AND ROLLING BEARING APPARATUS WITH A BEARING HOLDING DEVICE
A bearing holding device with an annular inner region and a flange region, extending at least approximately outwards in the radial direction, with recesses, which flange region is designed in one piece with the inner region and is narrower in the axial direction than the annular inner region, is described. The flange region is, in the circumferential region, surrounded at least in certain regions by a connection region, which is formed in one piece with the flange region and via which the inner region and the flange region can be firmly connected to a housing. Furthermore, a rolling bearing apparatus with the bearing holding device is proposed.
F16C 35/04 - Rigid support of bearing unitsHousings, e.g. caps, covers in the case of ball or roller bearings
F16C 19/06 - Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for radial load mainly with a single row of balls
F16C 35/077 - Fixing them on the shaft or housing with interposition of an element between housing and outer race ring
A bearing holding device with an annular inner region and a flange region, extending at least approximately outwards in the radial direction, with recesses, which flange region is designed in one piece with the inner region and is narrower in the axial direction than the annular inner region, is described. The flange region is, in the circumferential region, surrounded at least in certain regions by a connection region, which is formed in one piece with the flange region and via which the inner region and the flange region can be firmly connected to a housing. Furthermore, a rolling bearing apparatus with the bearing holding device is proposed.
A circuit board includes a plurality of circuit board layers arranged one on top of the other, wherein through-holes are integrated in the circuit board, wherein the through-holes are configured to receive metal screws that screw the circuit board to a heat sink. Insulating sleeves made of an insulating material are integrated into the circuit board, wherein the through-holes are formed in the circuit board in the region of the insulating sleeves.
The invention relates to a method for controlling a multi-phase electrical machine (2) comprising a stator (20) and a rotor (21), comprising the steps: identifying (S1) a short-circuit (K) in a turn of a winding (201) of the electrical machine (2) and at least one parameter describing the short-circuit (K) in the turn; setting (S2) an angle (η) of a current vector to the positive q-axis in the dq coordinate system of the rotor (21), having a negative d portion and a q portion which does not equal zero, on the basis of the at least one parameter describing the short-circuit (K) in the turn; and controlling (S3) the electrical machine (2) according to the set angle (η).
The invention relates to an engine, having—a centrifugal compressor, —an annular combustion chamber, which is arranged downstream of the centrifugal compressor in a longitudinal direction along an engine axis, —a turbine, which is arranged downstream of the annular combustion chamber in the longitudinal direction, and—arranged between the centrifugal compressor and the annular combustion chamber a guide channel arrangement, which is designed to deflect air flowing out of the centrifugal compressor. The guide channel arrangement comprises at least two different types of guide channel elements, which are designed to deflect air flowing out of the centrifugal compressor at different angles of outflow toward the engine axis and thus to deflect, with differing degrees of intensity, air flowing out of the centrifugal compressor in a circumferential direction extending around the engine axis.
The invention relates to a combustion chamber module having an annular combustion chamber, a feed device for fuel, and an injector assembly positioned in an annular configuration on a combustion chamber head and comprising injectors for feeding in the fuel. The feed device is configured for feeding in liquid and gaseous fuel. In addition to a first injector type for feeding in liquid fuel, the injector assembly has a second injector type, which is designed for feeding in gaseous fuel, in particular hydrogen, wherein the feed device can be controlled in such a way that the first injector type and the second injector type are not supplied simultaneously with fuel.
F02C 3/20 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
F23R 3/46 - Combustion chambers comprising an annular arrangement of flame tubes within a common annular casing or within individual casings
41.
STATOR FOR AN ELECTRIC MACHINE AND A CORRESPONDING METHOD OF ASSEMBLING, AN ELECTRICAL MACHINE INCLUDING THE STATOR, AND A METHOD OF OPERATING THE ELECTRICAL MACHINE
A stator includes a stator core having a plurality of stator slots that surround a circumference of the stator core. The plurality of stator slots includes six different stator slot groups. The stator further includes a plurality of wave winding coils including a first lane group and a second lane group. Each lane group includes three independent lanes. The lanes of the first lane group include wave winding coils of a first phase, a third phase, and a fifth phase, and the lanes of the second lane group include wave winding coils of a second phase, a fourth phase, and a sixth phase. The wave winding coils of each phase of each lane include a corresponding connector. Each of the wave winding coils of the same phase of different lanes of one lane group is supported by a same slot group among the six stator slot groups.
H02K 3/28 - Layout of windings or of connections between windings
B64D 27/30 - Aircraft characterised by electric power plants
H02K 15/04 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of windings prior to their mounting into the machines
Stator of an electrical machine The invention regards a stator (100) of an electrical machine. The stator comprises a plurality of teeth (1) arranged circumferentially, each tooth (1) extending in the axial direction (10). The stator further comprises circumferentially spaced and axially extending winding slots (2) formed between the teeth (1) and a plurality of insulated winding wires (3), each winding wire (3) wound to form a winding coil (30). The winding wires (3) are wound around the teeth (1) and form the winding coils (30) in accordance with a winding scheme. The winding coils (30) each comprise two straight sections (31, 32) that run in the axial direction within two of the winding slots (2) and two windings heads (33, 34) at the two ends of the straight sections (31, 32) in which the winding coils (30) are bent to connect the straight sections (31, 32). In each of the winding slots (2) the straight sections (31, 32) of at least two of the winding coils (30) are arranged, each straight section (31, 32) extending adjacent to one of the teeth (1). Axial cooling channels (4) are formed within the winding slots (2), each axial cooling channel (4) extending in the axial direction (10) while being limited in the circumferential direction by the straight sections (31, 32) of two of the winding coils (30), and means are provided for passing a liquid cooling fluid (9) directly through the axial cooling channels (4), wherein the liquid cooling fluid directly contacts the winding coils (30).
H02K 3/24 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors with channels or ducts for cooling medium between the conductors
H02K 1/20 - Stationary parts of the magnetic circuit with channels or ducts for flow of cooling medium
H02K 3/04 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors
H02K 5/20 - Casings or enclosures characterised by the shape, form or construction thereof with channels or ducts for flow of cooling medium
43.
METHOD FOR PRODUCING A NONLINEAR CYLINDRICAL SPRING AND USE OF SUCH A SPRING
A method for producing a nonlinear cylindrical spring produced by winding or coiling a spring wire having wire diameters varying over its length, and formed from a blank with a constant diameter. A drum roller shapes the blank and, between the outer lateral surface of an inner rotor driven in rotation about a central longitudinal axis and the inner lateral surface of a drum concentric with the rotor, has an annular gap which tapers continuously from an input side to an output side, the clear opening width of which, viewed in the radial direction, is greater than the diameter of the blank on the input side and equal to or smaller than the minimum wire diameter of the spring wire on the output side, and the blank is shaped by moving it into the annular gap from the input side to the output side.
A rotor assembly includes a rotating shaft having a rotation axis that defines an axial direction, permanent magnets attached to the rotating shaft, and at least one sleeve ring. The at least one sleeve ring is configured to radially retain the permanent magnets. The rotor assembly includes a sealing sleeve arranged between the permanent magnets and the at least one sleeve ring. The sealing sleeve includes a front end and a rear end, and is sealed both at a front end and at a rear end to provide for a hermetically sealed enclosure in which the permanent magnets are located.
H02K 1/02 - Details of the magnetic circuit characterised by the magnetic material
H02K 1/04 - Details of the magnetic circuit characterised by the material used for insulating the magnetic circuit or parts thereof
H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
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 σ 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.
The invention relates to a converter module (1) for a rotating electric machine (10, 11), the converter module having: a converter housing (2, 3), a converter unit (4) arranged in the converter housing (2, 3), input contacts (41) of the converter unit (4), which are arranged on the converter housing (2, 3), and output contacts (42) of the converter unit (4), which are arranged on the converter housing (2, 3). The converter module (1) is intended and designed to be electrically connected to an assigned interface (5, 6) of an electric machine (10, 11) via the output contacts (42).
A fault monitoring device for a power system includes: a first parallel circuit of resistors that includes a first branch and a second branch both connected to a high side voltage rail of the power system; and a second parallel circuit of resistors that includes a third branch and a fourth branch both connected to a low side voltage rail of the power system. The second branch includes at least two electrical resistors arranged in series, wherein at least one electrical resistor may be short-circuited by a first switch. The fourth branch includes at least two electrical resistors arranged in series, wherein at least one electrical resistor may be short-circuited by a second switch. A controller is configured to selectively switch the switches to provide for different states of the circuits and determine resistance values for the high side and low side insulation resistances of the power system.
G01R 31/3835 - Arrangements for monitoring battery or accumulator variables, e.g. SoC involving only voltage measurements
G01R 31/36 - Arrangements for testing, measuring or monitoring the electrical condition of accumulators or electric batteries, e.g. capacity or state of charge [SoC]
G01R 31/389 - Measuring internal impedance, internal conductance or related variables
H01M 10/48 - Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte
48.
HOLDING DOWN CONSTRUCTION FOR A PRINTED CIRCUIT BOARD
A holding down construction for a printed circuit board includes a grid structure having first ribs and second ribs arranged in a crossed manner, wherein the first ribs and the second ribs form intersections, and wherein the grid structure has an upper side and a lower side. The holding down construction further includes screwing posts attached to the grid structure and configured to be screwed against a printed circuit board and/or another component, and contact structures attached to the lower side of the grid structure and configured to lie against and exert a force against the printed circuit board.
An electrical machine for integration into a vehicle frame structure is provided. The vehicle frame structure includes a structural wall that at least partially encloses an inner volume. The electrical machine includes a rotor with a rotor shaft. The rotor shaft is rotatable around a rotational axis, and is connectable to a propulsor for transferring torque to or from a fluid. The electrical machine includes a first bearing unit configured to hold the rotor shaft in a rotatable manner and a second bearing unit configured to hold the rotor shaft in a rotatable manner. The first bearing unit is releasably attachable to a first wall region of the structural wall, and the second bearing unit is releasably attachable to a second wall region of the structural wall. The first wall region and the second wall region are spaced apart with respect to the rotational axis.
H02K 9/06 - Arrangements for cooling or ventilating by ambient air flowing through the machine having means for generating a flow of cooling medium with fans or impellers driven by the machine shaft
An arrangement (1) for an electric machine (2; 2') comprises: an assembly (21) having a body (10) and multiple windings (12A-12C), each of which has a first electrical conductor (120) and a second electrical conductor (121) that are wound at least in one winding section (122) along a winding axis (A) and alternate in at least one direction, in particular in the direction of the winding axis (A); multiple sensors (140) arranged at at least two points (X1, X2, X5, X6) of the first electrical conductor (120) and two points (X3, X4, X7, X8) of the second electrical conductor (121) of at least one of the windings (12A-12C) in order to measure a respective electrical variable; and a unit (131) set up to measure a first difference between the electrical variable at the two points (X1, X2, X5, X6) of the first electrical conductor (120) and a second difference between the electrical variable at the two points (X3, X4, X7, X8) of the second electrical conductor (121) and to output an output signal based on a deviation between the first difference and the second difference.
H02P 25/03 - Synchronous motors with brushless excitation
H02K 11/27 - Devices for sensing current, or actuated thereby
H02P 25/22 - Multiple windingsWindings for more than three phases
H02P 29/024 - Detecting a fault condition, e.g. short circuit, locked rotor, open circuit or loss of load
H02P 29/028 - Detecting a fault condition, e.g. short circuit, locked rotor, open circuit or loss of load the motor continuing operation despite the fault condition, e.g. eliminating, compensating for or remedying the fault
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
51.
AIRCRAFT DRIVE UNIT HAVING A MAIN AND AN AUXILIARY COOLING SYSTEM
The invention relates to a drive unit (1) for a vehicle, in particular for an aircraft (2), comprising: an electric motor (10); a main cooling system (11A; 11B) for cooling the electric motor (10); and an auxiliary cooling system (12A; 12B), which is independent of the main cooling system (11A; 11B), for cooling the electric motor (10), the main cooling system (11A; 11B) having a greater cooling capacity than the auxiliary cooling system (12A; 12B).
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
B64D 35/026 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions specially adapted for specific power plants for electric power plants the electric power plant being integral with the propeller or rotor
H02K 1/20 - Stationary parts of the magnetic circuit with channels or ducts for flow of cooling medium
H02K 3/24 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors with channels or ducts for cooling medium between the conductors
H02K 5/20 - Casings or enclosures characterised by the shape, form or construction thereof with channels or ducts for flow of cooling medium
A thermal management system for battery includes a plurality of cells, at least one inlet element having main inlet conduit and a plurality of inlet rail conduits, at least one outlet element having a main outlet conduit and a plurality of outlet rail conduits, and a plurality of battery holders. Each battery holder of the plurality of battery holders includes: a hollow wall structure surrounding a cavity in which a respective cell of the plurality of cells is to be accommodated; an inlet orifice; and an outlet orifice. The thermal management system may further include a coolant configured to be received via the main inlet conduit into a respective inlet rail conduit, wherein the coolant is configured to: circulate through the cavity of the hollow wall structure and exchange heat generated by the respective cell; and flow via a respective outlet rail conduit to the main outlet conduit.
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
B60L 58/26 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries for controlling the temperature of batteries by cooling
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
H01M 10/6568 - Liquids characterised by flow circuits, e.g. loops, located externally to the cells or cell casings
H01M 50/213 - Racks, modules or packs for multiple batteries or multiple cells characterised by their shape adapted for cells having curved cross-section, e.g. round or elliptic
An open-loop control system for a turbogenerator includes a closed-loop speed control module having: an input; a plurality of closed-loop controllers each configured to output an open-loop control signal based on a speed signal applied to the input; and an output. The closed-loop speed control module is configured to generate an output signal based on the speed signal from one or more of the open-loop control signals of the plurality of closed-loop controllers and to output a same signal at the output.
An assembly for an electric machine includes: a body; a plurality of teeth fixed to the body; a plurality of tooth windings, wherein each tooth winding includes a first electrical conductor and a second electrical conductor that are wound around the same tooth at least at one winding section along a winding axis and thereby alternate in the direction of the winding axis; and a differential protection device with a plurality of sensors, (e.g., current sensors), wherein each sensor is configured to detect a voltage at, and/or the strength of a current through, the first conductor or the second conductor at least at two points of a tooth winding of the plurality of tooth windings.
H02K 21/20 - Synchronous motors having permanent magnetsSynchronous generators having permanent magnets with stationary armatures and rotating magnets with magnets rotating within the armatures having windings each turn of which co-operates only with poles of one polarity, e.g. homopolar machine
55.
Piloting arrangement, nozzle device, gas turbine arrangement and method
A pilot arrangement for a nozzle of a gas turbine, in particular of an aircraft engine, including: a cavity extending along a longitudinal axis for conducting fuel, a narrowest flow cross section of which is larger than a flow cross section of a pilot fuel nozzle, in particular a pilot line. The pilot fuel nozzle, which adjoins the cavity in a downstream direction includes the pilot line and a pilot fuel outlet arranged at the downstream end of the pilot line, the narrowest flow cross section of which is configured to be smaller than that of the cavity. Reliable operation is made possible by virtue of an air opening arranged on the pilot arrangement in flow connection with the cavity so there can be an at least occasional flow of air through at least the cavity and the pilot fuel nozzle during the operation of the gas turbine.
B60L 15/00 - Methods, circuits or devices for controlling the propulsion of electrically-propelled vehicles, e.g. their traction-motor speed, to achieve a desired performanceAdaptation of control equipment on electrically-propelled vehicles for remote actuation from a stationary place, from alternative parts of the vehicle or from alternative vehicles of the same vehicle train
57.
PRE-SWIRL NOZZLE SYSTEM IN A GAS TURBINE AND PRE-SWIRL NOZZLE SYSTEM
The invention relates to a pre-swirl nozzle system in a gas turbine, in particular in an aircraft engine, having at least one pre-swirl nozzle, through which cooling air can flow, characterized in that the at least one pre-swirl nozzle has a region with a constant first cross section and a downstream region with a second cross section, which expands in the flow direction, in particular expands in a strictly monotonic manner.
A method for determining a shape of a mistuned blade of an impeller includes: providing a nominal blade with radially threaded-on profile elements; providing an initially mistuned blade with profile elements, the mistuned blade having a reduced or increased thickness at at least one of the profile elements compared with the nominal blade; determining the shape of the nominal blade in a hot state; determining the shape of the mistuned blade in the hot state; comparing the two shapes and determining a parameter of the mistuned blade which differs from the corresponding parameter for the nominal blade in the hot state; and changing the value of this parameter for the mistuned blade in the cold state such that the difference between the parameter for the mistuned blade and the nominal blade in the hot state no longer exists.
G01B 21/20 - Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring contours or curvatures, e.g. determining profile
59.
AIRCRAFT COMPONENT WITH A SURFACE EXPOSED TO AN AMBIENT AIR-FLOW AND A HEAT TRANSFER DEVICE AND A METHOD FOR OPERATING A HEAT TRANSFER DEVICE WITH A AIRCRAFT COMPONENT
The invention relates to an aircraft component, in particular an aircraft gas turbine (10), having a face (1) which can be flowed over or around by ambient air (L), in particular a housing (1) of the aircraft gas turbine (10) and a heat exchange apparatus (2) having at least one heat exchange face (3), characterized in that the at least one heat exchange face (3) is arranged on or in the face (1) in such a manner that it is in contact with the ambient air (L). The invention further relates to a method for operating heat exchange apparatuses.
A circuit board is disclosed that includes a plurality of circuit board layers located one on top of the other. The plurality of circuit board layers includes a topmost circuit board layer and a bottommost circuit board layer, wherein the topmost circuit board layer forms a top of the circuit board, wherein the bottommost circuit board layer forms a bottom of the circuit board, and wherein the plurality of circuit board layers together forms an end circuit-board edge that runs perpendicularly to the top and the bottom of the circuit board. The end circuit-board edge is provided with a coating made of an insulating material.
H05K 1/14 - Structural association of two or more printed circuits
H05K 3/00 - Apparatus or processes for manufacturing printed circuits
H05K 3/02 - Apparatus or processes for manufacturing printed circuits in which the conductive material is applied to the surface of the insulating support and is thereafter removed from such areas of the surface which are not intended for current conducting or shielding
H05K 3/10 - Apparatus or processes for manufacturing printed circuits in which conductive material is applied to the insulating support in such a manner as to form the desired conductive pattern
61.
POWER CONVERTER AND METHOD FOR OPERATING A POWER CONVERTER
The present invention relates to a power converter and to a method for operating same, wherein the power converter is designed to receive two input potentials DC+ and DC−, the power converter comprising a first anti-interference capacitor in order to connect the input potential DC+ capacitively to earth, a second anti-interference capacitor in order to connect the input potential DC− capacitively to earth, a first voltmeter for measuring a first voltage drop Uyp across the first anti-interference capacitor, a second voltmeter for measuring a second voltage drop Uyn across the second anti-interference capacitor, and a calculation unit which is designed to determine a DC link voltage Uzk dropping between the input potential DC+ and the input potential DC− using the first voltage drop Uyp and the second voltage drop Uyn.
The invention relates to a synchronous machine which is excited by permanent magnets and has a stator (2) and a rotor (1) which rotates adjacent to the stator (2) about a longitudinal axis (3). The rotor (1) comprises a number of surface magnets which are disposed along the circumference of the rotor (1). The surface magnets are designed as Halbach arrays (4), each of which comprises tangential segments (PM1, PM4, PM5, PM8), in which the magnetisation direction (M) is oriented predominantly in the circumferential direction, and normal segments (PM2, PM3, PM6, PM7), in which the magnetisation direction (M) is oriented predominantly in the radial direction or counter to the radial direction, and in the field of the stator (2) the tangential segments (PM1, PM14, PM5, PM8) are subjected to a radially inwardly directed force (−Fn) and the normal segments (PM2, PM3, PM6, PM7) are subjected to a radially outwardly directed force (+Fn). According to the invention, the tangential segments (PM1, PM4, PM5, PM8) and the normal segments (PM2, PM3, PM6, PM7) are shaped in such a way that, by form fitting, the tangential segments (PM1, PM4, PM5, PM8) partially compensate for the forces directed radially outwards onto the normal segments (PM2, PM3, PM6, PM7) by means of the forces directed radially inwards onto the tangential segments (PM1, PM4, PM5, PM8).
H02K 1/2783 - Surface mounted magnetsInset magnets with magnets arranged in Halbach arrays
H02K 21/16 - Synchronous motors having permanent magnetsSynchronous generators having permanent magnets with stationary armatures and rotating magnets with magnets rotating within the armatures having annular armature cores with salient poles
A power supply for an aircraft comprises: an input configured to receive electrical power from an energy source, an output for supplying electrical power, a plurality of converters, each of which being electrically connected to the input to receive electrical power from the input and being configured to convert the electrical power and to provide the converted electrical power to the output, and a control unit being configured to individually control each of the plurality of converters.
A power system for an aircraft includes at least one power distribution unit. The at least one power distribution unit includes at least one input configured to receive electrical power from at least one energy source, and at least one output configured to provide electrical power from the at least one input to at least one electrical load. The at least one power distribution unit also includes a control system configured to detect a condition, and to perform an action based on the detected condition.
H02K 21/24 - Synchronous motors having permanent magnetsSynchronous generators having permanent magnets with stationary armatures and rotating magnets with magnets axially facing the armatures, e.g. hub-type cycle dynamos
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
H02K 3/24 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors with channels or ducts for cooling medium between the conductors
66.
ELECTRICAL MACHINES FOR AIRCRAFT POWER AND PROPULSION SYSTEMS
An electrical machine for an aircraft electrical power system includes a stator having current-carrying coils and flux guiding stator iron defining one or more stator slots that house the current-carrying coils. The electrical machine further includes a rotor having a plurality of permanent magnets configured to interact with the stator to produce a torque. The electrical machine has an active parts mass, mact, which is a cumulated mass of components of the electrical machine that contribute to producing the torque. The electrical machine is configured to produce a peak rated torque, τpeak. The electrical machine has a slot current density, Jslot,peak, when producing the peak rated torque, τpeak. A value of a machine parameter, Λ, defined as: Λ=τpeak/(mact×Jslot,peak) is greater than or equal to 5 μNm3 kg−1A−1.
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
H02K 1/274 - Inner rotors the magnetisation axis of the magnets being perpendicular to the rotor axis the rotor consisting of two or more circumferentially positioned magnets
H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
67.
DRIVE DEVICE FOR AN AIRCRAFT WITH A CASING DEVICE FOR AIR GUIDING
The invention relates to a drive device (30) for an aircraft with a casing device (1) for air guiding, characterised in that the casing device (1) surrounds the drive device (30) at least partially in the peripheral direction, wherein the casing device (1) has a periodic profiling (10) running in the peripheral direction, wherein the open cross-section of the profiling (10) is orientated at least partially perpendicular to the direction of flight (F) of the aircraft, and a flow guiding device (31) running in the peripheral direction, which radially divides the cross-section of the profiling (10) into two parts, wherein a first profiling region (11) has at least one first opening (21) of a first air guiding channel (23), and a second profiling region (12) has at least one second opening (22) of a second air guiding channel (24), and air can be guided into the drive device (30) using the at least one first air guiding channel (23) and air can be guided out of the drive device (30) using the at least one second air guiding channel (24).
PP) 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.
H02P 27/04 - Arrangements or methods for the control of AC motors characterised by the kind of supply voltage using variable-frequency supply voltage, e.g. inverter or converter supply voltage
B64D 27/35 - Arrangements for on-board electric energy production, distribution, recovery or storage
H02K 1/18 - Means for mounting or fastening magnetic stationary parts on to, or to, the stator structures
H02K 3/28 - Layout of windings or of connections between windings
H02K 3/52 - Fastening salient pole windings or connections thereto
H02K 7/14 - Structural association with mechanical loads, e.g. with hand-held machine tools or fans
H02K 16/02 - Machines with one stator and two rotors
H02K 21/12 - Synchronous motors having permanent magnetsSynchronous generators having permanent magnets with stationary armatures and rotating magnets
H02K 21/14 - Synchronous motors having permanent magnetsSynchronous generators having permanent magnets with stationary armatures and rotating magnets with magnets rotating within the armatures
H02K 21/22 - Synchronous motors having permanent magnetsSynchronous generators having permanent magnets with stationary armatures and rotating magnets with magnets rotating around the armatures, e.g. flywheel magnetos
69.
Electrical machines for aircraft power and propulsion systems with air cooling of coils
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.
H02K 21/24 - Synchronous motors having permanent magnetsSynchronous generators having permanent magnets with stationary armatures and rotating magnets with magnets axially facing the armatures, e.g. hub-type cycle dynamos
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
H02K 3/24 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors with channels or ducts for cooling medium between the conductors
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
The invention relates to a segmented coil carrier (20; 20′) for an electric machine (2), comprising a plurality of separately formed, interconnected segments (1) with in each case one carrier (10) with a shaft (100) and a coil (11) surrounding the shaft (100), a groove (N) being formed between two adjacent carriers (10); and a groove wedge arranged in the groove (N).
H02K 15/02 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies
A method for producing a coil includes winding a wire in order to produce a wound coil, and stretching the wound coil from an initial state into a stretched state with an increased spread. The method includes providing the wound coil, in the stretched state, with a coating, and transferring the wound coil from the stretched state back into a state of smaller spread.
H02K 15/04 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of windings prior to their mounting into the machines
72.
Assembly for a gas turbine engine and method of attaching a blade retention plate to a rotor disk of a gas turbine engine
The invention relates to an assembly for a gas turbine engine which has a rotor disc, rotor blades and an annular blade retention plate, which adjoins the axially front side or the axially rear side of the rotor disc. The blade retention plate includes a radially outer region, which fixes the rotor blades axially, and a radially inner region, which is fixed axially by means of a securing ring in a recess on the axially front side or on the axially rear side of the rotor disc. Provision is made for the radially inner region of the blade retention plate to bear on the securing ring under axial preload. The invention relates further to a method for fastening a blade retention plate to a rotor disc of a gas turbine engine.
A stator for an electric machine comprises: —a body; —a plurality of stator teeth fixed on the body; and—a plurality of tooth windings, which each have a first electrical conductor, which runs from one end portion, via at least one winding portion around at least one stator tooth, to another end portion, and a second electrical conductor, which is electrically insulated from the first electrical conductor and which runs from one end portion, via the at least one winding portion around the same at least one stator tooth, to another end portion; wherein one end portion of each of the first and second electrical conductors of the tooth windings can be or is electrically connected to an inverter, and the other end portions of the first electrical conductors of the tooth windings are electrically interconnected at a star point.
B64D 27/30 - Aircraft characterised by electric power plants
H02K 21/20 - Synchronous motors having permanent magnetsSynchronous generators having permanent magnets with stationary armatures and rotating magnets with magnets rotating within the armatures having windings each turn of which co-operates only with poles of one polarity, e.g. homopolar machine
74.
Gas turbine engine control system and method for limiting turbine overspeed in case of a shaft failure
A gas turbine engine control system and a method for limiting turbine overspeed in case of a shaft failure. An overspeed protection system detects a shaft failure of the engine. A variable stator vane mechanism adjusts stator vanes of a compressor of the engine in their rotational position, and is activated to move at least one row of the stator vanes into a closed position which blocks air flow through the compressor in case a shaft failure is detected. Bleed valves in the compressor have closed and open positions and divert in the opened position airflow through the compressor to a bypass channel. A detection system detects directly or indirectly the position of the stator vanes, and the control system sets the bleed valves to the open position when the detection system detects that the stator vanes have moved into the closed position.
F02C 9/52 - Control of fuel supply conjointly with another control of the plant with control of working fluid flow by bleeding or by-passing the working fluid
F01D 21/02 - Shutting-down responsive to overspeed
F02C 9/54 - Control of fuel supply conjointly with another control of the plant with control of working fluid flow by throttling the working fluid, by adjusting vanes
75.
ELECTRICAL COIL OF A STATOR COMPOSED OF STRANDED WIRE, AND METHOD FOR PRODUCING SUCH AN ELECTRICAL COIL
Proposed is an electrical coil (1) that has a winding wire (10) that is wound to form a plurality of coil turns (11). The winding wire (10) has a strand (160) that comprises a multiplicity of thin, twisted individual wires (110), and the strand (160) is sheathed with a turn insulation (150). Additionally, a fixing band (21-24) is wound around the coil turns (11) in at least one portion (16), which fixing band, when the coil (1) has been compressed, locally encases and geometrically fixes the coil turns (11). The invention also relates to the associated method for producing the coil (1) for a single tooth (100) of a stator, wherein the coil is produced on a dummy winding body and is subsequently mounted onto the tooth (100).
H02K 15/04 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of windings prior to their mounting into the machines
The proposed solution relates to a fuel nozzle for the injection of hydrogen into a combustion chamber of an engine, the fuel nozzle including, for provision of a hydrogen-air mixture, a nozzle head having outflow openings (19, 21) at an end face of the nozzle head.
Multiple first outflow openings for hydrogen to be injected and at least one second outflow opening for air to be injected are present at the end face for the provision of the hydrogen-air mixture, where the at least one second outflow opening has a polygonal cross section and the multiple first outflow openings at the end face are arranged around the at least one second outflow opening.
The invention relates to a system (1) for the automatic detection of a state of a device (2), comprising: a signal acquisition means (10) for acquiring defective measurement data (D) of a physical variable characterising the device (2); and an analysis unit (11) for identifying a specified pattern (M) in the measurement data (D) acquired by the signal acquisition means (10). The analysis unit (11) is designed:— to compare at least two different pattern sections (M1-M14) of the specified pattern (M) separately from each other with the measurement data (D):— on the basis of the respective comparison, to determine at least one position of each of the pattern sections (M1-M14) in the measurement data (D):— on the basis of the positions determined and the order of the positions of the pattern sections (M1-M14), to detect the specified pattern (M) at one or more positions in the measurement data (D) and,— on the basis of the one or more positions of the specified pattern (M), to determine the state of the device (2).
A rotor of a gas turbine includes a rotating body with a platform with rotor blades arranged thereon, at least one turbine blade, the platform of the rotating body having first and second sections oriented at a respective angle of attack with respect to the engine longitudinal axis. The respective rotor blades are subject to crack growth in the state in which they are installed as intended into an engine, a respective crack spreading from a leading edge of the turbine blade as far as a predefined axial fracture crack length, at which blade fracture occurs. The first section has a smaller angle of attack than the second section, the first section extending from a leading edge of the platform as far as the axial fracture crack length. Moreover, the disclosure relates to a method for producing a rotor.
The invention relates to a device (1, 1', 1'') for an electric machine (2), comprising a holding ring (10) which extends about an axis (D) and which comprises mountings (100) for magnetically active elements (11), a housing ring (12) which is arranged coaxially to the holding ring (10), and an annular cooling segment (13', 13'') or multiple cooling segments (13A- 13D) arranged so as to form a ring (R), said cooling segment or each cooling segment at least partly forming at least one cooling path (130) for a cooling fluid (F), wherein the annular cooling segment (13', 13'') or the ring (R) of cooling segments (13A- 13D) is arranged between the holding ring (10) and the housing ring (12). The holding ring (10) and the annular cooling segment (13', 13'') or the ring (R) of cooling segments (13A- 13D) are fixed relative to each other in a form-locking manner and/or friction-locking manner, and the annular cooling segment (13', 13'') or the ring (R) of cooling segments (13A- 13D) and the housing ring (12) are fixed relative to each other in a form-locking manner and/or friction-locking manner.
A nacelle apparatus for a vertical take-off and landing (VTOL) aircraft includes a drive apparatus connected to a wing of the VTOL aircraft via a pylon apparatus and is configured to be pivoted relative to the pylon apparatus about a rotation axis between a propulsion position and a lift position. The nacelle apparatus further includes an air-conducting device having a first inlet opening on the pylon apparatus arranged in the region in which the first air flow strikes the pylon apparatus and a second inlet opening arranged on the nacelle apparatus and/or on the pylon apparatus so that a second air flow is configured to flow in through the second inlet opening in the propulsion position. The air-conducting device further includes an air distribution device with which the flowing air quantities from the first and second inlet openings are configured to be controlled inside the nacelle apparatus.
An air guidance device for a vertical take-off and landing aircraft is provided. A nacelle device with a drive device is connected via a pylon device to a wing of the vertical take-off and landing aircraft and is pivotable by a pivoting device, about an axis of rotation between a first position, such as a propulsion position, and a second position, such as a lift position, relative to the pylon device. A first inlet opening of the air guidance device is arranged on the pylon device in a region in which air conveyed by the drive device in the second position impinges on the pylon device and/or in a region of maximum propeller-generated pressure.
B64C 27/28 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
Vertical take-off and landing (VTOL) aircraft and nacelle devices for VTOL aircraft are disclosed. The nacelle device is connected via a pylon device to a wing of the vertical take-off and landing aircraft and is pivotable relative to the pylon device by a pivoting device about an axis of rotation between a first position, (e.g., a propulsion position), and a second position, (e.g., a lift position). The axis of rotation is arranged within the pylon device and/or the nacelle device, in particular on an axial center plane of the pylon device.
A structure for an electric machine includes a stator and a housing. The structure has a high-temperature torque transfer capability denoting a maximum transferrable torque between the stator and the housing at a first, higher temperature, and a low-temperature torque transfer capability denoting a maximum transferrable torque between the stator and the housing at a second, lower temperature. A ratio of the high-temperature torque transfer capability divided by the low-temperature torque transfer capability is greater than or equal to 1.2.
A structure for an electric machine includes a stator, a housing, and a cooling system for cooling the stator. The cooling system is configured to remove heat from the stator at a predefined reference temperature with a heat-removal rate that is greater than or equal to 5 kW.
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.
G05B 19/042 - Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
G05G 1/01 - Arrangements of two or more controlling members with respect to one another
G05G 1/04 - Controlling members for hand-actuation by pivoting movement, e.g. levers
G05G 5/00 - Means for preventing, limiting or returning the movements of parts of a control mechanism, e.g. locking controlling member
G05G 5/03 - Means for enhancing the operator's awareness of the arrival of the controlling member at a command or datum positionProviding feel, e.g. means for creating a counterforce
G05G 5/06 - Means for preventing, limiting or returning the movements of parts of a control mechanism, e.g. locking controlling member for holding members in one or a limited number of definite positions only
86.
SYSTEM AND METHOD FOR CONTROLLING A TREATMENT PROCESS
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.
B24B 49/00 - Measuring or gauging equipment for controlling the feed movement of the grinding tool or workArrangements of indicating or measuring equipment, e.g. for indicating the start of the grinding operation
B24B 31/06 - Machines or devices designed for polishing or abrading surfaces on work by means of tumbling apparatus or other apparatus in which the work or the abrasive material is looseAccessories therefor involving oscillating or vibrating containers
87.
Electrical machines for aircraft power and propulsion systems having a defined machine parameter based on a ratio between an active parts torque density and a power factor
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
H02K 3/24 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors with channels or ducts for cooling medium between the conductors
H02K 21/24 - Synchronous motors having permanent magnetsSynchronous generators having permanent magnets with stationary armatures and rotating magnets with magnets axially facing the armatures, e.g. hub-type cycle dynamos
An electric drive unit for an aircraft includes an electric motor, a control system having a memory in which at least two different configurations are stored, and a plug connector that is connectable to a mating plug connector. The control system is configured to scan an identification on the plug connector, select one configuration of the at least two configurations based on the identification, and operate the electric motor using the selected one configuration.
An electrical module and a method of producing such an electrical module are disclosed. The electrical module includes: a ceramic circuit carrier, an electrical component arranged on the ceramic circuit carrier, and a substrate having a potting material, wherein the ceramic circuit carrier and the electrical component are arranged in the substrate. The electrical module has an upper side that forms electrical contact areas. and stepped metal structures arranged on the upper side of the electrical module. Each metal structure has regions of different thickness. The metal structures form on their upper side in each case one of the electrical contact areas of the electrical module and contact on their underside in a region of increased thickness in each case one of the electrical contacts on the upper side of the electrical component.
A gear pump is described with at least two intermeshing gearwheels which are each rotationally fixedly connected to a shaft and separate a suction side from a delivery side. The shafts are mounted in a housing. One of the shafts can be brought into active connection with a drive unit and the other of the shafts can be brought into active connection with a pressure-control device which is to be driven by the drive unit via the two shafts. Furthermore, a drive device with the gear pump is proposed for setting an angle of attack of propeller blades of an adjustable-pitch propeller. In addition, an adjustable-pitch propeller having the drive device is described.
B64D 35/00 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions
F04C 2/18 - Rotary-piston machines or pumps of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing of other than internal-axis type with toothed rotary pistons with similar tooth forms
F15B 15/14 - Fluid-actuated devices for displacing a member from one position to anotherGearing associated therewith characterised by the construction of the motor unit of the straight-cylinder type
A system (1) for an aircraft (2, 2') comprises: an electric machine (10) which defines an axis of rotation (D), and an even number of elements (11) which each have a housing (110) and are arranged in pairs on opposite sides of the axis of rotation (D), wherein the housings (110) have end faces (111) of an identical size (111), wherein elements (11) adjacent to one another along a circumferential direction (U) about the axis of rotation (D) are arranged spaced apart from a vertical axis (Y) of an installation position of the electric machine (10), extending through the axis of rotation (D) and between the adjacent elements (11), on the aircraft (2, 2').
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.
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
H02K 3/24 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors with channels or ducts for cooling medium between the conductors
H02K 21/24 - Synchronous motors having permanent magnetsSynchronous generators having permanent magnets with stationary armatures and rotating magnets with magnets axially facing the armatures, e.g. hub-type cycle dynamos
93.
Drive system for an aircraft, aircraft having a drive system and method for operating an aircraft
A drive system for an aircraft which is constructed for operation with a liquid fuel and a gaseous fuel, includes: at least one engine having a combustion chamber for operation with the liquid fuel and/or the gaseous fuel; and per fuel at least one separate tank chamber which is or can be brought into connection in flow terms with the combustion chamber via a fuel line for supplying it with the corresponding fuel. A drive system which is optimized in terms of emissions and efficiency is provided in that the drive system is constructed in such a manner that, in the event of firing at a great height, exclusively gaseous fuel is or can be used in the at least one engine during a firing operation at a great height.
F02C 3/22 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
F02C 3/24 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being liquid at standard temperature and pressure
An electrical machine is disclosed that has a stator and a rotor. The rotor, spaced apart radially from the stator, is configured to rotate about a longitudinal axis. An air gap extends between the rotor and the stator. The rotor has a rotor shaft having two end faces and a surface. A plurality of permanent magnets is connected to the rotor shaft and adjoin the air gap. The rotor shaft has, spaced apart radially from the air gap, a plurality of cooling channels that extend in the longitudinal direction between the end faces of the rotor shaft.
The invention concerns an aircraft engine with an intake cone and a fan stage coupled thereto with a plurality of fan blades, wherein the fan blades are each connected to a drive shaft via a connecting means, wherein
a sealing device for blocking air is arranged between a blocking air space and the interior of the intake cone, and during operation of the aircraft engine a leakage air stream flows out of the blocking air space via the sealing device, characterized by at least one outflow means for the leakage air stream in a component of the aircraft engine to allow a flow of the leakage air stream into the interior of the intake cone.
A circuit board arrangement includes a circuit board having an upper side and an underside, and an electrical module, having an upper side and an underside, that is arranged with its upper side on the underside of the circuit board. The circuit board arrangement also includes a heat sink, means for providing a pressure, with which the underside of the electrical module is pressed against the heat sink, and a heat-conducting material that is arranged between the underside of the electrical module and the heat sink. The at least one electrical module is embedded in an encapsulating material that terminates with the underside of the electrical module without covering the underside of the electrical module. The encapsulating material is provided and configured to press the heat-conducting material against the heat sink in a region adjacent to the electrical module.
H01L 23/40 - Mountings or securing means for detachable cooling or heating arrangements
H01L 23/00 - Details of semiconductor or other solid state devices
H01L 25/11 - Assemblies consisting of a plurality of individual semiconductor or other solid-state devices all the devices being of a type provided for in a single subclass of subclasses , , , , or , e.g. assemblies of rectifier diodes the devices having separate containers the devices being of a type provided for in subclass
H05K 1/18 - Printed circuits structurally associated with non-printed electric components
An apparatus for an aircraft includes an electric machine and a gas turbine. The gas turbine includes a compressor, a turbine unit having a high-pressure turbine and a low-pressure turbine, and a combustion chamber. The compressor is connected via a high-pressure shaft to the high-pressure turbine, and the low-pressure turbine is connected via a low-pressure shaft directly to an output shaft of the electric machine. The high-pressure shaft and the low-pressure shaft are rotatable in different directions. The electric machine is operable as a generator and may be operated as a motor to start the gas turbine. The output shaft is connected via a gear box unit and a free-wheel to the high-pressure shaft. The free-wheel separates the connection between the output shaft of the electric machine and the high-pressure shaft in the presence of a torque flow from the high-pressure shaft in a direction of the output shaft.
The invention concerns an air inlet in a surface. The air inlet includes an opening in the surface having a longitudinal axis, wherein a fluid is intended to flow over the air inlet in the direction of the longitudinal axis, and wherein the opening has an upstream edge and a downstream edge. The air inlet furthermore comprises an outflow channel which adjoins the opening and extends at an angle to the surface, wherein the outflow channel has an inner wall with an upstream casing surface and a downstream casing surface. It is provided that the opening adjoining the upstream edge is partly or completely covered by a lattice and that the outflow channel has a bulge which protrudes into the outflow channel in the region of its upstream casing surface, constantly increases in thickness in the longitudinal direction of the outflow channel adjoining the upstream edge, forms a thickness maximum (dmax) and after the thickness maximum (dmax), constantly decreases in its thickness.
An electrical module and a circuit board arrangement including an electrical module are disclosed. The electrical module includes an upper side and an underside, the upper side having four rectangularly arranged side edges, an electrical component embedded in the electrical module, and at least three electrical solder pads formed on the upper side configured to make electrical contact with the electrical component and configured to come into contact with an associated electrical solder pad of a circuit board via a solder layer. The solder pads of the electrical module are arranged in a symmetrical arrangement on the upper side of the electrical module, and/or the solder pads are arranged axially symmetrically on the upper side of the electrical module, and/or the solder pads extend along two opposite side edges on the upper side of the electrical module.
The disclosure relates to an electronic device including a thermally and electrically conductive transmission element configured to dissipate heat from a heat source, wherein the transmission element is at a first electric potential and includes rounded edges. The electronic device further includes a heat sink at a second electric potential and an electrically insulating layer arranged between the heat sink and the transmission element in order to connect the transmission element to the heat sink in a thermally conductive manner.
patents
