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
6.
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
8.
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.
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
14.
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
16.
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.
H02M 7/537 - Conversion of DC power input into AC power output without possibility of reversal 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, e.g. single switched pulse inverters
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
21.
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
24.
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
28.
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
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
31.
METHOD FOR DETERMINING A SHAPE OF A MISTUNED BLADE OF AN IMPELLER OF A TURBOMACHINE
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
32.
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.
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.
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
35.
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.
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.
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.
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
39.
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
40.
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
42.
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
45.
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
47.
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
48.
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
59.
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
60.
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
66.
DRIVE SYSTEM FOR AN AIRCRAFT, AIRCRAFT HAVING A DRIVE SYSTEM AND METHOD FOR OPERATING AN AIRCRAFT
The invention relates to a drive system for an aircraft which is constructed for operation with a liquid fuel and a gaseous fuel, including
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.
The invention relates to a drive system for an aircraft which is constructed for operation with a liquid fuel and a gaseous fuel, including
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 can be 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.
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
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.
An electric machine includes a flow path for coolant fluid, a housing sealed off in relation to the flow path, a power supply unit, and at least one coil. The at least one coil includes at least one insulated section and contacts, wherein the contacts of the at least one coil are electrically connected inside the housing to contacts of the power supply unit and the at least one insulated section is arranged in the flow path.
H02K 9/00 - Arrangements for cooling or ventilating
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
H02K 3/32 - Windings characterised by the shape, form or construction of the insulation
H02K 5/10 - Casings or enclosures characterised by the shape, form or construction thereof with arrangements for protection from ingress, e.g. of water or fingers
H02K 5/20 - Casings or enclosures characterised by the shape, form or construction thereof with channels or ducts for flow of cooling medium
H02K 15/06 - Embedding prefabricated windings in the machines
An electric machine, (e.g., for an aircraft), includes a stator and a rotor that is rotatable relative to the stator, wherein a gap by way of which magnetic forces act between the stator and the rotor is configured between a gap face of the stator and a gap face of the rotor. The electric machine further includes a bearing installation by which the rotor is mounted so as to be rotatable relative to the stator in such a manner that the gap face of the rotor in a normal operation of the electric machine is spaced apart from the gap face of the stator. The stator and/or the rotor have/has a friction-reducing layer that at least partially forms the respective gap face and, along which the respective other gap face, is configured to slide in the event of a defect.
H02K 1/04 - Details of the magnetic circuit characterised by the material used for insulating the magnetic circuit or parts thereof
C09D 5/00 - Coating compositions, e.g. paints, varnishes or lacquers, characterised by their physical nature or the effects producedFilling pastes
C09D 127/18 - Homopolymers or copolymers of tetrafluoroethene
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
76.
ELECTRICAL MACHINE AND METHOD FOR CLEANING AN AIR GAP IN AN ELECTRICAL MACHINE
The disclosure relates to an electrical machine that includes: a stator that forms a cylindrical inner face; a rotor configured to rotate inside the stator about a longitudinal axis that defines an axial direction, the rotor forming a cylindrical outer face; and an air gap formed between the cylindrical outer face of the rotor and the cylindrical inner face of the stator. Apparatuses and mechanisms are provided for providing an air flow in the air gap, wherein the air flow flows in and/or counter to the axial direction in the air gap. The disclosure also relates to methods for cleaning an air gap in an electrical machine.
A bearing arrangement includes; a carrier supported by a support structure and a rotatable element having a support surface and being rotatably mounted by means of a bearing, the bearing having a component providing a bearing surface for the rotatable element, wherein a gap between the bearing surface and a surface of the rotatable element is filled with a fluid; wherein an elastic element arrangement with at least one deformable elastic element is provided so as to elastically act on the component of the bearing and a component of the carrier, wherein the rotatable element is supported via its support surface against the support structure with a support stiffness, and wherein the elastic element arrangement has a stiffness that is smaller than the support stiffness.
A system for finishing a surface of a workpiece. The system includes a laser unit configured to emit a laser radiation. The system further includes an attenuator disposed within the laser unit and configured to adjust optical parameters of the laser radiation. The system further includes a cavitation chamber storing a liquid medium. The workpiece is mounted within the cavitation chamber and is in contact with the liquid medium. The system further includes at least one lens configured to focus at least a portion of the laser radiation and transmit at least one laser beam towards the workpiece.
B23K 26/352 - Working by laser beam, e.g. welding, cutting or boring for surface treatment
B23K 26/06 - Shaping the laser beam, e.g. by masks or multi-focusing
B23K 26/0622 - Shaping the laser beam, e.g. by masks or multi-focusing by direct control of the laser beam by shaping pulses
B23K 26/57 - Working by transmitting the laser beam through or within the workpiece the laser beam entering a face of the workpiece from which it is transmitted through the workpiece material to work on a different workpiece face, e.g. for effecting removal, fusion splicing, modifying or reforming
The invention relates to a rotor (11) for an electric machine (1), comprising a base (110) with a magnet-receiving region (111) which is arranged concentrically with respect to a rotation axis (R) and forms a plurality of receiving pockets (112) which are arranged around the rotation axis (R) alternately closer to the rotation axis (R) and further away from the rotation axis (R), and a plurality of magnets (12A; 12B), wherein at least one or precisely one magnet (12A; 12B) is inserted into each of the receiving pockets (112).
H02K 1/2798 - Rotors axially facing stators the rotor consisting of two or more circumferentially positioned magnets where both axial sides of the stator face a rotor
H02K 1/2795 - Rotors axially facing stators the rotor consisting of two or more circumferentially positioned magnets
H02K 15/03 - Processes or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies having permanent magnets
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
H05K 1/18 - Printed circuits structurally associated with non-printed electric components
H05K 3/00 - Apparatus or processes for manufacturing printed circuits
H05K 3/32 - Assembling printed circuits with electric components, e.g. with resistor electrically connecting electric components or wires to printed circuits
H05K 3/34 - Assembling printed circuits with electric components, e.g. with resistor electrically connecting electric components or wires to printed circuits by soldering
81.
METHOD OF MANUFACTURING A PRINTED CIRCUIT BOARD ASSEMBLY
A method for producing a circuit board arrangement includes: providing a first board in which electrical components and electrical contacts assigned thereto are integrated and include upper first contact surfaces and lower second contact surfaces; providing a second board in which ceramic substrates are integrated and include upper third contact surfaces; providing a multi-layered circuit board that forms lower fourth contact surfaces; simultaneously connecting the upper side of the first board to the lower side of the circuit board and the upper side of the second board to the lower side of the first board, wherein the upper first contact surfaces of the first board are connected to the lower fourth contact surfaces of the circuit board by a first sintering layer, and the lower second contact surfaces of the first board are connected to the upper third contact surfaces of the second board by a second sintering layer.
H05K 1/14 - Structural association of two or more printed circuits
H05K 3/12 - 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 using printing techniques to apply the conductive material
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 1/18 - Printed circuits structurally associated with non-printed electric components
82.
Pilot arrangement, nozzle device, method and gas turbine arrangement
A pilot arrangement for a nozzle of a gas turbine, includes a cavity extending along a longitudinal axis for conducting fuel, the narrowest flow cross section of which is larger than a flow cross section of a pilot fuel nozzle, and the pilot fuel nozzle, which adjoins the cavity downstream and includes a pilot line and a pilot fuel outlet arranged downstream of the pilot line, the narrowest flow cross section of which is smaller than that of the cavity. A compact configuration is achieved in that the cavity is arranged in a central body arranged on the longitudinal axis, a swirling element is arranged in a circumferential manner around the central body, wherein the central body and the swirling element form a swirling arrangement, and the swirling element, the central body and the pilot fuel nozzle are configured as a continuous, integral component.
The invention concerns a combustion chamber assembly, in particular for use in an aircraft engine, including:
a peripheral wall which borders a combustion space oriented along a longitudinal axis, and
at least one, preferably a plurality of fuel nozzle(s) arranged on the input side of the combustion space for the supply of liquid fuel to the combustion space.
The invention concerns a combustion chamber assembly, in particular for use in an aircraft engine, including:
a peripheral wall which borders a combustion space oriented along a longitudinal axis, and
at least one, preferably a plurality of fuel nozzle(s) arranged on the input side of the combustion space for the supply of liquid fuel to the combustion space.
An alternative and/or combined optimised operation with fuels of different aggregate states can be achieved with comparatively low structural complexity in that the combustion chamber assembly is configured for operation with liquid and/or gaseous fuel, wherein at least one, preferably a plurality of gas supply openings arranged downstream of the fuel nozzle(s) on the peripheral wall is/are present, by means of which gaseous fuel can be introduced into the combustion space.
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. The upper side of the electrical module is arranged on the underside of the circuit board. The electrical module includes a solder pad that is in electrical contact via a solder layer with an associated solder pad of the circuit board. The electrical module includes a metallization layer located at a distance from the upper side, an electrical component that is arranged on the metallization layer and is electrically connected thereto, and at least one via extending from the solder pad on the upper side of the electrical module up to the metallization layer. A solder resist is partially arranged on the solder pad such that the at least one via, applied to the solder pad, is shielded from the solder.
H01L 23/00 - Details of semiconductor or other solid state devices
H01L 21/48 - Manufacture or treatment of parts, e.g. containers, prior to assembly of the devices, using processes not provided for in a single one of the groups or
H05K 3/34 - Assembling printed circuits with electric components, e.g. with resistor electrically connecting electric components or wires to printed circuits by soldering
A printed circuit board assembly includes a printed circuit board and a power connector. The printed circuit board includes an upper surface, a lower surface, and plated through-holes. The power connector is arranged at the upper surface of the printed circuit board and includes a plurality of pins extending through the plated through-holes. The plurality of pins are configured to extend through the plated through-holes and protrude from the lower surface of the printed circuit board. A heat spreading block located at the lower surface is provided. Ends of the plurality of pins are arranged in the heat spreading block.
A control device includes a mechanical system for moving a mechanical slide. The control device further includes a first electric drive configured to receive a position target value and to drive the mechanical system to move the mechanical slide to the position target value. The control device also includes a second electric drive configured to receive the same position target value and to drive the mechanical system to move the mechanical slide to the position target value. The two electric drives are provided and configured to jointly and simultaneously drive the mechanical system and, upon the other electric drive failing, to drive the mechanical system alone and, upon their own failure, not to obstruct the mechanical system from then being driven only by the other electric drive.
The invention relates to a blade component, a compressor or turbine stage of a gas turbine, in particular a gas turbine engine characterized in that the blade component includes at least two structural elements which can be connected together by means of a connection method, in particular sintering, and that the at least one connection face of the at least two structural elements lies on a face, wherein in particular the normal vector has, for at least a part of the face, a component perpendicular to the radial orientation of the blade component. The invention also concerns a method for manufacturing a blade component, and a gas turbine with a blade component.
A connecting apparatus for fluid connection between a fuel feed line system and a nozzle apparatus of a gas turbine arrangement, includes a gas fuel line which is surrounded by a wall for conducting a gaseous fuel, and a liquid fuel line which is surrounded by a wall for conducting a liquid fuel. Optimized operation is achieved by the connecting apparatus having at least one separate gas line portion arranged on the inlet side of the gas fuel line and a gas/liquid line portion which is arranged downstream of the separate gas line portion and within which the gas fuel line and the liquid fuel line are arranged to form a line arrangement for connection to the nozzle apparatus. The flow cross section of the gas fuel line is of at least substantially identically large configuration within the separate gas line portion and the gas/liquid line portion.
A nozzle device for feeding fuel into a combustion chamber of a gas turbine assembly, includes: a nozzle main body having nozzle openings for injecting the fuel into the combustion chamber; a nozzle bracket having a fuel line for fluidic connection between a manifold fuel line and the main body, wherein at least a portion of the fuel line is aligned along, a central longitudinal axis; and a throttle element disposed downstream of the manifold fuel line for throttling the fuel flow to a pre-specified target quantity. The throttle element includes two stages which are fluidically disposed in series, each stage having a line portion aligned along a central longitudinal axis and a flow cross section. A relaxation chamber is disposed between the stages, the flow cross section of the relaxation chamber being larger than the flow cross section of the upstream stage.
A planetary gear arrangement including a sun gear configured to rotate about an axis of rotation, a plurality of planet gears driven by the sun gear, a ring gear engaged with the plurality of planet gears and a plurality of journal pins arranged in the plurality of planet gears forming a converging gap and a diverging gap therebetween. Each journal pin has at least one longitudinal groove along an outer surface thereof, configured to guide oil on the outer surface when the oil is carried from the converging gap towards the diverging gap due to a revolving movement between a planet gear around a corresponding journal pin. A journal pin for supporting a gear and a gas turbine engine.
The invention relates to a planetary gear box, which has a sun gear, a plurality of planet gears, a ring gear, a plurality of plain bearing pins and an axially front carrier plate and an axially rear carrier plate. The plain bearing pin and the planet gear here configure a lubricated plain bearing which includes a plain bearing gap. Furthermore, the plain bearing pin, on the contact face thereof, configures a feed pocket which is provided and configured to receive oil and during the operation deliver oil in the circumferential direction to the plain bearing by way of a delivery edge. It is provided that the feed pocket is configured in the contact face of the plain bearing pin in such a manner that the delivery edge has a profile that deviates from a straight profile parallel to the longitudinal axis of the plain bearing pin.
A guide vane wheel of a turbomachine, has a plurality of guide vanes, forming a blade row extending radially inward in a flow path of the turbomachine, and two borescope accesses. The guide vanes form two segments each with a plurality of guide vanes circumferentially spaced apart, with the two segments having the same, constant cascade pitch and the two segments spaced such that the respective outermost guide vane adjacent to the respective other segment has an enlarged spacing in the circumferential direction from the adjacent guide vane of the other segment equal to 1.3 to 1.7 times the cascade pitch, the sum of the increased spacings being equal to 3 times the cascade pitch. The increased distance between the respective two adjacent outermost guide vanes of the two segments creates an enlarged vane passage between these guide vanes where the borescope accesses are formed.
H02M 7/00 - Conversion of AC power input into DC power outputConversion of DC power input into AC power output
H02M 7/537 - Conversion of DC power input into AC power output without possibility of reversal 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, e.g. single switched pulse inverters
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
An electric machine (1) having an axial air gap (S), in particular for an aircraft (2), comprising: a stator (10), a rotor (11) that is rotatable relative to the stator (10), at least one permanent magnet (12A-12D) which, on the rotor (11), is held form-fittingly on a base (111) of the rotor (11) by a holding portion (110) of the rotor (11), and a protective layer (13A-13D) which covers a side (120), facing towards the stator (10), of the at least one permanent magnet (12A-12D), wherein the holding portion (110) of the rotor (11) engages over the protective layer (13A-13D).
H02K 1/28 - Means for mounting or fastening rotating magnetic parts on to, or to, the rotor structures
H02K 1/04 - Details of the magnetic circuit characterised by the material used for insulating the magnetic circuit or parts thereof
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
The disclosure relates to an electric drive unit that includes: a motor housing that surrounds an electric motor and has an external side; cooling fins configured on the external side of the motor housing; and an electrical module having components to be cooled. The electrical module is disposed in or on an additional housing that adjoins the motor housing, wherein the additional housing on the external side thereof has cooling fins that run in the same direction as the cooling fins of the motor housing.
The invention relates to a printed circuit board assembly, comprising: a first printed circuit board (1) having an upper side (11) and a lower side (12), at least one electrical component (3) to be cooled arranged on the lower side (12) of the first printed circuit board (1), and a heat sink (4), arranged underneath the first printed circuit board (1), which is designed to cool the at least one component (3) to be cooled. A hold-down device (5), connected to the first printed circuit board (1), is provided, which is designed to exert pressure on the upper side (11) of the first printed circuit board (1). The hold-down device (5) has fastening means (53) for fastening a second printed circuit board (2) that extends parallel to the first printed circuit board (1), wherein the hold-down device (5) is arranged between the first printed circuit board (1) and the second printed circuit board (2).
The invention relates to a planetary gearbox device with a static ring gear, a rotatable planet carrier, a plurality of planet gears, each planet gear being connected to a bearing device, wherein at least one of the bearing devices is coupled to at least one lubricant scooping device and/or at least one lubricant reservoir device for collecting lubricant, in particular oil coming from the at least one bearing device, and at least one lubricant channel is for allowing a flow of the collected lubricant towards a lubrication location and/or a lubricant supply for the planetary gearbox device.
A method of designing and manufacturing a power electronics converter (1610) for an electrical power system is provided. A circuit design for the power electronics converter is selected. A shape constraint (600) for integrating the power electronics converter into the electrical power system is determined, and at least one multi-layer carrier substrate (1611) is obtained according to the determined shape constraint (600). A plurality of power semiconductor prepackages (12L1-3, 12H1-3) are obtained. Each power semiconductor prepackage (12L1-3, 12H1-3) includes a power semiconductor switching element embedded in a solid insulating material and an electrical connection extending through the solid insulating material from a terminal of the power semiconductor switching element to a connection surface of the prepackage. The power electronics converter (1610) is assembled by forming electrically conductive connections in a z-direction connecting terminals of the power semiconductor switching elements of the power semiconductor prepackages and one or more electrically conductive layers of the multi-layer carrier substrate (1611).
A power electronics converter is disclosed. The power electronics converter comprises a converter commutation cell comprising a power circuit and a gate driver circuit, the power circuit comprising at least one power semiconductor switching element and at least one capacitor. Each power semiconductor switching element has at least three terminals including a gate terminal. The gate driver circuit is electrically connected to and configured to provide switching signals to the gate terminal of each of the at least one power semiconductor switching elements. The power electronics converter may be an AC-DC power electronics converter (i.e., an inverter or a rectifier) or a DC-DC power electronics converter
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
H02M 7/219 - Conversion of AC power input into DC power output without possibility of reversal 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 in a bridge configuration
H01L 23/00 - Details of semiconductor or other solid state devices
H05K 1/11 - Printed elements for providing electric connections to or between printed circuits
H05K 1/18 - Printed circuits structurally associated with non-printed electric components
H05K 3/34 - Assembling printed circuits with electric components, e.g. with resistor electrically connecting electric components or wires to printed circuits by soldering
A circuit board arrangement includes a circuit board that has an upper side and an underside, at least one electrical component that is arranged on the underside of the circuit board, and a heat sink that has a cavity, into which the electrical component projects. In this case, the circuit board lies on the cavity and covers the cavity. The cavity of the heat sink is sealed such that neither particles nor a fluid may escape from or enter the cavity between the circuit board and the heat sink.
patents
