Hispano - Suiza Patent applications |
Patent application number | Title | Published |
20150369696 | DEVICE FOR MECHANICALLY TESTING A PINION BETWEEN AN INTERNAL TOOTHSET AND AN EXTERNAL TOOTHSET AND/OR BETWEEN TWO EXTERNAL TOOTHSETS AT AN ADJUSTABLE ANGLE - Mechanical test device including: an internal gear with internal teeth, configured to engage a pinion to be tested, the axis of the gear being fixed relative to the axis of the pinion to be tested; an internal gear support on which the gear is installed, a central movement transmission element configured to have a rotation movement about an axis fixed relative to the axis of the provided; a pinion to drive the gear, configured to engage the teeth of the gear; a mobile support on which the gear drive pinion is fixed; a support for the pinion to be tested, fixed relative to the support; and-an apparatus for putting the mobile support in rotation about the axis of the gear while the assembly composed of the pinion to be tested the gear the central transmission element and the pinion driving the gear is put into movement. | 12-24-2015 |
20150289410 | ELECTRONIC DEVICE WITH COOLING BY A LIQUID METAL SPREADER - An electronic device with cooling of a heat dissipation source, by a liquid metals spreader, the device including at least one heat dissipation source, at least one spreader through which at least one liquid metal circulation channel passes forming a loop routed below a heat dissipation source, at least one heat sink, and at least one electromagnetic pump moving the liquid metal in the at least one channel such that the liquid metal absorbs heat dissipated by a heat dissipation source and transports the absorbed heat to be evacuated by the heat sink. Each spreader includes at least two plates made of an electrical insulating material located on each side of at least one bar made of deformable material. | 10-08-2015 |
20150285153 | POWER TAKE-OFF GEARBOX ON A TURBOMACHINE, CONSISTING OF AN ASSEMBLED HOUSING - This gearbox to be assembled to a turbomachine portion and driven by a power take-off radial shaft thereof, includes several branches, the essential advantage of which is to allow a great amount of pieces of equipment to be driven to be accommodated, without implying a significant overall size in any dimension, since the gearbox remains close to the turbomachine and the pieces of equipment can be distributed on a large surface area. The housing ( | 10-08-2015 |
20150252889 | EPICYCLIC REDUCTION GEAR, NOTABLY FOR A TURBOMACHINE - An epicyclic reduction gear, for example for a turbomachine, including an internal sun gear and an external sun gear, which are coaxial, with the internal sun gear being movable in rotation about its axis, with the external sun gear being stationary. At least one planet gear is mounted to be movable in rotation on a planet carrier and meshing with both the internal sun gear and the external sun gear. The planet carrier is configured to pivot about the axis of the internal sun gear and the external sun gear, the planet gear having a cylindrical inner surface mounted to be movable in rotation around a cylindrical surface of the planet carrier. The reduction gear further includes a mechanism supplying oil at an interface between the cylindrical surfaces. | 09-10-2015 |
20150239571 | EMERGENCY POWER SUPPLY DEVICE FOR AN AIRCRAFT AND AIRCRAFT PROVIDED WITH SUCH A DEVICE - An emergency power supply device for aircraft, including at least one air intake duct configured to receive a relative airflow during a flight of the aircraft, a turbine arranged in the duct, to be driven by the relative airflow, and at least one device for generating power for the aircraft, the turbine being connected to the power-generating device to produce power for the aircraft at least under flight conditions thereof. | 08-27-2015 |
20150206652 | THREE-PHASE/TWO-PHASE ROTARY TRANSFORMER INCLUDING A SCOTT CONNECTION - A three-phase/two-phase rotary transformer includes a first single-phase rotary transformer and a second single-phase rotary transformer the first transformer including a first body defining a first slot, a first coil in the first slot, a second body defining a second slot, and a second coil in the second slot the second transformer including a third body defining a third slot, a third coil in the third slot, a fourth body defining a fourth slot, and a fourth coil in the fourth slot, wherein one terminal of the first coil is connected to the midpoint of the third coil, said the first body the first coil the third body, and said the third coil forming a three-phase portion of the transformer the second body the second coil the fourth body, and said fourth coil forming a two-phase portion of the transformer. | 07-23-2015 |
20150204246 | DRIVE GEARBOX ON A TURBOMACHINE, CONSISTING OF A DRIVE TRAIN WITH GEAR LINES EXTENDING INTO NON-PARALLEL PLANES - This A gearbox to be mounted on a turbomachine and driven by a radial drive shaft of the latter. The gearbox has a three-dimensional or sinuous shape, which can house a large quantity of equipment to be driven, without occupying a large amount of space in any dimension, since the gearbox remains close to the turbomachine and the equipment can be distributed over a large surface. The drive train of gears successively extends into several non-parallel planes and comprises an axial branch on the turbomachine and a branch forming an arc of circle around the turbomachine. | 07-23-2015 |
20150192199 | EPICYCLIC REDUCTION GEAR, NOTABLY FOR TURBOMACHINE - An epicyclic reduction gear, for example for a turbomachine, including a device forming a fluid circulation passage configured to generate a pressure drop, created by stacking at least two elements. Each element includes a passage for carrying fluid configured to generate a pressure drop and including an inlet and an outlet. The outlet, or inlet, of the passage of one of the elements is, respectively, connected to the inlet, or to the outlet, of the passage of the other element. | 07-09-2015 |
20150145626 | MAGNETICALLY SHIELDED THREE PHASE ROTARY TRANSFORMER HAVING THREE MAGNETIC CORES - A three-phase transformer including a primary portion and a secondary portion, the primary portion including a first body made of ferromagnetic material and primary coils, the secondary portion including a second body made of ferromagnetic material and secondary coils, the first body defining a first annular slot of axis A and a second annular slot of axis A, the primary coils including a first toroidal coil of axis A in the first slot, a second toroidal coil of axis A in the second slot, and one or more third toroidal coils connected in series, the third coils being wound around one of the legs, and passing via slots in the leg. | 05-28-2015 |
20150126049 | ELECTRICAL CIRCUIT FOR THE INTERCONNECTION OF AN ELECTRICAL COMPONENT, SUCH AS A POWER COMPONENT - An electrical circuit including at least one electrical component, such as a power component, and an electrical flex circuit, and at least one electrical conductor part connecting the electrical component to the flex circuit, the electrical conductor part including at least a first contact portion configured to receive in contact a contact element of the electrical power component and a second contact portion configured to receive in contact a conductive layer of the electrical flex circuit, the extent of the width of the second contact portion corresponding to the width of the flex circuit, and the extent of the length of same being adjusted to provide a contact surface that one of transmitting a density of electrical current of between 4.5 and 5.5 A/mm | 05-07-2015 |
20150108760 | ELECTRICAL POWER SUPPLY SYSTEM COMPRISING AN ASYNCHRONOUS MACHINE, AND AN ENGINE FITTED WITH SUCH AN ELECTRICAL POWER SUPPLY SYSTEM - An electrical power supply including an asynchronous machine, an arrangement for driving a rotor of the asynchronous machine in rotation by a rotor of an engine, and an electrical connection for powering electrical equipment by the rotor of the asynchronous machine. The asynchronous machine is configured to receive AC electrical power via a stator of the asynchronous machine, and it presents, over a predetermined range of drive speeds of the rotor of the asynchronous machine under drive by the rotor of the engine, efficiency in transferring electrical power from the stator to the rotor that is privileged relative to the efficiency with which rotary mechanical power is converted into electrical power. | 04-23-2015 |
20150082804 | TURBINE ENGINE INCORPORATING THERMOELECTRIC GENERATORS - A front-fan turbojet engine including at least one fluid circuit and an air/fluid heat exchanger by which the fluid is cooled by air external to the turbojet engine and a splitter for splitting a flow downstream of the fan between a primary flow and a secondary flow. The heat exchanger is associated with a thermoelectric generator including a first and a second thermal exchange surface, of which the first surface is in thermal contact with the airflow and the second surface is in thermal contact with the fluid to be cooled in the exchanger. | 03-26-2015 |
20150077207 | THREE-PHASE-TWO-PHASE STATIONARY TRANSFORMER WITH FORCED LINKED FLUX - A three-phase-two-phase transformer including a magnetic circuit, three-phase windings, and two-phase windings, wherein the magnetic circuit includes a first column, a second column, and a third column that are magnetically connected together, the three-phase windings including a first winding, a second winding, and a third winding. The two-phase windings include a fourth winding around the first column, a fifth winding around the first column, a sixth winding around the third column, and a seventh winding around the third column, the fourth winding and the seventh winding being connected in series and forming a first two-phase phase, and the fifth winding and the sixth winding being connected in series and forming a second two-phase phase. | 03-19-2015 |
20150042432 | COILED ELECTRONIC POWER COMPONENT COMPRISING A HEAT SINKING SUPPORT - A coiled electronic power component configured to be mounted on a base, the component including an axially extending magnetic core around which a plurality of turns are wound to form a magnetic coil, and at least one bracket for mounting on the base. The mounting bracket includes a first drain surface in thermal contact with the magnetic core and a second drain surface in thermal contact with the plurality of turns to drain calories from the magnetic core and from the plurality of turns to the base during operation of the component. | 02-12-2015 |
20150042431 | COILED ELECTRONIC POWER COMPONENT COMPRISING A HEAT SINKING SUPPORT - A coiled electronic power component configured to be mounted on a base, the component including an axially extending magnetic core around which a plurality of turns are wound to form a magnetic coil, and at least one bracket for mounting on the base. The mounting bracket includes at least one drain surface in thermal contact with the magnetic core and/or the plurality of turns to drain calories from the magnetic core and/or from the plurality of turns to the base during operation of the component. The mounting bracket has an equivalent thermal conductivity of greater than 400 W·m | 02-12-2015 |
20150042155 | DEVICE FOR SUPPLYING ELECTRICAL POWER TO AN AIRCRAFT ON THE GROUND - A device for supplying electrical power to an aircraft on the ground, including two electric generators driven by an auxiliary power unit. The first generator is connected by a connection/disconnection mechanism to an aircraft network and to an electric taxiing network, to supply either an AC voltage to the aircraft network when it is connected to the aircraft network, or an AC voltage or a power to the taxiing network when it is connected to the taxiing network. The second generator is connected by the connection/disconnection mechanism to the aircraft or taxiing networks to supply the AC voltage to one of those networks. | 02-12-2015 |
20150033890 | POWER TRANSMISSION SYSTEM FOR A TURBINE ENGINE - The invention relates to a power transmission system, in particular for a turbine engine such as an airplane turboprop or turbojet, the system comprising a transmission shaft ( | 02-05-2015 |
20140375128 | STABILIZING A DC ELECTRICITY NETWORK - A method of stabilizing a DC electricity network, the network including a DC voltage source powering electrical loads that are connected in parallel to terminals of the voltage source and each of which is to receive a current or voltage setpoint. The method stabilizes the network by regulating setpoints applied to the loads by a virtual stabilization impedance generated at terminals of each load, the virtual impedances being dimensioned to stabilize the network in desired operating points and in given configurations of the network including a state in which at least one load is inactive or has failed and a state in which the stabilization of a load is inactive. Each virtual impedance is generated by a non-linear regulation loop acting on the setpoint for the corresponding load. | 12-25-2014 |
20140333244 | CONTROL OF A PERMANENT-MAGNET ELECTRIC MACHINE - A method of controlling a permanent magnet synchronous machine including a stator and a rotor. The method includes determining an estimated position of the rotor, and determining a second in-phase voltage setpoint that, in alternation, is equal either to a first in-phase voltage setpoint or else to the first in-phase voltage setpoint plus a predetermined periodic signal. The determining an estimated position of the rotor includes determining a coupling term, determining a speed of rotation of the rotor as a function of the coupling term, and determining the estimated position of the rotor by integrating the speed of rotation of the rotor. | 11-13-2014 |
20140322017 | ROTARY MECHANICAL SYSTEM WITH CONTACTLESS ACTUATION - A mechanical system including: a shaft rotatably mounted about a primary axis thereof in relation to a structural element; a movable member mounted on the shaft to be fixed to the shaft for rotation therewith about the primary axis and configured to be moved selectively in relation to the shaft; a drive mechanism moving the movable member in relation to the shaft, and including a first fixed portion mounted on the structural element, a second movable portion mounted on the shaft and connected to the movable member, and an air gap electromechanical actuator between the first portion and the second portion. | 10-30-2014 |
20140150575 | ACCESSORY RELAY HAVING AN EXTENDED SERVICE LIFE - An accessory relay for a turbine engine, including a housing in which at least one gear wheel is installed for mechanically driving an accessory mounted on the housing, the gear of the wheel being driven via an input shaft supplying torque required for the mechanical drive, the shaft of the wheel being supported by at least two ball or roller bearings, and passing through at least one of the walls of the housing via an opening positioned opposite the accessory and closed by a first accessory cover attached onto the housing, wherein, for at least one of the gear wheels, the shaft thereof passes through two walls of the housing via openings closed by covers attached onto the housing, and the outer races of the two bearings are supported by the covers. | 06-05-2014 |
20140138479 | DEVICE FOR ELECTRICALLY POWERING AN AIRCRAFT ON THE GROUND - An electrical power supply device for an aircraft on the ground, the device including two electricity generators driven by an auxiliary power unit, wherein the first generator is connected by a selective connection/disconnection mechanism to an aircraft network and to an electrical taxiing network, and is configured to deliver either a first AC voltage to the aircraft network when it is connected to that network, or an AC voltage or a power to the taxiing network when it is connected to that network, and wherein the second generator is connected by the connection/disconnection mechanism to the aircraft network to deliver the first AC voltage to that network solely when the first generator is powering the taxiing network. | 05-22-2014 |
20140130628 | ACCESSORY GEARBOX FOR A GAS TURBINE - An accessory gearbox for a gas turbine, the gearbox including a front lateral face and a rear lateral face opposite from the front face and a peripheral rim closing the box, and at least one mounted gear train including a plurality of gearwheels meshing together, each gearwheel being carried by a central shaft held at each of its two ends by a respective rolling bearing, the rolling bearings of at least one of the two ends being fastened together on at least one perforated plate attached to the peripheral rim. | 05-15-2014 |
20140127000 | GAS TURBINE ACCESSORY GEARBOX INCORPORATING DECOUPLING MEANS - A gas turbine AGB has a front lateral face, a rear lateral face opposite from the front lateral face, and a peripheral rim closing the box. At least one gear train is mounted in the AGB and is made up of a plurality of gearwheels meshing together, and designed to be coupled to a drive shaft for driving an accessory. The AGB further comprises, mounted between a central shaft carrying each gearwheel and the drive shaft, a decoupling unit for decoupling the accessory and constituted by a dog clutch having axial teeth co-operating with complementary teeth of the central shaft. The dog clutch includes internal fluting engaged with the corresponding external fluting of the drive shaft. The decoupling unit is controlled by an electric actuator acting on the movement of a plunger pin having one end co-operating with an outer helical groove in the dog clutch. | 05-08-2014 |
20140008972 | ELECTRICAL POWER SUPPLY FOR AN AIRCRAFT - A generation method performed by a generator module of an electricity network of an aircraft, the electricity network including a power supply line powered by the generator module, a DC bus powered from the power supply line via a rectifier, and at least one electrical actuator powered with AC from the DC bus via an inverter. The generation method includes: delivering an AC voltage as a function of a voltage setpoint and of a voltage measured in the on-board network; and determining the voltage setpoint as a function of an operating parameter of the actuator. | 01-09-2014 |
20130285615 | MODULE FOR CONVERTING VOLTAGE BETWEEN A HIGH-VOLTAGE ELECTRICAL NETWORK OF AN AIRCRAFT AND AN ENERGY STORAGE ELEMENT - A module converting voltage between a high-voltage electrical network and at least one energy storage element an aircraft, the conversion module configured to reversibly convert between a DC voltage of the high-voltage electrical network and a DC voltage of the energy storage element, the DC voltage of the energy storage element floating relative to the DC voltage of the high-voltage electrical network and centered relative to the mass of the aircraft, the module including an input module including two filters each capable of receiving a DC voltage, a first arm and a second arm including switches, and a mechanism controlling the switches, operating per cycle of a switching period and capable of controlling at least one first switch and at least one second switch identically but offset by a half-period, whereby the first switch is open when the second switch is closed and vice versa. | 10-31-2013 |
20130234679 | AIRCRAFT POWER SUPPLY CIRCUIT INCLUDING AN ASYNCHRONOUS MACHINE - A power supply circuit for supplying electrical energy in an aircraft, the circuit including a power supply generator configured to be driven in rotation by the engine of the aircraft to power electrical equipment of the aircraft engine. The power supply generator includes an asynchronous machine connected to an excitation device. The asynchronous machine includes a rotor configured to be driven in rotation by the engine and a stator connected to the electrical equipment. The excitation device is configured to cause a reactive current of flow in the stator. | 09-12-2013 |
20130229053 | METHOD AND ARCHITECTURE FOR PROCESSING ELECTRICAL ENERGY REGENERATED FROM AN AIRCRAFT - A method and architecture processing electrical energy regenerated from an aircraft, to address drawbacks posed by customary solutions for dissipating low energy of resistors, conventionally ceramics, which require a significant volume of ceramic and an additional power converter. The method and architecture return energy to an electric generator to convert the energy into mechanical energy. The architecture includes a reversible electric generator, driven by a thermal machine and configured to deliver an AC voltage, electric actuators, and a voltage converter circuit with multiple links. The circuit includes AC voltage rectifiers for voltage originating from the generator and power converters arranged on the multiple links to drive as many electric actuators. The converter circuit also includes a mechanism for electrical energy inverse transmission applied to the generator operating in a motor mode. | 09-05-2013 |
20130206902 | POWER SUPPLY CIRCUIT FOR AN AIRCRAFT DE-ICING SYSTEM - An aircraft electrical supply circuit including: a power distribution network, onboard the aircraft, for electrical devices located in an engine of the aircraft or near the engine; and a power supply generator built into the engine of the aircraft to supply AC voltage power to a deicing or anti-icing system. The power supply generator is connected to a thrust reverser electromechanical actuator by a rectifier for supplying DC voltage power to the actuator. | 08-15-2013 |
20130177421 | ELECTRIC POWER SUPPLY FOR APPARATUSES SUPPORTED BY THE ROTOR OF AN AIRCRAFT ENGINE - An aircraft engine including: a stator; a main shaft; a first rotor; a second rotor; a transmission mechanism; a first electrical apparatus supported by the first rotor and a second electrical apparatus supported by the second rotor; at least one first field winding supported by the stator; a control unit configured to circulate direct electric current in the first field winding; at least one first armature winding supported by the first rotor and connected to the first electrical apparatus and at least one second armature winding supported by the second rotor and connected to the second electrical apparatus. | 07-11-2013 |
20130146348 | PRINTED CIRCUIT COMPRISING AT LEAST ONE CERAMIC COMPONENT - A printed circuit includes a substrate onto which at least one ceramic component is attached so as to enable the heat produced by the ceramic component to be discharged and to prevent cracks in the ceramic component and in the substrate. To this end, the ceramic component is attached onto the substrate using two connectors made of metal matrix composite material. The two connectors further have incisions so as to enable the mechanical stresses exerted in the substrate to be carried over into the connectors. | 06-13-2013 |
20130101397 | ELECTRICAL POWER SUPPLY FOR EQUIPMENT CARRIED BY A ROTARY SUPPORT - An apparatus including a fixed part, a rotary support configured to be driven in rotation relative to the fixed part, at least one item of electrical equipment carried by the rotary support, and a power supply device configured to supply electrical energy to the electrical equipment. The power supply device includes an asynchronous machine including a stator fixed to the fixed part and a rotor carried by the rotary support, and an excitation device. The stator includes an electrical circuit including at least one switch configured to switch between an open state in which the electrical circuit is open and a closed state in which the electrical circuit is closed. The rotor includes at least one winding connected to the electrical equipment. The excitation device is configured to provide a reactive current to the electrical circuit of the stator or to the winding of the rotor. | 04-25-2013 |
20130094266 | VOLTAGE INVERTER AND METHOD OF CONTROLLING SUCH AN INVERTER - A voltage inverter capable of operating in the event of a short-circuit or open-circuit fault. The voltage inverter includes: a load having three phases, each phase having a first terminal and a second terminal; first and second cells each including three branches connected together in parallel, each branch including two switches connected in series and a mid-point positioned between the two switches, each first terminal of each of the phases being connected to one of the mid-points of the first cell and each second terminal of each of the phases being connected to one of the mid-points of the second cell; and a DC voltage source, the first and second cells each being connected to the DC voltage source via two electrical isolators. | 04-18-2013 |
20130058789 | ACTUATING BLADES OF AN UNDUCTED FAN - An actuator device for actuating a swivel-mounted member carried by a rotor of a propulsion engine including: at least one electricity source; an electric actuator for swiveling the swivel-mounted member; a power supply circuit connecting the electricity source to the actuator; and an inertial device connected to the power supply circuit, the inertial device configured to convert electrical energy coming from the power supply circuit into mechanical energy, to store the mechanical energy, and to convert the mechanical energy into electrical energy for the power supply circuit. | 03-07-2013 |
20130009580 | METHOD AND DEVICE FOR CONTROLLING A POLYPHASE ELECTRICAL MACHINE - A polyphase electrical machine controlled by at least two parallel inverters, each including a number of branches equal to a number of phases of the machine and controlled by PWM. When detecting an inverter branch is faulty, the faulty branch is isolated and the phase in question is powered by each corresponding other inverter branch. The PWM is modified to make power switches of each other branch conductive in succession, without switching while absolute value of the current of the phase in question is greater than or equal to a threshold of 80% to 120% of (n−1)I | 01-10-2013 |
20120280777 | EASILY INSTALLED ROTARY TRANSFORMER - A rotary transformer configured to be installed about a rotatably movable shaft, the rotary transformer including, an annular inner core and an annular outer core for transmitting electrical energy via electromagnetic induction between the inner core and the outer core, which are coaxially mounted such that an inner surface of the outer core is capable of rotating opposite an outer surface of the inner core, wherein the inner core consists of a plurality of inner-core disjointed portions, which are assembled together by a first attachment, and wherein the outer core consists of a plurality of outer-core disjointed portions which are assembled together by a second attachment. | 11-08-2012 |
20120280641 | DEVICE FOR CONTROL OF A PMSM - A permanent magnet synchronous machine (PMSM) includes a stator and rotor powered by an inverter. A device to control the PMSM includes a sensor to sample a measurement θ | 11-08-2012 |
20120222933 | DEVICE FOR UNCOUPLING LOADED SHAFTS, FOR A POWER TRANSMISSION UNIT - A device for uncoupling a drive shaft of a piece of equipment from an input shaft. The device includes a claw including first teeth and first splines to (i) move longitudinally along a first of the shafts by co-operating with second splines borne by the second of the shafts and (ii) engage or disengage the first teeth in relation to the second teeth positioned on the second shaft. The device also includes a longitudinal movement mechanism including a stationary part acting on a longitudinally mobile piece to move the claw between a coupling position and an uncoupling position. The longitudinal movement mechanism drives the claw by co-operation between a rotationally fixed piece and a piece that is linked to the claw and rotated therewith, a longitudinal clearance being maintained during operation between the piece that is rotationally fixed and the rotated piece. | 09-06-2012 |
20120211981 | TURBINE ENGINE STARTER/GENERATOR, AND METHOD FOR THE CONTROL THEREOF - A turbine engine starter-generator including a main electrical machine including a stator and rotor with a wound rotor inducer and damper bars forming a cage, and an exciter including a stator inducer and rotor with rotor windings connected to the rotor inducer of the main electrical machine via a rotary rectifier. During a first starting stage, the electrical machine operates in asynchronous motor mode by injecting AC into its stator windings, a starting torque being generated by the damper bars, without the rotor inducer of the main electrical machine contributing significantly to generating starting torque. Then in a second starting stage, the main electrical machine operates in synchronous motor mode by injecting AC into its stator windings, while feeding its rotor inducer with DC via the exciter, the change from the first stage to the second stage taking place when rotation speed of the shaft reaches a predetermined value. | 08-23-2012 |
20120031071 | CONTROL SYSTEM FOR A TURBOREACTOR NACELLE - The invention relates to a system for controlling a plurality of actuators ( | 02-09-2012 |
20120003494 | CASING MOLDED WITH ATTACHED PIPES - A method for making a light alloy foundry part that includes at least one piping supported by a wall of the part. The method includes making the piping, making a mold reproducing a shape of the part without the piping, positioning the piping in the mold, and casting a metal for making the part. At least a portion of the piping is subjected, prior to the installation thereof in the mold, to a surface-processing to generate a thermal barrier between the portion of the piping and the casting metal, the mold including at least one hollow location around the piping for making a bridge for supporting the piping and extending from the wall of the foundry part. | 01-05-2012 |
20110284328 | ASSEMBLY INCLUDING AN AGB AND AN OIL TANK - An assembly that includes an accessory gearbox (AGB) and a tank for a liquid lubricant for a turbojet engine. The AGB includes a gear connected to parallel shafts for mechanically driving accessories. The assembly includes a housing with two compartments and a partition perpendicular to the shafts for separating the compartments, a compartment defining the accessory gearbox and a compartment defining the liquid tank. The assembly can be compact and easily manufactured. | 11-24-2011 |
20110273011 | ELECTRICAL SYSTEM FOR STARTING UP AIRCRAFT ENGINES - An electrical system ( | 11-10-2011 |
20110254475 | ELECTRIC BRAKE SYSTEM WITH MAGNETIC LOSS - An electric brake system for an electromechanical machine connected to output terminals of an inverter, input terminals of which are supplied by a DC voltage source. The system includes an electrical circuit connected between the input terminals of the inverter and including, connected in series: a mechanism dissipating electrical energy returned by the electromechanical machine to the input terminals of the inverter during a braking phase of the electromechanical machine, including an inductor wound around a magnetic circuit; and a switching mechanism to close the electrical circuit during a braking phase of the electromechanical machine and to open the electrical circuit in absence of a braking phase of the electromechanical machine. | 10-20-2011 |
20110215194 | ELECTRONIC POWER MODULE FOR AN AIRCRAFT ACTUATOR - An electronic power module, in particular an all-electric actuator for an aircraft, comprising a support having electronic components mounted thereon together with a package covering and surrounding the components and fastened on the support, the package having walls fastened on corresponding faces of an intermediate part that is fastened to the support inside the package. | 09-08-2011 |
20110169640 | TURBO-MACHINE CONTROL INSTALLATION EQUIPPED WITH A PASSIVE RADIOFREQUENCY IDENTIFICATION CHIP UNIT VERIFICATION SYSTEM - This invention relates to a control installation ( | 07-14-2011 |
20110139123 | Aircraft Engine Fuel Supply - A centrifugal pump driven by mechanical coupling with an engine has a low pressure inlet receiving fuel from a fuel circuit of an aircraft, a high pressure outlet connected to a regulator circuit for regulating the flow rate of fuel supplied to the engine, and an assistance pump unit that is electrically controlled, having an inlet connected to the aircraft fuel circuit and an outlet connected to the flow rate regulator circuit so as to deliver, via its outlet, fuel that is at a predetermined minimum pressure, the pressure of the fuel supplied to the regulator circuit being the higher of the pressures delivered by the centrifugal pump and the assistance pump unit. | 06-16-2011 |
20110121891 | ELECTRONIC CONTROL MODULE FOR A JFET TRANSISTOR - An electronic control module for a field effect transistor includes a gate, a drain and a source. The electronic control module includes: a control circuit including: a power supply able to provide a fixed potential to the gate of the field effect transistor; and an amplifier stage able to vary the potential of the source of the field effect transistor with relation to the potential of the gate of the field effect transistor; and a field effect transistor whose gate is connected to the fixed potential; and source is connected to the amplifier stage. | 05-26-2011 |
20110002782 | DEVICE FOR SUPPORTING AND SECURING A PIECE OF EQUIPMENT ON AN AIRCRAFT ENGINE OR NACELLE CASE - A device for supporting and securing a piece of equipment on an aircraft engine or nacelle case, including a vibration damper including a first part secured to the case and a second coaxial part rigidly connected to the piece of equipment, the damper associated with a safety member configured to hold the damper in place on the case in the event of damper failure or breakage. The safety member, which is independent of the damper, is mounted astride the damper and secured to the case. | 01-06-2011 |
20100283319 | ELECTRICAL POWER SUPPLY CIRCUIT IN AN AIRCRAFT FOR ELECTRICAL EQUIPMENT INCLUDING A DE-ICING CIRCUIT - The invention relates to an electrical power supply circuit in an aircraft, the circuit comprising an electricity distribution network | 11-11-2010 |
20100012234 | PROCESS FOR MANUFACTURING HOT-FORGED PARTS MADE OF A MAGNESIUM ALLOY - The present invention relates to a process for manufacturing a process for manufacturing a part made of a magnesium alloy, comprising a step of forging a block of said alloy followed by a heat treatment, characterized in that the alloy is a casting alloy based on 85% magnesium, and containing, by weight:
| 01-21-2010 |
20100003148 | ASSISTANCE AND EMERGENCY BACKUP FOR THE ELECTRICAL DRIVE OF A FUEL PUMP IN A TURBINE ENGINE - The invention relates to a system for driving a fuel pump in a turbine engine, said system comprising an electric motor and fluid flow assistance means controlled by a control valve. In said system, the control valve is a regulator valve the opening of which is controlled as a function of information representative of the speed of the pump, and/or the speed of the turbine engine, and/or the flow rate of fuel delivered to the turbine engine. As a result, operating safety of the turbine engine can be increased in the event of the electric motor failing or of its electricity generator failing, and the weight/size/cost ratios of the drive system are improved. | 01-07-2010 |
20090309461 | INTEGRATION OF A STARTER/GENERATOR MODULE IN A GAS TURBINE TRANSMISSION HOUSING - A starter/generator mechanically coupled to a gas turbine transmission housing comprises a generator ( | 12-17-2009 |
20090309432 | TURBOMACHINE WITH INTEGRAL GENERATOR/STARTER - A turbomachine such as an aircraft turbojet including an electrical generator/starter that can be mounted and dismounted by axial translation in an upstream enclosure of the turbomachine between the low-pressure compressor and the high-pressure compressor, and couple to electrical cables which extend inside the structural arms of the intermediate casing of the turbomachine. | 12-17-2009 |
20090252592 | SYSTEM FOR CONTROLLING A PLURALITY OF TURBOMACHINE DISCHARGE VALVES - The invention relates to a pneumatic unit for activating a plurality of discharge valves of a turbomachine, the pneumatic unit having activation outlets corresponding to the number of discharge valves forming said plurality of discharge valves, and a single control input receiving a single control signal from an electronic control unit, the control signal serving to act on a control winding of a manifold means having outlets that form said activation outlets. | 10-08-2009 |
20090235631 | TURBOMACHINE CONTROL SYSTEM - A turbomachine control system comprising an auxiliary hydraulic circuit with an auxiliary hydraulic pump, at least one hydraulic actuator, and at least one servo-valve, the auxiliary pump powering the actuator via the servo-valve. The auxiliary hydraulic circuit is connected in parallel with the main fuel or lubricating oil circuit of the turbomachine. Said auxiliary pump is driven by an electric motor. | 09-24-2009 |
20090232640 | ASSEMBLY FOR DRIVING GAS TURBINE ACCESSORIES - The invention provides an assembly for driving accessories of a gas turbine, the assembly comprising: a gearbox having a front side face and a rear side face opposite the front face and having mounted therein a first gear train made up of three toothed wheels meshing with one another, and a second gear train made up of four toothed wheels meshing with one another; a power transmission shaft that is coupled in rotation with the first and second gear trains by means of a toothed wheel pair, and that emerges from the front side face of the gearbox; and nine distinct gas turbine accessories mounted against the side faces of the gearbox, and each including a respective drive shaft that is coupled in rotation with one of the toothed wheels of the two gear trains. | 09-17-2009 |
20090173810 | TWO-STAGE FUEL INJECTOR - This injector with two valves ( | 07-09-2009 |
20090120098 | GAS TURBINE ENGINE COMPRISING A STARTER IN THE AUXILIARY GEAR BOX - A gas turbine engine incorporating a starter mounted on the gear box | 05-14-2009 |
20090094974 | FUEL FEED CIRCUIT FOR AN AIRCRAFT ENGINE - A head loss element is interposed between the outlet from the pump delivering high pressure fuel and the pipe feeding combustion chamber injectors. A servo-valve for feeding a hydraulic actuator of a variable-geometry component of the engine has an HP admission inlet connected to the outlet from the pump upstream from the head loss element and an LP outlet connected to the feed pipe downstream from the head loss element. Thus, the flow rate taken upstream from the head loss element for driving the actuator is compensated by the flow rate reinjected downstream from the head loss element, thereby avoiding any movement of the variable-geometry component giving rise to a disturbance in the flow rate delivered to the injectors. | 04-16-2009 |
20090078075 | SYSTEM FOR GEARING - A system for gearing, the system comprising a toothed wheel mounted on a shaft, the wheel being pierced by channels fed with lubricant, each channel opening out to the toothed periphery of the wheel. Said wheel is mounted on an end portion of the shaft, so as to be capable of being rotated by said shaft, said end portion being hollow so as to present an inside chamber, said chamber opening out to the end of the shaft via an orifice. Said channels communicate with said chamber. The system includes an injector for injecting lubricant into the chamber, the injector being situated outside the chamber and facing said orifice in such a manner as to inject the lubricant through said orifice, the lubricant penetrating into and flowing along the channels to the toothed periphery of the wheel under the effect of centrifugal force associated with rotation of the shaft. | 03-26-2009 |
20080308316 | Elbow Connection for Multiple-Wire Electric Cable - This invention relates to an elbow connection ( | 12-18-2008 |
20080262663 | METHOD FOR MONITORING PLANE ENGINES - A method for monitoring plane engines The present invention relates to a method for monitoring engines of a plane comprising at least two engines (m | 10-23-2008 |
20080258560 | Electric Supply for an Aircraft Gas Turbine Engine Equipment - A device supplying electricity power to and actuating equipments of a gas turbine airplane engine, including an electricity power supply circuit dedicated to the engine and distinct from an electricity network on board the plane and excitation, control or servo circuits for pieces of electrical equipment of the engine. The engine electrical power supply circuit includes a first bus distributing DC or AC voltage to excitation, control or servo circuits for first pieces of electrical equipment of the engine, a second bus distributing DC or AC voltage to excitation, control or servo circuits for other pieces of electrical equipment of the engine requiring higher electrical power compared with the first pieces of equipment, and a third bus connected to receive power from an electricity source such as an airplane on-board electricity distribution network or an electricity generator dedicated to the engine and driven thereby. The third bus supplies the first and second bus with electricity power. | 10-23-2008 |
20080238098 | DISTRIBUTED ARCHITECTURE FOR A GAS-TURBINE STARTER/GENERATOR - A gas-turbine starter/generator comprises: a generator module comprising a first casing, a generator housed in the first casing, and a first shaft constrained to rotate with the rotor of the generator, projecting from the first casing, and carrying a first mechanical coupling member; an exciter module, comprising a second casing, an exciter housed in the second casing, and a second shaft distinct from the first shaft, constrained to rotate with the rotor of the exciter, projecting from the second casing, and carrying a second mechanical coupling member; and an electrical connection comprising a rectifier and at least one connector for connecting the secondary circuit of the exciter to the primary circuit of the generator. The mechanical coupling members are coupled to a common gearwheel or to respective different gearwheels of a gearbox of the gas turbine. | 10-02-2008 |
20080230127 | ACTUATOR POSITION CONTROL DEVICE USING A FAIL FREEZE SERVO-VALVE - The actuator ( | 09-25-2008 |
20080209914 | DEVICE FOR COOLING ELECTRICAL EQUIPMENT IN A TURBOMACHINE - A device for cooling electrical or electronic equipment in a turbomachine, such as a unit for controlling actuators for variable-geometry elements, the device comprising at least one vortex tube having an inlet connected to means for feeding pressurized air taken from an element of the turbomachine, and a cold air outlet connected to means for cooling the electrical equipment. | 09-04-2008 |