| Hispano - Suiza Patent applications |
| Patent application number | Title | Published |
|---|
| 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 |
