Turbomeca Patent applications |
Patent application number | Title | Published |
20160126035 | HYBRID CUTOFF MEMBER FOR AN ELECTRIC CIRCUIT - A hybrid interrupter member for an electrical circuit, the interrupter member including a static interrupter component and an electromechanical interrupter component. The static component is mounted on a support carrying electrical contacts for the static component, the support being configured, on receiving a command to interrupt, to move in such a manner as to withdraw at least one of the electrical contacts from its respective pin, thereby forming the electromechanical interrupter component. | 05-05-2016 |
20160116387 | TEST BENCH COMBINING HIGH-FREQUENCY TRIBOLOGICAL STRESS AND OLIGOCYCLIC FATIGUE - Test rig combining high-frequency tribological stress and low-cycle fatigue, comprising a first test piece which is fixed to a frame and defines at least one bearing surface, a second test piece which is connected to traction means for loading the second test piece so that it bears against the or each bearing surface of the first test piece, means for heating the test pieces and means for loading the test pieces in a vibratory manner so as to carry out a fretting fatigue and low-cycle and high-cycle fatigue test, one of the test pieces comprising a portion which is in the shape of a turbine engine rotor blade root and which is inserted in a groove, the shape of which groove is substantially complementary to the other test piece so as to reproduce a turbine engine blade-disc attachment. | 04-28-2016 |
20160069209 | DEVICE FOR WASHING A TURBOMACHINE AIR INTAKE CASING - A turbomachine air intake casing including an inner annular wall and an outer annular wall defining an air passage and at least two cleaning agent injection nozzles, wherein a first nozzle is directed towards the outer wall while a second nozzle is directed towards the inner wall. | 03-10-2016 |
20160053774 | RADIAL OR MIXED-FLOW COMPRESSOR DIFFUSER HAVING VANES - The invention relates to a vane ( | 02-25-2016 |
20160024926 | TURBINE RING FOR A TURBOMACHINE - A turbine engine turbine ring, in particular for a helicopter, in which vibratory behavior is reduced. The turbine ring includes an essentially cylindrical support, and one or more sectors forming a circle configured to define a segment of an air passage, each sector being fastened to the support by an attachment device, wherein the attachment device includes a hook portion belonging to the support and projecting towards the sector, and a hook portion belonging to the sector and projecting towards the support, the hook portions of the support and of the sector being configured to co-operate in order to fasten the sector to the support, the ring further includes a damper device provided within the attachment device and stressed radially between a portion of the sector and a portion of the support so as to damp relative movements between the sector and the support. | 01-28-2016 |
20160017817 | METERING DEVICE FOR A FUEL FEED CIRCUIT OF AN ENGINE - A metering device for an engine fuel feed circuit, the device including a metering valve, and a pressure regulator device maintaining a constant pressure difference from downstream to upstream across the metering valve, wherein the metering valve includes a seat provided with an inlet orifice and an outlet orifice, a shutter arranged within the seat, and an actuator controlling the position of the shutter, and wherein, between the inlet orifice and the outlet orifice the shutter defines a passage of minimum section that is variable as a function of the position of the shutter along a stroke extending between a bottom abutment and a top abutment and passing via a threshold position. | 01-21-2016 |
20150377059 | METHOD FOR MONITORING A DEGREE OF CLOGGING OF THE STARTING INJECTORS OF A TURBINE ENGINE - A method for monitoring a degree of clogging of the starting injectors of a turbine engine, which includes: a combustion chamber into which at least one starting injector supplied with fuel leads, the starting injectors being suitable for initiating the combustion in the chamber by igniting the fuel; and a turbine rotated by the gases resulting from the combustion of the fuel in the chamber, the method including the steps involving: the measurement, during a phase of starting the turbine engine, of the temperature of the exhaust gases at the outlet of the turbine; and the determination, from the changes over time in the temperature thus measured, of a degree of clogging of the starting injectors. A system for monitoring a degree of clogging capable of implementing the method, and a turbine engine including such a system. | 12-31-2015 |
20150375312 | BROACH AND METHOD FOR BROACHING SLOTS FOR PARTS SUCH AS TURBINE ROTOR DISKS OR TURBOMACHINE COMPRESSOR DISKS - The invention relates to the broaching of at least one slot ( | 12-31-2015 |
20150330402 | SEALING ASSEMBLY FOR TURBOMACHINE - The invention relates to a turbine engine comprising an air compression stage comprising at least one movable compressor wheel, an air inlet duct coupled to said air compression stage, a first sealing device, which is arranged between a front portion of the movable compressor wheel and the air inlet duct and comprising at least one seal, a channel for conveying the air compressed by the movable wheel and a second sealing device, which is arranged between a rear portion of the movable compressor wheel and the conveying channel and is configured to receive an airflow coming from the conveying channel, the turbine engine being remarkable in that the second sealing device is configured to allow some of the air passing therethrough to be bled and in that the bleed air is conveyed to the seal of the first sealing device so as to keep it under pressure. | 11-19-2015 |
20150315965 | DEVICE AND METHOD FOR TEMPORARILY INCREASING POWER - A device and a method of temporarily increasing power of at least a first turbine engine is disclosed. The device includes a coolant liquid tank and a first injection circuit connected to the tank and leading to at least one injection nozzle suitable for being installed upstream from at least one compressor stage of the first turbine engine. This first injection circuit includes at least a first flow valve configured to open when a pressure exceeds a predetermined threshold compared with a downstream pressure from at least one compressor stage of a second turbine engine so as to enable the coolant liquid to flow towards the injection nozzle of the first injection circuit. | 11-05-2015 |
20150275681 | COMPRESSION ASSEMBLY FOR A TURBINE ENGINE - Compression assembly for a turbine engine, in particular a turboshaft engine, said assembly comprising an air inlet duct capable of receiving an air flow, at least one air compression stage comprising at least one movable compressor wheel onto which the duct discharges, and a pre-rotation grille which is positioned in the air inlet duct upstream of the movable compressor wheel in order to adjust the speed of the air in said flow at the inlet of the movable wheel and comprises a plurality of variable-setting vanes, the assembly being characterized in that the pitch between two consecutive vanes of the grille is greater than the chord of one of the two vanes at a given height of the air duct, preferably in its upper part. | 10-01-2015 |
20150267544 | ROTOR-STATOR ASSEMBLY FOR A GAS TURBINE ENGINE - A rotor-stator assembly for a gas turbine engine, the assembly including a rotor having a layer of ceramic material forming an abrasive coating deposited on its tip, the layer being constituted mainly by zirconia and possessing a void ratio less than or equal to | 09-24-2015 |
20150260406 | TWO-CIRCUIT INJECTOR FOR A TURBINE ENGINE COMBUSTION CHAMBER - A start-up injector for a turbine engine combustion chamber, said injector including a fuel injection circuit; and a fuel ignition circuit including a fuel injector supplied by the fuel injection circuit and a spark plug for igniting the injected fuel. The start-up injector also includes a partitioned enclosure including a first compartment in which the fuel is ignited by the spark plug and a second compartment separated from the first compartment by a thermally conductive partition; and a main combustion start-up circuit which includes at least one fuel injector supplied by the fuel injection circuit and opens into the second compartment of the enclosure such as to inject the fuel against the wall. | 09-17-2015 |
20150260106 | SUPPLY AND DRAIN DEVICE FOR AN INJECTOR - A device for a turbomachine chamber injector, including a conduit having at least a first opening, and a second opening ( | 09-17-2015 |
20150247459 | TURBINE ENGINE COMBUSTION ASSEMBLY WITH A VARIABLE AIR SUPPLY - A turbine engine combustion assembly including a casing, a combustion chamber, and at least one fuel injector. The combustion chamber includes an internal wall and an external wall extending one inside the other and connected by an annular chamber base wall. The external wall of the chamber is secured to an annular external wall of the casing. The injector is attached to the annular external wall of the casing and includes a fuel ignition enclosure extending inside the casing successively through openings in the casing wall and in the external wall before opening into the chamber. At least one wall of the ignition enclosure extending between the casing wall and the combustion chamber wall includes at least one air intake port. The external wall of the combustion chamber is solidly connected to a device for plugging the air intake port according to a thermal expansion state of the combustion chamber. | 09-03-2015 |
20150232171 | ACCESSORY DRIVE GEARBOX FOR CONTROLLING THE FLAPS OF AN AIRCRAFT - An accessory gearbox for a turboshaft engine of an aircraft, the gearbox including a casing, an aircraft wing flap control rod arranged so as to slide axially inside the gearbox and an actuator for driving the control rod which is mounted on the casing, the actuator including a hollow body, a piston which is arranged so as to move in translation inside the body and a piston rod which is connected to the piston and extends at least in part outside the body of the actuator the piston rod being connected to the control rod, wherein the actuator is arranged between the connection of the piston rod and the control rod, and the casing of the gearbox. | 08-20-2015 |
20150219539 | METHOD OF DETERMINING THE NON-PROPAGATION THRESHOLD OF FATIGUE CRACKS AT HIGH FREQUENCY - A method of determining the non-propagation threshold of fatigue cracks at high frequency, wherein cyclic loading is exerted on at least one testpiece having an elliptical hole in a testpiece zone, the elliptical hole having a notch at one end and the testpiece being held between two rigid masses with two rigid pre-stress plates being arranged on either side of the at least one testpiece and each fastened at its two ends to the two rigid masses, which cyclic loading is at a frequency that is selected as being equal to the resonant frequency of the assembly including the testpiece, the masses, and the stress plates, so as to generate a fatigue crack from the notch, and then once it has been observed that the crack has stopped propagating, the final length of the crack is measured and a chart is used to determine the non-propagation threshold. | 08-06-2015 |
20150211421 | METHOD AND SYSTEM FOR STARTING AN AIRCRAFT TURBOENGINE - The invention relates to a method for starting an aircraft turboshaft engine, said turboshaft engine comprising a combustion chamber, a compressor shaft on which a compressor wheel is mounted to feed compressed air to said combustion chamber, at least one starter connected to said shaft so as to provide it with a specified starting torque for driving it in rotation. The method comprises accelerating the compressor shaft during a first start-up phase, then stabilising the rotational speed of the compressor shaft during a second start-up phase. During acceleration of the compressor shaft, the rotational speed of the shaft is regulated such that the acceleration of the shaft remains substantially constant. | 07-30-2015 |
20150203343 | FILLER DEVICE FOR A FLUID TANK - A filler device for a fluid tank, including: a filler duct; a first stopper, for preventing overfilling of the tank, and a second stopper for preventing fluid from leaving the tank in unwanted manner; a first float mechanically connected to the first stopper such that, on being placed in a predetermined position, the first float closes the first stopper; and a holder system for holding the second stopper, which system, when fluid leaves the tank, closes the second stopper, and when fluid enters into the tank, opens the second stopper. In an operating position of the device, and under effect of a heavy element, the holder system acts continuously on the second stopper, tending to maintain the second stopper permanently in its closed position. | 07-23-2015 |
20150184592 | DRAINAGE METHOD AND PURGE COLLECTOR OF A CARBURATION SYSTEM OF A HELICOPTER - A helicopter engine collector includes an external longitudinal wall and two closed end walls, a longitudinal symmetry axis inclined ascendingly, couplings configured to be connected to purge drains, and a connection connected to a gas ejection pipe and connected to the bottom end wall. The collector also includes, in its internal space, a chamber with its symmetry axis substantially parallel to the axis of the collector. The chamber includes a longitudinal wall and two transverse end walls. The chamber is connected to the purge coupling of the injection wheel via a radial connection emerging on its longitudinal wall, the symmetry axis of the chamber being inclined, with respect to the horizontal reference ground when the helicopter is in a ground position, by a reference angle such that this axis is situated parallel to the reference ground when the helicopter is in an acceleration phase. The collector prevents formation of fumes. | 07-02-2015 |
20150176496 | DUAL-CIRCUIT MODULAR INJECTION TUBE - A turbomachine injection manifold assembly including a main circuit for feeding fuel to sets of injectors, and an auxiliary circuit for feeding fuel to a set of injectors. The manifold assembly also includes i a double coupling presenting a first endpiece receiving one end of a transfer tube of the main circuit, a second endpiece receiving one end of a transfer tube of the auxiliary circuit, and a mounting surface with a first orifice in fluid flow communication with the first endpiece and a second orifice in fluid flow communication with the second endpiece said the mounting surface of the double coupling being suitable for connecting the double coupling to an injector of said first set of injectors. | 06-25-2015 |
20150128592 | METHOD AND SYSTEM FOR THE EMERGENCY START-UP OF AN ENERGY GENERATOR SET - An emergency starter that allows responsiveness within a few seconds, without having disadvantages associated with mass and size of a back-up hydraulic or pneumatic starter. An instantaneous gas thrust of pyrotechnic type is coupled with a positive displacement transmission generator in conjunction with automatic coupling to/uncoupling from a set that is to be started. An emergency start-up system includes at least one pyrotechnic gas generator connected to an electrical initiator itself connected to a computer, a positive displacement motor housing straight-cut gears, the pyrotechnic gas generator being coupled to the motor by an inlet in the casing. The motor includes a mechanism of connection capable of moving at one end of the drive shaft configured to couple the transmission shaft to a driven shaft of the set that is to be started via a centrifugal clutch. | 05-14-2015 |
20150122944 | METHOD AND ARCHITECTURE FOR THE OPTIMIZED TRANSFER OF POWER BETWEEN AN AUXILIARY POWER MOTOR AND THE MAIN ENGINES OF A HELICOPTER - A method and architecture to optimize an entire traction system available on a helicopter by using an auxiliary engine to provide energy to equipment and accessories of the helicopter connected to the engines. Main engines and an APU unit, as an auxiliary engine, include a gas generator connected to, for the main engines, a reduction gearbox and an accessory gearbox for mechanical, electrical, and/or hydraulic power take-off and connected to, for the APU unit, at least one power conversion member. The power conversion member of the APU unit is connected to the equipment and accessories by the reduction gearbox and/or the accessory gearbox of the main engines. | 05-07-2015 |
20150086334 | CENTRIFUGAL COMPRESSOR PROVIDED WITH A MARKER FOR MEASURING WEAR AND A METHOD OF MONITORING WEAR USING SAID MARKER - A device and method for precise measurement of erosion of compressors, without removing an engine, and with easy positioning. A centrifugal compressor of a gas turbine with a radial air inlet includes an impeller including blades and a casing for an air stream to flow in the blades of the impeller. The casing, covered with an abradable coating, includes an annular elbow zone in a substantially median part. Marking depressions of predetermined depths, preferably in groups, are machined in the abradable coating of the zone. Examinations by endoscopy are successively performed to provide an image signal of the markers. Processing the endoscopic signal supplies a number of remaining markers and a criterion for decision on removing the engine is applied thereto. Erosion occurs in the elbow of the casing and evolution thereof may enable monitoring of erosion of other components of the compressor, in particular the blades of the impeller. | 03-26-2015 |
20140373546 | METHOD FOR DISCHARGING EXHAUST GAS FROM A GAS TURBINE AND EXHAUST ASSEMBLY HAVING OPTIMISED CONFIGURATION - A method for discharging exhaust gas from a gas turbine wherein a number of sectors, position, and angle at the center of at least one sector of a peripheral opening capable of forming an area for reingestion of a primary flow into an engine bay are determined by correlation of interactions between secondary cooling flows and the primary flow, from following behavior parameters: air gyration and speed at an inlet of a pipe, geometry of an exhaust stream, routing of the secondary cooling flow for cooling the engine bay, and a geometry and position of inlets of the secondary flows. The peripheral opening is then closed over the identified at least one angular sector. The method prevents backflow of hot primary air into the peripheral opening formed between a pipe and an ejector of the exhaust stream of a gas turbine. | 12-25-2014 |
20140303871 | METHOD AND SYSTEM FOR REGULATING POWER IN THE EVENT OF AT LEAST ONE AIRCRAFT ENGINE FAILURE - A method to optimize resources needed to continue flight if at least one main engine is lost, by relieving a propulsion system that has remained operative of all or some of non-propulsive energy demands, by additional generation of non-propulsive power, operating continuously. The method uses a GPP unit that operates constantly in flight while taking up some of nominal total non-propulsive power of the aircraft, to supply increased non-propulsive power almost instantaneously, based on at least three respective emergency regimes at a time of engine failure. A control and monitoring function of the GPP calculates elapsed time for each emergency regime, and informs a data processing unit thereof, while emitting an alarm if operating periods allocated to each emergency regime are exceeded, and the emergency function adjusts non-propulsive power demands made by the aircraft between main engines and the unit GPP either automatically or on orders of a pilot. | 10-09-2014 |
20140298819 | TURBINE ENGINE COMPRISING AN ELECTRICALLY ACTIVATED FUEL SUPPLY PUMP, AND TURBINE ENGINE FUEL SUPPLY METHOD - A turbine engine for an aircraft including a turbine engine shaft and a pumping module, including: a pump shaft, connected to the turbine engine shaft; a pump for supplying fuel to the turbine engine, mounted on the pump shaft, configured to deliver a flow of fuel as a function of a speed of rotation of the turbine engine shaft; and an electrical device mounted on the pump shaft and configured, according to a first mode of operation, to drive the pump shaft in rotation to actuate the supply pump and, according to a second mode of operation, to be driven in rotation by the pump shaft to supply electrical power to equipment of the turbine engine. | 10-09-2014 |
20140290287 | METHOD AND ARCHITECTURE FOR RECOVERY OF ENERGY IN AN AIRCRAFT - A method and architecture for recovery of energy in an aircraft, both at altitude and on the ground, and recovering thermal energy from an exhaust. An architecture for recovery of energy includes an auxiliary power unit APU including an exhaust nozzle and a gas generator including a shaft transmitting power to a load compressor. The compressor supplies compressed air via a supply duct to an ECS air conditioning system of a passenger cabin. A recovery turbocharger is connected, directly or via a transmission case, to the shaft of the APU. The turbocharger includes a recovery turbine powered by a downstream branch of a conduit mounted on a heat exchanger fitted to the nozzle. The conduit includes an upstream branch connected to channels connecting air outlets of the cabin and the compressor. A second exchanger can be mounted between the supply duct and the cabin outlet channel. | 10-02-2014 |
20140260257 | ANNULAR WALL OF A COMBUSTION CHAMBER WITH IMPROVED COOLING AT THE LEVEL OF PRIMARY AND/OR DILUTION HOLES - An annular wall of a combustion chamber of a turbine engine including: a cold side and a hot side; plural dilution holes to allow circulating air of the cold side to enter the hot side for dilution of an air/fuel mixture; plural cooling orifices to allow the circulating air of the cold side to enter the hot side to form a film of cooling air along the annular wall, the cooling orifices distributed spaced axially from one another and with geometric axes inclined, in an axial direction of flow of combustion gases, by an inclination angle relative to a normal to the annular wall; plural additional cooling orifices arranged directly downstream of the dilution holes and distributed spaced axially from one another, with geometric axes arranged in a plane perpendicular to the axial direction and inclined by an angle of inclination relative to a normal to the annular wall. | 09-18-2014 |
20140216191 | PINION VIBRATION DAMPING USING VISCOELASTIC PATCH - A gearwheel extending in an axial direction and in a radial direction, the gearwheel including a radial web carrying an axial annular rim, the rim carrying gear teeth. The web includes a vibration damper device including a layer of viscoelastic material and a backing layer. The layer of viscoelastic material is arranged axially between the radial web and the backing layer, and the layer of viscoelastic material is fixed directly to the web. | 08-07-2014 |
20140208763 | COMBUSTION CHAMBER WALL - An annular wall for a combustion chamber of a turbomachine. The wall presents a hot side and a cold side and includes at least one primary hole for enabling a first flow of air flowing on the cold side of the wall to penetrate to the hot side of the wall to feed combustion of fuel inside the combustion chamber, and together with a plurality of cooling holes, each having a diameter no greater than 1 mm, to enable a second flow of air flowing on the cold side of the wall to penetrate to the hot side of the wall to cool the hot side of the wall. The plurality of cooling holes can also dilute combustion gas resulting from the combustion by using the flow of air penetrating to the hot side of the wall through the cooling holes. | 07-31-2014 |
20140207726 | SYSTEM FOR RECOMMENDING HELICOPTER ENGINE MAINTENANCE - The invention relates to a system for recommending maintenance of helicopter engines depending on the technical condition of the engine, the standard replacement of parts between engines, and the replacement of parts with different parts. The system comprises: a centralized database storing data relating to (i) working condition and working condition indicators, (ii) modifications of the engines, (iii) maintenance plans for the engines, (iv) causes of unscheduled events, (v) maintenance applied to the engines, and (vi) instantiated configurations; means for acquiring the working condition indicators and for updating the working condition data; means for identifying maintenance to be applied to the engines depending on the data; means for generating an alarm for identified maintenance to be performed; means for the digitally-signed updating of the applied maintenance and configuration data according to maintenance operations; and means for deactivating an alarm once the maintenance associated with the alarm is completed. | 07-24-2014 |
20140147278 | VARIABLE-PITCH NOZZLE FOR A RADIAL TURBINE, IN PARTICULAR FOR AN AUXILIARY POWER SOURCE TURBINE - A radial turbine nozzle of a turbine engine rotating about a central axis includes a first annular array of fixed blades and a second annular array with a same number of variable-pitch blades. The blades have pressure and suction surfaces. Each variable-pitch blade is connected to cups and is configured to be rotated by a controller about a geometric axis connecting centers of the cups. Each variable-pitch blade is mounted at a distance from the axis of the cups such that this axis of rotation is positioned facing the suction surface of the blade and substantially closer to a trailing edge than to a leading edge of that blade. The nozzle can modify the reduced flow admitted by a radial turbine in accordance with requirements of a thermodynamic cycle and produce a seal in an area of maximum load of the nozzle blades. | 05-29-2014 |
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 |
20140133957 | METHOD OF DIFFUSING A GAS TURBINE COMPRESSION STAGE, AND DIFFUSION STAGE FOR IMPLEMENTING SAME - A diffusion stage of a radial or mixed gas turbine engine compressor includes an impeller formed by two plates, between which fluid flows in a centrifugal or inclined manner from a center towards a periphery. Blades of a cascade are distributed between the plates to channel the flow of the fluid between leading edges of the blades at the center and trailing edges at the periphery. At least one of the plates has an internal face including at least one zone with alternating hollow and bump curvatures between two adjacent blades, in at least one of two substantially perpendicular directions, in the direction of flow along the blades and in an inter-blade tangential direction. | 05-15-2014 |
20140127023 | CENTRIFUGAL COMPRESSOR IMPELLER - An impeller of a centrifugal compressor, the impeller including a web and blades secured to the web on a front face of the web. A point of intersection between a trailing edge and a blade root is at least one half-thickness of the web further forward than the blade root at an intermediate diameter of the impeller, and a point of intersection between the trailing edge and the blade tip is also further forward than the blade tip at an intermediate diameter of the impeller. | 05-08-2014 |
20140124160 | AIR CONDITIONING SYSTEM FOR AN AIRCRAFT PASSENGER COMPARTMENT - An air conditioning system for an aircraft passenger compartment, the system including: an air supply circuit connecting at least one external air inlet to at least one air distribution outlet which opens into the compartment, an auxiliary power unit mounted in the supply circuit and configured to compress an air stream in the supply circuit, the supply circuit including a heating first branch that connects the auxiliary power unit to the air distribution outlet, and in which a heating mechanism is mounted, a cooling second branch that connects the auxiliary power unit to the air distribution outlet, and a switching mechanism configured to distribute the air stream between the heating first branch and the cooling second branch. | 05-08-2014 |
20140123673 | A METHOD OF STARTING A TURBOMACHINE WHILE REDUCING THERMAL UNBALANCE - A method of starting a turbomachine, performed by an electronic unit, the turbomachine including a gas turbine engine including at least one rotor and a starter to drive the rotor in rotation, the method including: receiving an order to start the turbomachine, and executing in response to receiving the order to start: a primary acceleration during which the starter is operated to increase speed of rotation of the rotor; a thermal homogenization during which the starter is operated to keep the speed of rotation of the rotor constant or to decrease it until a predetermined condition is satisfied; after the predetermined condition is true, a secondary acceleration in which the starter is operated to increase the speed of rotation of the rotor; and an ignition in which ignition of the engine is ordered. | 05-08-2014 |
20140116384 | METHOD FOR INJECTING FUEL INTO A COMBUSTION CHAMBER OF A GAS TURBINE, AND INJECTION SYSTEM FOR IMPLEMENTING SAME - An air/fuel mixer system of a combustion chamber of a gas turbine includes at least one compressed air intake swirler, the swirler having a central axis of symmetry, and a fuel injector including an injection head having an axis of symmetry. Each injector is mounted in the corresponding swirler with aid of a guide mechanism, so that the axis of symmetry of the injection head is off-center with respect to the central axis of symmetry of the swirler. The system can reduce, or even eliminate, combustion instabilities, by injecting the fuel along a particular axis which is off-center relative to the axis of the air/fuel mixer system, inducing a flow of fuel which is no longer perfectly axially symmetrical. | 05-01-2014 |
20140112756 | A TWO-SPOOL DESIGN FOR A TURBOSHAFT ENGINE WITH A HIGH-PRESSURE COMPRESSOR CONNECTED TO A LOW-PRESSURE TURBINE - A turboshaft engine including a low-pressure compressor, a high-pressure compressor, a low-pressure turbine, a high-pressure turbine, and a regulator for regulating a speed of rotation of the low-pressure turbine to a speed that is substantially constant. The low-pressure turbine is coupled by a first shaft to the high-pressure compressor, while the high-pressure turbine is coupled by a second shaft to the low-pressure compressor. | 04-24-2014 |
20140109595 | ANNULAR COMBUSTION CHAMBER OF A TURBOMACHINE - An annular combustion chamber for a turbomachine presenting an axial direction, a radial direction, and an azimuth direction, the combustion chamber including a first annular wall and a second annular wall, each annular wall defining at least a portion of an enclosure of the combustion chamber. The first annular wall and the second annular wall present complementary assembly mechanisms that co-operate by engagement in azimuth. | 04-24-2014 |
20140105723 | GAS TURBINE DIFFUSER BLOWING METHOD AND CORRESPONDING DIFFUSER - A diffuser of a compressor of centrifugal or mixed type includes two end plates which enclose a plurality of regularly distributed circumferential blades, and at least one transverse upstream passage produced in lower or upper surfaces of the blades. An injection/withdrawal coupling is achieved by a recirculation of a stream in an air passage of the diffuser on the basis of injection of air from at least one point in a leading edge zone of an upstream side of the diffuser. Blowing of air is then effected in at least one groove formed along a lateral flank of each blade by withdrawal of the air stream in a region of a trailing edge. Thereby, effectively separation of the air in a boundary layer in a gas turbine compressor diffuser is realized by re-energizing the boundary layer with air at a higher pressure by a suction/re-injection coupling. | 04-17-2014 |
20140084677 | METHOD FOR RATIONALISING A CHAIN OF ELECTRICAL COMPONENTS OF AN AIRCRAFT, IMPLEMENTATION ARCHITECTURE AND CORRESPONDING AIRCRAFT - A chain of components for transmitting electric power of an aircraft includes an auxiliary power unit (APU), main engines and end consumer systems via power networks and electronic connections controlled by a unit. The APU supplies power to a shaft by a connection to at least one energy converter unit, via a transmission unit, each converter unit comprising only one convertible electromechanical component. The transmission of power is effected by a direct connection to the transmission unit and to the end consumer system. The connection between a converter unit and the APU is provided by connecting the shaft of the APU to the shaft of the starter/generator (SG) via a directional transmission of power operating in one direction only from the shaft of the APU to the shaft of the SG. | 03-27-2014 |
20140075916 | METHOD AND DEVICE FOR SUPPLYING A LUBRICANT - A device and method feeding turbomachines with lubricant, the turbomachine including a first set of bearings and a second set of bearings. Both the first and the second sets of bearings are fed with lubricant, and the second set of bearings operate at a temperature higher than the first set. The second set of bearings is fed with lubricant at a temperature higher than the first set. | 03-20-2014 |
20140045599 | MECHANICAL PROTECTION DEVICE - A mechanical protection device including: a transmission shaft having a main axis of rotation and an element that is frangible under a torsional overload; a movable member secured to the transmission shaft to rotate about the main axis and configured to move radially outwards relative to the main axis from a first position to a second position; a spring urging the movable member towards the first position; and a tangential abutment configured to stop rotation of the movable member about the main axis when the movable member is in the second position. The movable member and the spring are calibrated so that from a predetermined trigger angular speed the movable member moves from the first position to the second position under effect of centrifugal force greater than prestress of the spring. | 02-13-2014 |
20140000276 | TURBOMACHINE COMPRISING A PRIVILEGED INJECTION DEVICE AND CORRESPONDING INJECTION METHOD | 01-02-2014 |
20130327119 | METHOD FOR CALIBRATING A TORSION TORQUEMETER - A method for calibrating a torsion torquemeter including: placing a torsion torquemeter in a first state; performing first measurements determining first and second angular offsets, and measuring torque output by the power shaft using a reference torquemeter; placing the torsion torquemeter in a second state; performing second measurements determining the first and second angular offsets, and measuring torque output by the power shaft; placing the torquemeter in a third state; performing third measurements determining the first and second angular offsets, and measuring the torque output by the power shaft; placing the torquemeter in a fourth state; performing fourth measurements determining the first and second angular offsets, and measuring the torque output by the power shaft; calibrating the calculation unit based on the first, second, third, and fourth measurements. | 12-12-2013 |
20130305726 | INJECTOR FOR THE COMBUSTION CHAMBER OF A GAS TURBINE HAVING A DUAL FUEL CIRCUIT, AND COMBUSTION CHAMBER PROVIDED WITH AT LEAST ONE SUCH INJECTOR - A starting injector usable in all flight modes without additional cost or weight. The starting injector includes a dual fuel circuit and an air circuit. An injector for a combustion chamber of a gas turbine includes a dual fuel injection circuit including a starting fuel circuit for ignition and then for all the flight modes, and a main fuel circuit for all the flight modes after starting. The circuits include parallel pipes in a common tube having an axis. The pipe of the starting circuit is substantially in communication with a center of a spherical injector body. At the end, the pipe accommodates an injection manifold coupled to a central channel passing through a central wall of a swirler. The pipe of the main circuit is in communication with an annular channel opposite jet channels. An air circuit is guided between two portions shaped as concentric spheres. | 11-21-2013 |
20130298686 | DEVICE AND METHOD FOR MONITORING A ROTOR - A monitoring device for monitoring rotors of turbines, including: an acoustic sensor; and a sound waveguide for connecting the acoustic sensor to a sensing point close to the rotor of the turbine. The acoustic sensor is configured to detect, as soundwaves, pressure fluctuations due to pressure differences between suction and pressure sides of blades of the rotor as they move past in proximity of a sensing point. A method of monitoring a rotor of a turbine transmits pressure fluctuations due to pressure differences between suction sides and pressure sides of blades of the rotor going past the proximity of a sensing point by a sound waveguide to an acoustic sensor to be picked up as soundwaves. | 11-14-2013 |
20130291551 | METHOD FOR STARTING A TURBOMACHINE - A method of starting a turbine engine, including a re-try performed if a main injector has not ignited when a shaft has reached a first predetermined speed value, the re-try including: a stopping during which a starter and the ignitor device are stopped; a second ignition during which fuel is injected into the combustion chamber, the ignitor device being actuated, the second ignition being performed when a speed of rotation of the shaft reaches a second predetermined speed value; and a second starting during which the starter is actuated once more to drive the shaft in rotation. | 11-07-2013 |
20130280098 | MECHANICAL PROTECTION METHOD AND DEVICE - A device and method for providing mechanical protection, and in particular to a mechanical protection device including a transmission shaft with a resonant frequency in bending that corresponds to a predetermined rotary overspeed of the transmission shaft, the transmission shaft being insufficiently damped to avoid breakage of the transmission shaft as a result of the resonance in bending. In the mechanical protection method, the transmission shaft breaks as a result of this resonance in bending. | 10-24-2013 |
20130280068 | METHOD FOR DAMPING A GAS-TURBINE BLADE, AND VIBRATION DAMPER FOR IMPLEMENTING SAME - A turbine wheel with optimal-mass dampers to dampen a predetermined resonance in context of vibration of a turbine, particularly a low-speed turbine, while assisting in flexibility of adapting to bearing surfaces of recesses of the dampers, by separating mass and flexibility functions by a flexible portion for clamping against the platform, and a mass portion for controlling frictional forces. A damper includes a plate and a counterweight. The plate is stamped from a metal sheet that is substantially thinner than that of the counterweight. The plate includes a wall configured to flexibly contact a platform of the blade of the wheel, while at least partially surrounding a surface of the counterweight. The damper can be used in particular for a wheel of a turbine of a turbine engine, of a fan, or of a BP compressor having mounted blades. | 10-24-2013 |
20130241195 | COUPLING SYSTEM INCLUDING A SAFETY FASTENER DEVICE - The present invention relates to a coupling system comprising a coupling for fastening to one end of a pipe via a fastening connection, said coupling system further including safety fastener means in the form of a sleeve surrounding the fastening connection and having a first end for welding to the pipe, and a hook-forming second end for co-operating with the coupling in such a manner that the hook is suitable for providing fastening between the coupling and the pipe in the event of the fastening connection being damaged. | 09-19-2013 |
20130234506 | METHOD FOR CONTROLLING THE GENERATION OF ELECTRICITY APPLIED TO AN AIRCRAFT GAS TURBINE, AND DEVICE IMPLEMENTING SUCH A METHOD - A method improving acceleration efficiency of a gas generator of a gas turbine by reducing take-up of electric power, during transition phases, to conserve a sufficiently large surge margin for an operating line. The method increases acceleration/deceleration power of the gas generator by adjusting voltage of an electric network onboard the aircraft. After a phase of starting the gas turbine, voltage of the onboard network is adjusted by a voltage set value controlled by determining unballasting/ballasting status of a main electricity generation source of the onboard network. The status-determining is executed according to demand for taking power to be supplied for propulsion of the aircraft. The status-determining is followed by selecting a voltage set value from plural levels according to the determining the unballasting/ballasting status, and applying the selected set value to a control loop of the voltage supplied to the onboard network. | 09-12-2013 |
20130219905 | METHOD OF OPTIMIZING THE SPECIFIC FUEL CONSUMPTION OF A TWIN ENGINE HELICOPTER AND TWIN ENGINE ARCHITECTURE WITH CONTROL SYSTEM FOR IMPLEMENTING IT - A method and architecture to reduce specific fuel consumption of a twin-engine helicopter without compromising safety conditions regarding minimum amount of power to be supplied, to provide reliable in-flight restarts. The architecture includes two turbine engines each including a gas generator and with a free turbine. Each gas generator includes an active drive mechanism keeping the gas generator rotating with a combustion chamber inactive, and an emergency assistance device including a near-instantaneous firing mechanism and mechanical mechanism for accelerating the gas generator. A control system controls the drive mechanism and emergency assistance devices for the gas generators according to the conditions and phases of flight of the helicopter following a mission profile logged beforehand in a memory of the system. | 08-29-2013 |
20130211691 | SYSTEM FOR REAL TIME SIMULATION OF THE ENVIRONMENT OF AN AEROENGINE - A system for real time simulation of the environment of an aeroengine includes a digital computer having its inputs switched by a selection module included in the computer either to a respective sensor or else to a substitution digital bus configured to convey substitution digital data generated by a real time simulator. | 08-15-2013 |
20130205745 | LUBRICATING DEVICE HAVING A BYPASS VALVE - A lubrication device including a bypass valve with an inlet connected to a feed circuit, a first outlet to be connected to elements to be lubricated, and a second outlet connected to a bypass circuit. The valve includes a valve member slidable between first and second positions, and separating a cavity into first and second chambers. The first chamber is connected to the inlet. In the first position, a fluid flow passage from the first chamber to the second chamber is open, and from the first chamber to the first outlet is closed. In the second position, a fluid flow passage from the first chamber to the first outlet is open, and from the first chamber to the second outlet is closed. At least in the second position, the valve member separates the chambers in substantially leaktight manner, while the second chamber remains in fluid flow communication with the second outlet. | 08-15-2013 |
20130202428 | METHOD FOR ATTACHING THE COVER OF A CENTRIFUGAL COMPRESSOR OF A TURBINE ENGINE, COMPRESSOR COVER IMPLEMENTING SAME AND COMPRESSOR ASSEMBLY PROVIDED WITH SUCH A COVER - An attachment arrangement at a middle of a cover having an elastically deformable portion. The cover includes a concave shell including an inner surface spaced apart from the compressor including an impeller including blades by an attachment. The attachment includes one connection end at the middle of the shell, another end attached to a casing of the turbine engine, and an axisymmetric diaphragm having a generally frusto-conical configuration having an arm profile coupled to the end for attachment to the casing by a double-elbow joint having right and obtuse angles when in a rest position. The distance between the inner surface of the shell and upper edges of the blades can be held constant during operation with minimum clearance adjustment. The cover can be moved such that clearance between the cover and blades of the compressor impeller remains substantially constant and as low as possible. | 08-08-2013 |
20130151112 | METHOD FOR OPTIMIZING THE CONTROL OF A FREE TURBINE POWER PACKAGE FOR AN AIRCRAFT, AND CONTROL FOR IMPLEMENTING SAME - A method optimizing fuel-injection control with driving speeds of apparatuses adjusted by controlling a turbine speed according to power, and optimizing control of a free turbine power package of an aircraft, including a low-pressure body, supplying power to apparatuses and linked to a high-pressure body. The method varies the low-pressure body speed to obtain a minimum speed for the high-pressure body, so power supplied by the apparatuses remains constant. Power supplied by the apparatuses is dependent upon the apparatuses driven speed by the low-pressure body, and a speed set point of the low-pressure body is dependent upon a maximum value of minimum speeds of the apparatuses, enabling required power to be optimized, upon a positive or zero incrementation added to the speed set point of the low-pressure body to minimize speed of the high-pressure body to the apparatuses power supply. | 06-13-2013 |
20130151039 | METHOD FOR OPTIMIZING THE OVERALL ENERGY EFFICIENCY OF AN AIRCRAFT, AND MAIN POWER PACKAGE FOR IMPLEMENTING SAME - A method and system limiting specific consumption of an aircraft by matching sizing of a power supply to actual power needs of a cabin pressure control system. The method optimizes overall efficiency of energy supplied onboard an aircraft including, in an environment near the cabin, at least one main power-generating engine, sized to serve as a single pneumatic energy-generating source for the cabin and as an at most partial propulsive, hydraulic, and/or electric energy-generating source for the rest of the aircraft. The method minimizes power differential between a nominal point of the power sources when the sources are operating, and a sizing point of non-propulsive energy contributions of the sources when the main engine has failed, by equally dividing power contributions of the main engines and the main power generator under nominal operating conditions and in an event of failure of a main engine. | 06-13-2013 |
20130142634 | METHOD FOR MOUNTNG SHIELDING ON A TURBINE CASING, AND MOUNTING ASSEMBLY FOR IMPLEMENTING SAME - A method and structure negating thermal inertia of a solid portion, such as shielding, which influences mechanical behavior of parts of an engine structure, by reducing forces transmitted to the engine structure during an event in which a turbine blade ruptures, while preserving mechanical strength and vibratory positioning. The structure includes a flexible fastener for a shield, enabling producing a fusible section. An assembly for mounting a shielding onto a casing of the engine structure of a turbine includes connection lugs and points for attachment to the casing and shielding. The attachment points are sufficiently spaced apart in accordance with curvature of the shielding and casing so connection between the lugs and the shielding or casing, and connection of the attachment points, are substantially tangential. The lugs are sized so the connection has sufficient flexibility to control vibratory positioning thereof and ensure sufficient mechanical strength under thermo-mechanical loads. | 06-06-2013 |
20130139522 | METHOD FOR OPTIMIZING THE OPERABILITY OF AN AIRCRAFT PROPULSIVE UNIT, AND SELF-CONTAINED POWER UNIT FOR IMPLEMENTING SAME - A method for optimizing operability of an aircraft propulsive unit, and a self-contained power unit implementing the method. The method removes mechanical bleed constraints in engines during transient flight phases of an aircraft to optimize operability of the engine assembly during the phases. To this end, a supply of power is provided, particularly during the phases, by an additional indirectly propulsive engine power source. The method for optimizing operability of the propulsive unit of an aircraft including main engines as main drive sources includes, using a main engine power unit GPP as a power source, providing all the non-propulsive power and, during the transient engine phases, at most partially providing additional power to the body of the main engines. | 06-06-2013 |
20130134706 | COUPLING SYSTEM INCLUDING A SAFETY FASTENER DEVICE - A coupling system including a coupling for fastening to one end of a pipe via a fastening connection; and a sleeve surrounding the fastening connection is disclosed. The sleeve includes a first end for welding to the pipe, and a hook-forming second end for co-operating with the coupling in such a manner that the hook is suitable for providing fastening between the coupling and the pipe in the event of the fastening connection being damaged. | 05-30-2013 |
20130129487 | DEVICE FOR CONTROLLING PIVOTABLE VANES OF A TURBO-MACHINE - A control device for controlling pivotable vanes of a turbo-machine, including: a plurality of pivotable vanes distributed in azimuth over at least 90° around the axis of the turbo-machine, the pivotable vanes being oriented substantially radially relative to the axis of the turbo-machine; and a control ring portion for controlling pivoting of the vanes, each vane being connected to the control ring portion by a link, the control ring portion being held around the axis of the turbo-machine by the links; wherein at least two of the links are connected to the ring portion by respective ball-joint connections, with other links being connected to the ring portion via respective sliding pivot connections. | 05-23-2013 |
20130119048 | METHOD FOR THE INDUCTION BRAZING OF PARTS HAVING COMPLEX SHAPES, AND SINGLE OR MULTIPLE BRAZING STATION FOR IMPLEMENTING SAME - A method for brazing parts having complex profiles, while enabling reproducible implementation conditions to be defined. The method adjusts a heat cycle during brazing by controlling and mapping heat, while taking emissivity coefficient of the material to be brazed into account. Further, a brazing station includes a power generator configured to supply a predetermined voltage to a transformer connected to a circuit forming a shape inductor, the circuit having an overall shape of the parts to be brazed. A pressure mechanism exerts a load on the parts to be brazed. A camera establishes a heat map. A laser-sighted infrared pyrometer measures the brazing temperature by radiation after parameterizing an emissivity coefficient, other parameters being fixed. A controller supplies a set power to the generator on the basis of the measured temperature. | 05-16-2013 |
20130098052 | METHOD AND ARCHITECTURE FOR RECOMBINING THE POWER OF A TURBOMACHINE - A method and architecture for recombining power of a turbomachine improving on problems of size, mass, or reliability. In the method energy is recovered in an exhaust nozzle and converted and recirculated using a mechanical and/or electrical power recombining mechanism. An example of an architecture of a turbomachine includes a main turbine engine and a heat exchanger positioned in the exhaust nozzle and coupled, via pipes, to an independent system that converts thermal energy into mechanical energy. This independent system is connected to a localized mechanical recombination mechanism via a power shaft to supply power to a power transmission shaft according to aircraft requirements. | 04-25-2013 |
20130098042 | DETECTION OF THE OVERSPEED OF A FREE TURBINE BY MEASURING USING A TORQUE METER - An overspeed protection device includes at least one torque measurement unit supported by an output shaft coupled mechanically to a free turbine of a turbine engine and a signal processing unit able to transmit to a turbine engine regulating system a command to reduce a flow of fuel injected if it is detected that the torque has dropped below a first datum value. The signal processing unit is shaped to command a reduction of the flow if it is detected that the torque has dropped below a first datum value, the torque measurement used to trigger the reduction being taken during a rotation corresponding to a fraction of a revolution of the output shaft. | 04-25-2013 |
20130089409 | NON-LUBRICATED ARCHITECTURE FOR A TURBOSHAFT ENGINE - A turbine engine for a helicopter, the helicopter including a main gearbox, a rotor, and a speed-reducing device housed entirely within the main gearbox of the helicopter while also being connected to the rotor, the turbine engine including a casing, a gas generator with a gas generator shaft, and a free turbine for being driven in rotation by a gas stream generated by the gas generator, the free turbine including a free turbine shaft. When the turbine engine is fastened to the gearbox of the helicopter, the free turbine shaft extends axially into the main gearbox of the helicopter to be connected directly to the speed-reducing device. | 04-11-2013 |
20130089284 | METHOD FOR DYNAMICALLY ABSORBING SHOCKS IN A POWER SHAFT, IN PARTICULAR A SUPERCRITICAL SHAFT, AND SHOCK-ABSORBING ARCHITECTURE FOR IMPLEMENTING SAID METHOD - An architecture making it possible to provide sufficient absorption of shocks for a power shaft while maintaining rigidity at front bearings so as to not compromise meshing of power teeth of a drive pinion. A compressible dynamic shock absorption is provided in alignment with a downstream shock absorber of an additional meshing. An assembly for dynamically absorbing shocks for a power shaft includes upstream and downstream bearings including power rollers mounted on two casings and flanking a speed-reducing teeth meshing. The downstream bearing is coupled to at least one additional roller bearing associated with a compressible shock absorber to form a downstream shock absorber axially offset relative to the upstream bearing opposite the teeth meshing. Both downstream bearings are connectable by a flexible frame mounted on the common casing. The architecture can be used for power-transmission shafts, for example supercritical shafts in turbine engines. | 04-11-2013 |
20130086906 | HEAT-EXCHANGE ARCHITECTURE BUILT INTO THE EXHAUST OF A TURBINE ENGINE - A heat-exchange architecture for exhaust of a turbine engine, including heat-exchange elements partially obstructing a hot exhaust gases stream. In an architecture built into an exhaust line for gas streams of a turbine engine, the turbine engine is a turboshaft engine including a gas generator and a free turbine supplying power to a shaft via a through-shaft and an upstream reduction gear. An annular plate-shaped exchanger is installed in the axisymmetric portion of the ejector. The exchanger includes inlet and outlet channels, connected to the inlet and outlet of a central channel wound into a helix shape or sine curve in the annular plate. The channels are connected at the other ends to mechanical or electromechanical mechanisms for recovering and recycling energy. The energy is recovered via a cold fluid heated in the central channel by transfer of heat from residual gases. | 04-11-2013 |
20130061964 | DEVICE FOR MULTIPOINT ACQUISITION/DISTRIBUTION OF FLUID, IN PARTICULAR PROBE FOR TAPPING PRESSURE IN A TURBOMACHINE AIR INLET - To achieve accurate and rapid acquisition or distribution of fluid—at multipoints—with good spatial resolution and minimal bulk, a twisted arrangement of ducts is provided in the acquisition/distribution zone making it possible to perform several acquisitions/distributions over several heights with one and the same device. The device is a pressure probe in which a probe body exhibits a first part or section for acquiring pressure forming a cylinder less than 6 mm in diameter. The probe exhibits internal ducts forming parallel helicoidal traces on the section and channels formed in a metal alloy body between the ducts and inlet orifices. The number of internal ducts is advantageously equal to nine, including three orifices being disposed over three different heights of the probe body. | 03-14-2013 |
20130047621 | MULTI-PIERCED COMBUSTION CHAMBER WITH COUNTER-ROTATING TANGENTIAL FLOWS - A combustion chamber, for example for a turbine engine, presenting an inner annular wall, an outer annular wall, and a pierced annular chamber end wall extending around an axis, the chamber end wall including at least one opening receiving a fuel injector, the opening being substantially centered on a circular line defining a first chamber end wall portion extending radially between the circular line and the inner annular wall, and a second chamber end wall portion extending radially between the circular line and the outer annular wall. First and second channels are inclined relative to a normal vector normal to the chamber end wall while extending tangentially, the first channels arranged to provide a flow of air in a first rotary direction, the second channels arranged to provide a flow of air in a second rotary direction opposite to the first rotary direction. | 02-28-2013 |
20130034425 | METHOD FOR ADAPTING THE AIR FLOW OF A TURBINE ENGINE HAVING A CENTRIFUGAL COMPRESSOR AND DIFFUSER FOR IMPLEMENTING SAME - A method for maintaining efficiency and duty of a turbine engine compressor to reduce specific consumption, while guaranteeing a high enough pumping margin with partial load. The method adapts airflow to a variable demand for flow or mechanical or electric power in a centrifugal compressor of a turbine engine. The method includes diffusing the airflow through a first annular blade ring having variable pitch blades, radially bordered by a second annular blade ring having a same number of fixed pitch blades with an equivalent extension, guiding the radial extension diffusion by coupling the blades of the two blade rings. According to the method, each blade of the first blade ring is spun off-axis. | 02-07-2013 |
20130000770 | GAS-GUIDING PIPE COMPRISING A NOISE-ATTENUATING COVERING WITH VARIABLE POROSITY - A noise-attenuating covering configured for example for a pipe for guiding gases along a gas path. The covering includes a wall defining the gas path and at least one resonance cavity, the wall being pierced with holes for fluid communication between the gas path and the resonance cavity to attenuate noise. The holes have substantially identical diameters and, since the pipe is arranged to guide the gases in the downstream direction, a number of the openings per wall surface unit decreases continuously along the gas path in the downstream direction, such as to confer on the wall substantially constant acoustic resistance along the gas path, for which the noise attenuation is optimized along the gas path. | 01-03-2013 |
20130000748 | DEVICE FOR EJECTING GAS FROM A GAS TURBINE ENGINE AND GAS TURBINE ENGINE - A device for ejecting gas from a gas turbine engine, which includes: an outer wall and an inner wall defining a gas flow path therebetween, the inner wall forming a central body defining an inner cavity, the outer wall being perforated and communicating with at least one outer resonance cavity for attenuating noise in a first range of sound frequencies; and a mechanism for placing the outer and inner cavities in fluid communication, extending through the gas flow path, the inner cavity thus forming a resonance cavity for attenuating the noise in a second range of sound frequencies. The device can, for example, be used to attenuate two ranges of sound frequencies. | 01-03-2013 |
20120321460 | VERTICAL SHAFT TURBOMACHINE - A turbomachine includes a compressor, a first shaft, a second shaft, a first turbine, and a second turbine. The first shaft carries at least one turbine wheel belonging to one of the elements selected from the first and second turbines. The second shaft carries at least one turbine wheel belonging to the other element selected from the first and second turbines. The first and second shafts are oriented substantially vertically in normal utilization situations of the turbomachine. The first shaft is held by a first single bearing while the second shaft is held by a second single bearing. | 12-20-2012 |
20120321447 | FLEXIBLE REAR BEARING MOUNTING, HAVING AN ABUTMENT, FOR A TURBINE ENGINE - An assembly including a part for mounting at least one shaft bearing of a turbine engine and a support part that forms an abutment for the mounting part. The mounting part includes at least one channel through which engine gases pass, and connection parts that are capable of connecting the channel to an outer structure of the engine and to a housing holding the bearing. At least one of the connection parts is flexible so as to enable radial movement of the channel, an amplitude of the radial movement being limited by at least one of the elements of the mounting part coming onto an abutment supported by the support part. The support part extends longitudinally with regard to the direction of the rotational axis of the turbine engine so as to generate a turbine shroud that is configured to be positioned in alignment with a turbine wheel of the turbine engine. | 12-20-2012 |
20120291441 | INJECTOR DEVICE AND COMBUSTION CHAMBER FOR A TURBOMACHINE PROVIDED WITH SUCH INJECTOR DEVICE - A low-cost combustion chamber injector device that has sturdier construction and is safer for use. Parts are configured specifically to be nested, to dispense with welding between the cellular parts. The device for injecting a fuel-air mix includes, centered on a single axis, a swirl chamber including at least two annular air suction parts, a centering guide, and a retainer ring. The annular parts have cellular conduits connecting to axial inner and outer Venturi tubes. The parts are coaxially mounted, the inner part being configured to be self-centered in the outer part by engagement of the axial and radial walls and then, after assembly, the outer part is welded to the retainer ring and to the inner part in a single radial plane. | 11-22-2012 |
20120257954 | METHOD FOR COOLING TURBINE STATORS AND COOLING SYSTEM FOR IMPLEMENTING SAID METHOD - A method and system for cooling turbine engine turbines, the system includes: at least one pair of parts to be cooled, the pair including a stator upstream from the rotor valve, and a sealing ring mounting a downstream movable blade rotor that is adjacent to the stator; a turbine casing; and an outlet path. The system further includes: at least one opening in the casing facing at least one part to be cooled; and an air circuit producing a forced convection in connection with the parts and at least one downstream outlet in the path so as to draw in and transport an ambient air flow. | 10-11-2012 |
20120210725 | NON-FLAME-OUT TEST FOR THE COMBUSTION CHAMBER OF A TURBINE ENGINE - A method for ground control of proper operation of an aeronautical turbine engine for a plane. A test includes carrying out, on the operating turbine engine and from a predetermined speed, a quick reduction in fuel flow according to a programmed decrease to evaluate flame-out resistance of the combustion chamber of the turbine engine during a quick inflight deceleration maneuver of the speed thereof. | 08-23-2012 |
20120201681 | TURBINE WHEEL FITTED WITH AN AXIAL RETAINING RING THAT LOCKS THE BLADES RELATIVE TO A DISK - A turbine wheel having an axis of rotation and including: a disk having a periphery and a side face; a plurality of blades assembled on the disk, each blade having a blade root and a first hook oriented radially and defining a first groove that opens radially towards the axis of rotation of the turbine wheel. The disk includes a series of second hooks oriented radially and defining a second groove that opens radially towards the axis of rotation of the turbine wheel. An axial retaining ring for placing in the first and second grooves includes a tab for placing between two adjacent blade roots to limit movements of the ring in azimuth. | 08-09-2012 |
20120201658 | METHOD FOR PROTECTING THE PASSAGE OF AIR IN A DRIVE PART COUPLING IN AN UNPROTECTED ENVIRONMENT, COUPLING FOR IMPLEMENTATION, AND ROTOR LINE FITTED WITH SUCH COUPLINGS - A method to prevent blockage of air passages in curvic couplings between drive parts and to prevent potential damage to the drive parts during weakening of protective elements. To this end, axial abutments are formed by ring gears of the curvic couplings. A coupling includes two rings, each ring being on the end of one drive part and engaged with the other so as to transmit to the drive part a rotation around a central axis while allowing air to pass between male and female portions of the teeth of the rings behind a bearing area. The rings are extended in an at least partially radial manner relative to each other to form an outer ring extension and an inner ring extension respectively facing elements surrounding the drive part that are mounted onto the other ring. The rotor lines can be used in turbine engines. | 08-09-2012 |
20120192533 | DEVICE FOR FILTERING THE INTAKE AIR OF AN INTERNAL COMBUSTION ENGINE HAVING VENTILATION MEANS - A device for filtering intake air of an internal combustion engine, including at least one filtering element including an inlet for air being treated, a first clean air outlet toward the engine, and a second air outlet toward the outside, and a ventilation mechanism driving the air from the second air outlet. The ventilation mechanism includes a fan wheel driven by a turbine set into motion by a gas flow taken from the engine. | 08-02-2012 |
20120174587 | FUEL FLOWMETER HAVING AN IMPROVED REGULATOR DEVICE - A fuel flowmeter for being fed by a pump including an inlet and an outlet, including: a metering valve including an inlet and an outlet, and arranged downstream from the outlet of the pump; a return circuit connecting the inlet of the metering valve to the inlet of the pump; and a pressure regulator device including: a movable valve member to close and open the return circuit, a pressure difference detection surface fastened to the valve member and axially separating a first chamber in communication with the inlet of the metering valve from a second chamber in communication with the outlet from the metering valve, a piston axially separating the second chamber from a third chamber connected to the outlet of the metering valve, and a channel putting the second chamber in communication with the third chamber. | 07-12-2012 |
20120167591 | TURBOSHAFT ENGINE WITH PARALLEL SHAFTS - A free-turbine turboshaft engine including a gas generator including at least one compressor supplied with air, a combustion chamber receiving the compressed air at the output of the compressor, and at least one generator turbine mechanically connected to the compressor by a drive shaft and driven by gases from combustion of fuel carried out in the combustion chamber, and including a free turbine supplied by the gases from the combustion after passing through the generator turbine and which drives a power shaft positioned non-coaxially relative to the drive shaft of the gas generator and supplying the power of the turboshaft engine via a reduction gear. The combustion chamber is a substantially cylindrical or frusto-conical chamber, coaxial with the axis of the generator turbine, and includes a single injector. | 07-05-2012 |
20120163957 | DEVICE FOR SUPPORTING A TURBINE RING, TURBINE HAVING SUCH A DEVICE, AND TURBINE ENGINE HAVING SUCH A TURBINE - A device for supporting a ring of a gas turbine, the ring configured to surround mobile blades of the turbine which are driven by a gas stream flowing upstream to downstream. The device includes at least one upstream hook facing upstream, to be housed in an upstream groove of the ring, opened toward the downstream direction, and at least one downstream hook facing downstream, to be housed in a downstream groove of the ring, opened toward the upstream direction. The hooks are protected and clearances at apexes of the blades are more easily controlled. The device further includes, upstream from the upstream hook, a mechanism injecting cooling gas to cool the upstream hook and/or includes, downstream from the downstream hook, a mechanism injecting a cooling gas to cool the downstream hook. | 06-28-2012 |
20120087800 | CENTRIFUGAL IMPELLER FOR A COMPRESSOR - A centrifugal impeller for a compressor, through which a fluid is to pass. The impeller includes blades each having a leading edge and a trailing edge, the rotation of the impeller sucking fluid in through the front of the impeller, the fluid leaving the impeller via its outer periphery, the trailing edges of the blades being such that in a radial section plane intersecting the trailing edges of the blades, they are curved in the direction opposite to the direction of rotation of the impeller, and the trailing edge portions of the blades are redirected in the direction of rotation of the impeller to form respective end fins serving to deflect the flow of the fluid by redirecting it radially. | 04-12-2012 |
20120055169 | TURBINE ENGINE COMPRISING AN EXHAUST-GAS GUIDE CONE WITH A SOUND SUPPRESSOR - A gas turbine engine, in which gases flow upstream to downstream, including a combustion chamber, a high-pressure turbine placed downstream from the combustion chamber, arranged so as to receive combustion gases from the combustion chamber, a free turbine, and an exhaust-gas guide cone attached to the free turbine downstream from the free turbine, the turbine engine emitting sound waves during operation. The guide cone includes a sound suppressor, for example with a Helmholtz resonator structure, with a resonant cavity and a resonator neck in communication with an opening, arranged so as to suppress the sound waves emitted by the turbine engine. | 03-08-2012 |
20120041723 | DATA STRUCTURE FOR A LIST OF PARTS - A data structure for a parts list of a mechanical device, the parts list including at least one set including at least one element selected from a component and a set of components. The structure includes: an identifier of the set; an identifier of the element; at least one link between the identifier of the element and at least one CAD file including a geometrical representation of the element; at least one link between the identifier of the set and at least one data file including a three-dimensional positioning matrix of the at least one element of the set, together with at least one pointer to the CAD file containing the geometrical representation of the element of the set; and a three-dimensional positioning vector for positioning the element in the set. | 02-16-2012 |
20120037280 | METHOD FOR PRODUCING A PART MADE FROM A SUPERALLOY BASED ON NICKEL AND CORRESPONDING PART - A method for manufacturing a blank part in Ni-base superalloy, wherein an alloy is prepared and heat treatments are conducted characterized in that: the said superalloy contains at least a total of 2.5% of Nb and Ta; heat treatment is conducted comprising a plurality of steps: a first step at between 850 and 1000° C. held for at least 20 minutes to precipitate the δ phase at the grain boundaries; a second step held at a temperature higher than the temperature of the first step allowing partial dissolution of the δ phase obtained at the first step; ageing treatment comprising a third step and optionally one or more additional steps at a temperature below the temperature of the first step and allowing precipitation of the hardening phases γ′ and γ″. Part thus obtained. | 02-16-2012 |
20120036865 | AIR BLEED HAVING AN INERTIAL FILTER IN THE TANDEM ROTOR OF A COMPRESSOR - The invention relates to a secondary air system for a compressor of centrifugal or mixed type including a rotor presenting an axis of rotation, said compressor being adapted to compress an oxidizer gas. The secondary air system includes an oxidizer gas bleed system arranged in the rotor. | 02-16-2012 |
20120020789 | TURBINE WHEEL HAVING DE-TUNED BLADES AND INCLUDING A DAMPER DEVICE - A turbine wheel including: a plurality of first and second blades, at least one of the first blades being adjacent to at least one of the second blades; a disk presenting an axis of rotation and a periphery having the blades mounted thereat, each of the blades including a head solid with a root engaged in a housing that opens to the periphery of the disk, each of the blades including a keying mechanism including a respective shelf arranged between the head and the root of the blade, the shelves of the first blades presenting an azimuth length different from the azimuth length of the shelves of the second blades; and a damper device arranged at least between the adjacent blades, the damper device being arranged between the shelves of the blades and the periphery of the disk. | 01-26-2012 |
20110318188 | AXIAL CENTRIFUGAL COMPRESSOR WITH SCALABLE RAKE ANGLE - A mobile wheel for a centrifugal or axial centrifugal compressor for a turbine engine, that includes a base on which a plurality of vanes are attached at their feet and extend between a leading edge and a trailing edge, the trailing edge being inclined at the base of the vane by a slope angle relative to the middle plane extending through the base thereof in the rotation direction of the compressor. The trailing edge has at the head of the vane a slope angle smaller than the slope angle at the vane base. | 12-29-2011 |
20110311366 | TURBINE WHEEL PROVIDED WITH AN AXIAL RETENTION DEVICE THAT LOCKS BLADES IN RELATION TO A DISK - A turbine wheel including a plurality of blades, each of the blades presenting an airfoil, a platform, and an attachment member, a disk having the blades mounted at the periphery thereof, the attachment member of each blade being engaged in a housing that opens into a periphery of the disk and extending axially between two opposite faces of the disk, the housings being separated by teeth, and an axial retention device for retaining the blades. The disk includes a first stop member, and the platform of the blade includes a projection projecting axially beyond one of the faces of the disk. The projection includes a second stop member. The axial projection, the second stop member, and the face of the disk together form a groove facing towards the axis of the disk, the groove serving to receive the axial retention device. | 12-22-2011 |
20110299987 | EROSION INDICATOR FOR A COMPRESSOR WHEEL - A centrifugal compressor wheel including a hub, a web extending radially from the hub, and a plurality of blades carried by the wheel. The web includes an erosion indicator of the wheel. | 12-08-2011 |
20110284318 | SOUNDPROOF EXHAUST PIPE FOR A TURBINE ENGINE - The soundproofed exhaust duct for a turbine engine comprises a perforated inner shell defining a flow passage, and a solid outer shell, the inner and outer shells defining between them a space that is closed at the upstream and downstream ends of said space. A core extends between the inner and outer shells at a distance therefrom, and contains at least one sound energy dissipating layer made up of hollow beads that are held against one another. A frame with upstream and downstream portions connected together by longitudinal members supports the core and partitions it into a plurality of boxes that are filled with hollow beads that are held between perforated textures, the frame being secured to the outer shell and/or to the inner shell via at least one of its upstream and downstream portions. | 11-24-2011 |
20110283712 | THERMOELECTRIC GENERATION FOR A GAS TURBINE - A device for producing electrical power in a gas turbine or the like of an aircraft, the device including a plurality of thermoelectric cells having a face surrounding a hot source. A cold source is constituted by a cold fluid flowing over the other face of the thermoelectric cells. | 11-24-2011 |
20110255962 | DIFFUSER HAVING BLADES WITH APERTURES - A diffuser for a mixed flow or centrifugal compressor of a gas turbine. The diffuser includes at least one vane presenting a pressure side, a suction side, and a first flank. The vane includes a plurality of orifices opening out into the suction side and/or the pressure side and communicating with at least one cavity formed in the vane, the cavity extending transversely relative to the vane and opening out into its first flank. The cross section of the cavity varies in the transverse direction of the vane, the cross section increasing towards the first flank. | 10-20-2011 |
20110250071 | TURBINE WHEEL WITH AN AXIAL RETENTION SYSTEM FOR VANES - A turbine wheel includes: a plurality of blades, a rotor including a disk having the blades mounted at a periphery thereof, each blade including an airfoil with a foot secured to a platform carrying an attachment member engaged in a housing that opens into the periphery of the disk and that extends axially between two opposite side faces of the disk, the housings being spaced apart from one another by portions of the disk that form teeth, and an axial retention plate retaining the blades on the disk and including a retention plate situated on one side of the disk. On the other side of the disk, the teeth of the disk present portions in relief that project radially and that form abutments pressing axially against the portions in relief that are formed under the platforms of the blades and that are set back relative to side faces of the attachment members situated beside a second side face of the disk, and side faces of the attachment members of the blade and of the disk at its periphery are situated in substantially a same plane on each side of the disk. | 10-13-2011 |
20110236203 | RING SEGMENT POSITIONING MEMBER - A positioning member for presenting a ring segment for a turbine wheel mounted to rotate about an axis inside a casing. The member presents: a fastener portion for fastening to the casing; a resilient portion forming a spring; and a bearing portion connected to the resilient portion and serving to bear axially against the ring segment such that when the member is mounted the ring segment is pressed axially against a portion of the casing by the positioning member. | 09-29-2011 |
20110123350 | HOLLOW TURBINE WHEEL VANE COMPRISING A RIB AND ASSOCIATED WHEEL AND TURBOMACHINE - A turbine blade extends radially between a blade root and a blade tip having an open cavity referred to as a bathtub formed therein, which cavity is defined by a closed end wall and a side rim. The side rim of the cavity carries at least one rib extending between a leading edge and a trailing edge of the blade. | 05-26-2011 |
20110076141 | COMPRESSOR COVER FOR TURBINE ENGINE HAVING AXIAL ABUTMENT - A centrifugal compressor for a turbine engine, including a cover with an upstream end and a downstream end; a casing presenting an upstream edge and a downstream edge; and a bladed impeller mounted to rotate in the casing. The cover covers the blades of the impeller to define an outside surface of a gas-flow passage extending between the upstream and downstream edges of the casing, while being fastened to the upstream edge of the casing via its upstream end while its downstream end remains free. The cover further includes an abutment limiting axial movement of its downstream end relative to the downstream edge of the casing while the compressor is in operation. | 03-31-2011 |
20110064583 | COMPRESSOR IMPELLER BLADE WITH VARIABLE ELLIPTIC CONNECTION - A compressor impeller including at least one blade connected to an impeller hub via a junction of curved shape, the blade extending along a defined chord between a leading edge and a trailing edge of the blade. The junction presents the shape of an ellipse that varies along the chord. | 03-17-2011 |
20110056309 | DEVICE FOR MEASURING THE TORQUE TRANSMITTED BY A POWER SHAFT - A torque measurement device including: a power shaft transmitting rotary torque about the axis of the power shaft; a first wheel carrying angle marks, the wheel being secured to the power shaft; a reference shaft including a second wheel carrying angle marks; and a sensor placed facing at least one of the wheels to determine the torque transmitted by the power shaft. The first wheel includes first and second series of angle marks and the second wheel includes third and fourth series of angle marks. The marks of the first and third series are mutually parallel, while the marks of the second and fourth series are mutually parallel and are inclined relative to a first axial plane containing the axis, the marks of the first series being inclined relative to the marks of the second series, whereby the signal supplied by the sensor is representative of temperature of the power shaft. | 03-10-2011 |
20110049891 | TURBINE ENGINE INCLUDING A REVERSIBLE ELECTRIC MACHINE - A turbine engine, for example for a helicopter, the engine including a gas generator and a free turbine driven in rotation by a gas stream generated by the gas generator, the turbine engine further including a reversible electric machine for coupling to the gas generator, the reversible electric machine configured to set the gas generator into rotation during a stage of starting the turbine engine. To generate electricity, the reversible electric machine is also configured to be coupled to the free turbine after the turbine engine has started. | 03-03-2011 |
20100119368 | DOUBLE SEAL WITH PRESSURISED LIP - A sealing device for providing sealing between a casing and a shaft rotatably mounted in the casing. The device includes first and second annular lip gaskets for placing axially side by side between the casing and the shaft. A stream of pressurized gas is delivered into an annular casing defined by the first lip gasket, the second lip gasket, and an outside surface of the shaft, such that during rotation of the shaft, the gas stream is suitable for causing at least one of the two lip gaskets to lift off a little from the outside surface of the shaft in order to flow out from the cavity. | 05-13-2010 |
20100101206 | DEVICE FOR DE-ICING THE AIR INTAKE OF A GAS TURBINE - A de-icer device for de-icing an air inlet of a gas turbine, such as a helicopter turbine engine. The de-icer device includes an essentially metallic enclosure for admitting air into the engine, the enclosure including a first opening for admitting air into the enclosure, the first opening including a first essentially metallic grid, the enclosure further including a second opening for directing the air towards a compression stage of the gas turbine. The de-icer device further includes a wave generator for generating electromagnetic waves in the enclosure at a frequency suitable for causing ice to melt. | 04-29-2010 |
20100058731 | ASSISTANCE DEVICE FOR TRANSIENT ACCELERATION AND DECELERATION PHASES - A turbine engine, for example for a helicopter, including a gas generator and a free turbine driven in rotation by the gas flow generated by the gas generator. The turbine engine further includes a motor/generator coupled to a shaft of the gas generator, to provide a quantity of additional rotational kinetic energy to the shaft during a stage of turbine engine acceleration, or to draw a quantity of rotational kinetic energy from the shaft during a stage of turbine engine deceleration. | 03-11-2010 |
20090314064 | PRE-SIGNALING MAGNETIC PLUG - The invention relates to a signaling magnetic plug for a liquid circuit, the plug including a first magnetic electrode and a second magnetic electrode for coming into contact with the liquid flowing in the liquid circuit when the magnetic plug is mounted so as to detect the presence of metal particles that might be contained in the liquid. According to the invention, the plug also includes a preferably non-magnetic intermediate electrode disposed between the first and second magnetic electrodes while also being designed to be in contact with the liquid flowing in the liquid circuit when the magnetic plug is mounted, whereby said plug enables the presence of such metal particles to be detected early. | 12-24-2009 |
20090116955 | TURBINE ENGINE COMPRISING MEANS FOR HEATING THE AIR ENTERING THE FREE TURBINE - The invention relates to a turbine engine ( | 05-07-2009 |
20080209910 | METHOD OF STARTING A GAS TURBINE HELICOPTER ENGINE, A FUEL FEED CIRCUIT FOR SUCH AN ENGINE, AND AN ENGINE HAVING SUCH A CIRCUIT - At least one of the main injectors of the engine, forming a starter main injector, is fed directly by the pressurized feed pipe, while a head loss is imposed between the pressurized feed pipe and the other main injectors. Ignition is caused to take place at the starter main injector, and after ignition, said head loss imposed between the feed pipe and the other main injectors is eliminated so that all of the main injectors are fed with fuel at substantially the same pressure, without any imposed head loss. | 09-04-2008 |