| Patent Number |
Title Of Patent |
Date Issued |
| 7619331 |
Turbomachine with integral generator/starter |
November 17, 2009 |
| Turbomachine such as an aircraft turbojet comprising an electrical generator/starter (26) that can be mounted and dismounted by axial translation in an upstream enclosure (18) of the turbomachine between the low-pressure compressor and the high-pressure compressor, and couple to elec |
| 7618232 |
Compressor comprising a plurality of cells reconstituting an annular volume of separation of flo |
November 17, 2009 |
| This turbine engine compressor comprises a separating nose extended by inner and outer annular walls defining in cooperation an annular volume (V) of separation of a primary flow (F1) and a secondary flow (F2). This volume (V) comprises a plurality of annular segments in the form of cell |
| 7617688 |
Combustion chamber of a gas turbine engine with an upstream fairing for separating the gas strea |
November 17, 2009 |
| The present invention is concerned with an annular combustion chamber of a gas turbine engine with an external annular wall and an internal annular wall, including an upstream fairing for separating the gas stream at the inlet of the chamber into a combustion stream and a bypass stream w |
| 7614846 |
Ceramic-based bushing for a variable-pitch vane system in a turbomachine |
November 10, 2009 |
| The invention relates to a ceramic-based bushing for mounting in a turbomachine casing to provide a smooth bearing for a pivot of a variable-pitch vane. The bushing is constituted by a metal jacket and a ceramic ring secured to the inside wall of said jacket by brazing. The invention |
| 7614845 |
Turbomachine inner casing fitted with a heat shield |
November 10, 2009 |
| The present invention relates to an improvement in the clearances 12 between a casing and the moving blades 11 of a rotor 1 of a turbomachine, in particular a casing provided for this purpose, and also to a turbomachine fitted with such a casing. The invention applies in particular t |
| 7614236 |
Positioning bridge guide and its utilisation for the nozzle support pipe of a turboprop |
November 10, 2009 |
| A bridge positioned between two parts, such as a nozzle support pipe envelope and a heat shield liner, includes a central part with inversed curvature thus having two contact zones with the nozzle support pipe envelope. Furthermore, the bridge includes two lugs, one of which can be m |
| 7614234 |
Turbomachine combustion chamber with helical air flow |
November 10, 2009 |
| The invention relates to a turbomachine combustion chamber having an inner wall, an outer wall surrounding the inner wall so as to co-operate therewith to define a space forming a combustion area, a transverse wall interconnecting the inner and outer walls, and fuel injection systems. |
| 7607213 |
Method of making a device for measuring deformation |
October 27, 2009 |
| A method of making a device for measuring deformation includes a step of depositing a silicon adhesion underlayer on a silicon carbide surface by chemical vapor spraying, and a step of depositing a coating on the silicon adhesion underlayer by atmospheric thermal spraying. |
| 7600953 |
Rotary cutting tool comprising two cutting portions having opposed cutting directions |
October 13, 2009 |
| A method of machining a workpiece with a rotary cutting tool extending along a longitudinal axis and including a first cutting portion including a plurality of first helical teeth having a helix direction and being designed to work in a first direction of rotation of the tool. The tool |
| 7600384 |
Gas exhaust nozzle for a bypass turbomachine having an exhaust or throat section that can be var |
October 13, 2009 |
| The invention relates to an exhaust nozzle for a bypass turbomachine, the nozzle comprising a central body, a primary cowl surrounding the central body to define a primary channel, and a secondary cowl surrounding the primary cowl to define a secondary annular channel, the secondary cowl |
| 7600383 |
Turbojet with protection means for a fuel injection device, an injection device and a protective |
October 13, 2009 |
| The turbojet of the invention includes a combustion chamber, a channel for heating the gas stream, where the heating channel includes at least one device for injection of fuel into the gas stream, which includes an open chamber, with a U-shaped section, having at least one wall within wh |
| 7597538 |
Thermostructural turbomachine part that is circularly symmetrical about a longitudinal axis, the |
October 6, 2009 |
| In the method, a support is provided that presents a base for an annular wiper, and a wiper is built up that presents height that varies around its circumference, by forming a plurality of projecting portions by performing following successive steps: a laser source connected to an |
| 7596938 |
Turbomachine with a deflector system |
October 6, 2009 |
| A turbomachine front portion includes an internal support shroud for the fan outlet guide vanes, and a flow splitter fairing from which a primary duct and a secondary duct originate. The front portion includes at least one deflector system configured to prevent/limit the ingress of h |
| 7594792 |
Sealing device for a chamber of a turbomachine, and aircraft engine equipped with said sealing d |
September 29, 2009 |
| The gastight sealing device associated with a functional clearance existing between two sectors of a turbomachine includes an annular plate wound up on itself over at least one turn, covering functional clearance. |
| 7594324 |
Method of assembling a turbomachine |
September 29, 2009 |
| A method of assembly of a turbomachine that includes a first module and a second module with a second shaft assembled by a bearing, the bearing including an outer ring shrink-fitted inside a journal integral with the first module and an inner ring integral with the second shaft. The seco |
| 7591594 |
Turbomachine with a compact roller bearing |
September 22, 2009 |
| A turbomachine roller bearing that supports a shaft constituted by a trunnion of a shaft line of a high-pressure spool of a turbomachine to rotate relative to a stationary support that is connected to a casing of the turbomachine, said bearing comprising rollers inserted between an o |
| 7591136 |
Antirotation injection system for turbojet |
September 22, 2009 |
| Injection system of a turbojet engine. It comprises a fixed part and a sliding crossmember. The sliding crossmember comprises a flange capable of sliding on the sliding surface of the fixed part. The fixed part comprises antirotation means and the sliding crossmember of the complemen |
| 7588416 |
Pivot bushing for a variable-pitch vane of a turbomachine |
September 15, 2009 |
| A pivot bushing for a variable-pitch vane of a turbomachine, the bushing being for mounting in a recess in a ring of the turbomachine, the recess being of a shape that is substantially complementary to the shape of the bushing. The bushing comprises a substantially tubular body of lo |
| 7584618 |
Controlling air flow to a turbine shroud for thermal control |
September 8, 2009 |
| A system for controlling a flow of air applied to a gas turbine shroud in an airplane engine, the air flow being adjusted by a regulator valve of position that is controlled by a first control signal calculated on the basis of a first setpoint value corresponding to predetermined clearan |
| 7584615 |
Method of improving the ignition performance of an after-burner device for a bypass turbojet, an |
September 8, 2009 |
| The after-burner device receives a "hot" central primary flow from the turbine of the turbojet and a "cold" peripheral secondary flow, and it has an after-burner ignition zone situated in the secondary flow that reaches the after-burner device. A fraction of the primary flow is broug |
| 7584546 |
Alignment control for a water-jet cutting system |
September 8, 2009 |
| Device for checking the alignment of a water jet in a water-jet cutting system, comprising means for positioning an annular element at the outlet of a focusing tube, at some distance from this outlet and aligned with respect to the axis of this focusing tube, this annular element having |
| 7583200 |
Method and system for detecting and measuring the disturbances in terms of frequency of the rate |
September 1, 2009 |
| A method and system for detecting the variations of speed (R) of a rotor. Signals are measured representative of the march-past of the teeth of a measurement device secured to the rotor for a determined duration (T). The measurements are sampled, digitized and stored to obtain an initial |
| 7582174 |
Metal component treated by putting sublayers in compression, and method of obtaining such a comp |
September 1, 2009 |
| The invention relates to a metal component comprising at least a first zone treated by putting layers beneath the surface thereof in compression. It is characterized in that it comprises at least a first layer put in compression by shot peening and a deeper subjacent second layer put |
| 7581932 |
Method of manufacturing a composite turbomachine blade, and a blade obtained by the method |
September 1, 2009 |
| The invention relates to a method of manufacturing a composite turbomachine blade, the method comprising the following steps: a) making a preform by three-dimensionally weaving yarns including tracer yarns disposed at least at the surface of the preform; b) cutting out said preform |
| 7581920 |
Method for air circulation in a turbomachine compressor, compressor arrangement using this metho |
September 1, 2009 |
| An air circulation method in a turbomachine compressor includes minimizing an inner flowpath between two adjacent blades by providing labyrinths on an inner casing between the two adjacent blades, and sucking in air from the minimized inner flowpath through a radially inner orifice of a |
| 7581400 |
Elbow-shaped propulsion gas exhaust assembly in an aircraft |
September 1, 2009 |
| A propulsion gas exhaust assembly is presented for use in an aircraft propelled by hot gases produced along the axis of the latter by a gas generator. The assembly may include a first cylindrical duct, two second ducts, two third ducts, and two axial gas-ejection nozzles. The first c |
| 7581384 |
Turbomachine nozzle cover provided with triangular patterns having a point of inflexion for redu |
September 1, 2009 |
| The invention relates to an annular cover for a turbomachine nozzle, the cover having a plurality of patterns extending a trailing edge of said cover and spaced apart circumferentially from one another, each pattern having an outline that is substantially triangular in shape, with a base |
| 7578059 |
Method for manufacturing constituents of a hollow blade by rolling |
August 25, 2009 |
| In a method for manufacturing a hollow blade for a turbomachine, the blade is made from a preform derived from external primary parts. Each primary part comprising a root part is formed by flattening a blank cut out from a ring with a large diameter provided with a protuberance, in order |
| 7574866 |
Turbo-jet engine with a protective screen of the fuel manifold of a burner ring, the burner ring |
August 18, 2009 |
| A double flow turbo-jet engine includes a re-heating channel of the primary flow and an ejection nozzle, the secondary flow emerging at least partially in the primary flow upstream of the re-heating channel, the re-heating channel including a burner ring, including a flame holder gut |
| 7571614 |
Turboshaft engine comprising two subassemblies assembled under axial stress |
August 11, 2009 |
| Turboshaft engine including two subassemblies defining between them an annular chamber housing a seal. The two subassemblies are assembled under axial stress thereby defining an annular chamber housing the seal and an interposed part is inserted between the butting surfaces of the two pa |
| 7569251 |
Method of forming a thermal protective coating on a super alloy metal substrate |
August 4, 2009 |
| A method of forming a gas turbine part includes forming a bonding underlayer on a superalloy metal substrate, the underlayer including an intermetallic compound of aluminum, nickel, and platinum, and forming a ceramic outer layer on the alumina film formed on the bonding underlayer. |
| 7568350 |
Combustion chamber for a turbomachine |
August 4, 2009 |
| Combustion chamber for a turbomachine, comprising a chamber endwall equipped with fuel injection means and axisymmetric walls connecting the chamber endwall to internal and external flanges for fastening to internal and external casings, these flanges including annular portions pierc |
| 7568345 |
Effervescence injector for an aero-mechanical system for injecting air/fuel mixture into a turbo |
August 4, 2009 |
| A fuel injector for an aero-mechanical injection system for injecting an air/fuel mixture into a turbomachine combustion chamber, the injector comprising a main tubular structure of axis XX' opening out at a downstream end for delivering the air/fuel mixture, a tubular fuel duct that |
| 7568336 |
Aeroengine fitted with heat exchanger means |
August 4, 2009 |
| An aeroengine includes a primary air circuit; a high-pressure compressor fed by the primary air; and a secondary air circuit. The engine further includes at least one heat exchanger mounted in the primary air circuit upstream from the high-pressure compressor, the heat exchanger includin |
| 7566029 |
Suspension for suspending a jet engine on an aircraft strut |
July 28, 2009 |
| A suspension for suspending a jet engine on an aircraft strut includes a beam having a platform provided with fasteners for fastening the beam to the aircraft strut and arranged transversely with respect to a longitudinal axis of the jet engine. The suspension also includes first and |
| 7565851 |
Geometrical construction process for a flash land for the forging of a complex part |
July 28, 2009 |
| A process for geometrical construction of a flash land is provided for a flash land that is to be provided in a die for forging of a turbomachine vane, in accordance with determined parameters, where the vane includes a blade. The process includes choosing at least three reference planes |
| 7562691 |
Core for turbomachine blades |
July 21, 2009 |
| The present invention relates to a ceramic core used in the manufacture, by lost wax casting, of a turbomachine blade with cooling cavities and a squealer, comprising at least one main core, wherein the main core (10) comprises an element (10B) shaped so as to constitute the squealer and |
| 7556474 |
Turbomachine, for example a turbojet for an airplane |
July 7, 2009 |
| A turbomachine including a wheel with hollow blades that are cooled internally by a forced flow of cooling air. According to an important characteristic of the invention, a hook-annulus (70) is interposed between the outer edge of the labyrinth-disk (52) and the rotor disk (36), the |
| 7556083 |
Process for manufacturing the blade of a turbomachine, and assembly of the cores for implementat |
July 7, 2009 |
| A plugged assembly of cores includes a first core having a first end portion, and a second core having a second end portion. The first end portion of the first core is connected to the second end portion of the second core by a mortise and tenon type connection to form an assembly of |
| 7555939 |
Method for the modular balancing of a turbomachine rotor |
July 7, 2009 |
| A method of balancing a first turbomachine module (20), including along an axis of rotation a bearing plane (22) on one side and a junction plane (24) on the other, with respect to a rotor (1) including said module (20), in which an equivalent complementary module is defined such that |
| 7555894 |
Swivelling exhaust nozzle for an aircraft engine |
July 7, 2009 |
| Swivelling nozzle for an aircraft engine, the nozzle 10 being pivotally mounted about a transverse yaw axis by means of two elastically deformable one-piece articulations 24 mounted on two external pivots 22 of the nozzle and housed in engine case elements, the nozzle being caused to |
| 7553130 |
Nozzle ring adhesive bonded blading for aircraft engine compressor |
June 30, 2009 |
| A compressor nozzle ring for an aircraft includes an inner shroud, an outer shroud and a multiplicity of blades extending from the inner shroud to the outer shroud. Each blade passes through the inner shroud and is attached to it with sealing cement containing an organic polymer adhe |
| 7553126 |
Device for varying the section of the throat in a turbine nozzle |
June 30, 2009 |
| A device for varying the section of the throat of a turbine nozzle, the nozzle being formed by a plurality of stationary vanes extending radially between outer and inner annular platforms and spaced apart from one another in order to define a throat presenting a minimum flow section. |
| 7553125 |
Method of calibrating the mass of components intended to be mounted at the periphery of a rotor |
June 30, 2009 |
| A method of calibrating the mass of components intended to be mounted at the periphery of a rotor, the method consisting, for each of the components, in removing by machining a volume of material in a region of the component situated on one of its axes of inertia in order to bring th |
| 7552591 |
Twin spool turbine engine with power take-off means on the low-pressure and high-pressure rotors |
June 30, 2009 |
| The invention relates to a twin spool turbine engine comprising a high-pressure rotor and a low-pressure rotor, at least one accessory gearbox, a drive means, driving coaxial transmission shafts that transmit movement to the accessory gearbox, characterized in that the drive means co |
| 7550968 |
Measurement of wall thicknesses particularly of a blade, by eddy currents |
June 23, 2009 |
| A method for evaluating the wall thickness of a hollow part, of the turbomachine blade type, at least at a point having a determined radius of curvature at this point, within determined ranges of radii of curvature and thicknesses, including the determination of impedance values of a |
| 7549838 |
Taking air away from the tips of the rotor wheels of a high pressure compressor in a turbojet |
June 23, 2009 |
| A turbomachine compressor comprises at least one plurality of moving blades and spaced apart therefrom in an axial direction relative to a central longitudinal axis of the turbomachine, a plurality of stationary vanes, and a stationary casing surrounding said plurality of moving blad |
| 7549603 |
Deflection system for a gas stream in a nozzle |
June 23, 2009 |
| Deflection system for a gas stream 11 in an exhaust nozzle 10 of a flying craft, comprising fixed structural housings 18,20 which extend perpendicularly to the gas stream 11 and which are fed with deflection gas through one of their ends external to the nozzle 10, these housings 18,2 |
| 7549294 |
Turbomachine with angular air delivery |
June 23, 2009 |
| A turbomachine assembly comprising: an annular compression section; a casing formed by an outer annular shell (204) and an inner annular shell (206) secured inside the outer shell by means of a plurality of radial support arms (208); an annular combustion section housed inside the ca |
| 7543442 |
Turbojet engine comprising a connector arm for ancillary systems, and the connector arm for anci |
June 9, 2009 |
| A turbofan jet engine includes an outer fan duct, an inner fan duct, fluid-conveying ancillaries located outside the outer fan duct, fluid-conveying ancillaries located inside the inner fan duct. At least one removable modular arm forming a connection for ancillaries is arranged betw |
