| Turbomeca Patent applications |
| Patent application number | Title | Published |
|---|
| 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 |
