Abstract: A turbomachine turbine nozzle extending around a central axis, including at least one radially outer shroud, at least one radially inner shroud, and at least one blade made of ceramic matrix composite material, distinct from the radially inner shroud and from the radially outer shroud, and extending radially between the radially inner shroud and the radially outer shroud, the blade being hollow and including a cavity opening at a radially inner end and at a radially outer end of the blade, the nozzle including at least one tubular mast arranged in the cavity of the blade and allowing routing the ventilation air passing through the cavity of the blade, the mast including a radially outer end attached to the radially outer shroud, and a radially inner end cooperating with a radial flange for positioning the radially inner shroud.

Abstract: A turbine ring assembly having ring segments made of ceramic matrix composite material and each having first and second attachment tabs and a cavity for the circulation of air flow, a metal support having a first bracket and a second bracket bearing axially upstream against the second tab, a first metal flange arranged upstream of the first bracket and having an inner periphery bearing axially downstream against the first tab and an outer periphery fastened to the first bracket, and air passage orifices formed in the inner periphery of the first flange and/or in the second bracket, the orifices configured to ensure that the air flow passes from the cavity to the outside of the assembly.

Abstract: An epicyclic reduction gear for a turbomachine includes a sun gear that is rotatable about a first axis and a ring gear surrounding the sun gear and also rotatable about the first axis. The ring gear is secured to a ring gear carrier that rotates a fan shaft. At least one planet gear is rotatable about a second axis and is meshed with the sun gear and the ring gear. The planet gear is guided in rotation about the second axis relative to a bearing of the planet carrier. A piece of equipment comprising a rotor. The piece of equipment is attached to the bearing of the planet carrier and has a rotor rotated by the ring gear carrier.

Abstract: A polymer blend, including: (i) a poly(aryl ether ketone); (ii) a polysiloxane; and (iii) a block copolymer containing polysiloxane blocks. A process for manufacturing the polymer blend, the use of the polymer blend for the manufacture of parts, notably in the petroleum, cabling, aeronautical, motor vehicle, electronics, electrotechnical, composite, additive manufacturing and medical device sectors and also a part at least partially manufactured from said blend.

Abstract: A turbomachine with a counter-rotating turbine for an aircraft includes a counter-rotating turbine and a mechanical reduction gear with an epicyclic, planetary-type gear train. The gear train includes a planet carrier secured to a stator housing of the turbomachine situated upstream from the counter-rotating turbine in relation to a direction of gas flow within the turbomachine. The planet carrier is secured to the stator housing by an annular part with an elongated shape extending inside the second shaft. The annular part includes an upstream end secured to the intermediate casing and a downstream end coupled to the planet carrier. The annular part also includes an integrated circuit for conveying lubrication oil from its upstream end to the planet carrier.

Abstract: The invention relates to an epicyclic reduction gear for a turbomachine, including a sun wheel that is rotatable about a first axis (A); a ring gear surrounding the sun wheel and being rotatable about the first axis (A); at least one planetary gear that is rotatable about a second axis (B), the planetary gear being meshed with the sun wheel and the ring gear; an immobile planet carrier, the planetary gear being rotatably guided about the second axis (B) with respect to a bearing of the planet carrier; an item of equipment including a rotor. The invention is characterized in that the item of equipment is fastened to the bearing of the planet carrier and the rotor of the item of equipment is rotatably driven by the planetary gear.

Abstract: Methods, servers, and computer programs for processing multiple data records in response to a database request with search indications are provided. The server retrieves multiple data records with parameter values in the fields which correspond to the search indications indicated by the database request, determines weight values for at least two of the fields based on the corresponding parameter values of the at least two fields, calculates an aggregated score for at least a number of the retrieved data records based on the determined weight values, and returns at least a subset of the retrieved data records to the client based on the calculated aggregated scores.

Abstract: An insulated conductor including: at least one electrical conductor; and, an insulating coating covering said electrical conductor, having n layer(s), “n” being an integer greater than or equal to 1, the nth layer being the outermost layer having a pseudo-amorphous composition Cn including at least 50% by weight of a polyaryletherketone. A process for manufacturing the insulated conductor, a heat-welding process using two sections of insulated conductor, and a coil capable of being obtained by heat-welding a winding of the insulated conductor.

Abstract: A process including: the provision of a semicrystalline or crystallizable composition, having a glass transition temperature Tg, including at least one polyaryletherketone; the provision of a compression forming means including: a mold, the mold having at least one cavity; the preparation of the composition in the molten state in said at least one cavity, the mold having a temperature T0 at the end of the preparation stage; the compression and the cooling of the composition in the molten state, the mold being cooled from the temperature T0 down to a final temperature Tfof less than or equal to (Tg+30)° C., to form a compression-formed article; and the removal of the compression-formed article from the mold; in which the composition has a melting point strictly of less than 340° C.

Abstract: Turbomachine (10) having a contrarotating turbine for aircraft, the turbomachine comprising a contrarotating turbine (22) of which a first rotor (22a) is configured to rotate in a first direction of rotation and is connected to a first turbine shaft (36), and a second rotor (22b) is configured to rotate in an opposite direction of rotation and is connected to a second turbine shaft (38), the first rotor comprising turbine discs that are interleaved between turbine discs of the second rotor, said first shaft (36) being guided by at least two guide bearings (60, 62) mounted between this first shaft and a stator casing, and said second shaft (38) being guided by at least two guide bearings (56, 58) mounted between this second shaft and another stator casing (28).

Abstract: A turbomachine with a counter-rotating turbine for an aircraft includes a counter-rotating turbine and a mechanical reduction gear with an epicyclic, planetary-type gear train. The gear train includes a planet carrier secured to a stator housing of the turbomachine situated upstream from the counter-rotating turbine in relation to a direction of gas flow within the turbomachine. The planet carrier is secured to the stator housing by an annular part with an elongated shape extending inside the second shaft. The annular part includes an upstream end secured to the intermediate casing and a downstream end coupled to the planet carrier. The annular part also includes an integrated circuit for conveying lubrication oil from its upstream end to the planet carrier.

Abstract: A reduction gear for a turbomachine (6) extending around an axis (X-X) of rotation, comprising a ring gear (9) connected to a ring gear carrier (12), wherein the ring gear carrier (12) has, according to a section view along a plane including the axis (X-X), an internal segment (124), an external segment (126) and a ring gear support (128), extending successively from the internal shaft (122) until the ring gear support (128), the internal segment (124) extends until a radius R1 with respect to the axis (X-X), the external segment (126) forms an angle ? with the internal segment (124), the ring gear support (128) forms an angle ? with the external segment (126), and is secured to the ring gear (9) via a bolted connection accomplished at a nominal radius R2 with respect to the axis (X-X), in that the ratio R1/R2 is comprised between 0.3 and 0.7.

Abstract: A mechanical reduction gear for a turbomachine, in particular for an aircraft, including a first sun gear having a central axis forming a main axis of the reduction gear, a ring gear, planet gears, a planet carrier, and at least one electric generator, in which the electric generator has a first set of electromagnetic elements and a second set of electromagnetic elements, wherein one among the first and second set of electromagnetic elements is a first set of coils, each coil of this first set of coils being wound around a direction parallel to the main axis, and in which the other among the first and second set of electromagnetic elements is configured to induce a current in the first set of coils when it is driven with a relative movement with respect to the first set of coils.

Abstract: The invention relates to an epicyclic reduction gear for a turbomachine, including a sun wheel that is rotatable about a first axis (A); a ring gear surrounding the sun wheel and being rotatable about the first axis (A); at least one planetary gear that is rotatable about a second axis (B), the planetary gear being meshed with the sun wheel and the ring gear; an immobile planet carrier, the planetary gear being rotatably guided about the second axis (B) with respect to a bearing of the planet carrier; an item of equipment including a rotor. The invention is characterized in that the item of equipment is fastened to the bearing of the planet carrier and the rotor of the item of equipment is rotatably driven by the planetary gear.

Abstract: An epicyclic reduction gear for a turbomachine includes a sun gear that is rotatable about a first axis and a ring gear surrounding the sun gear and also rotatable about the first axis. The ring gear is secured to a ring gear carrier that rotates a fan shaft. At least one planet gear is rotatable about a second axis and is meshed with the sun gear and the ring gear. The planet gear is guided in rotation about the second axis relative to a bearing of the planet carrier. A piece of equipment comprising a rotor. The piece of equipment is attached to the bearing of the planet carrier and has a rotor rotated by the ring gear carrier.

Abstract: The use of PEKK for lowering the CO2 and H2S permeability of a part intended to enter into contact with a petroleum effluent. Also, a pipe for transporting a petroleum effluent, including a layer intended to be in contact with the petroleum effluent, wherein the layer intended to be in contact with the petroleum effluent comprises PEKK and has a CO2 permeability at 130° C. of less than 10?8 cm3, for a thickness of 1 cm and a surface area of 1 cm2 and per second and bar of CO2 pressure and/or an H2S permeability at 130° C. of less than 10?8 cm3 for a thickness of 1 cm and a surface area of 1 cm2 and per second and bar of H2S pressure, the amount of CO2 and H2S being measured by GC, respectively. Lastly, a number of methods for manufacturing such a pipe.

Abstract: Methods, servers, and computer programs for processing multiple data records in response to a database request with search indications are provided. The server retrieves multiple data records with parameter values in the fields which correspond to the search indications indicated by the database request, determines weight values for at least two of the fields based on the corresponding parameter values of the at least two fields, calculates an aggregated score for at least a number of the retrieved data records based on the determined weight values, and returns at least a subset of the retrieved data records to the client based on the calculated aggregated scores.

Abstract: A reduction gear for a turbomachine (6) extending around an axis (X-X) of rotation, comprising a ring gear (9) connected to a ring gear carrier (12), wherein the ring gear carrier (12) has, according to a section view along a plane including the axis (X-X), an internal segment (124), an external segment (126) and a ring gear support (128), extending successively from the internal shaft (122) until the ring gear support (128), the internal segment (124) extends until a radius R1 with respect to the axis (X-X), the external segment (126) forms an angle ? with the internal segment (124), the ring gear support (128) forms an angle ? with the external segment (126), and is secured to the ring gear (9) via a bolted connection accomplished at a nominal radius R2 with respect to the axis (X-X), in that the ratio R1/R2 is comprised between 0.3 and 0.7.

Abstract: The invention concerns a process for the assembly of an epicyclic or planetary gear train of a planet gear carrier comprising one or more bores, each of the bores being intended to receive a pivot (18), the process comprising the following steps: a) manufacturing of at least one pivot (18) comprising a real axis (46) distinct from a theoretical axis; b) measuring the position of a real axis of each of said one or more bores of the carrier; c) for each bore of the carrier, mounting a pivot (18) in said bore and orienting it angularly so that the eccentricity of the pivot (18) at least partially makes up for the eccentricity of said bore.

Abstract: The invention concerns a process for the assembly of an epicyclic or planetary gear train from at least one pivot (18) and a planet gear carrier (20) comprising one or more bores, each of said bores being intended to receive a pivot (18), the process comprising the following steps: a) measuring the position of a real axis of each of said at least one pivot (18) and of said one or more bores of carrier (20); b) dividing each of said pivots (18) into n angular sectors i1 . . . iq . . . in extending about the theoretical axis of said pivot and dividing each of said holes of the carrier (20) into k angular sectors j1 . . . jl . . .