Safran Aircraft Engines

Safran Transmission Systems

Fabien Roger Gaston Caty

Serge René Morreale

Patrice Jocelyn Francis Gedin

Paco Maurer

Olivier Belmonte

Antoine Jean-Philippe Beaujard

Thierry Georges Paul Papin

Paul Ghislain Albert Levisse

Christophe Marcel Lucien Perdrigeon

Amélie Argie Antoinette Chassagne

Cedric Zaccardi

Mohamed-Lamine Boutaleb

Sebastien Vincent Francois Dreano

A turbo machine including a device for ventilating and pressurising a turbine rotor of a turbomachine having an axis, the device including at least one collection pipe suitable for collecting a fraction of the air circulating in a high-pressure compressor of the turbomachine and conveying it to a first inner chamber inside the turbomachine that communicates with a second inner chamber delimited by the turbine rotor, the first and second chambers being at least partially separated by a stationary shroud having the axis, wherein it includes at least one injector passing through the stationary shroud and having a cross-section that varies in response to a pressure difference between the first and second chambers.

Turbomachine with device for cooling and pressurising a turbine

Disclosed is a turbomachine () with counter-rotating turbine for an aircraft, comprising: &#x2014;a high-pressure body, &#x2014;a low-pressure counter-rotating turbine (), &#x2014;a planetary-type mechanical epicyclic reduction gear (), &#x2014;a guide bearings (-) for the turbine shafts (), characterised in that said reduction gear () and certain of the bearings () are housed in a lubrication chamber () supplied with oil and comprising dynamic seals (-), and in that the turbomachine comprises circuits (C, C) for pressurising these seals.

Pressurising of lubrication chambers in a turbomachine with counter-rotating turbine

The invention concerns an assembly comprising an epicycloidal gear train () having a central pinion (), an outer crown () and satellite pinions () in engagement with the central pinion () and the outer crown () and each mounted freely rotatable on a satellite carrier (), the central pinion () surrounding and being rotationally fixed to a shaft () and the gear train comprising means for lubricating the teeth and axes () of the satellite pinions (), these means including an annular cup () fixed to the satellite carrier () opened radially inward. According to the invention, the assembly includes fixed oil spraying means () configured to spray oil towards oil deflecting means () towards the inside of the annular cup ().

Assembly comprising a planetary gearset

A ventilated chamber (), subject to an irruption of air at a pressure higher than that in a surrounding chamber () through labyrinth seals separating them and evacuation of excess air through an evacuation duct (), comprises a motor-driven compressor () in the evacuation duct to facilitate suction and evacuation, even when the engine speed does not allow a large overpressure in the chamber ().

Device for evacuation of a ventilated lubricated chamber of a turbomachine

The invention concerns an epicycloidal gear train () comprising a central pinion (), an outer crown () and satellite pinions () in engagement with the central pinion () and the outer crown () and each mounted freely rotatable on a satellite carrier (), the gear train () comprising an annular cup () being integral with the satellite carrier () and open radially inward. According to the invention, the cup () is divided into a circumferential succession of first basins () of the first oil circuit and second basins () of the second oil circuit, the first basins () being fluidly separated from the second cells () and characterised in that the cup () comprises two annular walls () axially facing, the annular wall () of which is furthest from a median transverse plane () of the gear train () has openings () opening into the second basins ().

Planetary gearset

A guide vane for a twin-spool aircraft turbomachine has an aerodynamic part that includes an internal lubricant cooling passage extending along a principal lubricant flow direction. The aerodynamic part is made in a single piece and also includes heat transfer fins arranged in the passage connecting the intrados and extrados walls and extending approximately parallel to the direction, these fins being distributed in successive rows along the principal direction and made such that for two rows of staggered directly consecutive fins, a first row includes fins forming a positive acute angle A1 with a dummy reference plane, while a second row includes fins forming a negative acute angle A2 with this plane.

Growing community of inventors

Moissy-Cramayel, France

Fabien Roger Gaston Caty