Safran Aircraft Engines

Yanis Benslama

Jeremy Dievart

Dominik Igel

Nathalie Nowakowski

Serge Rene Morreale

Serge René Morreale

Alexandre Jean-Marie Tan-Kim

Jérémy Dievart

Olivier Belmonte

Michel Gilbert Roland Brault

Julien Fabien Patrick Becoulet

Paul Ghislain Albert Levisse

Romain Guillaume Cuvillier

Serge Benyamin

Marion Jeanne Pierrette Verdier

A turbomachine includes a single ducted fan including a first shaft rotated by a second shaft via a speed reduction gearset, the second shaft being rotated by a third shaft of a turbine, the first shaft being guided in rotation with respect to a fixed structure via a first bearing and a second bearing placed upstream of the speed reduction gearset. The second shaft is guided in rotation with respect to the first shaft via a rolling bearing placed upstream of the speed reduction gearset, the rolling bearing comprising an outer ring housed in the first shaft, an inner ring connected to the second shaft and rolling elements arranged between the inner and outer rings.

Aircraft turbomachine with reducer

A dual-flow turbojet engine having a central shaft surrounded by a high-pressure body which rotate about the same longitudinal axis while being independent in rotation, and including a fan driven by the central pressure shaft; a high-pressure compressor and a high-pressure turbine mounted on the high-pressure body; an inter-turbine casing; a low-pressure turbine mounted on a low-pressure rotor surrounding the central shaft; an exhaust casing on which an output cone is mounted; a reduction gear with which the low-pressure rotor drives the central pressure shaft; two bearings mounted on the exhaust casing and respectively receiving the central shaft and the low-pressure rotor; a bearing mounted on the inter-turbine casing and receiving the low-pressure rotor.

Dual-flow turbojet engine arrangement with epicyclic or planetary reduction gear

Turbine engine () with a contra-rotating turbine for an aircraft,

Turbine engine with a contra-rotating turbine for an aircraft

A turbofan having a dilution rate of at least 10 and including a fan having a disc provided with blades at the periphery thereof, a distance between the head of the blades and the housing of the fan being less than or equal to ten millimeters; a primary flow space and secondary flow space that are concentric; a turbine, housed in the primary flow space and in fluid communication with the fan; and a reduction mechanism coupling the turbine and the fan.

Gas turbine engine with minimal tolerance between the fan and the fan casing

A ducted fan module with variable-pitch blades for a turbo engine includes a rotor carrying a plurality of blades, a stationary casing, and a blade pitch changing and control system. The rotor includes a central shaft and a surrounding blade support ring. A front end of the blade support ring is connected to a front end of the central shaft, creating a rearward-opening annular space between the blade support ring and the central shaft. A tubular part is connected to the stationary casing and extends into the annular space.

Fan module with variable-pitch blades for a turbine engine

The invention relates to a fan module having variable-pitch blades for a turbine engine, including a rotor () having blades (), a stationary casing (), and a system for adjusting and controlling the pitch of the blades (), the rotor () including a central shaft () and a ring () for supporting the blades surrounding the shaft, a front end of the ring being connected to a front end of the shaft so as to define an annular space between the ring and the shaft which is open towards the rear, said annular space of the rotor () housing said system, and the shaft () being guided by a first bearing () mounted in the stationary casing (), to the rear of the ring (), characterised in that the ring () is guided by at least one complementary bearing () located upstream of the first bearing ().

Fan module having variable-pitch blades for a turbine engine

The invention relates to a fan module with variable-pitch blades for a turbomachine, comprising a rotor () carrying blades (), a stationary housing (), a mechanism () for regulating the pitch of the blades (), which is connected to the rotor, and a control means () mounted on the stationary housing () and comprising a control part () that can be moved in translation according to an axis (X) of rotation of the rotor (), and a bearing () for load transfer between the control part () and said mechanism, characterised in that it also comprises a stationary track () supporting the elastic restoring means () which are arranged so as to exert an axial restoring force on the control part () towards a determined position, preferably corresponding to the blade () feathering.

Fan module with variable-pitch blades for a turbomachine

A turbofan engine including: a turbine shaft; a fan shaft; and a reduction mechanism coupling the turbine shaft and the fan shaft, is provided. The turbofan engine has a bypass ratio greater than or equal to 10, and the turbine shaft is supported by four bearings such that the flexural deformation modes of the turbine shaft are positioned in transient phase or outside the operating range of the turbofan engine.

Turbofan comprising a low-supercritical-pressure shaft

A bearing suspension device includes first and second elastically flexible members extending in an axial direction; and first and second thrust points that are movable in the axial direction and that are in radial contact respectively with the first and second elastically flexible members. The bearing suspension device is configured to transmit a radial force by the first elastically flexible member bending between the first thrust point and a first end of the first elastically flexible member, and also to transmit the radial force by the second elastically flexible member bending between the second thrust point and a first end of the second elastically flexible member.

Growing community of inventors

Moissy-Cramayel, France

Yanis Benslama