Snecma

Safran Aircraft Engines

Hispano Suiza

Stephane Rousselin

Jacques Rene Bart

Didier Rene Andre Escure

Philippe Pierre Vincent Bouiller

Arnaud Jean-Marie Pierrot

Didier Rene Escure

Claude Marcel Mons

Gilles Alain Marie Charier

Philippe Pierre Bouiller

Michel Gilbert Roland Brault

Laurent Donatien Behaghel

Jacky Raphael Michel Derenes

Jeremy Giordan

Anthony Lorand

Laurent Raberin

Michel Brault

Jean-Francois Adnot

Jacky Raphael Derenes

Francois Gallet

Regis Eugene Henri Servant

Bruno Jacques Gerard Dambrine

Serge Rene Morreale

Nicolas Jerome Jean Tantot

Ludovic Edmond Camille Molliex

Adrien Philippe Fabre

Ludovic Edmond Molliex

Thierry Jean-Jacques Obrecht

Caroline Aumont

Thomas Julien Roland Earith

Jean-Marc Rongvaux

Jean-Yves Guedou

Jean-Francois Fromentin

Cedric Magret

Etienne Juchauld

Stephan Yves Aubin

Thibault Xavier Alexis Berranger

Mathieu Raymond Paul Sezeur

Florian Joseph Bernard Kockenpo

Sylvie Charles

Guillaume Jose Rodrigues

Sandrine Chatel

Claude Daniel Nottin

Roxane Carmelle Jeanne Yvonne Touret

Alain Auguste Jacques Foucault

Pascal Coat

Patrick Marcellin

Romuald Gentils

Benoit Mascrier

Pascal Brunel

Frederic Patard

Cedric Kevin Magret

Roxane Touret

A measuring device for measuring at least one parameter of an aerodynamic flow of a turbine engine. The device operates to collect parameters of the flow. A body extends along a radial axis (L). A connecting part is fastened to a first end of the body and designed to secure the measuring device to a radially outer wall of the turbine engine. A stud is inserted and mounted on a second end of the body radially opposite the first end. The stud includes at least a portion of a rubberlike material designed to come into contract with a radially inner wall of the turbine engine.

Device for measuring at least one parameter of an aerodynamic flow of a turbine engine equipped with a vibratory damping means and turbine engine duct equipped with such a device

An annular air flow passage includes two radially internal and external annular walls. An element is elongated in a direction between the internal and external annular walls and a first of the internal or external ends of the element is fixed rigidly to a first of the internal or external walls. The center of gravity position of the element is variable.

Instrumented flow passage of a turbine engine

A turbomachine fitted with a device for gathering the information recorded during operation of the former by a strain gauge positioned on a fan blade borne by a fan disc of the turbomachine, the device including a hollow cylindrical pipe positioned inside one of the rotating shafts of the turbomachine in order to guide at least one wire for transmitting this information, wherein the device further includes a part for attaching the pipe to the rotating shaft.

Measurement installation for blade failure testing in a turbomachine

A nut screwed around a rotating shaft with a view to securing a part to said shaft and to cooperate with a fixed sensor sensing a quantity of material in a pre-defined volume to measure the speed of rotation of the shaft, including a ring of teeth separated by slots. At least a portion of the teeth includes at least one recess maintaining the clamping function of the ring of teeth, the at least one recess forming, with notches separating the teeth, respective material deficit intervals detected by said sensor when passing through the detection volume during the rotation of the nut. A method of using the nut with a sensor in a rotational speed measuring device and the production of same.

Bearing nut for measuring the rotational speed of a shaft connected to a turbomachine and associated measuring device

A fan portion of a dual flow turbojet engine including a plurality of fan blades, a disk supporting the blades and configured to be rotated relative to a stator portion of the fan, along a longitudinal axis of the fan, and a system for setting the angle of attack associated with each fan blade, the systems configured such that the angle of attack of each blade varies according to a same setting law according to the angular position of the blade relative to the stator portion, along the longitudinal axis, the same setting law being periodic with a period of P=360&#xb0;/n, where n is an integer at least equal to 1.

Gas turbine engine having fan blades of adjustable pitch with cyclic setting

An installation for calibration of a stress gauge for an external bearing block of a turbomachine roller bearing, the bearing block including a radially internal roller bearing race. The installation includes a support table on which the bearing block is attached; an internal roller bearing ring mounted coaxial with the bearing block; a drive shaft driving the ring. The installation also includes a device for applying an axial stress to the bearing block including a support drum on which the internal ring is removably fixed and a connection with the device for applying the axial stress.

Installation of calibration gauge for measuring constraints

A rotor element including an annular surface portion about the rotor rotational axis, a fluid passage being formed through the surface portion, a passage-blocking mechanism including a blocking element that is deformable depending on the rotor rotating speed and arranged so as to adjust the fluid flow depending on the rotor rotating speed, and an annular collar with a free edge engaging with the blocking element so as to form the blocking mechanism. The free edge of the annular collar defines, together with the blocking portion of the blocking element, a diaphragm that blocks the fluid passage.

Rotor element with a fluid passage and passage-blocking member and turbine engine including the rotor element

Measuring the twist of a rotating shaft by means of a laser beam and polarizing filters. The measurement device includes a laser beam generator, two polarizing filters secured to the shaft and spaced apart from each other, and a laser radiation receiver receiving the laser beam after it has passed through both filters.

Device for measuring the twist of a rotating shaft

A rotary assembly for a turbomachine fan includes a disk rotatable about an axis; a plurality of blades fastened by their roots to the disk and extending radially outwards from the disk; and a plurality of inter-blade platforms, each extending between two adjacent blades and defining the inner profile for the flow section of the fluid passing through the fan. On their facing side faces, these adjacent blades present slides between which the platform can slide, these slides limiting outward radial movement of the platform.

Rotary assembly for a turbomachine fan

A bypass turbojet engine including an outer fan duct and an inner fan duct (IFD), between which the secondary flow passes, and a high pressure compressor having an outer casing is disclosed. The IFD is fastened on the outer casing.

Bypass turbojet

A guide shaft bearing including an internal ring mounted on a cylindrical contact surface of a shaft and a device for the axial locking of the ring including a ring mounted sliding on the cylindrical contact surface and an annular rib made of shape memory material mounted in two annular grooves of the cylindrical contact surface and of the ring is disclosed. The annular rib is able to expand radially by shape memory effect when it is subjected to a temperature greater than a transition temperature of its material to pass to a locking position of the ring on the cylindrical contact surface.

Device for the axial locking of a guide shaft bearing in a turbomachine

A turbomachine fan including blades mounted in slots at the periphery of a rotor disk, and inter-blade platforms having radial lugs for fastening to corresponding lugs of the disk is disclosed. Each platform is fastened to the disk by a pin inserted into orifices in the lugs of the platform and into corresponding orifices in the lugs of the disk.

Turbomachine fan

A dual-flow turbomachine (), essentially comprising a fan (), a compressor (), a combustion chamber (), a turbine () and an exhaust casing (), which comprises an auxiliary air compressor () driven by a Stirling engine () mounted downstream of the combustion chamber () and having a hot chamber in thermal contact with the flow (B) of hot gases leaving the turbine and a cold chamber in thermal contact with a flow (A) of cold gases generated by the fan () and flowing around the turbine () and the exhaust casing ().

Component ventilation and pressurization in a turbomachine

A coupling device for coupling a turbine upstream guide vane which is coupled to a supporting part which itself attached to a stabilizing part is disclosed. The coupling device includes a interlocking device for interlocking a supporting end of the supporting part with a stabilizing end of the stabilizing part, and a retaining part to keep the supporting end and the stabilizing end interlocked. The coupling device may be used to couple an upstream guide vane of a turbojet turbine.

Coupling device for a turbine upstream guide vane, a turbine comprising same, and aircraft engine fitted therewith

A device for detecting breakage of a turbomachine shaft is disclosed. The device includes a shaft having an upstream end and a downstream end; a rod having an upstream end and a downstream end, and placed coaxially inside the shaft, the downstream end of the rod being securely fastened to the downstream end of the shaft and the upstream end of the rod being free to rotate relative to the upstream and of the shaft; and a sensor suitable for detecting a difference in speed of rotation between the upstream end of the rod and the upstream end of the shaft.

Device for detecting breakage of a turbomachine shaft

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Hericy, France

Stephane Rousselin