Snecma

Safran Aircraft Engines

Ge Aviation Systems Limited

Didier Rene Andre Escure

Stephane Rousselin

Jacques Rene Bart

Claude Marcel Mons

Gilles Alain Charier

Gilles Alain Marie Charier

Bruno Jacques Gerard Dambrine

Tewfik Boudebiza

Philippe Pierre Vincent Bouiller

Ludovic Edmond Camille Molliex

Thomas Julien Nguyen Van

Thierry Jean-Jacques Obrecht

Caroline Aumont

Thomas Julien Roland Earith

Christopher Roy Carrington

Denis Louis Bocquet

Jean-Francois Fromentin

Cedric Magret

Aleksander Krzysztof Szymandera

Jan Sikorski

Jean-Yves Guedou

Stephan Yves Aubin

Marek Malitka

Belmonte Olivier

Jean Philippe Pierre-Alain Reigner

Sandrine Chatel

Jeremy Phoria Lao

Engine comprising a propeller unit with a pair of contrarotating propellers (), a gas generator () supplying a power turbine (), the pair of propellers being rotationally driven by the shaft (A) of the power turbine via a speed reduction gearbox, the axis of rotation (XX) of the pair of propellers not being coaxial with that (YY) of the power turbine, the speed reduction gearbox comprising a differential gearset () and a first stage () comprising a simple gearset connecting the turbine shaft (A) and the differential gearset (), the engine air intake comprising an air intake duct (), the air intake duct () being in the shape of a lobe adjacent to the assembly formed by the simple gearset and the differential gearset ().

Turbine engine with a pair of contrarotating propellers placed upstream of the gas generator

The assembly () links a static housing () of the turbomachine, into which supply lines, in particular fluid supply lines (), arrive, to the blades of the propeller, and comprises: &#x2014;a system for controlling fluid pitch (), rigidly connected to the static housing (), capable of being linked to the supply lines, &#x2014;a linear actuator () having two chambers separated by a piston () of which the sliding is dictated by the control system and allows the blades to rotate, and &#x2014;two concentric tubes () housed in the planetary shaft of the epicyclic reduction gear and linking the system () to the actuator () by delimiting two fluid passages () linked, respectively, with the two chambers () of the actuator.

Turbomachine provided with an assembly for controlling the pitch variation of a propeller

A turbo engine includes a system for changing a pitch of blades of a propeller, the system including an annular fluid cylinder with a linear drive and a link mechanism linking the cylinder to the blades of the propeller to change an orientation of the propeller. The annular cylinder of the system can be rigidly mounted on a fixed housing supporting the propeller and internal to the propeller, unlike the blades mounted in an external rotating hub of the propeller, and the link mechanism includes a displacement transfer bearing fixed, on one side, to the mobile part of the cylinder and cooperating, on the other side, with a mechanism linking to the blades of the rotating hub of the propeller.

Turbo engine with propeller(s) for an aircraft with a system for changing the pitch of the propeller

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

A device for, in a gas turbine engine, braking a turbine including a rotor driving a shaft capable of rotating with respect to a stator in the event of said shaft breaking is disclosed. The device includes a first braking member provided with at least one abrasive element and a second braking member including a ring-shaped element (A) made of a material capable of being eroded by the abrasive element. One of the two braking members being secured to the rotor and the other of the two braking members being secured to the stator. The braking members come into contact with one another through axial displacement of the rotor once the shaft has broken. The abrasive element of the first braking member eroding the ring-shaped element of the second braking member.

System providing braking in a gas turbine engine in the event of the turbine shaft breaking

A device for supplying ventilation air to a turbine rotor of a gas turbine engine including a first turbine disk, a second turbine disk, and a downstream shell ring together forming a one-piece drum is disclosed. The second turbine disk includes cavities machined in the rim to house the turbine blades, where the blades are axially retained by axial retaining segments. The downstream shell ring has at least one aperture drilled therethrough, downstream of the rim, which places an internal volume of the drum in fluid communication with at least one of the cavities via a passage formed in the segments.

Device for supplying ventilation air to the low pressure blades of a gas turbine engine

A device for, in a gas turbine engine, braking a turbine including a rotor, having at least one disk with a rim driving a shaft and capable of rotating with respect to a stator, is disclosed. The device is for the event of the shaft breaking and includes a first braking member, secured to the rim and provided with at least one cutting element, and a second braking member secured to the stator downstream of the rim and including a ring-shaped element made of a material that can be cut by the cutting element. The two braking members coming into contact with one another through axial displacement of the rotor once the shaft has broken. The cutting element of the first braking member cuts the ring-shaped element of the second braking member.

System for dissipating energy in the event of a turbine shaft breaking in a gas turbine engine

A device () for limiting overspeed in a turbomachine in the event of breakage of the turbine shaft (), comprising means () of propelling a pin () into the path of the blades (), these propelling means being controlled by means () that detect overspeed or that the turbine shaft has broken.

Device for limiting turbine overspeed in a turbomachine

Devices for intaking gases from the boundary layer through ducts hollowed out in blades. These devices are suitable for variable setting blades, installed on the stator using pivots. The seal is maintained despite the variation in the relative position between the moving pivots through which ducts pass, and the fixed intake header pipe.

Air bleed device on a machine stator pivoting blade

A compressor with a centripetal air takeoff system that includes pipes installed between an outer collar and an inner collar. Each pipe is fitted in a hole in the outer collar and in a hole in the inner collar. The system further includes a locking mechanism between the pipe and the inner collar.

Compressor with centripetal air takeoff

A turbomachine rotor including at least one disk having a ring constituted, for example, by a winding of metal-coated silicon carbide or alumina yarn. According to the invention, the composite ring is received in a closed annular cavity, e.g. defining by machining a groove in an enlarged portion of the disk and closing the groove by means of an annular plate after the ring has been put into place.

Growing community of inventors

Nandy, France

Didier Rene Andre Escure