Snecma Moteurs

Snecma

Patrick Morel

Wouter Balk

Jacques Rene Bart

Daniel Georges Plona

Gael Bouchy

François Gallet

Fabienne Lacorre

Yann Lebret

Daniel J Martin

Pierre Pandelakis

Bertrand Jean-Joseph Marie Heurtel

Henry Souyeaux

Eric Jean Masson

Vanessa Le Rousseau

Bertrand Jean-Joseph Heurtel

Bien-Aime Rakotodrainibe

Daniel Martin

Jacques Julliard

A device adapted to be fitted with propeller blades includes a first retention ring including over a periphery thereof a plurality of radial bores; and a second retention ring including over a periphery thereof a plurality of radial bores, the first and second retention rings being mounted one on top of the other in the radial direction, each bore in the first retention ring being positioned opposite a bore in the second retention ring, a bore in the first retention ring arranged opposite a bore in the second retention ring forming a bore pair adapted to receive a foot of a blade.

Device adapted to be fitted with propeller blades

The invention relates to aerodynamically matching the rear fan of a turbojet having two fans and a low-pressure compressor at the front of the intermediate casing, said fans being driven by two independent shafts. Said compressor is disposed between the blades of the two fans and includes at least one ring of rotor blades around the periphery of a wheel driven by the drive shaft for the front fan, and at least two grids of stator vanes disposed on either side of the ring of rotor blades and inside a grid carrier ring. A stationary outer grid and a stator of variable pitch connect the ring to the fan casing.

Three-spool by-pass turbojet with a high by-pass ratio

The invention relates to a rotary shaft arrangement carrying equipment at one end and extending rearwards from the equipment, the shaft () being supported by a first bearing () behind the equipment, and by a second bearing () behind the first bearing (), the first bearing () being carried by a casing () surrounding the shaft () and extending rearwards from the first bearing () to a stator structure () to which the casing () is fastened by screws () that extend parallel to the shaft () and that are fusible in traction, the arrangement being characterized by the fact that the second bearing () is disposed with radial clearance (J) in a bore () of an annular support () secured to the stator structure (), and is fastened to said annular support () by screws () that are parallel to the shaft () and that are fusible in shear, whereby the second bearing () can bear against said support () in the event of said screws () rupturing. The invention relates more particularly to the support for the fan shaft of a turbojet.

Breakable coupling system for a turbojet fan shaft

The invention provides a device for supporting and recentering a shaft ( ) after decoupling. The device comprises an annular support ( ) surrounding the shaft ( ), a bearing ( ) secured to the annular support ( ) and having an inner ring ( ) which is spaced apart from the shaft by clearance J. The inner ring ( ) has two webs or tenons ( ) that are normally held to the periphery of two troughs ( ) carried by the shaft ( ). Two sets of balls ( ) normally bear against the bottoms of indentations ( ) formed facing one another in the adjacent radial walls of the troughs ( ) and of the inner ring ( ). Resilient means ( ) tend to urge the troughs ( and ) towards each other. In the event of the webs or tenons ( ) breaking due to a large unbalance, the balls ( ) roll on the walls of the indentations ( ) and move the troughs ( ) apart from each other. The resilient mans ( ) tend to bring the balls ( ) back towards the bottoms of the indentations and to recenter the shaft ( ) relative to the inner ring ( ).

Device for supporting and recentering the shaft of a turbojet fan after uncoupling

Growing community of inventors

Chartrettes, France

Patrick Morel