Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Snecma Moteurs

Daniel J Martin

Bruno Albert Beutin

Jean-Louis Charbonnel

Pierre A Glowacki

Gael Bouchy

Patrick Morel

Monique A Thore

Andre C Collot

Claude Dejaune

Philippe Fessou

Jean-Claude Asselin

Pierre Pandelakis

Henry Souyeaux

Eric Jean Masson

Bertrand Jean-Joseph Marie Heurtel

Jean-Francois Ranvier

Herve Paitre

Jean-Claude Gregoire

Alain Espenel

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 arrangement of a gas turbine engine suitable for high bypass ratio aircraft engines in which gases circulate in a primary air channel (7) and a secondary channel (8) concentric to said primary air channel, is characterized in that structural vanes (22) connecting the channel delimitation casings (2, 10, 14, 5) with each other, alternate with aerodynamic vanes (20) for guiding the gases on a common circumference of the engine bypass air channel (8), and in that the structural channels branch out between the two channels. The resulting advantages are simplicity of construction associated with a reduction in the space required for housing the channels and good resistance without notable increase of the total mass.

Arrangement of gas turbine engine comprising aerodynamic vanes and

An aircraft turbo-engine having an intake grille formed by radial struts disposed between inner and outer rings, each of said radial struts being in two parts, an upstream, fixed structural first part, and a downstream second part pivoted on said first part and forming an adjustable flap which constitutes an intake guide vane, all of said struts having the same cross-section as each other and at least some of the struts incorporating a pipe for the passage of oil, those oil pipe carrying struts each having its structural first part divided by a radial portion into an upstream chamber for the passage of hot air and a downstream chamber which is open along the length of its trailing edge and which receives the oil pipe.

Turbo-engine air intake grill

Growing community of inventors

Bombon, France

Daniel J Martin