Snecma

Patrick Charles Georges Morel

Gilles Alain Charier

Gael Bouchy

Michel Gilbert Roland Brault

Bruno Albert Beutin

Regis Eugene Henri Servant

Régis Eugène Henri Servant

Jacques Rene Bart

Georges Jean Xavier Riou

Eric Stephan Bil

Philippe Jacques Pierre Fessou

Jacques Michel Albert Julliard

Olivier Michael Molinari

Zoltan Zsiga

Pierre Pandelakis

Alain Mazelet

Daniel Jean-Marie Martin

An accessory gear box driveshaft in a turbojet engine with intermediate casing, designed to be mounted in a radial arm of the intermediate casing is disclosed. The shaft is mechanically connected, at a first end, to a an engine shaft of the turbojet engine, and is mechanically connected, at a second end, to a gear box. The shaft includes a bevel gear between the two ends, to provide mechanical transmission to an additional accessory. This shaft is notable in that, together with the gear, it is contained in a case forming an oil circuit sealed against the arm. The accessory includes a drive shaft collaborating with the gear of the transmission shaft and forming a modular assembly therewith.

Turbojet engine accessory gear box driveshaft; modular additional accessory

The bypass turbomachine comprises, between a primary flowpath () and a secondary flowpath (), a structural intermediate casing (). A bleed passage () allows the diversion of a portion of the gas stream toward the secondary flowpath (), downstream of support arms () situated at the periphery of the intermediate casing. A bleed opening () emerges upstream of the support arms (). A slide valve () slides between three positions, namely a closed position in which the slide valve () completely blocks off the bleed passage and opening, an intermediate position in which the bleed opening () emerging upstream of the support arms () is blocked off, while the bleed passage () for diverting a portion of the gas stream downstream of the support arms () is open, and an open position in which the bleed opening () emerging upstream of the support arms () and the bleed passage () emerging downstream of the support arms are both open.

Bleed system for a low-pressure compressor of a turbomachine

The present invention relates to a structural or non-structural turbojet engine fan casing connecting arm that also acts as a flow straightener downstream of the fan rotor. Its distinctive feature is that it is constructed to form an acoustic attenuator. In particular, it comprises a closed cavity and perforations on one of the faces so as to form a Helmholtz resonator. The arm forms part of the intermediate casing.

Acoustic flow straightener for turbojet engine fan casing

The invention relates to a twin spool turbine engine comprising a high-pressure rotor and a low-pressure rotor, at least one accessory gearbox, a drive means, driving coaxial transmission shafts that transmit movement to the accessory gearbox, characterized in that the drive means comprises a high-pressure drive pinion secured to the high-pressure rotor near its upstream end, a low-pressure drive pinion secured to the low-pressure rotor upstream of the high-pressure rotor, and a power take-off module in direct mesh with the drive pinions, driving the transmission shafts. By virtue of the invention, the transmission shafts run coaxial with one another and therefore pass through a single arm. The use of a power take-off module simplifies the mechanism. The turbine engine is simpler to assemble.

Twin spool turbine engine with power take-off means on the low-pressure and high-pressure rotors, and power take-off module for the turbine engine

An arrangement of bearing supports for a rotating shaft mounted on bearings connected to an engine stator structure by bearing supports of which at least one is made up of N&#x3e;1 elements effectively acting in parallel to simultaneously connect the bearing to the structure, of which N&#x2212;1 of the N elements form this connection by fusible links, is made up of a first bearing supported by a first bearing support and a second bearing supported by a second bearing support, that of the two bearing supports which makes up the N&#x3e;1 elements being the second bearing support.

Arrangement of bearing supports for the rotating shaft of an aircraft engine and an aircraft engine fitted with such an arrangement

The invention relates to a turbomachine comprising a rotor with a drive shaft centered on the axis of the turbomachine by a first bearing and a second bearing which bearings are supported respectively by a first-bearing-support piece and a second-bearing-support piece which are secured to one another and connected to the turbomachine fixed structure by a decoupling device. This turbomachine comprises means designed to collaborate with at least one element of the turbomachine fixed structure in order to perform a dual function, that of preventing the bearing supports, from rotating and that of radially retaining the drive shaft in the event of the bearings becoming decoupled.

Turbomachine with a decoupling device common to first and second bearings of its drive shaft, compressor comprising the decoupling device and decoupling device

Growing community of inventors

Chartrettes, France

Patrick Charles Georges Morel