Snecma

Snecma Moteurs

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

Societe Nationale Detude Et De Construction De Mothers D'aviation 'snecma'

Safran Aircraft Engines

Eric Stephan Bil

Marc R Marchi

Anne-Marie Arraitz

Chantal Giot

Michel Gerard Hacault

Didier Marie Mortgat

Laurent Philippe Leray

Michel Gilbert Roland Brault

Gilles Alain Marie Charier

Gilles Alain Charier

Maurice Guy Judet

Serge Louis Antunes

Patrick Charles Georges Morel

Philippe Jacques Pierre Fessou

Jean-Francois Rios

Delphine Roussin-Leroux

Michel Jean-Pierre Pernot

Nicolas Hervy

Thomas Schlesinger

Michel Jean Loubet

Jean Manuel Morcillo

Thierry Christian Sanz

Christian Gosselin

Isabelle Monique Marie Bourriaud

A turbomachine including an intermediate casing including, fastened to the end thereof, an outer casing of a high pressure compressor, and an air bleed mechanism bleeding air downstream from the stream through the compressor and including an outlet connected to an air reinjection mechanism reinjecting air upstream from the compressor via an annular manifold surrounding the inner wall of the intermediate casing and situated radially between the inner wall and an outer wall defining a secondary flow stream of the turbomachine.

Gas turbine high pressure compressor fluid return and reinjection including an annular air bleeding manifold

A diffuser which straightens the flow of air issuing from a centrifugal compressor in a turbine engine is provided. The diffuser having a cylindrical shape and including a first part having the form of two substantially parallel discs extending substantially radially relative to the axis of symmetry of the diffuser, a second bent part, and a third part intended to open out into a downstream cavity, positioned downstream of the diffuser and fed with air issuing from the compressor. The first part is traversed by a plurality of channels distributed evenly over its circumference and opening out on its downstream face so as to bring the air contained in the downstream cavity into communication with a bleed cavity situated upstream of the diffuser.

Bleeding of air via the diffuser of a centrifugal compressor of a turbine engine

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

This turbine engine compressor comprises a separating nose extended by inner and outer annular walls defining in cooperation an annular volume (V) of separation of a primary flow (F) and a secondary flow (F). This volume (V) comprises a plurality of annular segments in the form of cells separated in pairs by blades of a first fan, these blades passing through both the primary flow (F) and the secondary flow (F). These cells are fixed to an upstream annular collar and a downstream annular collar driven rotationally by the aforementioned blades.

Compressor comprising a plurality of cells reconstituting an annular volume of separation of flows in a turbine engine

Rotor blade for a compressor or a gas turbine, in particular for a turbojet engine, including a suction side and a pressure side, which are joined at their upstream ends by a leading edge and at their downstream ends by a trailing edge for the gases, a platform connecting the suction side and the pressure side to a blade root, and a stiffener formed beneath the downstream part of the platform and including at least one notch or a cut-away in line with the trailing edge, in order to reduce the stresses in the joint region between the aerofoil and the platform.

Rotor blade for a compressor or a gas turbine

A system for controlling a leakage zone under platforms of blades of a turbomachine blade-wheel by liners having edges that flare radially inwards, and that are disposed in inter-blade cavities defined by the platforms, by upstream and downstream radial walls of the blades and by the periphery of the wheel disk. One of the flared edges, upstream or downstream, presents an elastic zone bearing on an inclined surface of the adjacent radial wall relative to a radial plane, such that the liner tends to move axially towards the radial wall facing, under action of centrifugal forces, to improve sealing in the zone, and so that when the wheel stops, the elastic zone moves radially inwards, the liner pivoting around an axis distant from the elastic zone.

Control of leak zone under blade platform

A sheet metal sealing sleeve placed under a pair of juxtaposed blade platforms in a turbomachine so as to cover the gap between them is provided with apertures to allow the flow of a ventilating gas to the platforms. The apertures are provided in bosses formed on the sleeve to define chambers between the sleeve and the platforms which provide for greater heat exchange by virtue of the forcible impact of the gas blown through the apertures under the platforms. The sleeve also aids in damping platform vibration.

System for ventilating a pair of juxtaposed vane platforms

A method of reducing the gap between a liner and a turbine distributor of a turbojet engine. The method allows for the improvement of the seal on the inside of the distributor of the high pressure turbine at the lower platform. The method includes the steps of: applying a protective deposit to the lower part of the external surface of the liner, before carrying out a filling by diffusion brazing between the liner and the distributor. The protective deposit, preferably a anti-adherent ceramic, makes it possible for the braze to avoid fixing the liner onto the distributor at the lower platform level. The method also has applications to turbojet engines.

Method of reducing the gap between a liner and a turbine distributor of

This seal (6) running between gaps (6) between two stator sectors of a gas urbine engine is made up of several thin flexible slabs, capable of sliding one over the other, which gives a better seal.

Seal of stacked thin slabs that slide within reception slots

Growing community of inventors

Chartrettes, France

Eric Stephan Bil