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

Snecma Moteurs

Snecma

Other

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

Marc R Marchi

Jean-Claude Christian Taillant

Eric Stephan Bil

Patrice Rosset

Kamel Benderradji

Anne-Marie Arraitz

Laurent Palmisano

Didier Marie Mortgat

Michel Gerard Hacault

Laurent Philippe Leray

Gilles Alain Charier

Maurice Guy Judet

Gerard M Mandet

Jean-Baptiste Arilla

David Audeon

Serge Louis Antunes

Paul Rodrigues

Guy Dusserre-Telmon

Patrice Jean-Marc Rosset

Jean-Pierre Mareix

Zoltan Zsiga

Gerard Jacques Stangalini

Christophe Bernard Texier

Chantal Giot

Jean-Pierre Mourlan

Nicolas Hervy

Michel Jean-Pierre Pernot

Christian Largillier

Patrice Jean Marc Rosset

Mischa&euml;l Fran&ccedil;ois Louis Derrien

Philippe Christian Pellier

Isabelle Marie Monique Valente

Michel Jean Loubet

Ludovic Nicollas

Jean Manuel Morcillo

Thierry Christian Sanz

Christian Gosselin

Patrick Rossi

Theophile F Le Mao/u/ T

Andre F Ollivier

Patrick Pierre Bernard Gazeau

Xavier G&eacute;rard Andr&eacute; Coudray

Thierry Henri Marcel Tassin

Patrick Pierre Gazeau

The gastight sealing device associated with a functional clearance existing between two sectors of a turbomachine includes an annular plate wound up on itself over at least one turn, covering functional clearance.

Sealing device for a chamber of a turbomachine, and aircraft engine equipped with said sealing device

A turbomachine roller bearing that supports a shaft constituted by a trunnion of a shaft line of a high-pressure spool of a turbomachine to rotate relative to a stationary support that is connected to a casing of the turbomachine, said bearing comprising rollers inserted between an outer ring disposed adjacent to the stationary support and an inner ring disposed adjacent to the high-pressure trunnion, the inner ring extending along the axis beyond a downstream end of the high-pressure trunnion to which it is secured by clamping means, and being provided with anti-rotation means for preventing said inner ring from rotating relative to the high-pressure trunnion.

Turbomachine with a compact roller bearing

A turbomachine including a wheel with hollow blades that are cooled internally by a forced flow of cooling air. According to an important characteristic of the invention, a hook-annulus () is interposed between the outer edge of the labyrinth-disk () and the rotor disk (), the hook-annulus including a retaining shoulder () constituting an outer annular hook in which the outer edge of the labyrinth-disk is engaged, and a bearing shoulder () constituting an inner hook engaged in a groove around the circumference of the rotor disk.

Turbomachine, for example a turbojet for an airplane

A turbine ring made up of an assembly of a plurality of sectors forming the outer shroud of the rotor of said turbine. The sectors are united end to end with interposed sealing systems comprising tongues housed in slots, said tongues being rectilinear and engaged in respective rectilinear slots in the radial faces of said sectors.

Turbine ring

A device for holding an annular end plate against a radial face of a rotor disc, the disc having in the radial face an annular recess behind a collar extending radially outwards, and the end plate having, in its radially inner part, an annular base bearing against the radially outer wall of the recess and a foot extending radially inwards in the recess from the base, the device including a split annular retaining ring disposed in the recess. The ring is constituted by a snap ring interposed axially between the foot of the end plate and the collar and the peripheral surface of which butts against the base, the peripheral surface and the collar comprising, when joined, notches, which open radially outwards and are intended to receive compression tools for the snap ring, which tools retract into the contour of the collar during the assembly or disassembly of the end plate.

Holding system for a rotor end plate

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 turboshaft engine, such as for example a turbine, including a segmented seal between two longitudinally adjacent elements such as, for example, a casing and a ring of sectors of vanes. According to one embodiment, a seal is interposed between a casing and a ring of sectors of vanes and includes a plurality of flexible segments having a straight deformation zone and a straight fluid-tight bearing zone.

Turboshaft engine comprising two elements connected to each other with the interposition of a seal

The invention provides a device for holding strip sealing gaskets on a turbomachine nozzle, the nozzle being constituted by a plurality of sectors having guide vanes which extend between inner and outer platforms elements, at least one of said platform elements having a sealing strip () disposed radially in a space between said platform element and an adjacent structural element in order to provide fluid tightness between said elements, the corresponding strips of two adjacent sectors touching, and their joint being covered by a joint cover () disposed between said strips, and by a holding member for holding said strips in the sealing position.

Device for maintaining joints with sealing leaves

A turbomachine includes a casing, a rotor, and a plurality of cooled ring segments installed between the casing and the rotor, each ring segment containing a main cooling cavity and being attached to the casing by a fastening device. The fastening device can include a clamping screw positioned more or less radially and pinning the ring segment against the casing. The clamping screw is crossed through by a cooling airway that communicates with the main cooling cavity of the ring segment.

Turbomachine with cooled ring segments

A sealing device is disclosed comprising a least one sealing leaf maintained axially in position by a retaining bracket which comprises a first end bearing on the sealing leaf and a bent-back second end engaged in a groove in a structural element. The sealing leaf is preferably retained radially in position by lugs which are bent so as to engage below lugs provided on the retaining bracket. When the sealing device comprises at least two adjacent sealing leaves placed edge to edge, the device also comprises a cover sheet so disposed between the sealing leaves and the retaining bracket as to cover the joint between the two adjacent leaves.

Leaf seal

The invention provides a turbomachine including a device for supplying pressurized gas, the gas being bled from the compressor of the turbomachine via a bleed orifice and cooled in a cooling cavity disposed within the compressor rotor upstream of the bleed orifice. This arrangement has the effect of cooling the bled gas by heat transfer through the outer wall of the compressor rotor to the gas stream which is being compressed by the compressor upstream of the bleed orifice, and has the result of reducing the drop in the performance of the compressor as a result of the gas being bled off.

Turbomachine including a device for supplying pressurized gas

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

A cooling system is disclosed for cooling the platforms of turbine blades fixed to the periphery of a turbine rotor, each turbine blade having an airfoil portion, a platform with opposite longitudinal edges, a root portion affixed to the turbine rotor, and a shank portion connecting the root portion to the platform. Adjacent turbine blades are located such that a longitudinal edge of one platform is adjacent to a longitudinal edge of an adjacent platform. A cavity is formed bounded by a portion of the periphery of the turbine rotor, the shank portions of the adjacent turbine blades, and the platforms of the adjacent turbine blades. A cooling air passage supplies cooling air to the cavity. One or more cooling channels are formed in a side of the platform facing the turbine rotor, each cooling channel having a cooling air collector at an end located adjacent to the air supply passage and communicating with the cavity. The cooling channels also include venting holes distributed along each of the cooling channels. A sealing plate extends across surfaces of adjacent platforms facing toward the turbine rotor so as to seal any gap existing between the adjacent longitudinal edges of the platform. The sealing plate covers the cooling channels to form cooling passages, the sealing plate having an orifice aligned with the cooling air collector of the cooling channel to enable cooling air from the cavity to enter the cooling channel and exit through the plurality of venting holes to cool the blade platform. The cavities are, in known fashion, sealed at their forward and rear ends by annular seals affixed to the turbine rotor.

Cooling system for turbine blade platforms

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

Layout for adjusting the diameter of a turbine engine ring (5) positioned facing mobile rotor blades (4) and connected to a case element (7). The latter is provided with a cavity (16) communicating with chambers (21, 23) around a gas flow stream (31). A limited air current traverses the cavity (16) and is sufficiently reduced to ensure the development of a heat convection, which renders uniform the temperature of the case element (7) and the ring (5) and consequently the diameter of the latter.

Layout and process for adjusting the diameter of a stator ring

Growing community of inventors

Le Mee sur Seine, France

Marc R Marchi