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

Snecma

Jean-Claude L Delonge

Jean G Bouiller

Gerard R Vermont

Jacky S Naudet

Jean-Louis Charbonnel

Christian Bariaud

Daniel J Marey

Michel R Ayache

Claude J Loudet

Guy Franck Dusserre-Telmon

Marcel L Rigo

Jean-Pierre Galivel

Jean-Christophe M Cordier

Laurent Gille

Thierry Henri Tassin

Didier G Zietek

Corrine G Delahaye

Didier M Nouveau

A variable camber vane for a turbomachine comprises leading and trailing edge parts, at least one of which is pivotable relative to the other, and a resilient joining part inserted into a space provided between the leading and trailing edge parts, the joining part being formed by a block of resilient material which is bonded to the leading and trailing edge parts and which ensures the continuity of the intrados and extrados faces of the vane to permit an even flow of fluid along the vane. The vane may also include means for enabling a cooling or heating fluid to flow in the leading and trailing edge parts, and a plurality of ducts in the resilient joining part establishing communication between the fluid flow means of the leading and trailing edge parts.

Variable camber turbomachine blade having resilient articulation

A device for ensuring the sealing in a rotary machine between a rotor and fixed blade stages. Blade edges are joined by rings carrying circular seals in slots. Springs force the seals in the longitudinal direction towards transverse faces of reinforcements of the rotor. A turbulence-free gas flow is obtained as a result of the total seal obtained by the seals (19). Moreover, the rotor can be constructed with a substantially rectilinear ferrule which only induces limited stress concentrations.

Sealing device between blade stages and a rotary drum, particularly for

Apparatus for the transfer of a module, the module including an outer casing in which is held the stator stage and a turbine rotor constituted by disks supporting blade rows, the disks being held by tie bolts, the apparatus having a holding device of the outer casing on the balancing machine, a temporary interconnection means of the disks of the turbine, and a transport device ensuring the securing of the turbine disks after withdrawal of the holding device.

Apparatus for the transfer of a complete turbine module from a balancing

A turbo-machine comprises means for securing a fluidtight seal to the shaft thereof including a segment in the shape of a sector of a ring located in a groove formed in the wall of the shaft, the groove and the sector being of complementary shape. The radially outer surface of the sector is in tight contact with the radially inner surface of a part of the seal carrying lips which in turn provide a sealing effect by close proximity to an opposed surface of the seal on another part of the turbine. The segment is made rigid with the shaft by detachable means which pass through the lip carrying member and into the sector. In order to prevent both axial and rotational motion of the sector relatively to the groove, the mating surfaces are toroidal and eccentric with respect to the common axis of the segment and of the shaft.

Fluidtight labyrinth seal for a turbo-machine

From an external turbine chamber (17), cooling air passages are formed through coils mounted in ball-and-socket fashion (26) in a cavity portion (21) above the stationary turbine nozzle vanes (16) from which it escapes downstream through holes (29) in the platform (15) of the stationary vanes (16) in the form of jets of air parallel to the flow of the main gas flow to create a cooling film on the leading edge (30) of the shroud (9) of the movable blades (10) of the turbine rotor in order to cool these blade shroud (9). An airtight connection between this supply chamber (17) and the main flow is ensured by a flexible seal (32) formed of elastic blades (33) in sections attached to one end of the downstream flange (14) of the turbine nozzle housing (11) and supported at the other end by the turbine ring (5).

Cooling device for movable turbine blade collars

A retractable damping device for the blades of a turbojet, located between two consecutive blades against the lower face of the platforms of said blades. The damping element, mounted to rotate by one of its ends in the middle part of the space formed between the blades and a rotor disk positioned along an axis perpendicular to a radial axis of the disk, exhibits an upper part which constitutes a projecting dihedral that takes the form of the protruding dihedral consisting of the platforms of the two consecutive blades under the action of centrifugal force.

Retractable damping device for blades of a turbojet

A device for moving air from the jet flow of an axial compressor of a gas rbine group, to be conducted along the axis of the group to the turbine to be cooled. The air is moved by a wheel having an outer rim serving as a brace between two adjacent compressor disks and centripetal blading which moves the air through openings formed in the rim, to accelerate it and discharge it into a space surrounding the axis of the compressor.

Growing community of inventors

Corbeil-Essonnes, France

Jean-Claude L Delonge