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

Snecma

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

Jean M Surdi

Claude Dubois

Jacques M Stenneler

Pierre Xavier Bussonnet

A vane for a fan including a platform, a root and a blade. The platform has opposite outer and inner surfaces, and opposite upper and lower surfaces. The upper surface has a camber shape, and the lower surface has a concave shape corresponding to the camber shape of the upper surface. The root is fixed to the inner surface of the platform and adapted to be fixed to a hub of the fan. The blade is fixed to the outer surface of the platform at a position shifted toward the lower surface from a center line between the upper and lower surfaces.

Movable fan vane with a safety profile

Damper disposition (8) mounted between two neighboring vanes (5) and which ncludes free inners (22) in housings (21) delimited by a radially external wall (16) slanted outwardly in the direction of the respective vane (5). The centrifugal forces produced by rotation of the disk of the rotor (4) move the inners (22) outside the housings (21) and forcibly apply them to the vanes (5) so as to dampen the vibrations, especially when considerable friction is produced against the outer wall (16). Application for turbo-engines and especially for the large vanes of input blowers.

Damper disposition mounted between rotor vanes

A turbine engine rotor includes two bolted, coaxial sections. One of the sections carries blades engaged by their roots in through broachings. The axial force exerted on the blades by the centrifugal operating component due to the inclination of the broaching is not transmitted to the bolts joining the two sections as a result of a mounting where the flanges are joined at their rear faces. The blades abut against the flange of the other of the sections. The invention is more particularly applicable to highly curved, so-called large chord blades of a turbine engine fan and the other of the sections is then a low pressure compressor drum.

Turbine engine rotor having axial or inclined, issuing blade grooves

A device for axially locking a turbine blade onto a rotor disk includes a foot portion of the blade which is slidably retained in a slot provided on the periphery of the rotor disk. An axial projection extends from the foot portion so as to engage a locking ring attached to the rotor disk when the blade is moved in a radially outward direction. A block inserted between the foot portion of the blade and the rotor disk serves to impart such movement to the rotor blade. Brackets on a downstream compressor drum and an upstream cover portion serve to axially lock the block in position.

Device for locking a turbine blade to a rotor disk

Axial and radial fan blade retention device, the blade comprising a root of dovetail or other re-entrant form capable of being engaged by axial sliding in corresponding bores of the rim of the disc. It comprises a member of elastomer material in the form of a trough extending axially and interposed between a wedge and the flanks and the base of a groove, the trough having an opening in which is engaged an abutment of the wedge constituting a central seating of the wedge on the base of the groove.

Fan blade axial and radial retention device

Device for the locking of blade roots and the fastening of the forward cowl consisting of a fastening piece comprising a parallelepipedic part (16) engaging radial slots (5) of the teeth (4) of the rim, a prismatic part (17), the convergent faces of which are resting against the sides of the groove and a cylindrical part (22) for the fastening of the cowl (24). The parallelepipedic (16) and prismatic (17) parts are parallel to each other and perpendicular to the cylindrical part (22). The cowl (24) has perforated counterbores (25) through which the cylindrical parts (22) are passing, with the ends of the cylindrical parts receiving a screw (27) to fasten the cowl.

Device to lock the blades of a turboblower and to fasten the front cowl

A rotor for jet engines includes a drum formed by disks and carrying blad Between the blades of two adjacent stages, braces are interspaced, the braces being projections which engage in sockets provided for this purpose on the disks. Each disk has two series of sockets, one receiving the roots of the blades, and the other, interspaced between the preceding, the projections of the braces. The blades are immobilized in translation at the upstream end by one ring and downstream by another ring, against which the roots of the blades of the terminal stages abut. The invention is particularly applicable to the building of axial type compressor rotors having several stages.

Rotor for jet engines

The invention concerns balancing devices for rotating mobile pieces, using alancing weights attached as necessary to one of several collars. Each balancing weight has a beak engaging a groove of a collar and is secured to the rotor by a suitable fastener, such as a rivet. Following balancing, a ring abutting against the grooved face of the collar is set in place. The ring is equipped with uniformly distributed recesses each intended to form a socket for a balancing weight and one of the ends of its fastener, so as to prevent the ejection of any of these elements in case of a failure of the means of fixation. The ring cooperates with the rotor in forming a chamber, to retain the other end of the fastener. The invention is applicable to the balancing of any rotating mobile piece and particularly to that of the rotors of axial compressors.

Growing community of inventors

Melun, France

Jean M Surdi