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

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

Jacques M Stenneler

Jacky S Naudet

Claude R Lejars

Jean M Surdi

Jean-Max M Silhouette

Pierre Marc Lechervy

Patrick L Girault

Pierre Xavier Bussonnet

Jean V Reboul

Denis C Charreron

A method and apparatus is described for producing a large number of identical parts from a bar of material by electrochemical machining without the intervention of an operator. The apparatus comprises a spindle for supporting the bar and periodically feeding it in the direction of its axis, and an electrochemical machining assembly comprising cathodes for shaping the leading end portion of the bar to form the part. After the part has been shaped, it is electrochemically cut from the bar, and the bar is advanced longitudinally by the spindle in order to proceed with the machining of the next part.

Method and apparatus for the serial production of parts by

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

Damping disposition for vanes (3) fitted with stilts (4, 5) engaged in the alveoles of the rotor disk (1). Damping elements (10) are added including a portion (11, 12) extending along the flanks (6) of the stilts (4) and including a portion (15) leaning against them. The beating vibrations of the vanes (3) and dampened by these elements able to be used on smooth vanes without any platform, such as large blower vanes. Application for turbo-engines.

Damping disposition for rotor vanes

A turbocompressor disk having on its periphery a circular groove able to receive blade roots having a substantially hammer shape, said circular groove comprising an upstream lip and a downstream lip against which bear the blade roots. The upstream lip has a curvature of gradient inclined by an angle .alpha. with respect to the plane perpendicular to the rotation axis and the downstream lip has a curvature of gradient inclined by an angle .beta. with respect to the plane perpendicular to the rotation axis, .alpha. being strictly different from .beta..

Turbocompressor disk provided with an asymmetrical circular groove

A turbojet engine rotor, wherein the circumference of the disk is occupied y teeth and slots in an alternating form. The teeth have a variable rigidity in the axial direction, which leads to different shapes of their cross-section. The teeth have a twisted outer surface and oblique recesses are provided on the circumference of the rotor for receiving vane roots which alternate with the teeth for separating and retaining the vanes.

Turbojet engine rotor

Rotor blades having roots of the hammer-head type which are received in a circumferential groove in the rim of a rotor disc to secure the blades on the disc are provided with a raised portion on the underside of the blade platform which extends over the entire circumferential length of the platform and has a width equal to that of the mouth of the groove in the rim of the disc. The root of each blade is mounted on this raised portion, and when the root is received in the groove of the disc the raised portion is received closely in the mouth of the groove to ensure the correct alignment of the blade.

Rotor blade fixing providing improved angular alignment of said blades

A turbine plant compressor disc is formed from two halves which are welded together near the rim and define an internal cavity in which a centripetal accelerator is mounted for inducing cooling air to flow from the compressor through inclined passages in the rim on the downstream side of the blades carried by the rim, through the cavity of the disc, and towards the turbine to be cooled in the vicinity of the turbine shaft. The centripetal accelerator is composed of sectors which are removably mounted in the cavity of the disc, the sectors forming a perforated ring disposed in the central bore of the disc and each sector having a flat web extending radially outwards in the inner cavity of the disc to form radial centripetal channels communicating with the air passages in the rim.

Turbine plant compressor disc with centripetal accelerator for the

A turbo-machine compressor which includes variable incidence stator vanes the angular adjustment of which is controlled by a control ring coupled to individual vanes by individual links. Each link has at least one contact surface on each of its longitudinal edges, such surfaces being either plane or convex. In the event of failure of any link, the change in orientation is controlled within narrow limits by contact with the contact surfaces of adjacent links which have not failed.

Turbo-machine compressor with variable incidence stator vanes

A turbomachine rotor disc assembly includes a rotor disc having a plurality of blade-root grooves in its periphery, each two adjacent grooves defining a lobe lug between them. Rotor blades each include an aerofoil portion, a root portion, a platform defining the radially inner boundary of the aerofoil portion, and a stilt portion interconnecting the radially inner face of the platform and the root portion, a free space being defined between each adjacent pair of blades. The angular clearance of each blade in its groove is limited by wedges operative between adjacent blades on the stilts thereof and connecting members carrying the wedges secured to the rotor disc and capable of transmitting shock loads and distributing resultant forces over an adjacent sector of the rotor. The wedges are so dimensioned in relation to the dimensions of the stilts of adjacent blades that the angular clearance is limited to the permissible angular clearance of each blade during auto-rotation of the rotor.

Fan or compressor angular clearance limiting device

A method of manufacturing a variable incidence stator blade assembly comprising forming a blade with a root which forms an extension of the aerodynamic profile of the blade, forming a bush with a recess accommodating the root by ultrasonic, electro-chemical or electro-erosion machining and assembling the blade and bush in a turbo-machine outer casing and in an inner ring of channel section. A variable incidence stator blade assembled in a compressor of a gas turbine is also described, the blade assembly being as manufactured by the method. The channel section inner ring carried an abradable layer which co-operates to form a seal with annular lips carried by the compressor rotor drum.

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Le Chatelet En Brie, France

Jacques M Stenneler