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

Other

Ludovic Edmond Molliex

Jean-Claude Robert Berthelemy

Gerard Philippe Gauthier

Daniel G Girault

Gilles J Bessenay

Anthony G Razzell

Andre C Collot

Gilles Charles Klein

Xavier Jean Guyonnet

Philippe Louis Alassoeur

Fabrice Rossignol

Robert Lundberg

Olivier Sudre

Julien Parmentier

Magnus Holmquist

Michel Parlier

Alain Robert Perroux

The present method of manufacturing a ceramic composite material, composed of matrix and reinforcing materials and an intermediate weak interfice material, creates a composite material particuarly intended for use at temperatures above 1400&deg; C. and in an oxidizing environment. The matrix and reinforcing materials consist of the same or different ceramic oxides having a melting point above 1600&deg; C. The interface material provides in combination with the matrix and reinforcing materials a stress field liable to micro aciding. The reinforcing material is immersed into a powder slurry containing carbon (C) and ZrO,so as to be coated thereby and then dried. After which, the thus created composite material is subjected to green forming and densifying steps. Finally, the composite material undergoes a heat-treatment in air leaving a porous structure of the interface material.

Method for manufacturing a ceramic composite material

A blank consisting of a spirally wound fiber for use in the manufacture of a fiber reinforced article of composite material is made by winding the fiber onto a helical track on the surface of a frusto-conical spindle, covering the wound fiber with a thermoplastic binder which sets to form a frusto-conical shell encasing the fiber, removing the shell from the spindle and placing the shell with its base on a plate, and heating the shell starting from its base so as to soften it and cause it to progressively collapse onto the plate to form a disc comprising a spirally wound fiber. If necessary the collapse of the shell may be assisted by pressing on the shell in a direction towards the plate.

Method of making a disc consisting of a spirally wound fibre

A process for constructing a circular metallic article which includes a hub and a plurality of vanes mounted on the periphery of the hub wherein the vanes are placed in position around the hub, formers are arranged between the blade portions of the vanes, a dimensionally stable belt having a low thermal expansion coefficient is placed circumferentially around the vanes and the formers, and the assembly is subjected to an isostatic compression at the isothermal forging temperature and pressure of the materials of the hub and the vanes such that the vanes are diffusion welded to the hub and the blade portions of the vanes are compressed to shape.

Process for obtaining a bladed circular metallic article

An apparatus for producing a circular metal article reinforced by fibres in selected parts of its cross-section is described in which a metal blank of the article is formed and provided with at least one annular groove opening in the axial direction, preforms of reinforcing fibre and filler metal are placed in the groove which is then closed by a metal plug, and the assembly is isothermally forged to produce the article in a single forging step which serves to compress the preforms, weld the assembly together, and shape the article. Such articles may be used for machining high performance rotors for turbojet engines.

Method of producing a circular fibre-reinforced metal article, and

A method of producing a circular metal article reinforced by fibres in selected parts of its cross-section is described in which a metal blank of the article is formed and provided with at least one annular groove opening in the axial direction, preforms of reinforcing fibre and filler metal are placed in the groove which is then closed by a metal plug, and the assembly is isothermally forged to produce the article in a single forging step which serves to compress the preforms, weld the assembly together, and shape the article. Such articles may be used for machining high performance rotors for turbojet engines. Apparatus for use in the method is also described.

A method of producing a fibre-reinforced metallic circular part having a tral hollow, wherein the reinforcing fibres are disposed in the part in the vicinity of the hollow, comprises providing an annular metallic blank with a channel-sectioned groove opening towards the axis of the blank, placing uncompressed concentric layers of the reinforcing fibres and additional metal alternately in the groove followed by a more rigid expansion ring, evacuating the groove and sealing it by a deformable closure member which covers the groove, placing this assembly in an autoclave and subjecting it to a temperature and pressure sufficient to effect superplastic forging of the layers of additional metal whereby the fibre layers and the additional metal layers are compressed and welded to the blank in a single operation, and machining the resulting assembly to obtain the required shaped part.

Method of producing a fibre-reinforced metallic circular part

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Paris, France

Ludovic Edmond Molliex