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

Other

Snecma

Daniel G Girault

Gilles J Bessenay

Joel M Benoit

Laurent Jean David

Ludovic Edmond Molliex

Gerard Philippe Gauthier

Jean-Claude Robert Berthelemy

Christophe Gerard Grosbois

Ludovic Edmond Camille Molliex

Bruno Jacques Dambrine

G&eacute;rard Philippe Gauthier

Patrick Fouche

Catherine L Guet

The invention concerns a method for producing parts made of thin, light and rigid metal alloy essentially having the following steps: producing a core having the part shape; producing cavities in the core; producing shells made of metal alloy combined with reinforcing fibers with high modulus of elasticity; densifying the shells; and diffusion welding of the shells on the core by compression at temperature and pressure conditions for isothermal forging of the metal alloy used.

Method for obtaining thin, light and rigid metal parts

A process for moulding high strength elongated parts made of a fibre-resin composite material, especially turbomachine blades such as fan blades, is disclosed wherein a plurality of heating and cooling elements are arranged within the body of the mould at intervals along the length of the mould cavity, and the liquid resin which is injected at one end into the mould cavity containing the fibre preform is polymerized progressively from the opposite end of the mould cavity, while maintaining the supply of liquid resin under pressure to the cavity, by successively de-activating the cooling elements, which maintain the resin in the liquid state, at predetermined time intervals starting from said opposite end of the mould cavity and progressing in turn towards said one end, and in synchronism therewith successively activating the heating elements to raise the temperature of the resin to the polymerizing temperature progressing in turn from said opposite end to said one end of the mould cavity. The process enables shrink cavities in the finished part to be avoided.

Process for moulding high strength elongated parts made of a fibre-resin

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 heat treatment installation for parts made of a composite material having a ceramic matrix and including a treatment enclosure which is connected to a microwave generator by a waveguide and which includes a press for hot pressing a part to be treated in the enclosure and a gas source for introducing a protective gas into the enclosure.

Installation and method for heat treating parts made of a composite

A gas turbine blade includes a central core covered by a plurality of layers of composite material, and optionally also an outer sleeve of woven composite material. A network of transverse seams pass through the layers of composite material, and preferably also the core and the outer sleeve. This construction is particularly applicable to large diameter turbine blades.

Gas turbine blade comprising layers of composite material

A molding apparatus for the hot pressing of parts made of refractory material includes at least one element, such as a mold or an intermediate element, which is formed by a material capable of withstanding high temperatures, having adequate mechanical resistance and possessing particular anisotropic properties of thermal conductivity, in particular as a result of a structure including thermally conductive fibers oriented so that a preferential heat transfer occurs towards the areas of the part which are furthest away from its edges of the part, ensuring homogeneous heating or cooling throughout the part at all times.

Molding apparatus having elements made of composite material

A system for the distribution of atomized lubricating fluid includes a cylindrical ring placed upstream from an intershaft bearing of an inner shaft. The outer surface of the ring forms part of a labyrinth joint. Within the ring are cells open on the upstream surface of the ring, into which flows pressurized air. In the downstream end of each cell is an atomizing orifice directed toward the bearing. In the radially inner wall of each cell is an approximately radial bore. These bores cooperate with the means supplying lubricating fluid, which comprise radial bores in the wall of the inner shaft and emptying into a groove provided on the inner surface of the inner shaft. The groove receives lubricating fluid through fixed tubing that passes through the interior of the inner shaft.

Growing community of inventors

Melun, France

Daniel G Girault