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Association Pour La Recherche Et Le Developpement Des Methodes Et

Office National D'etudes Et De Recherches Aerospatiales

Office National D'etudes Et De Recherches Aerospatiales (onera)

Onera (office National D'etudes Et De Recherches Aerospatiales)

Office National D'etudes Et De Recherche Aerospatiales (onera)

Tecphy

Michel Marty

Andre M Walder

Christian A Ducrocq

Shigehisa Naka

Christophe Delaunay

Tasadduq Khan

James Henry Davidson

Marc Thomas

Gerard Lemaitre

Yves C Bienvenu

Henri Octor

Michel L Allouard

Pierre Thevenin

Michele Soucail

Didier P Lestrat

Jean Charles Lautridou

Bernard Paintendre

Catherine Duquenne

Titanium aluminide which can be used at high temperature

A nickel-based superalloy possessing good mechanical properties when hot regarding traction, creep and cracking resistance has a chemical composition which comprises, in percentages by weight: Co 14.5 to 15.5 ; Cr 12 to 15 ; Mo 2 to 4.5 : Al 2.5 to 4; Ti 4 to 6; Hf not more than 0.5 ; C 100 to 300 ppm; B 100 to 500 ppm; Zr 200 to 700 ppm; possibly W up to 4.5; and nickel as the remainder. Components made from these alloys have an excellent microstructural stability when operating at temperatures up to 800.degree. C.

Nickel-based superalloys with high temperature stability

Tantalum-based and niobium-based alloys made up entirely of a crystalline medium exhibiting a substantially continuous centered cubic structure, comprising an intermetallic compound of formula Ti.sub.2 AlMo, and having the following compositions on an atomic basis:

Niobium or tantalum based high specific strength inter metallic

A niobium and titanium based alloy having a density less than 6.5 and possessing a high resistance to oxidation at high temperatures in the region of 900.degree. C. has a chemical composition comprising, in atomic percentages:

Niobium and titanium based alloys resistant to oxidation at high

Superalloy with a nickel base matrix having good mechanical properties when ot in respect of tensile strength, creep resistance, low cycle fatigue and resistance to crack-propagation of which the composition in percentages by weight is as follows: Cr 11 to 13; Co 8 to 17; Mo 6 to 8; Nb less than or equal to 1.5; Ti 4 to 5; Al 4 to 5; Hf less than or equal to 1; C, B, Zr each less than or equal to 500 ppm; Ni remainder to 100. The alloy can be manufactured advantageously by powder metallurgy techniques and used in the manufacture of turbo machine disks.

Superalloy compositions with a nickel base

A process for forming a titanium base alloy comprises compacting a powder formed of particles of titanium or of a mother alloy thereof and of a dispersion of fine particles of a product curbing the growth of the grain size, in a proportion per volume which is less than that which would lead to the formation of a continuous layer of fine particles about the particles of titanium powder. Then the alloy is heat treated at a temperature higher than the point of transformation into phase .beta. and quenched. The product is typically selected among S, P, B, As, Se, Te, Y and the lanthanides.

Process for forming a titanium base alloy with small grain size by

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Michel Marty