Office National D'etudes Et De Recherches Aerospatiales

Safran

Safran Aircraft Engines

Snecma Moteurs

Safran Helicopter Engines

Odile Lavigne

Virginie Jaquet

Jérémy Rame

Pierre Caron

Joël Delautre

Jean-Yves Guedou

Didier Locq

Mikael Perrut

Marie-Pierre Bacos

Serge Alperine

Daniel Morvan

Frederic Rousseau

Catherine Rio

Marie-Helene Vidal-Setif

R&eacute;my Mevrel

V&eacute;ronique Arnault

Philippe Belaygue

Jeremy Rame

Joel Delautre

Frédéric Rousseau

Marie-Hélène Vidal-Setif

The invention relates to a nickel-based superalloy comprising, in percentages by mass, 4.0 to 5.5% rhenium, 1.0 to 3.0 ruthenium, 2.0 to 14.0% cobalt, 0.3 to 1.0% molybdenum, 3.0 to 5.0% chromium, 2.5 to 4.0% tungsten, 4.5 to 6.5% aluminum, 0.50 to 1.50% titanium, 8.0 to 9.0% tantalum, 0.15 to 0.30% hafnium, 0.05 to 0.15% silicon, the balance being nickel and unavoidable impurities. The invention also relates to a single-crystal blade (A,B) comprising such an alloy and a turbomachine () comprising such a blade (A,B).

Nickel-based superalloy, single-crystal blade and turbomachine

A nickel-based superalloy comprises, in percentages by mass, 4.0 to 5.5% rhenium, 1.0 to 3.0 ruthenium, 2.0 to 14.0% cobalt, 0.3 to 1.0% molybdenum, 3.0 to 5.0% chromium, 2.5 to 4.0% tungsten, 4.5 to 6.5% aluminum, 0.50 to 1.50% titanium, 8.0 to 9.0% tantalum, 0.15 to 0.30% hafnium, 0.05 to 0.15% silicon, the balance being nickel and unavoidable impurities. A single-crystal blade comprises such an alloy and a turbomachine comprising such a blade.

A nickel-based superalloy comprises, in percentages by mass, 4.0 to 5.5% rhenium, 3.5 to 12.5% cobalt, 0.30 to 1.50% molybdenum, 3.5 to 5.5% chromium, 3.5 to 5.5% tungsten, 4.5 to 6.0% aluminum, 0.35 to 1.50% titanium, 8.0 to 10.5% tantalum, 0.15 to 0.30% hafnium, 0.05 to 0.15% silicon, the balance being nickel and unavoidable impurities. A single-crystal blade comprises such an alloy and a turbomachine comprising such a blade.

A nickel-based superalloy comprises in mass percent: 4.0% to 6.0% chromium; 0.4% to 0.8% molybdenum; 2.5% to 3.5% rhenium; 6.2% to 6.6% tungsten; 5.2% to 5.7% aluminum; 0.0 to 1.6% titanium; 6.0% to 9.9% tantalum; 0.0 to 0.7% hafnium; and 0.0 to 0.3% silicon; the balance being constituted by nickel and any impurities. A monocrystalline blade comprises such an alloy and a turbomachine including such a blade.

Superalloy based on nickel, monocrystalline blade and turbomachine

The invention relates to a method for repairing a thermal barrier of a component comprising a substrate coated with such a thermal barrier, said substrate being made of a high-performance alloy, said thermal barrier being adhered to the alloy and having lower thermal conductivity than the alloy, the thermal barrier including at least one ceramic, one region of the thermal barrier being a region to be repaired, wherein said method includes the following steps: a) defining the region to be repaired, using a mask which protects the other regions of the thermal barrier; b) injecting a carrier gas loaded with droplets of ceramic precursor into a plasma discharge inside a plasma chamber of a plasma reactor containing the component to be repaired, while making the concentration of ceramic precursor in the carrier gas dependent on at least one parameter of the reactor selected from among: the pressure of the plasma chamber, the power of the plasma generator and the diameter of the precursor droplets, in order to control the state&#x2014;liquid, gel or solid&#x2014;of the ceramic precursor having an effect on the region to be repaired; c) injecting a gas not loaded with ceramic precursor into a plasma discharge within the plasma chamber, steps b) and c) being repeated.

Method for locally repairing thermal barriers

A low thermal conductivity heat barrier composition, particularly for a superalloy article, is disclosed comprising a zirconia base and a dysprosium oxide having the dual function of stabilizing the zirconia and reducing the thermal conductivity thereof. Optionally, the composition also comprises a metal oxide containing a quadrivalent metallic ion selected from the group consisting of hafnium dioxide, cerium dioxide, uranium dioxide, and mixtures thereof.

Heat barrier composition, a mechanical superalloy article provided with a ceramic coating having such a composition, and a method of making the ceramic coating

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Odile Lavigne