Safran

Office National D'etudes Et De Recherches Aerospatiales

Safran Aircraft Engines

Centre National De La Recherche Scientifique

Safran Helicopter Engines

Université De Poitiers

Universite De La Rochelle

Ecole Nationale Superieure De Mecanique Et D'aerotechnique De Poitiers

Joël Delautre

Virginie Jaquet

Jérémy Rame

Pierre Caron

Odile Lavigne

Jean-Yves Guedou

Didier Locq

Mikael Perrut

Sarah Hamadi

Fernando Pedraza Diaz

Jonathan Cormier

Philippe Belaygue

Christophe Philippe Audic

Annie Pasquet

Satoshi Utada

Patrick Villechaise

A turbomachine part includes a nickel-based superalloy substrate including, in mass content, 5.0% to 8.0% cobalt, 6.5% to 10% chromium, 0.5% to 2.5% molybdenum, 5.0% to 9.0% tungsten, 6.0% to 9.0% tantalum, 4.5% to 5.8% aluminum, hafnium in a mass content between 500 ppm and 1100 ppm, and optionally including niobium in a mass content less than or equal to 1.5%, and optionally at least one of carbon, zirconium and boron each in a mass content less than or equal to 100 ppm, the remainder being composed of nickel and unavoidable impurities.

Superalloy turbomachine part with an optimized hafnium content

The invention concerns a method for manufacturing an aircraft part, the part comprising a monocrystalline nickel-based superalloy substrate, the method consecutively implementing the steps of moulding the part at a moulding temperature greater than the melting temperature of the superalloy, and cooling the part, such that the monocrystalline superalloy has a γ phase and a γ phase, solution heat treatment of the part at a first temperature between the solves temperature of the γ' phase and the melting temperature of the superalloy, homogenising the crystalline structure or the part, cooling the part to ambient temperature, first tempering and second tempering.

Method for manufacturing a part made of a monocrystalline superalloy

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

Growing community of inventors

Moissy-Cramayel, France

Joël Delautre