Safran Aircraft Engines

Centre National De La Recherche Scientifique

Snecma

Safran

Université Paul Sabatier (Toulouse III)

Université De Poitiers

Universite De La Rochelle

Institut National Polytechnique

Ecole Nationale Superieure De Mecanique Et D'aerotechnique De Poitiers

Sarah Hamadi

Justine Menuey

Joël Delautre

Andre Hubert Louis Malie

Virginie Jaquet

Jérémy Rame

Jean-Pierre Bonino

Florence Ansart

Andre Hubert Malie

Annie Pasquet

André Hubert Louis Malie

Fernando Pedraza Diaz

Jonathan Cormier

Hélène Cerda

Nadine Alice Helene Harivel

Marie-Ange Boheas

Guillaume Pujol

Christophe Philippe Audic

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

To protect a superalloy substrate from oxidation and hot corrosion, disclosed herein is coating made by a process that deposits successive layers on the substrate, a first layer of aluminium and of at least one element capable of being alloyed with sulphur, and a second layer of a material that isolates the at least one element capable of being alloyed with sulphur.

Coating for protection against oxidation and against hot corrosion on a superalloy substrate

A method of measuring temperature reached by a part, for example a turbine engine part, in operation, the method including: mechanically treating the part; oxidizing the part; and depositing a layer including a temperature indicator for indicating the temperature reached by the part in operation.

Method of measuring the temperature reached by a part, in particular a turbine engine part

An estimation method for estimating thickness of a ceramic thermal barrier coating that is to be deposited by physical vapor deposition from at least one target and onto a gas turbine hot part mounted on a support tooling, the method including: digitally modeling a geometrical shape of the hot part and its movements relative to the target; representing the modeled hot part as a surface mesh; and estimating, for at least one mesh element of the hot part exposed to the radiation from the target during deposition of the coating, a coating thickness to be deposited on the mesh element at a given instant by using a radiation model modeling radiation from the target and taking account of the position of the mesh element at that given instant relative to the target.

Method and device for estimating a thickness of a ceramic thermal barrier coating

A method of localized repair to a damaged thermal barrier, the method including subjecting a part coated in a damaged thermal barrier to electrophoresis treatment, the part being made of an electrically conductive material, the damaged thermal barrier including a ceramic material and presenting at least one damaged zone that is to be repaired, the part being present in an electrolyte including a suspension of particles in a liquid medium, the ceramic coating being deposited by electrophoresis in the damaged zone in order to obtain a repaired thermal barrier for use at temperatures higher than or equal to 1000&#xb0; C., the particles being made of a material different from the ceramic material present in the damaged thermal barrier.

Method for localised repair of a damaged thermal barrier

To protect a superalloy substrate from oxidation and hot corrosion, disclosed herein is a process that deposits successive layers on the substrate, a first layer of aluminum and of at least one element capable of being alloyed with sulphur, and a second layer of a material that isolates the at least one element capable of being alloyed with sulphur.

Process for depositing a coating for protection against oxidation and against hot corrosion on a superalloy substrate

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Paris, France

Sarah Hamadi