Safran Aircraft Engines

Snecma

Safran

Alexandre Gimel

Arnaud Nicolas Negri

Denis Gabriel Trahot

Marc Soisson

Maxime Paul Numa Givert

Amar Saboundji

Ba-Phuc Tang

Stéphane Knittel

Saïd Boukerma

Vijeay Patel

Elsa Maxime

Gabriela Mihaila

Josserand Jacques André Bassery

Slim Bensalah

Thomas Lardellier

Jérôme Salmon

Christophe Gleize

Axel Pereira

Jean François Richard

Christophe Damour

Janusz Lisowski

Romain Bard

Said Boukerma

Arnaud Negri

Jean-François Richard

The invention relates to a method for producing a metal bladed element for a turbomachine of an aircraft, said bladed element comprising at least one blade having a lower surface and an upper surface extending between a leading edge and a trailing edge of the blade, the trailing edge having to have a thickness X, said method comprising the steps of: a) producing the bladed element by lost-wax casting, and b) finishing the bladed element, characterised in that step b) comprises the chemical milling at least of the trailing edge of the or each blade so as to obtain said thickness Xwhich cannot be directly obtained by step a).

Method for producing a metal bladed element for a turbomachine of an aircraft

A turbine engine has a blade with lower and upper surfaces. The blade has a root at a radially external end and includes a transverse head section in a plane perpendicular to a radial direction of the blade, taken at the radially external end with a first center of gravity. The root has a second center of gravity defined in a plane parallel to the transverse head section and transversely offset from the first center of gravity. The second center of gravity is defined in a predetermined zone at least partly demarcated by a V that is open towards the lower surface and includes a peak, the orthogonal projection of which on the transverse head section is located on the first center of gravity.

Vane for a turbine engine with optimized heel and method for optimizing a vane profile

The invention relates to a method for producing a turbomachine compressor blade, comprising the following steps:—installing primary pins () comprising a material other than a titanium-based alloy in primary bores () of a core, the primary bores forming at least one polygon, and installing a secondary pin made of titanium-based alloy in a secondary bore of the core; —producing a stack () of a suction-face sheet (), a core () and a pressure-face sheet (); —compacting the stack; —removing the primary pins () from the primary bores (); —removing the secondary pin from the secondary bore; and—taking the core () away from the stack.

Method for manufacturing a turbomachine compressor blade by compacting

A rough cast blading of this blade includes, a suction sidewall and/or a pressure sidewall of this blading intended to respectively form the suction sidewall and/or the pressure sidewall of the blade, a casting allowance extending over a determined width from a trailing edge of the blading intended to form the trailing edge of the blade in the direction of a leading edge of the blading intended to form the leading edge of the blade, except for a reserved area adjacent to the trailing edge of the blading and whose width is at least one radius of the trailing edge of the blading, over at least part of the height of the blading.

Rough cast blading with modified trailing edge geometry

A turbomachine rotor blade, said blade having, at the distal end thereof, a heel comprising: a platform () having a first edge () on the lower side and a second edge () on the upper side, at least one sealing member having a first end portion () on the lower side and a second end portion () on the upper side, said sealing member having a sealing top that extends radially outwards from said platform () between said first and second end portions (), characterized in that, for at least one sealing member, the heel () comprises, on at least at one of the edges (), a portion forming a bowl () extending along the end portion () of the sealing member which corresponds to the edge (), the portion forming the bowl () being suitable for receiving a deposit of anti-wear material.

Turbomachine rotor blade

A blank casting for producing a turbine engine rotor blade, with a vane connected by a platform to a root, is provided. The root has an axial machining allowance intended to be removed by machining from each of its axial extremities. At least one of the axial extremities of the root includes at least one transverse channel that extends over the entire transverse width of the root and whose depth is greater than the machining allowance. A process for obtaining the blade by machining this blank casting is also provided.

Blank casting for producing a turbine engine rotor blade and process for manufacturing the rotor blade from this blank

Growing community of inventors

Moissy-Cramayel, France

Alexandre Gimel