Safran Aircraft Engines

Maria Goossens

Benoit Guillaume Silet

Nicolas Contini

Rémy Miled Michel Haynau

Arnaud Lasantha Genilier

Laurent Claude Descamps

A turbine for a turbomachine includes an annular row () of moving blades () surrounded by a support ring () of abradable material () carried by a housing (). The turbine also includes a distributor () mounted downstream of the moving blades () and having an attachment mechanism with a radially outer spoiler () coming to bear radially inwards on a cylindrical wall () connected to housing (). An annular wall () extends radially inwards from the cylindrical wall () and engages at its radially inner end in an annular groove () of the support ring (), and in which a free annular space () is formed between a radially outer face () of the ring () and the cylindrical wall ().

Turbine for a turbomachine, such as an aeroplane turbofan or turboprop engine

An air-jet cooling device for a casing of a turbomachine, in particular a turbine casing, including a cooling air housing having a wall, and a tube having a first end mounted on the wall of the housing so as to put the tube into fluid communication with the housing, orifices being formed in a wall of the tube in order to eject the cooling air coming from the housing on the casing. The tube has a section at the first end with a gradual variation that defines a boss. The boss has a curved surface to be immersed in the cooling air so as to avoid a detachment of a boundary layer of the cooling air at an interface between the first end of the tube and the housing.

Growing community of inventors

Moissy-Cramayel, France

Maria Goossens