Safran Aircraft Engines

Nicolas Contini

Clément Jarrossay

Damien Bonneau

Benoit Guillaume Silet

Pascal Cédric Tabarin

Maria Goossens

Rémy Miled Michel Haynau

Francesco Salvatori

Baptiste Marie Aubin Pierre Jouy

Arnaud Lasantha Genilier

Sébastien Jean Laurent Prestel

Laurent Claude Descamps

Vincent Dubois Dorogi

Arnaud Doublier

A high-pressure gas turbine for a turbomachine includes a nozzle guide vane assembly, an annular array of movable blades mounted downstream of the nozzle guide vane assembly, a bleed cavity, an upstream sealing element mounted on the nozzle guide vane assembly and a downstream sealing element mounted on the annular array of movable blades, a double baffle being formed by said upstream and downstream sealing elements, an external upstream cavity being formed in the upstream sealing element.

High-pressure gas turbine for turbomachine and turbomachine

A high-pressure gas turbine for a turbomachine includes a nozzle guide vane assembly, an annular array of movable blades mounted downstream of the nozzle guide vane assembly, a first recirculation cavity, a second recirculation cavity, and a bleed cavity. An upstream sealing element is mounted on the nozzle guide vane assembly and a downstream sealing element is mounted on the annular array of movable blades.

High-pressure gas turbine for a turbine engine and turbine engine

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.

Device for cooling a turbine casing with air jets

A cooling device () for a turbine of a turbomachine extending along an axis includes at least one radially inner metal sheet () and one radially outer metal sheet () that are joined to one another and delimit, between them, cooling air circulation channels () extending circumferentially from a connection region (). Each channel () includes at least one air inlet and air ejection orifices (), that are designed to be oriented toward a region to be cooled. The cooling device also includes at least one cooling duct () intended for the circulation of cooling air, the duct () located radially outside said metal sheets () and close to or in contact with the metal sheets so as to cool said metal sheets using the cooling air circulating in the duct (), the cooling duct () extending axially and arranged toward the circumferential end regions of the channels ().

Cooling device for a turbine of a turbomachine

Growing community of inventors

Moissy-Cramayel, France

Nicolas Contini