Safran Aircraft Engines

Benoit Guillaume Silet

Nicolas Contini

Laurent Claude Descamps

Maria Goossens

Rémy Miled Michel Haynau

Stéphane Pierre Guillaume Blanchard

Bertrand Guillaume Robin Pellaton

Arnaud Lasantha Genilier

Julian Nicolas Girardeau

Fabien Stéphane Garnier

Josselin Luc Florent Sicard

Bertrand Pellaton

Jean Charles Marie Coussirou

Thibaud Louis Zaia

Anne-Flore Karine Houlet

Hélène Marie Barret

Josselin Luc Sicard

Helene Marie Barret

A blade and a sealing element forming an assembly for a turbomachine turbine. The blade includes an airfoil and a platform to which the sealing element is connected. An internal channel passes through the platform so as to draw off fluid circulating in a primary duct that it delimits and to inject the thus drawn-off fluid into an inter-lip cavity delimited by the sealing element.

Turbine blade for an aircraft turbomachine, provided with a channel for ejecting a primary flow towards an inter-lip cavity

A rotor of a turbine extending around a longitudinal axis includes a rotor disc bearing at its periphery one or more rotor blades, each blade including an airfoil provided at its radially outer end with a platform equipped with an upstream lip and a downstream lip, the platform having a front lateral edge and a back lateral edge with respect to the normal direction of rotation of the rotor about the longitudinal axis, and a suction face portion which extends from the front lateral edge to the suction face of the airfoil. The upstream lip and the downstream lip each includes sawtooth-shaped cut-outs such as to form a front tooth and a back tooth which are contiguous, in that the back tooth has a cutting edge and in that the front tooth of each lip is disposed on the suction face portion of the platform.

Turbine rotor for a turbomachine

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

A turbomachine turbine casing that extend around an axis and includes an annular wall and a cooling device. The annular wall is provided with a casing hook which extends in radial protrusion from an inside of the annular wall. The casing hook allows a mounting, on the turbomachine turbine casing, of ring segments disposed circumferentially end to end around the axis. The cooling device includes a collector duct intended to convey cooling air, the collector duct extending circumferentially around the annular wall. The collector duct has a cooling air inlet and a cooling air outlet. The collector duct and the annular wall have a common portion, which delimits the collector duct and from which the corresponding casing hook extends.

Turbine housing cooling device

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 an annular casing of a turbomachine includes a collector housing having ejection openings in a radially inner part of the collector housing facing the annular casing and at least two cooling tubes extending circumferentially from the collector housing and having election openings in a radially inner part of the tubes facing the annular casing. The collector housing having an air passage formed by a radial groove extending radially from a radially inner end of the collector housing to a radially outer end of the collector housing and an axial groove extending from a first axial end to a second axial end of the collector housing.

Device for cooling a turbomachine housing

A turbine rotor for a gas turbine engine, includes an upstream turbine disk; a downstream turbine disk; an annular flange; a first ferrule connecting the upstream turbine disk to the annular flange; a second ferrule connecting the downstream turbine disk to the annular flange; an air flow separator device including: a first part, forming a first ring, arranged between the upstream turbine disk and the downstream turbine disk; a second part, forming a second ring, having a first portion facing the downstream turbine disk, and a second portion arranged between the first ferrule and the second ferrule; and a thermal insulation area arranged between the first part and the second part.

Growing community of inventors

Yerres, France

Benoit Guillaume Silet