Safran Aircraft Engines

Julian Nicolas Girardeau

Simon Nicolas Morliere

Sébastien Jean Laurent Prestel

Ghislain Hervé Abadie

Benjamin Franklin François Gillot

Nicolas Xavier Trappier

Patrick Jean Laurent Sultana

Baptiste Dorian Lawniczek

Benoit Guillaume Silet

Matthieu Simon

Simon Jean-Marie Bernard Cousseau

Patrice Jean-Marc Rosset

Maxime Aurélien Rotenberg

Patrick Joseph Marie Girard

Kenny Beauboit

The present invention relates to a nozzle guide vane for a turbine, having an axis of revolution and comprising:

Turbine nozzle guide vane comprising an annular sealing element

A turbine rotor of a turbine engine of an aircraft, the rotor comprising a rotor disc provided at its periphery with a plurality of cavities for receiving the root of a blade. Each blade includes a circumferential coupling rib, a plurality of platforms, a main wall that is extended at its two ends by an upstream radial wall and by a downstream radial wall, the two longitudinal edges of each platform comprising a groove for receiving part of said coupling rib of one of the two blades between which this platform is assembled, and in that the height of each upstream radial wall is such that said wall extends radially inwards beyond the bottom of the cavity, until it is in front of the upstream face of the rotor disc.

Turbine rotor and platform for such a rotor

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

An abradable member for a turbomachine turbine, including a cellular structure including walls defining wells which open through a wear face. The cellular structure includes at least one flow straightener jutting from the wear face.

Abradable member for a turbine of a turbomachine, comprising a wear face provided with guide vanes

A turbine includes a rotor surrounded by a stator, a first movable stage including a series of rotating vanes, a second movable stage including a second series of rotating vanes, a distributor including a series of stationary vanes, the vanes including platforms jointly delimiting a separation between a main space in which a hot flow circulates through the vanes, and a secondary space surrounding a hub of the rotor. The rotor includes an aperture through which air is blown towards the secondary space, this air being discharged towards the main space. Straightening fins are carried by the distributor in the secondary space for straightening the air flow in order to change its gyration.

Turbine having an internal secondary space equipped with fins for correcting gyration of an airflow

The disclosure provides devices for cooling a turbine casing for a turbomachine and methods of using the same. The devices extend around an axis (X) and include air-distribution means configured to take in air and convey it to the casing. The air-distribution means include a first ramp and a second ramp extending circumferentially about the axis (X), each ramp having air ejection orifices intended to be directed towards the casing in order to cool it The devices further include adjustment means capable of adjusting the flow rate of air ejected at the level of the first ramp with respect to the flow rate of air ejected at the level of the second ramp.

Turbine casing cooling device for a turbomachine

The invention relates to a cooling device () extending circumferentially around a turbine engine casing (), such as, for example, a turbine casing (), comprising a support () extending axially and intended to be attached to the casing (), at least one cooling tube () extending circumferentially, at least one attachment member () comprising a radially inner portion () at least partially surrounding the tube (), and a radially outer portion () attached to the support (), the radially outer portion () of the attachment member () being attached to the support () through connecting means () formed by L-shaped sheets.

Cooling device for a turbine of a turbomachine

Cooling device () extending circumferentially around a turbomachine casing, such as a turbine casing, comprising a support () extending axially and designed to be secured to the casing, at least one cooling tube extending circumferentially, at least one securing member (), comprising a radially inner portion () at least partially surrounding the tube, and a radially outer portion () secured to the support (), the radially outer portion () of the securing member () being secured to the support () via the intermediary of a connection member () comprising a central portion () having a circumferential end portion () and a second circumferential end portion () which are circumferentially opposite, the first end portion () and the second end portion () each extending in an opposite axial direction, the first and second end portions () each being secured to the support (), the radially outer portion () of the securing member () being secured to the central portion () of the connection member ().

Growing community of inventors

Moissy-Cramayel, France

Julian Nicolas Girardeau