Safran Aircraft Engines

Safran

Vianney Simon

Adrien Bernard Vincent Rollinger

Ba-Phuc Tang

Léandre Ostino

Romain Pierre Cariou

Patrice Eneau

Michel Slusarz

Pierre Guillaume Auzillon

Thomas Olivier Michel Pierre De Rocquigny

Patrick Jean Laurent Sultana

Patrice Jean-Marc Rosset

Jean-Claude Christian Taillant

Myriam Pelleterat De Borde

Jérémy Jacques Attilio Fanelli

Vincent Keciyan

Romaine Pierre Cariou

The present invention relates to a rotating assembly of a turbomachine, comprising: —a shaft configured to drive a propeller of the turbo machine around an axis and comprising a first flange radially extending from the shaft, the first flange being monolithic with the shaft; —a sleeve fitted onto the shaft and comprising a second flange radially extending from the sleeve, the sleeve being attached to the first flange of the shaft by means of the second flange; and —at least one component connected to the shaft by means of the sleeve so as to be rigidly connected to the shaft to move therewith, the component comprising at least one sealing element.

Sleeve mounted onto a low-pressure shaft in a turbomachine

A turbine vane includes a root carrying a blade terminated by a squealer tip, the blade having intrados and extrados walls, a leading edge, a trailing edge, and a tip wall delimiting a bottom of the squealer tip, by which the intrados wall is connected to the extrados wall. The blade also includes: a serpentine median circuit, including a first radial pipe that collects air at the root and is connected by a first bend to a second radial pipe that is connected by a second bend to a third radial pipe; a cavity under the squealer tip running along the extrados wall and extending from a central region of the squealer tip to the trailing edge; and a central radial pipe collecting air at the root and extending between at least two of the three pipes of the median circuit and directly supplying the cavity under the squealer tip.

Turbomachine blade with improved cooling

A turbine engine blade includes an airfoil with a pressure-side wall and a suction-side wall which are connected upstream by a leading edge and downstream by a trailing edge. A cooling circuit has an internal cavity extending inside the airfoil and a plurality of outlet openings, each oriented substantially along a longitudinal axis X. Each outlet opening communicates with the cavity and is arranged in the vicinity of the trailing edge. A calibration device is arranged in the cavity and provided with calibration conduits arranged substantially opposite the outlet openings. The calibration conduits each include an oblong transverse section which is substantially perpendicular to the longitudinal axis.

Turbine engine blade provided with an optimized cooling circuit

The invention relates to a turbine engine vane including a blade extending along a radial axis and a first cooling circuit arranged inside the blade, the first cooling circuit including a first cavity and a second cavity disposed downstream of the first cavity in a direction of circulation of a coolant in the blade, the first and second cavities radially extending inside the blade and being at least partly separated by a first radial partition having a radially internal free end, which at least partly demarcates a first coolant passage connecting the first and second cavities. According to the invention, the radially internal free end is enlarged by having a general transverse section substantially in the form of a keyhole.

Turbine engine vane equipped with a cooling circuit and lost-wax method for manufacturing such a vane

A turbine blade including a root carrying an impeller terminated by a tip in the form of a squealer tip. This impeller also includes a serpentine median circuit, including a first radial pipe collecting air at the root and that is connected by a first bend to a second radial pipe that is connected by a second bend to a third radial pipe, a cavity under the squealer tip running along the pressure side wall, extending from a central region of the tip to the trailing edge, and a radial central pipe collecting air at the root extending between at least two of the three pipes of the median circuit and directly supplying the cavity under the squealer tip.

Turbine engine blade with improved cooling

A turbine blade includes a root and an airfoil extending from a base, through which it is connected to the root, to a tip. The airfoil includes an intrados wall and an extrados wall, connected by a leading edge and by a trailing edge with a cooling circuit. The cooling circuit includes a conduit with a duct and a manifold prolonging this conduit. The conduit collects air from the blade root to supply the duct and the manifold that is located downstream from the duct and that supplies the slits in the trailing edge with air. The duct supplies air to one end of the manifold close to the tip. The manifold is separated from the duct by a partition including a portion close to the tip that is curved to be concave when seen from the trailing edge.

Turbomachine blade with trailing edge having improved cooling

Growing community of inventors

Moissy-Cramayel, France

Vianney Simon