Safran Aircraft Engines

Safran

Thomas Olivier Michel Pierre De Rocquigny

Ba-Phuc Tang

Romain Pierre Cariou

Patrice Eneau

Adrien Bernard Vincent Rollinger

Léandre Ostino

Michel Slusarz

Vianney Simon

Pierre Guillaume Auzillon

Jeremy Jacques Attilio Fanelli

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 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 engine vane including a blade extending following a radial axis and a cooling circuit arranged inside the blade, the cooling circuit including a first cavity and a second cavity arranged downstream from the first cavity following a direction of circulation of a cooling fluid, the first and second cavities extend radially inside the blade and being separated at least partially by a radial partition having a radially external free end which delimits at least partially a passage connecting the first and second cavities, the radial partition connecting a first wall in contact with the outside environment of the blade to a second opposite wall substantially following a transversal axis, perpendicular to the radial axis, respectively in a connection zone. According to the invention, at least one connection zone presents a thickening having a substantially triangular general transversal cross-section.

Turbine engine blade equipped with a cooling circuit with optimized connection zone

Growing community of inventors

Moissy-Cramayel, France

Thomas Olivier Michel Pierre De Rocquigny