Turbomeca

Safran Helicopter Engines

Jean-Luc Pierre Sahores

Jean-Maurice Casaux-Bic

Olivier Pierre Descubes

Frédéric Philippe Jean-Jacques Pardo

Carole Jaureguiberry

Marc Maurice Dijoud

Gontran Martineau

Kévin Pilette

Julien Carbon

Michel Francois Leon Beaucoueste

Damien Chauveau

Michel Francois Beaucoueste

Michel François Léon Beaucoueste

A blade of a high-pressure turbine of a turboshaft engine, the blade including an airfoil extending in a spanwise direction, terminating in an apex and having a suction wall and a pressure wall joined by a leading edge and joined by a trailing edge. The blade further includes an internal cooling circuit having only an upstream duct and a central chamber for cooling the blade by circulating air. The upstream duct and the central chamber are separately supplied with air. The upstream duct being dedicated to the cooling of the leading edge and the suction wall, and the central chamber being dedicated to the cooling of the pressure wall and the trailing edge and being provided with bridge elements each connecting the pressure wall and the suction wall.

Ventilated high pressure blade of a helicopter turbine comprising an upstream duct and a central cooling chamber

A turbine wheel with optimal-mass dampers to dampen a predetermined resonance in context of vibration of a turbine, particularly a low-speed turbine, while assisting in flexibility of adapting to bearing surfaces of recesses of the dampers, by separating mass and flexibility functions by a flexible portion for clamping against the platform, and a mass portion for controlling frictional forces. A damper includes a plate and a counterweight. The plate is stamped from a metal sheet that is substantially thinner than that of the counterweight. The plate includes a wall configured to flexibly contact a platform of the blade of the wheel, while at least partially surrounding a surface of the counterweight. The damper can be used in particular for a wheel of a turbine of a turbine engine, of a fan, or of a BP compressor having mounted blades.

Method for damping a gas-turbine blade, and vibration damper for implementing same

A method and structure negating thermal inertia of a solid portion, such as shielding, which influences mechanical behavior of parts of an engine structure, by reducing forces transmitted to the engine structure during an event in which a turbine blade ruptures, while preserving mechanical strength and vibratory positioning. The structure includes a flexible fastener for a shield, enabling producing a fusible section. An assembly for mounting a shielding onto a casing of the engine structure of a turbine includes connection lugs and points for attachment to the casing and shielding. The attachment points are sufficiently spaced apart in accordance with curvature of the shielding and casing so connection between the lugs and the shielding or casing, and connection of the attachment points, are substantially tangential. The lugs are sized so the connection has sufficient flexibility to control vibratory positioning thereof and ensure sufficient mechanical strength under thermo-mechanical loads.

Method for mounting shielding on a turbine casing, and mounting assembly for implementing same

An assembly including a part for mounting at least one shaft bearing of a turbine engine and a support part that forms an abutment for the mounting part. The mounting part includes at least one channel through which engine gases pass, and connection parts that are capable of connecting the channel to an outer structure of the engine and to a housing holding the bearing. At least one of the connection parts is flexible so as to enable radial movement of the channel, an amplitude of the radial movement being limited by at least one of the elements of the mounting part coming onto an abutment supported by the support part. The support part extends longitudinally with regard to the direction of the rotational axis of the turbine engine so as to generate a turbine shroud that is configured to be positioned in alignment with a turbine wheel of the turbine engine.

Flexible rear bearing mounting, having an abutment, for a turbine engine

A turbine wheel having an axis of rotation and including: a disk having a periphery and a side face; a plurality of blades assembled on the disk, each blade having a blade root and a first hook oriented radially and defining a first groove that opens radially towards the axis of rotation of the turbine wheel. The disk includes a series of second hooks oriented radially and defining a second groove that opens radially towards the axis of rotation of the turbine wheel. An axial retaining ring for placing in the first and second grooves includes a tab for placing between two adjacent blade roots to limit movements of the ring in azimuth.

Turbine wheel fitted with an axial retaining ring that locks the blades relative to a disk

Growing community of inventors

Mazeres-Lezons, France

Jean-Luc Pierre Sahores