Snecma Moteurs

Snecma

Safran Aircraft Engines

Paul Rodrigues

Jean-Luc Soupizon

Jean-Baptiste Arilla

Olivier Belmonte

Olivier Renon

Jean-Claude Christian Taillant

Marc R Marchi

Pierre Debeneix

Sylvie Coulon

Christian Rene Schnell

Patrice Rosset

Stevan Le Goff

Patrice Jean Marc Rosset

Christian Ren)e Schnell

Florence Ir&egrave;ne No&euml;lle Leutard

A cooling device for cooling the slots of a turbomachine rotor disk is provided. The turbomachine includes an upstream rotor disk having a fastener flange with a periphery that is festooned; a downstream rotor disk; an endplate for holding blades and arranged around the ring of the downstream disk and co-operating therewith to form an air diffusion cavity; a cone for driving disks in rotation and having a fastener flange with a periphery that is festooned; and a plurality of bolted connections passing from upstream to downstream through the fastener flanges of the upstream disk and of the cone, the fastener flange of the endplate, and the fastener flange of the downstream disk. The fastener flange of the endplate is pierced by ventilation orifices opening out into the air diffusion cavity, the cavity opening out into the slots of the downstream disk at their upstream ends.

Cooling device for cooling the slots of a turbomachine rotor disk downstream from the drive cone

A device for mounting a suspension member on the casing of a turbine engine is disclosed. The device includes a yoke with at least one lug, secured to the casing, a pin fixed to the yoke supporting the member via a ring surrounding the pin, and a rotation-prevention device that includes a counter-rotation plate attached to the lug. The plate and the pin include an assembly consisting of a peg and of a cutout or a hole, into which the peg fits in order to prevent the pin from rotating in the yoke.

Means for preventing the rotation of a pin supporting a turbine engine suspension member

An attachment device for attaching a blade to a turbine rotor disk in a turbomachine, the blade root forming a male portion engaged and held radially in a cavity of complementary shape in the rotor disk, with means for preventing the blade root from moving axially in the cavity, the blade axis being inclined relative to a perpendicular to the axis of rotation of the rotor, in a direction and at an angle that are designed to compensate at least in part for the displacement of the axis of the blade caused by the mechanical and thermal stresses applied to the rotor during operation of the turbomachine.

Device for attaching a moving blade to a turbine rotor disk in a turbomachine

A turbomachine includes a casing, a rotor, and a plurality of cooled ring segments installed between the casing and the rotor, each ring segment containing a main cooling cavity and being attached to the casing by a fastening device. The fastening device can include a clamping screw positioned more or less radially and pinning the ring segment against the casing. The clamping screw is crossed through by a cooling airway that communicates with the main cooling cavity of the ring segment.

Turbomachine with cooled ring segments

A joint between a turbine ring. The ring is jointed to a spacer of the turbine by a joint including hooks which fit together on one side, and an abutment of flanges as well as a mortise and tenon joint on the other side. According to the joint, the tenon and mortise are separated from the flanges in abutment to limit the plays in the axial direction, produced by design or by expansions, to increase mechanical strength and simplify manufacturing.

Device for fixing a turbine ferrule

Growing community of inventors

Savigny sur Orge, France

Paul Rodrigues