Safran Aircraft Engines

Snecma

Pascal Casaliggi

Thierry Laurent Capolungo

Didier Pasquiet

Emilie Pouzet

Benjamin Cyrille Jacques Oudin

Didier Desire Rene Pasquiet

Remi Bourion

Didier Désiré René Pasquiet

A rotor of a member of a turbomachine, for example a rotor of a turbine, the rotor including a first element, a second element defining with the first element a ventilation cavity, the rotor including a spacer that is introduced and secured between the first element and the second element and that includes a row of through-passages that are configured to permit injection of cooling fluid into the ventilation cavity.

Turbine rotor comprising a ventilation spacer

A device cools a disk of a turbine extending along an axis. The disk includes on its circumference at least one recess surrounded by disk teeth each having an upstream face. The recess includes a bottom in fluid communication with an upstream cavity by way of at least one lunula. The lunula includes lateral surfaces that are inclined with respect to the radial plane which constitutes the plane of symmetry of the recess into which the lunula opens.

Device for cooling a turbomachine rotor

A rotor disc () for a turbomachine, including a radial flange () that includes a plurality of fastening holes (), and a plurality of scallops () forming notches in the flange (), and being separated by inter-scallop flange portions (). The flange alternatively has, in its circumferential direction: a fastening hole () and an inter-scallop flange portion () arranged in the radial extension of the fastening hole (), and a scallop (), in such a way that one or more of the scallops (--) has a volume greater than the volume of each of the other scallops (--), and one or more of the inter-scallop flange portions () has a volume less than the volume of each of the other inter-scallop flange portions (), in order to balance said disc (). A turbomachine including that rotor disc and a method for balancing a turbomachine rotor disc are also disclosed.

Balanced rotor disc, and balancing method

A sealing ring configured to be pressed against a rotor disc of a turbine stage for an aircraft turbomachine, the ring including a plurality of anti-rotation pegs which prevent it from rotating in relation to the rotor disc, each peg protruding axially from a ring body and including two opposite circumferential-end surfaces, respectively configured to be located facing two directly consecutive blades carried on the rotor disc. An axially opening slot passes radially through at least one of the anti-rotation pegs.

Growing community of inventors

Moissy-Cramayel, France

Pascal Casaliggi