Snecma

Safran Aircraft Engines

Fabrice Garin

Maurice Guy Judet

Thomas Langevin

Stephane Pierre Guillaume Blanchard

Stéphane Pierre Guillaume Blanchard

Mathieu Dakowski

Damien Bonneau

Wilfried Lionel Schweblen

Delphine Roussin-Leroux

Laurent Jacques Michel Coulombeau

The invention relates to a trunnion () for a high-pressure turbine (), to be arranged between a shaft of a low-pressure turbine () and an inner surface () of a seal mounting () of the low-pressure turbine (), the trunnion () being characterized in that it includes a drop-launching extension () arranged such as to extend opposite a flared portion () of the inner surface () of the seal mounting (), such that when the trunnion () is rotated about the shaft of the low-pressure turbine (), oil (H), which tends to penetrate between the trunnion () and the seal mounting (), is thrown by centrifugal effect from the drop-launching extension () toward the flared portion () of the inner surface () of the seal mounting ().

Trunnion for high-pressure turbine, and turbojet engine including such a trunnion

A turbomachine high-pressure turbine including a rotor disc with upstream and downstream annular flanges separating a radially internal annular cavity in which the hub of the disc extends from two radially external annular cavities, of which one is upstream of the disc and receives a ventilation air flow and of which the other is downstream of the disc, the upstream flange of the disc including a mechanism connecting to the upstream eternal cavity and the internal cavity for ventilating the hub of the disc.

Ventilation of a high-pressure turbine in a turbomachine

An assembly with a turbine disk for a gas turbine engine and a bearing-supporting journal, the turbine disk having a radial annular fastening flange secured to a radial annular part of the journal by bolts, the bolts passing successively through fastening bores formed in the radial annular fastening flange of the turbine disk and in the radial annular part of the journal, the radial annular part of the journal having air circulation openings, the openings being formed between the fastening bores of the journal.

Assembly including a turbine disk for a gas turbine engine and a bearing-supporting journal, and cooling circuit for the turbine disk of such an assembly

The present invention relates to a turbomachine rotor balancing system comprising a balancing flange () provided with through-passageways (), the system further comprising balance weights () each mounted fixedly on the flange () by means of a first and a second screw/nut assembly () having a first and a second screw () passing through a first and a second passageway (). According to the invention, said first screw is pressing against a first tangential end side () of the first through-passageway, and at a distance from a second tangential end side, and the second screw is pressing against a second tangential end side () of the second through-passageway, and at a distance from the first tangential end side.

Balancing system for turbomachine rotor

A turbomachine rotor balancing system including a balancing flange provided with through-passageways, and balance weights mounted fixedly on the balancing flange by at least one screw/nut assembly passing through one of the passageways is disclosed. For each of the passageways, the flange has on its first face a first recess passing via the radial summit of the passageway. This first recess being deprived of contact with the screw head pressing on this first face. The flange has on its second face a second recess passing via the radial summit. The second recess being deprived of contact with the balance weight pressing on this second face.

A retention device for axially retaining a rotor disk flange, the device including a split annular retaining ring. The ring has an external face bearing against an internal face of the rim, thereby resulting in a first axial force, an internal face bearing against an external face of the root, thereby resulting in a second axial force, the axial forces being radially offset relative to each other, and an outer face bearing against an inner face of the base of the flange, thereby resulting in a radial force. The outer face of the ring presents an annular setback in such a manner that the radial force is situated in a plane that is offset axially relative to a radial plane passing through the center of gravity of the ring so as to obtain mechanical equilibrium between the forces acting on the ring.

Growing community of inventors

Boissise la Bertrand, France

Fabrice Garin