Safran Aircraft Engines

Snecma

Hervé Pohier

Laurent Jablonski

Philippe Gérard Edmond Joly

Damien Merlot

Christophe Perdrigeon

Jean-Luc Le Strat

Romain Jean-Louis Robert Thory

The invention proposes a fan, in particular for a turbomachine of small size such as a jet engine, having a hub ratio which corresponds to the ratio of the diameter of the inner limit of the incoming air stream at the radially inner ends of the leading edges of the fan blades, divided by the diameter of the circle around which the outer ends of the fan blades pass, having a value of between 0.20 and 0.265.

Fan for a turbomachine

The invention proposes a fan, in particular for a turbomachine of small size such as a jet engine, having a hub ratio which corresponds to the ratio of the diameter of the inner limit of the incoming air stream () at the radially inner ends of the leading edges of the fan blades (), divided by the diameter of the circle around which the outer ends of the fan blades pass, having a value of between 0.20 and 0.265.

A balancing device for a rotating part of a turbomachine, includes a ferrule pierced with a plurality of ports, a balancing screw passing through each port, each balancing screw including a body and a head, the head of each balancing screw being pierced with a recess, the balancing screws being of at least one first type, the recess of the screws of the first type being formed by a driving recess from which an additional recess extends.

Growing community of inventors

Moissy-Cramayel, France

Hervé Pohier