Safran Aircraft Engines

Snecma

Damien Merlot

Philippe Gérard Edmond Joly

Laurent Jablonski

Philippe Gerard Joly

Jean-Marc Claude Perrollaz

Christophe Perdrigeon

Hervé Pohier

Herve Pohier

Francois Jean Comin

François Jean Comin

Hanna Reiss

Benoit Fayard

Marco Nucci

Jacky Rodriguez

Adrien Biscay

Etienne Ide

Remi Sers

Benoît Fayard

A fan blade for an airplane turbojet, the blade including an airfoil extending axially between a leading edge and a trailing edge and including a plurality of airfoil sections stacked radially between a root section and a tip section. All of the airfoil sections situated between the root section and an airfoil section situated at a radial height corresponding to 30% of a total radial height of the airfoil possess a skeleton curve having a point of inflection.

Airplane turbojet fan blade of cambered profile in its root sections

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 relates to a blade, the platform () of which has at least one bumper () which rises, on the inner face, from a connection to an intermediate area of the blade located along a longitudinal axis of the blade, between the blade root and the outer face (), towards a free side edge () of the platform. The platform bumper () locally has a thinned portion at a distance from said free side edge of the platform. The invention is applicable to turboshaft engine fans.

Blade with a platform and a hollow bumper

A fan blisk for a turbomachine, the blisk comprising a hub delimited by an upstream face and a downstream face in addition to an outer peripheral face and a revolving inner peripheral face delimiting an inner opening, the hub carrying blades each having a leading edge and a trailing edge, the hub and the blades forming a one-piece assembly. The upstream face and/or the downstream face is offset, being located along the axis of rotation (AX) between the leading edges and the trailing edges of the blades, the blisk (bladed disk) comprising a filling member mounted on the offset face, the filling member comprising an inner centring ferrule engaging in the inner face of the hub, a radial portion resting against the offset face and an outer ferrule extending the outer peripheral face of the hub.

Blisk comprising a hub having a recessed face on which a filling member is mounted

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.

The shank of a blade includes a first side and a second side provided with a depression. By concentrating this depression on a single side, a shank that is more rigid and resistant with an equal lightening is obtained, with the stress concentrations depending on the depth of the depression but being absent from first flat side. The vibrations and bending deformations are also reduced.

Blade comprising a shank, provided with a depressed portion

The invention relates to a single-piece fan blisk () for a turbojet, this blisk () comprising a hub () with a general shape of revolution about a rotation axis (AX) and comprising an external peripheral face () of revolution extending radially towards the rotation axis at an upstream face () and a downstream face both of which are in the form of rings. This hub () supports radially oriented blades () at its external peripheral face (), each comprising a base through which it is connected to this external peripheral face (), each blade () having a leading edge () and a trailing edge () that are radially oriented. The spacing between the upstream face () and the downstream face of the hub () along the rotation axis (AX) is less than the distance separating the leading edge () from the trailing edge () of each blade.

Single-piece blisk for turbomachine fan comprising an upstream and/or downstream recess making its blades more flexible

An assembly for an aircraft turbine engine including an integral element including a disk and a plurality of blades is provided. Each blade has a connection zone connecting the blade to the disk, the connection zone including a first part arranged at the external flowpath delimitation surface provided on the disk, and at least one second end part arranged at a recess formed in the disk along the axial extension of the external surface, the average fillet radius defined by the second end part being larger than the fillet radius defined by the first part. The assembly further includes a flowpath reconstruction part formed in the aerodynamic continuity of the external surface, so as to cover the recess.

Blisk with low stresses at blade root, preferably for an aircraft turbine engine fan

A turbine engine cowl capable of covering a fan cone, the cowl including attachment components configured to engage with connection components of the cone in order to maintain the cowl and the cone secured to one another.

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Vaux Le Penil, France

Damien Merlot