Snecma

Safran Aircraft Engines

Vincent Perrot

Laurent Jablonski

Matthieu Jean Luc Vollebregt

Damien Joseph Cellier

Olivier Stephane Domercq

Agnes Pesteil

Hanna Reiss

Didier Merville

Thierry Jean-Jacques Obrecht

Lucie Galons

Celine Ghilardi

Jean-Christophe Gerard Roger Boniface

Nicolas Jean Fernand Pignier

Antoine Brunet

Jean-Christophe Gerard Boniface

Olivier Domercq

Agnès Pesteil

Céline Ghilardi

Jean-Christophe Gérard Roger Boniface

Matthieu Jean Vollebregt

Nicolas Jean Pignier

A method for modeling at least part of a non-axisymmetric surface () of one portion () of a part (). The portion () is bounded by first and second extremal planes (PS, PR). The method includes processing data from a device (), by: (a) modeling at least two basic non-axisymmetric surfaces (Sk, SI, SE) making up the surface, each of the basic surfaces (Sk, SI, SE) extending between both extremal planes (PS, PR) of the portion (S); (b) constructing at least one connection curve (CR) tangential to the first and second surfaces; (c) locally modifying the first and second basic surfaces (Sk, SI, SE) to keep to the connection curve (CR) near a discontinuity; and (d) restoring, at least part of the obtained surface ().

Method for modeling a non-axisymmetric surface

A compressor for a turbine engine, including: a casing, at least one compressor stage including an impeller having stationary blades and an impeller having moving blades positioned downstream of the stationary blade impeller, and cavities in a thickness of the casing that are disposed along a circumference of the casing opposite the moving blades. The cavities, which are elongate and extend along a main direction of orientation, are closed upstream and downstream by upstream and downstream faces respectively, and an upstream border and a downstream border are formed at the intersections between same and the casing. The cavities are offset in relation to the moving blades to overlap the moving blade impeller in the upstream portion, thereby covering the upstream end thereof. The downstream border of the cavities is oriented parallel to the chord at the head of the moving blade.

Compressor casing comprising cavities with optimised setting

A turbomachine element including an airfoil set including a plurality of airfoils that are offset from one another in a lateral direction, and upstream from at least one end of each airfoil, a group of a plurality of vortex generator devices that are mutually offset both laterally and axially.

Turbomachine element

A one-block bladed disk includes blades, a leading edges of which has sweep and dihedral angles, both strongly variable and increasingly large upon approaching a connection to a hub to improve mechanical strength of the whole and obtain good distribution of gas flow over the height of the blade.

One-block bladed disk provided with blades with adapted foot profile

A turbine engine blade, including an airfoil which extends radially between a blade root and an airfoil tip, axially between a leading edge and a trailing edge, and tangentially between a pressure side and a suction side, the profile of the blade having a series of basic profiles, in a form of a vane section, stacked on one another along a stacking line connecting the center of gravity of all the vane sections. The projection of the stacking line of the airfoil on at least one plane extending radially from the blade root includes a double tangential inversion of the direction of the curvature thereof, located in the last thirty percent of the height of the airfoil, the projection plane being positioned substantially perpendicular to the chord of the blade.

Turbine engine blade having improved stacking law

Growing community of inventors

Maisons Alfort, France

Vincent Perrot