Snecma

Safran Aero Boosters Sa

Cenaero

Safran Aircraft Engines

Vasiliki Iliopoulou

Vincent Paul Gabriel Perrot

Eric Jacques Boston

Thierry Jean-Jacques Obrecht

Agnes Pesteil

Alexandre Franck Arnaud Chartoire

Lieven Baert

Ingrid Lepot

Vincent Paul Perrot

Alexandre Franck Chartoire

Agnès Pesteil

The present disclosure provides a subsonic rotor and/or stator blade profile of an axial turbomachine compressor, such as a turbojet. The blade comprises a leading edge with an S-shaped lateral profile in its mid-plane. Specifically, the profile includes, from its inner end to the outer end, a first convex portion including the foremost point of the blade, and a second concave portion including the rearmost area of the blade. This profile enables the fluid flow between 20% and 80% of the blade's length to be redistributed. This so-called 'sweep' profile increases the performance of the stage with such blades because it reduces blade tip vortex losses as well as secondary losses.

Blade with an S-shaped profile for an axial turbomachine compressor

A turbine engine compressor including a casing having its inside wall defining an aerodynamic reference surface for a gas-passing passage and in which a rotor wheel having radial blades is mounted. A circumferential trench is formed in the inside wall of the casing. Its shape is defined from upstream to downstream by three surfaces, respectively an upstream surface, a middle surface, and a downstream surface, which surfaces are substantially conical. The upstream surface extends upstream from the leading edges of the blades. The middle surface is substantially parallel to the aerodynamic reference surface. The downstream surface extends downstream at least as far as the trailing edges of the blades. The junction between the middle and downstream surfaces is in a range of 30% to 80% or 50% to 65% of the axial length of the blades starting from their leading edges.

Compressor and a turbine engine with optimized efficiency

A rotor of a turbomachine compressor, including a bladed rotor disk fitted at its radially external end with a wall forming the inner end of an annual flow channel of a primary gas flow, and formed from multiple angular sectors, each of which is delimited between two blades of the disk which are consecutive in a circumferential direction and includes a bulging portion which is convex in the axial direction and in the circumferential direction, together with, upstream from the bulging portion, a troughed portion which is concave in the axial direction and in the circumferential direction and which has a base which is roughly punctiform.

Rotor of a turbomachine compressor, with an optimised inner end wall

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Ixelles, Belgium

Vasiliki Iliopoulou