Safran Aircraft Engines

Office National D'etudes Et De Recherches Aerospatiales

Centre National De La Recherche Scientifique

Université Claude Bernard Lyon I

Ecole Centrale De Lyon

Fernando Gea Aguilera

Vincent Joudon

Mathieu Simon Paul Gruber

Raphaël Barrier

Matthieu Fiack

Cyril Polacsek

Hélène Dominique Jeanne Posson

Georges Jean Xavier Riou

Josselin David Florian Regnard

Norman Bruno André Jodet

Anthony Binder

Eva Julie Lebeault

Jean-Michel Daniel Paul Boiteux

Paul Clément Guillaume Laffay

Marc Cornelius Jacob

Stéphane Moreau

Adrien Clément Marcel Dubois

Ludovic Mathieu René Wiart

An aeronautical thruster having a longitudinal axis and having a hub and at least two annular rows of unducted blades including an upstream annular row and a downstream annular row which are spaced apart from one another along the longitudinal axis, the upstream annular row being rotatable around the longitudinal axis, and the downstream annular row comprising a series of blades including a first blade and a second blade each extending in a radial direction from the hub to define a radial dimension between the hub and a radially outer end of the corresponding blade, wherein the radial dimension of the first blade is greater than the radial dimension of the second blade.

Aeronautical thruster

An acoustic treatment panel including acoustic absorption cells each comprising a bottom wall, a porous inlet wall, an enclosure extending in an axial direction between the bottom wall and the inlet wall, and a first acoustic horn extending inside the enclosure between a first opening and a second opening that is smaller than said first opening, the first opening facing said inlet wall. Each cell comprises a second horn extending inside the enclosure in the first axial direction between a first opening of the second horn and a second opening of the second horn that is smaller than said first opening.

Reduced bulk acoustic treatment panel for a turbojet engine

An airflow profile structure having a leading and/or trailing edge profiled with a serrated profile having a succession of teeth and depressions. Along the leading and/or trailing edge, from a first location to a second location, the teeth of the serrated profile are individually inclined towards the second location.

Turbine engine with a flow splitter having a profile with inclined serrations

An acoustic treatment grid intended to be mounted inside or at the outlet of a duct of a bleed valve of a turbomachine of an aircraft intended to convey a gas flow, the grid comprising a perforated plate and circular orifices traversing the perforated plate along a first direction, the orifices having a diameter and a geometrical center. Each orifice is separated from an adjacent orifice by a space, the length of which is equal to the product of the diameter of said orifice and a spacing coefficient of a value between 1.1 and 6.

Optimised discharge line grid and optimized discharge valve

An airflow profiled structure having a profiled leading edge. The profiled leading edge having, along a leading edge line, a serrated profile line with a succession of teeth and depressions. The airflow profiled structure also includes a porous acoustically absorbent region located towards the bottom of the depressions.

Profiled structure and associated turbomachine

A turbomachine includes a rotor and a stator, the stator having a plurality of profiled structures, each profiled structure being elongated in a direction of elongation in which the profiled structure has a length exposed to an airflow, and having a leading edge and/or a trailing edge, at least one of which is profiled and has, in said direction of elongation, serrations defined by a succession of peaks and troughs and having a geometric pattern transformed, over at least a part of said length exposed to the airflow, by successive scaling, via multiplicative factors, in the direction of elongation and/or transverse to the direction of elongation. The geometric pattern, as defined with reference to a radial distribution of the integral scale of the turbulence, evolves in a non-periodic manner.

Profiled structure for an aircraft or turbomachine for an aircraft

A profiled structure for an aircraft or turbomachine is elongated in a direction in which the structure has a length exposed to an airflow and includes serrations defined by successive teeth and depressions. The serrations may be transverse to a leading edge and/or a trailing edge of the profiled structure and in the direction of elongation. Along the profiled leading edge and/or profiled trailing edge, the successive teeth and depressions may extend only over a part of the length exposed to the flow. The amplitude and/or spacing of the teeth may vary monotonically except for the few teeth nearest each end of the part, with a remaining part of the length being smooth.

Profiled structure for an aircraft or turbomachine

An airflow profile structure having a leading and/or trailing edge profiled with a serrated profile. The serrated profile has a succession of teeth and depressions, characterized in that, along the leading and/or trailing edge, from a first location to a second location, the teeth of the serrated profile are individually inclined towards the second location.

The invention relates to a profiled structure elongated in a direction in which the structure has a length exposed to an airflow and transversely to which the structure has a leading edge and/or a trailing edge, at least one of which is profiled and has, along said direction of elongation, geometric serration patterns defined by a succession of peaks and troughs. Along the profiled leading edge and/or trailing edge, the serration patterns have a geometric pattern that is repeated in the direction of elongation, the shape of which is stretched and/or contracted transversely to the direction of elongation and/or in the direction of elongation.

A front fan turbomachine includes an annular separating wall having a slat for separating an air flow between a primary flow and a secondary flow, the slat having a leading edge; inlet guide vanes (IGV) for guiding the primary flow and outlet guide vanes (OGV) blades for guiding the secondary flow. The leading edge of the slat has a serrated profile having a succession of teeth and depressions.

Growing community of inventors

Moissy-Cramayel, France

Fernando Gea Aguilera