Safran Aircraft Engines

Laurent Soulat

Eva Julie Lebeault

Kevin Morgane Lemarchand

Gilles Alain Charier

Nathalie Nowakowski

Tewfik Boudebiza

Anthony Binder

Augustin Marc Michel Curlier

Pierre-Alain Jean Philippe Reigner

Adrien Pierre Jean Pertat

Norman Bruno André Jodet

Guillaume Martin

Michael Franck Antoine Schvallinger

Damien Bernard Emeric Guegan

Aurélien Mazzella

Antoine Claude Baudouin Raoul Marie Secondat De Montesquieu

Raul Martinez Luque

Aircraft turbine engine including two coaxial annular walls defining between them a main annular duct for the flow of a primary airflow; —a rotor blading extending radially through the first duct; —an annular separator arranged downstream of the rotor blading and configured to divide the primary airflow into two to form the secondary air flows; —first variable guide vanes which are distributed around the shaft and each comprise a leading edge which is located upstream of the separator and trailing edges which are located in the secondary airflows; —and fixed guide vanes which are distributed around the shaft in the external airflow and downstream of the first variable vanes.

Aircraft turbomachine

The invention relates to a bypass turbomachine () for an aircraft, comprising a gas generator () and a ducted fan () comprising variable pitch blades () configured to take a reverse thrust position driving a reverse flow () of air within a secondary duct (), the gas generator () being connected to a fan casing () by a stator blade assembly () that passes through the secondary duct, first openings () for letting in air from the reverse flow being located on an outer casing () at least partially internally delimiting the outer duct, and second openings () for letting said air out being located on an inner casing () at least partially externally delimiting an inner duct (). The first openings are located within a plane that is perpendicular to a longitudinal axis (C) of the turbomachine and passes substantially through the middle of the blade assembly.

Bypass turbomachine for an aircraft

An aircraft including at least one unducted turbine engine for the propulsion of the aircraft. The turbine engine comprising: a rotor and a stator comprising a plurality of stator blades extending radially with respect to the longitudinal axis, each stator blade being defined, in a plane transverse to the longitudinal axis, by an angular position; and at least one aerodynamic obstruction positioned close to the turbine engine. The stator of the turbine engine comprises stator blades having a first chord, referred to as conventional blades, and at least one stator blade having a second chord larger than the first chord, referred to as the elongate blade, said at least one elongate blade being positioned in an interference angular range defined opposite the aerodynamic obstacle, so as to increase the straightening of the airflow from the rotor in the interference angular range.

Unducted turbine engine comprising stator blades having different chords

The invention relates to a portion of a turbofan () extending about a longitudinal axis (A), comprising: —an outer wall (Pe) and an inner wall (Pi), defining a secondary duct portion (Vs), —a cascade of guide vanes (OGV), each guide vane extending within the secondary duct portion (Vs) between the outer wall (Pe) and the inner wall (Pi), wherein, in the region of the cascade of guide vanes (OGV), and in a plane orthogonal to the longitudinal axis (A), the distance from the outer wall (Pe) to the longitudinal axis (A) along a first axis (Xi) orthogonal to the longitudinal axis (A) is greater than the distance from the outer wall (Pi) to the longitudinal axis (A) along a second axis (X) orthogonal to the longitudinal axis (A) and to the first axis (X).

Non-axisymmetric secondary duct portion

The present invention concerns a turbomachine hub, intended to be mounted so as to be able to rotate about a longitudinal axis (X) of the turbomachine, the hub comprising a main body () arranged around the longitudinal axis (X), an outer surface of which has a plurality of recesses; a plurality of platforms () comprising an outer surface delimited by a circular outer edge of radius r, each platform () being arranged in a corresponding recess of the plurality of recesses of the main body (), and intended to receive a variable pitch blade (), the pitch of which is variable according to a pitch change axis (Z), the platform () being centred and able to rotate about the pitch change axis (Z); characterised in that, for each platform, at least one part of the outer surface of the platform () and the main body () of the hub comprises a curvature defined by a same sphere portion of radius R and centre C, the at least one part being situated at the outer edge of the platform (), in a junction zone between the platform () and the main body of the hub (), the centre C of the sphere being situated on the pitch change axis (Z) outside a hemispherical zone delimited between the longitudinal axis (X) and the outer surface of the platform ().

Turbomachine polyspherical hub for variable pitch blades

A turbomachine compressor module comprising an annular array of struts provided with pivotable flaps. The struts can define inter-strut spaces between two circumferentially adjacent struts, and variably oriented stator vanes are disposed at least partially in the inter-strut spaces. Also, a turbomachine having such a module and a row of rotor blades directly downstream of the module.

Compressor module for turbomachine

A stator wheel of a turbomachine configured to be mounted in an aircraft, the turbomachine extending along an axis, the turbomachine comprising a core flow stream for a first air flow and a bypass flow stream for a second air flow, wherein the stator wheel is configured to be mounted along the axis, the stator wheel comprising a plurality of vanes extending radially from the axis, each vane comprising a leading edge and a trailing edge that together define a chord in a plane of revolution defined relative to the axis, at least two vanes having different chords at a same radial distance, the difference in chords between two adjacent vanes being less than or equal to 25%.

Stator wheel of a turbomachine comprising vanes having different chords

A flow-straightener vane of a bypass turbomachine includes a plurality of vane sections stacked radially with respect to a longitudinal axis (X) along a stacking line (L) between a root end and a tip end. Each vane section has a pressure-face surface and a suction-face surface extending axially between an upstream leading edge and a downstream trailing edge. Between the leading and trailing edges of each vane section there is formed a profile chord (CA) the length of which is substantially constant between the tip end and the root end, and the stacking line (L) exhibits a curvature in a plane passing more or less through the axis (X) and through the stacking line (L), situated in the vicinity of the tip end and oriented from downstream towards upstream.

Turbomachine fan flow-straightener vane, turbomachine assembly comprising such a vane and turbomachine equipped with said vane or said assembly

The present invention relates to a powerplant of an aircraft including at least one twin-spool gas generator of longitudinal axis (XX), at least one main fan arranged upstream of the gas generator on the longitudinal axis (XX) and driven in rotation by the gas generator, the main fan being shrouded with a main fan housing; and at least one auxiliary fan with axis (XY, XY') offset relative to the longitudinal axis (XX) and driven by the gas generator, the auxiliary fan being shrouded with an auxiliary fan housing, the gas generator including at least one low-pressure compressor and a low-pressure turbine connected by a low-pressure shaft, the low-pressure turbine driving in rotation the main fan and the auxiliary fan via at least one power transmission system including a differential gear system incorporating a bevel gear.

Aircraft propulsion assembly equipped with a main fan and with a least one offset fan

An aircraft propulsion assembly comprising at least a main turbine mounted along a longitudinal axis, at least one main fan arranged upstream of the main turbine along the longitudinal axis and driven in rotation by the said main turbine, the said main fan being ducted by a main fan casing, an auxiliary turbine mounted along the longitudinal axis, the auxiliary turbine being independent of the main turbine, an auxiliary fan of axis offset with respect to the longitudinal axis and driven by the auxiliary turbine, the auxiliary fan being ducted by an auxiliary fan casing, the main casing being separate and distinct from the auxiliary casing so as respectively to generate a main secondary flow and an auxiliary secondary flow which remain independent of one another until they are discharged into the atmosphere.

Growing community of inventors

Moissy-Cramayel, France

Laurent Soulat