Safran Aircraft Engines

Nicolas Marc Florent

Francois Robert Bellabal

Marc Patrick Tesniere

Mathieu Ange Poisson

Bruno Marc-Etienne Loisel

Marion France Chambre

Carine Thuy-Huong Pragassam

Geoffroy Marie Gerard Nicq

A rotor blade for a rotor disk of a turbine of an aeronautical turbomachine includes, in a radial direction from inside to outside, a blade foot root, a support, a platform and a rotor vane, where the root is connected to the support by a neck. The neck has a curvilinear profile defining, in a section in a plane perpendicular to the radial direction, a curved shape. The neck section overlaps at least 75% of the section of the rotor vane, as a projection of the sections of the neck and of the rotor vane in a plane perpendicular to the radial direction, where the section of the rotor vane joins with the platform.

Turbine rotor disk blade having a foot of curvilinear shape

An aircraft propulsion assembly includes: a gas generator coupled by a coupling mechanism to a thrust generator having a structural torque transmission gearbox, and a rigid cradle rigidly supporting the thrust generator in a first suspension plane and the gas generator in distinct second and third suspension planes, the cradle being for securing to a structural element of the aircraft via a vibration-filtering flexible connection.

Aircraft propulsion assembly with a filtered cradle

The ball joint device () for suspending a turbine engine from a strut or suspending equipment on the body of a turbine engine. Said device comprises a first member (), one end of which carries a ball joint () and is interposed between the two lugs () of a second member (), the ball joint comprising a bore () for the passage of a shaft (), the ends of which shaft pass through openings () in the lugs. A first () of the lugs comprises or carries first means for axially holding the shaft on the side opposite the ball joint, which means comprise a cover ('), and a second () of the lugs comprises or carries second means () for axially holding the shaft on the side opposite the ball joint. The device further comprises a resilient member (&#x2032;) that is deformable under compression and is held by the cover, said resilient member (&#x2032;) being designed to bias a support element (), through which the shaft passes and which is in axial abutment on the ball joint (), axially in a direction away from the cover.

Ball joint device for a turbine engine

A method of manufacturing an assembly including a first structure which is arranged to be rigidly connected to a housing of a turbojet engine; a second annular structure surrounding the first structure; and a hyperstatic trellis of connecting rods which maintains the first structure relative to the second structure, is provided. The method includes mounting the connecting rods of the hyperstatic trellis between the structures; and pre-stressing at least one of the connecting rods to a pre-determined level, which is carried out before the mounting thereof between the structures.

Method of producing suspension for a structure in a turbojet engine using a hyperstatic trellis with pre-stressed link elements

A suspension structure for suspending a turboprop including two unducted propellers from a structural element of an aircraft, the structure including a suspension frame for fastening to a structural element of the aircraft and including a main beam extending parallel to a longitudinal axis of the turboprop, the suspension frame being fastened to an air intake structure of the turboprop by an attachment frame.

Suspension structure for suspending a turboprop having two unducted propellers from a structural element of an aircraft with rigid fastening of the air intake structure

Growing community of inventors

Paris, France

Nicolas Marc Florent