Safran Aircraft Engines

Aurélien Mazzella

Damien Joseph Cellier

Laurent Soulat

Jean Bertucchi

Ghislain Maxime Romuald Madiot

Irwin Pierre Robert Kernemp

Irwin Kernemp

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

A part or an assembly of parts of a splitter stage of a turbofan, including a plurality of obstacles including at least one a blade and at least one arm, and a platform from which the obstacles extend, wherein the arm is defined by a skeleton angle having a trailing value on the trailing edge of between 3&#xb0; and 15&#xb0;.

Dimensioning of the skeleton angle of the trailing edge of the arms crossing the by-pass flow of a turbofan

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MOISSY-CRAMAYEL, France

Aurélien Mazzella