Safran Aircraft Engines

Snecma

Benjamin Lukowski

Romain Nicolas Lagarde

Matthieu Jean Luc Vollebregt

Philippe Jacques Pierre Fessou

Julien Antoine Henri Jean Szydlowski

Jean-Frederic Pierre Joseph Bruhat

Ghislain Maxime Romuald Madiot

Philippe Jacques Fessou

Esteban Bernardos-Chamagne

Matthieu Jean Vollebregt

Jacques Pierre Philippe

Jean-Frédéric Pierre Joseph Bruhat

The invention relates to an intermediate housing hub () comprising a discharge stream conduit () having a given length (L), and discharge fins () extending in the discharge stream conduit () and having a given chord length (L), the chord length (L) of at least one of the discharge fins () being at least equal to 50% of the length of conduit (L).

Intermediate housing hub comprising discharge flow guiding channels formed by the discharge fins

A hub of an intermediate casing for a dual-flow turbine engine includes a discharge flow duct extending between an inner shroud and an outer shroud of the hub, the discharge flow duct leading into the secondary flow space through an outlet opening formed in the outer shroud, the outlet opening included in a discharge plane substantially tangential to the outer shroud; and discharge fins including an upstream fin and a downstream fin. An upstream acute angle between the discharge plane and the skeleton line of the upstream fin is smaller than a downstream acute angle between the discharge plane and the skeleton line of the downstream fin.

Discharge flow duct of a turbine engine comprising a VBV grating with variable setting

The present invention relates to a turbomachine component () or collection of components comprising at least a first and a second blade (I,E) and a platform () from which the blades (I,E) extend, characterized in that the platform () has a non-axisymmetric surface (S) bounded by a first and a second end plane (PS, PR) and defined by at least two class C construction curves each one representing the value of a radius of said surface (S) as a function of a position between the pressure face of the first blade (I) and the suction face of the second blade (E) in a plane substantially parallel to the end planes (PS, PR), these including at least one upstream curve and one downstream curve; each construction curve being defined by at least one pressure face control end point and one suction face control end point such that: &#x2014;the tangent to the downstream curve at the suction face control end pointis inclined by at most 5&#xb0;; &#x2014;any other tangent to a construction curve at a control end point is inclined by at least 5&#xb0;.

Turbomachine component with non-axisymmetric surface

A hub of an intermediate casing for an aircraft turbojet engine, including an inner shell intended to define a primary flow space of a primary gas stream into a turbojet engine, and at least one intermediate space, the inner shell being provided with at least one primary port and at least one movable door forming a primary air passage conduit, the door being capable of collecting, from the primary port, air flowing in the primary gas space and of sending the air collected in this way, via the intermediate space, towards a secondary air passage conduit. The primary conduit has an inner surface including, from upstream to downstream, a converging upstream part, then a nonconverging downstream part, in which the downstream part includes two portions of downstream side surface, and in which the upstream portion further includes two portions of upstream side surface.

Hub of an intermediate casing for an aircraft turbojet engine comprising doors with contoured geometry

Growing community of inventors

Moissy-Cramayel, France

Benjamin Lukowski