Safran Aircraft Engines

Snecma

Benoit Argemiro Matthieu Debray

Mario Cesar De Sousa

Frederic Noel

Gregory Ghosarossian-Prillieux

Nicolas Pommier

Guillaume Sevi

Mathieu Ange Poisson

Baghdad Achbari

Dominique Michel Fouquet

Paul Moreau

Jeremie Sylvain Bonnaudet

Nicolas Rene Bruno Michelidakis

Sylvain Pichon

The invention relates to an assembly comprising: a turbomachine exhaust case () that includes an external sleeve and an internal sleeve inside the former, both sleeves extending concentrically about a turbomachine axis, and also includes a plurality of arms extending radially between the sleeves; and an annular part () that is centered about the axis, is mounted on one sleeve of the exhaust case, and is located downstream of the exhaust case in the direction in which the air flows inside the turbomachine; the assembly is characterized in that the annular part and the sleeve of the exhaust case on which the annular part is mounted each have a circumferential thread (), said threads cooperating with each other in order to allow the annular part to be screwed onto the sleeve of the exhaust case.

Assembly comprising an exhaust case and a downstream rotationally symmetrical part

An exhaust casing of a turbine engine for an aircraft which extends along an axis and includes: a central hub, an annular outer shroud and arms which connect the central hub to the outer shroud, at least one yoke for attaching the exhaust casing to the turbine engine being located on the outer shroud and forming at least one lug extending in a plane perpendicular to the axis and protruding toward the exterior of the outer shroud. The outer shroud includes ribs which form a constant excess of the outer shroud, which are located on either side of the at least one lug of the at least one yoke, and which are aligned with the at least one lug.

Reinforced exhaust casing and manufacturing method

The invention relates to a turbomachine casing () comprising: a hub (), an outer shroud (), and yokes () projecting from the outer shroud (), for attaching the housing (), characterized in that it comprises at least one stiffener () extending between pairs of yokes () facing each other, and comprising a central part () and side arms () projecting from the central part ().

Turbomachine casing comprising a cavity-free shroud and yokes reinforced by stiffeners

The invention relates to a fairing () for a mixer () of a nozzle () of a dual-flow turbomachine (), said mixer being of an overall annular shape and extending along a longitudinal axis () of the turbomachine, said mixer comprising an upstream part () provided with a flange () extending radially toward the outside of the mixer, intended to be fastened to an exhaust casing () of the turbomachine, and a downstream part () forming a flow mixing area, the fairing () being of an overall annular shape and configured to extend around the upstream part () of the mixer () and to be attached to the flange () of said upstream part (), the fairing being without means for fastening to the downstream part () of the mixer (), in such a way as to connect the fairing () to the mixer () at a distance from the flow mixing area.

Fairing for a mixer of a nozzle of a dual-flow turbomachine

The invention relates to a turbomachine bearing support () supporting at least one bearing and extending according to a longitudinal principal axis of the turbomachine and comprising:

Bearing support having a geometry for easier evacuation of casting cores

A bypass engine bearing holder () that holds an upstream bearing () and defines, with said upstream bearing, an oil chamber () and an air chamber (), comprising a frusto-conical portion () defining an upstream bearing chamber () and a downstream inner chamber (), and includes an outer collar () connected, by a weld (), to a flange () that extends outward from the frusto-conical portion (). The outer collar () has a sealable gimlet () engaging with the upstream bearing () such as to seal the oil chamber (). The bearing holder () includes a plurality of oil recovery ducts () leading to the downstream inner chamber () and to the upstream bearing chamber (). The oil recovery ducts () lead to the upstream bearing chamber (), downstream from the weld () of the outer collar () on the flange (), the weld () of the outer collar () being axisymmetric.

Bearing holder having a axisymmetric sealable gimlet

An assembly including an exhaust casing and an exhaust cone for a gas turbine engine, each including an axial annular flange, the two flanges being inserted into one another, one being radially external and the other radially internal, and held together by a mechanical attachment, and the assembly further including a guide by which, during operation of assembling the annular flanges to each other, the exhaust cone is in a predetermined angular position relative to the exhaust casing.

Gas turbine engine comprising an exhaust cone attached to the exhaust casing

The invention relates to a turbine engine exhaust casing (), characterized in that it comprises: The invention also relates to a turbine engine comprising such an exhaust casing.

Growing community of inventors

Moissy-Cramayel, France

Benoit Argemiro Matthieu Debray