Snecma

Safran Aircraft Engines

L'air Liquide, Soci&#xe9;t&#xe9; Anonyme Pour L'etude Et L'exploitation Des Proc&#xe9;d&#xe9;s Georges Claude

Frederic Noel

Mario Cesar De Sousa

Benoit Argemiro Matthieu Debray

Gregory Ghosarossian-Prillieux

Olivier Renon

Panayotis Cocolios

Nicolas Pommier

Mathieu Ange Poisson

Baghdad Achbari

Dominique Michel Fouquet

Benoit Debray

Paul Moreau

Sylvain Pichon

Edgar Sanders

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

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 present invention relates to a turbine engine casing (), in particular a turbojet exhaust casing, including at least one hoop () and at least one flange () at least partially defining one end of said hoop (), and at least one cap () positioned at least partially on the outer surface of the hoop (), said cap () including a bore () capable of receiving an element for fastening the casing () to a bracket, the flange including an access cut-out () substantially coaxial with the bore () of said at least one cap (), said access cut-out () enabling access to the bore (), the access cut-out () being provided at a release cut-out () which is wider than the flange () and constitutes a recess on said release cut-out (). The invention also relates to a turbine engine including a casing () and to a method for machining the latter according to the present invention.

Turbine engine casing having a cut-out flange

An exhaust housing hub of a turbomachine, including a connecting wall and an inner channel wall, the connecting wall connecting the inner channel wall to inner attachment flanges, wherein a radial section of the connecting wall is curved and can be formed, as required, as a single component with the inner channel wall, the hub also including a series of ribs extending radially between the connecting wall and the inner channel wall.

Exhaust housing hub for a 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

Frederic Noel