Snecma

Safran Aircraft Engines

Snecma Moteurs

Mario Cesar De Sousa

Didier Hippolyte Hernandez

Frederic Noel

Benoit Argemiro Matthieu Debray

Gregory Ghosarossian-Prillieux

Nicolas Pommier

Jacques Marcel Arthur Bunel

Eric Conete

Caroline Aumont

Patrice Andre Commaret

Florian Andre Francois Bessagnet

Florian Andre Bessagnet

Thomas Olivier Marie Noel

Guillaume Sevi

Baghdad Achbari

Benoit Debray

Thomas Olivier Noel

Denis Jean Maurice Sandelis

Christophe Pieussergues

Olivier Renon

Georges Habarou

Luc Henri Claude Daguenet

Mathieu Ange Poisson

Gilles Ulryck

Patrice André Commaret

Laurent Pierre Elysee Gaston Marnas

Stephane Henri Guy Touchaud

Laurent Pierre Marnas

Dominique Michel Fouquet

Nicolas Christian Raymond Leblond

Paul Moreau

Grégory Ghosarossian-Prillieux

Laurent Marnas

Philippe Guerville

Sylvain Pichon

Morgan Robin

Frédéric Noel

Thomas Noël

Florian Bessagnet

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

A device for mounting a spark plug in a combustion chamber of a gas turbine engine includes a chimney including a collar extending radially inwards, a washer fastened on an axial end of the chimney so as to project towards the inside of the chimney, and a bushing forming a spark plug guide and including an inner collar and an outer collar that are axially spaced apart from each other by a cylindrical portion. Each collar extends radially outwards. The bushing is floatingly mounted inside the chimney with its collars axially positioned between the collar of the chimney and the washer. The inner collar comes in operation to bear against the collar of the chimney. The outer collar presents an outside diameter (d) greater than the inside diameter (d) of the washer.

Device for mounting a spark plug in a combustion engine of a gas turbine engine

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.

Exhaust casing comprising a fluid discharge device and turbine engine

A method for assembling a nozzle and an exhaust case of a turbomachine is disclosed. The exhaust case includes a hub and an outer ferrule connected to each other by a plurality of arms. The nozzle is attached to the outer ferrule of the exhaust case substantially at the trailing edges of the arms.

Method for assembling a nozzle and an exhaust case of a turbomachine

A turbine engine combustion chamber including at least one ignition sparkplug carried by an outer casing and extending through a guide mechanism carried by a wall forming a body of revolution of the chamber. The guide mechanism includes a tubular guide having the sparkplug passing axially therethrough, which guide is mounted with axial and transverse clearance on a chimney fastened to the wall of the chamber and opening out therein. The guide includes an annular collar engaged with clearance in an internal annular groove of the chimney. The annular collar is urged to press against a wall of the groove by a resilient member mounted in the groove.

Guiding a sparkplug in a turbine engine combustion chamber

A combustion chamber of a gas turbine engine including a wall, a well secured to the wall, the well forming a recess for a spark plug leading into the combustion chamber, and a spark-plug guide mounted on the well to be transversally mobile relative to the axis of the well, the spark-plug guide including a cylindrical wall portion for guiding and supporting the spark plug and a seal ring mounted such as to engage slidably with a bearing surface of the well. In the combustion chamber the spark-plug guide includes a cooling chamber having openings for supplying cooling air to the chamber.

Combustion chamber having a ventilated spark plug

A turbomachine combustion chamber has primary and dilution air inlet orifices formed by die stamping to have edges that project into the inside of the combustion chamber, and stress relaxation and/or reduction means in the edges or in the vicinity of the edges of said orifices, said means comprising, for each orifice, one, two, or three slots formed in the edge or around a fraction of the edge of said orifice.

Combustion chamber in a turbomachine

An annular fairing for covering the annular chamber end wall of a turbomachine combustion chamber, and in particular of an airplane turbojet. The fairing presents openings for passing fuel injectors that are supported by the chamber end wall. The fairing is subdivided into a plurality of adjacent sectors, each sector presenting inner and outer fastener edges capable of being fastened on either side of said chamber end wall. Each sector includes a lip on one of its side edges, which lip is connected to the remainder of the sector by a step, said lip being designed to over the side edge of the adjacent sector.

Growing community of inventors

Cesson, France

Mario Cesar De Sousa