Snecma

Safran Aircraft Engines

Snecma Société Anonyme

Nicolas Pommier

Mario Cesar De Sousa

Frederic Noel

Gregory Ghosarossian-Prillieux

Olivier Renon

Benoit Argemiro Matthieu Debray

Christian Rene Schnell

Mathieu Delalandre

Mathieu Bissardon

Valentine Bader

Stephane Nicolas Piron

Alain Dominique Gendraud

Mathieu Dakowski

Alain Pierre Page

Alain Rene Cayre

Michel Andre Albert Desaulty

Mario César De Sousa

Mathieu Ange Poisson

Claire Dorin

Stephane Henri Guy Touchaud

Laurent Pierre Elysee Gaston Marnas

Baghdad Achbari

Benoit Argémiro Matthieu Debray

Grégory Ghosarossian-Prillieux

Laurent Marnas

Benoit Debray

Jacques Andre Michel Roche

Sylvain Pichon

Jacques-A Roche

Frédéric Noel

Michel Desaulty

Laurent Pierre Elysée Gaston Marnas

A method for manufacturing a turbine engine part in which a first rough casting element includes a first face and a second face opposite to each other is assembled by the second face on an orifice which has a second element of the part. The method includes machining a through-cavity in the first element which opens at the first face and from the second face of the first element and machining the first face of the first element so as to form an area suitable for ensuring the attachment of a conduit on the first element. The machining of the cavity and of the first face is achieved by using a machining reference frame based on the second element.

Method for manufacturing a turbine engine part and the thereby produced part

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

A turbomachine exhaust case having an annular groove perforated with an orifice in which there is mounted a drain, which is formed by a tubular cylindrical body, for discharging liquids retained in this groove is disclosed. The drain includes a skirt, formed at one end of the cylindrical body, for fastening the drain by crimping in the orifice in the groove of the case.

Turbomachine exhaust case drain

A turbine stage in a turbine engine, including a wheel with blades rotating inside a sealing ring held by a casing of the turbine, and an annular thermal protection sheet mounted between the casing and the sealing ring is disclosed. The annular thermal protection sheet is formed by a plurality of curved plates mounted end-to-end and attached by pins to the casing.

Control of clearance at blade tips in a high-pressure turbine of a turbine engine

A turbomachine exhaust casing with connection roots between the structural arms of the casing and the annular endplates of the hub of the casing, each of said the roots having a profile that is optimized so as to reduce the level of stress in the connection portions, and thus increase the lifetime of the exhaust casing.

Exhaust casing for a turbomachine

An exhaust casing hub includes a hub center, and an upstream flange and a downstream flange arranged on either side of the hub center. Each flange is terminated by a rim. A plurality of cuffs are arranged on the hub center so as to form an angle from the tangent toward the radial direction of 10&#xb0; to 80&#xb0; , preferably 15&#xb0; to 75&#xb0;. At least one rib is formed at the base of each cuff below a critical stress region in the cuff. The rib is joined to the downstream flange by a downstream end and to the upstream flange by an upstream end.

Exhaust casing hub comprising stress-distributing ribs

The invention relates to a device for injecting a mixture of air and fuel into a combustion chamber of a turbomachine where the supply of air is improved. The invention relates more particularly to a new type of sliding bushing.

Device for injecting a mixture of air and fuel, combustion chamber and turbomachine both equipped with such a device

A double flow turbo-jet engine includes a re-heating channel of the primary flow and an ejection nozzle, the secondary flow emerging at least partially in the primary flow upstream of the re-heating channel, the re-heating channel including a burner ring, including a flame holder gutter in the form of a ring portion whereof the upstream section is situated in the secondary flow, receiving a fuel manifold and a protective tubular screen of the manifold. The gutter includes an upstream recess linked with the secondary flow, and the screen includes, on its upstream section, at least one ventilation orifice of the space situated between the screen and the manifold.

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Brunoy, France

Nicolas Pommier