Snecma

Safran Aircraft Engines

Laurent Bernard Cameriano

Romain Nicolas Lunel

Denis Jean Maurice Sandelis

Sylvain Duval

Pierre-François Simon Paul Pireyre

Brice Le Pannerer

Christophe Pieussergues

Stephane Pierre Guillaume Blanchard

Mathieu Dakowski

Alain Pierre Page

Caroline Jacqueline Denise Berdou

Michel Pierre Cazalens

Jeremy Giordan

Thierry Cortes

Jérémy Giordan

Nicolas Pierre-Marie Girard

Aurelien Lionel Tedesco

Eric Masson

Herve Bernard Plisson

Caroline Jacqueline Berdou

Stephane Pierre Blanchard

Aurélien Lionel Tedesco

Hervé Bernard Plisson

The invention relates to an annular combustion chamber in a turbine engine, comprising two coaxial walls of revolution, one an internal wall () and the other an external wall (), between which emerge fuel injectors () each engaged in centring means () which are moveable in the radial direction in support means (), the chamber also comprising means () of axial retention in the upstream direction of the centring means. According to the invention, the means of axial retention in the upstream direction are removably fixed to at least one of the internal () or external () walls of revolution.

Combustion chamber in a turbine engine

The invention relates to a device for supporting and centring a fuel injector in a turbine engine combustion chamber, which includes means for centring a fuel injector along an axis, which are movable in a plane that is radial to the centring axis () in supporting means intended for being attached to the bottom of an annular chamber (). According to the invention, the centring means include at least two radially external tabs () each inserted respectively in a circumferential recess () of the supporting means, the device including circumferential abutment means () of the radial tabs () of the centring means in the circumferential recesses (), the circumferential abutment means being configured such as to enable a greater angular displacement of a first () one of the radial tabs in a first circumferential recess () relative to a second () one of the radial tabs in a second circumferential recess ().

Annular combustion chamber in a turbine engine

A measuring comb for temperature and/or pressure and/or chemical composition of the gases flowing at the outlet of a turbine engine flow path, in which the flow path extends around an axis of revolution of the flow path, is provided. The measuring comb includes: a comb body with an elongated shape, intended to face the outlet of the flow path, the comb body including at least one measuring opening arranged along an axis, the measuring opening being configured to tap gases flowing at the outlet of the flow path; and an adjusting system configured to adjust an angle between the axis of the at least one measuring opening and the axis of revolution, so as to allow orientation of the at least one measuring opening in the flow direction of the gases at the outlet of the flow path.

Measuring comb for measuring parameters of the gases exiting a turbomachine working section

A combustion chamber for a turbine engine such as an airplane turboprop or turbojet has inner and outer annular walls forming bodies of revolution that are connected together by an annular chamber end wall. The inner wall is constituted by a single thickness of material that presents thickness and/or nature varying along the longitudinal axis and/or the circumferential direction of said wall.

Combustion chamber for a turbine engine

A fuel injection device for an annular combustion chamber of a turbine engine, the device including a pilot circuit feeding an injector, a multipoint circuit feeding injection orifices formed in a front face of an annular chamber, and an annular ring mounted in the annular chamber and including fuel-passing orifices opening out into the injection orifices, each fuel-passing orifice formed in the annular ring including a zone of small section that is extended at least downstream or upstream by an orifice portion of increasing section.

Injection device for a turbine engine combustion chamber

A fuel injection system for an annular combustion chamber of a turbomachine including a support device for supporting and centering a fuel injector head; and a bowl arranged downstream from the support device and including at its downstream end an annular collar that extends radially outwards and that is cooled by air impacting against its upstream radial surface is disclosed. The upstream radial surface includes a device which disturbs the flow of cooling air and increases the heat exchange area between the air and the collar.

Fuel injection system for a combustion chamber of a turbomachine

A casing cover for enclosing a casing in a jet engine is disclosed. The casing cover includes two coaxial shells arranged one inside the other and radial envelopes which connect the two coaxial shells. Radial arms of the casing extend inside the radial envelopes. The cover is fastened at its downstream end to a first element of the casing and axially abuts at its upstream end on a second element of the casing. In a free state, an axial dimension of the cover of less than the axial distance of the casing between the point where the first element of the casing is fastened to the downstream end of the cover and the point where the second element of the casing axially abuts the upstream end of the cover such that the cover is tensioned axially when it is mounted on and fastened to the casing.

Casing cover in a jet engine

An exhaust cone of composite material. The exhaust cone is mounted to extend an adapter ring and it is held by an elastically deformable element that acts axially.

Exhaust cone for channeling a stream of gas downstream from a turbine

A structural turbine engine casing is disclosed. The casing includes a central hub, at least one intermediate shroud, and an external ring, which are concentric, the external ring and the intermediate shroud being connected via links, the intermediate shroud and the central hub being connected by a series of radially fastened hollow arms. The series of arms includes at least one main arm and at least one secondary arm, each main arm being arranged in the continuation of a link and having a mass which is greater than that of a secondary arm arranged at a distance from the links.

Structural turbine engine casing

A turbomachine combustion chamber includes an inner annular wall, an outer annular wall surrounding the inner wall so as to co-operate therewith to define an annular space forming a combustion area, a plurality of fuel injector systems including pilot injectors alternating circumferentially with full-throttle injectors, and at least one air admission opening out into the upstream end of the combustion area in a substantially longitudinal direction. The outer wall has a plurality of pilot cavities extending between the two longitudinal ends of the outer wall and extending radially towards thereof, the pilot cavities being fed with air from outside the combustion chamber in a common substantially circumferential direction. Each pilot injector opens out radially into a pilot cavity, and each full-throttle injector opens out radially between two adjacent pilot cavities.

Growing community of inventors

Avon, France

Laurent Bernard Cameriano