Snecma

Snecma Moteurs

Office National D'etudes Et De Recherches Aerospatiales

Snecma Propulsion Solide

Safran Aircraft Engines

Herakles

Didier Hippolyte Hernandez

Patrice Andre Commaret

Thomas Olivier Marie Noel

Mario Cesar De Sousa

Eric Conete

Romain Nicolas Lunel

Alexandre Forestier

David Locatelli

Gw&eacute;na&euml;lle Calvez

Caroline Aumont

Georges Habarou

Sylvain Duval

Denis Jean Maurice Sandelis

Christophe Pieussergues

Denis Gabriel Trahot

Matthieu Francois Rullaud

Gilles Lepretre

Jacques Marcel Arthur Bunel

Antoine Robert Alain Brunet

Guillaume Sevi

Clément Roussille

Pierre Camy

Caroline Jacqueline Denise Berdou

Michel Pierre Cazalens

Sebastien Alain Christophe Bourgois

Mario César De Sousa

Laurent Pierre Elysee Gaston Marnas

Florian Andre Francois Bessagnet

Patrice André Commaret

Emilie Lachaud

Romain Biebel

Laurent Pierre Marnas

Sébastien Alain Christophe Bourgois

Martine Bes

Philippe Soyris

Thomas Olivier Noel

Dominique Guezengar

Christian Guin

Pascale Rollet

Laurent Marnas

Denis Jean Sandelis

Patrick Audin

Yann Francois Jean-Claude Vuillemenot

Beno&icirc;t Carrere

Francis Mirambeau

Philippe Guerville

Jean-Michel Duret

Yann Francois Jean-Claude Vuillemont

Michel Zischek

Thomas Noel

Michel Roger Buret

David Pinchon

Matthieu François Rullaud

Jean-Michel Serge Marcel Duret

Dominique Lains

André Lafont

Pascale Valérie Cothilde Rollet

Michel Buret

Thomas Noël

Yann François Jean-Claude Vuillemenot

Florian André François Bessagnet

Dominiqe Guezengar

Florian Andre Bessagnet

Yann Francois Vuillemenot

Antoine Robert Brunet

An air and fuel injection system for a turbine engine combustion chamber dome, including at least two fuel injection devices including a central injector and a peripheral annular injector arranged around the central injector, and an inner annular air inlet channel into which the central injector opens up to enable mixing between the fuel from the central injector and the air inlet into the inner annular channel, and at least one outer annular air inlet channel to enable enrichment of this mix with air and to stabilize the pilot combustion zone, wherein the inner annular channel and at least one outer annular channel are separated by an intermediate annular wall extending around the central injector and having a convergent inner profile.

Injection system for a combustion chamber of a turbine engine, comprising an annular wall having a convergent inner cross-section

An annular combustion chamber for a turbine engine is provided. The chamber includes an annular row of fuel injectors including heads engaged in fuel injection systems mounted in openings in the chamber end wall. Each injector head includes at least one fuel-passing helical channel for causing fuel to rotate about the longitudinal axis of the head. Each injection system includes at least one swirler including air-passing channels of sections with axes that are inclined relative to the plurality axis of the swirler at an angle that is substantially equal to a helix angle of the helical channel, to within &#xb1;10&#xb0;, and are oriented in a same direction as the channel about the longitudinal axis of the swirler.

Annular combustion chamber for a turbine engine

A sectorized nozzle for a turbine engine turbine including an inner sectorized annular platform and an outer sectorized annular platform connected together by radial airfoils, at least one of the platforms including a plurality of orifices for passing air in a neighborhood of its upstream end, the orifices being distributed over the circumference of the platform and opening out at their ends remote from the airfoils into a circumferential annular cavity of the sector of the platform, which cavity is closed by a metal sheet fastened to the platform sector and pierced by orifices for feeding cooling air.

Turbine nozzle guide vane assembly in a turbomachine

An air and fuel injection system for the back of a turbomachine's annular combustion chamber, including a central injector and a peripheral annular fuel injector including at least one fuel injection aperture made in an annular wall and emerging in a peripheral annular channel separated from a central channel by the annular wall and having an annular space of admission of air. The system also includes multiple air ejection apertures made in the annular wall downstream from the fuel ejection aperture or apertures in reference to the flow of the air stream, for an additional injection of air into the channel.

Injection system for a turbomachine combustion chamber, including air injection means improving the air-fuel mixture

A fuel mixing device for an annular combustion chamber of a turbine engine, including a member for centering a turbine engine injector head, at least one air intake ring including blades allowing swirling of air, a bowl including an annular row of air intake orifices, an annular cavity communicating with the air intake orifices, and channels arranged through the blades to feed air to the annular cavity.

Fuel mixing device for turbine engine combustion chamber comprising improved air feed means

A fuel injector device for an annular combustion chamber including a pilot circuit feeding an injector and a multipoint circuit feeding injection orifices formed in a front face of an annular chamber, an annular ring being mounted in the annular chamber to define therein a fuel feed circuit for the injection orifices and a cooling circuit operating by passing the fuel feeding the injector and extending over the front face of the chamber in immediate vicinity of the injection orifices.

Multipoint injector for a turbine engine combustion chamber

A fuel injector device for an annular combustion chamber of a turbine engine, including a pilot circuit feeding an injector and a multipoint circuit feeding injection orifices formed in a front face of an annular ring mounted in an annular chamber, together with a thermal insulation mechanism insulating the front face and including an annular cavity formed around the injection orifices between the front face of the annular ring and a front wall of the annular chamber and configured to be filled in operation with air or with coked fuel.

Multipoint injection device for a combustion chamber of a turbine engine

A turbomachine including an annular combustion chamber; a centrifugal compressor; an annular diffuser with a radially oriented upstream portion presenting diffusion passages connected to the outlet of the compressor; a curved intermediate portion; and a downstream portion having a series of circularly spaced-apart deflector vanes. The turbomachine also includes an outer casing externally surrounding the combustion chamber and the downstream portion. The zone of the outer casing that is situated facing the deflector vanes is covered in a coating of abradable material, and the flow passage through the downstream portion is defined on the outside by the outer casing and by the coating.

Turbine engine with diffuser

A multipoint injector for a turbomachine according to which any risk of fuel coking is eliminated is disclosed. The multipoint fuel which is liable to stagnate inside the circuit thereof is cooled uniformly, due to the formation of continuous baffles which each communicate with at least one separate circulation channel and of which the peripheral baffles open out into a fuel admission chamber arranged in a zone diametrically opposing the circulation channels and which communicates with the injection nozzle for pilot fuel in order to achieve uniform supply and cooling of the injector.

Multipoint injector for turbomachine

In a fuel injection device at a base of a combustion chamber, a mixing air inlet screw is manufactured with its peripheral holes extending only over a sector of a circle directed towards the air's propagation cone, wherein the remainder of the periphery of the screw is closed. It is then possible to reduce load loss of the injection system while obtaining an improved quality of the mix supplied to the chamber. Such a device can be used in gas turbines fitted with centrifugal compressors and in which the air flow towards the combustion chamber must therefore be made convergent.

Mixing screw for a fuel injector in a combustion chamber of a gas turbine, and corresponding combustion device

A diffuser for a turbine engine that includes two annular webs extending inside one another and connected between them by substantially radial vanes, wherein the downstream peripheral edge of at least one of the webs includes indentions evenly distributed about the longitudinal axis of the diffuser.

Diffuser for turbine engine including indented annular webs

A flame-holder device for an afterburner of a turbofan, the turbofan including a first inner annular casing and a second inner annular casing, these defining a passage for a primary flow, and an outer annular casing defining with the first inner annular casing a passage for a secondary flow, including at least one arm-support made of metallic material configured to be fixed to the outer casing by an upper plate and at least one flame-holder arm of a one-piece structure of composite material including two mutually attached walls arranged to define a groove whose profile is approximately a V. The walls support, on their upper part situated in the secondary flow, a fixing mechanism for fixing to the arm-support. The upper parts are approximately planar and are positioned facing each other.

Device for attaching a flame-holder arm to an afterburner housing

A gas turbine engine combustion chamber including at least one deflector mounted on the chamber end wall and including an opening for a carburetted air supply device. The deflector includes an opening, corresponding to the chamber end wall opening, with an annular cylindrical part for attachment to the wall, the cylindrical part including a mechanical attachment mechanism collaborating with a complementary attachment mechanism on a metal sleeve secured to the wall and a cylindrical centering cup fixed by one end to the sleeve and housed inside the cylindrical part of the deflector.

Gas turbine engine combustion chamber comprising CMC deflectors

A baffle for the bottom of a combustion chamber of a gas turbine engine is disclosed. The baffle includes a flat portion of wall with an opening for an injector of the combustion chamber to pass through, two longitudinal edges for the assembly to two adjacent baffles and two transverse edges. At least one of the edges includes a joint cover arranging a housing along the edge for an edge of an adjacent baffle so as to seal the junction between the two edges. A combustion chamber incorporating the baffles is also disclosed.

Chamber-bottom baffle, combustion chamber comprising same and gas turbine engine fitted therewith

An annular shroud (), having an internal face intended to cover the back end wall () of an annular combustion chamber () of a turbomachine () fitted with a centrifugal compressor, together with an external face opposite said internal face, and where said shroud includes multiple apertures () intended to allow fuel injectors () supported by said back end wall () to pass through, together with multiple bosses () which extend as projections on said external face radially towards the interior respectively from the respective radially internal edges () of said apertures (), such that each of said bosses () delimits an extension () of the corresponding aperture () open radially towards the exterior so as to form an air intake scoop.

Aerodynamic shroud for the back of a combustion chamber of a turbomachine

Growing community of inventors

Moissy Cramayel, France

Didier Hippolyte Hernandez