Snecma

Safran Aircraft Engines

Denis Jean Maurice Sandelis

Christophe Pieussergues

Romain Nicolas Lunel

Patrice Andre Commaret

Alain Rene Cayre

Michel Andre Albert Desaulty

Claude Gautier

Didier Hippolyte Hernandez

Laurent Bernard Cameriano

Dominique Maurice Jacques Lains

Romain Biebel

Jacques Marcel Arthur Bunel

Mario Cesar De Sousa

Thomas Olivier Marie Noel

Guillaume Sevi

David Locatelli

Denis Gabriel Trahot

Jackie Raymond Julien Prouteau

Luc Henri Claude Daguenet

Sebastien Alain Christophe Bourgois

Jeremy Giordan

Mario César De Sousa

Patrice André Commaret

Stephane Henri Guy Touchaud

Nicolas Christian Raymond Leblond

Jérémy Giordan

Aurelien Lionel Tedesco

Sébastien Alain Christophe Bourgois

Nicolas Leblond

Gerard Edouard Emile Caboche

Christophe Baudoin

Francois Rene Daniel Bainville

Alain Cayre

Aurélien Lionel Tedesco

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 turbine engine having an annular combustion chamber formed by two coaxial annular shrouds, an inner shroud and an outer shroud relative to the axis of the turbine engine, which shrouds are arranged one inside the other and are connected together at their upstream ends by an annular chamber end wall that is fastened to an outer casing surrounding the outer annular shroud, the downstream ends of the inner and outer annular shrouds being connected to flanges fastened to an inner casing and to the outer casing, respectively. The upstream end of at least one of the inner and outer shrouds is centered by bearing radially against the annular chamber end wall and co-operates therewith in leaktight axial sliding.

Annular combustion chamber

An injection system for a turbine engine combustion chamber is provided. The injection system includes a first annular deflector surrounded by the bowl of the injection system and extending in the downstream direction from the downstream transverse surface that delimits the downstream side of the swirler. The first deflector has a free downstream end offset in the upstream direction from a downstream end of the bowl, so as to guide an air film output from the first orifices formed through the bowl. The internal radius of the cross section of the first annular deflector increases from the downstream transverse surface as far as the downstream end of the first annular deflector.

Injection system for a turbine engine combustion chamber configured for direct injection of two coaxial fuel flows

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

An annular combustion chamber including inner and outer walls forming surfaces of revolution that are connected together upstream by an annular chamber end wall having injection systems passing therethrough. Each injection system includes at least one swirler for producing a rotating stream of air downstream from a fuel injector, and a frustoconical bowl downstream from the swirler and formed with an annular row of air injection orifices, the outer wall having an annular row of primary dilution orifices. The orifices of the bowls are distributed and dimensioned such that sheets of air/fuel mixture present a local enlargement circumferentially intersecting an adjacent sheet of fuel upstream from the primary dilution orifices.

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 annular combustion chamber of a turbine engine, the chamber including inner and outer coaxial walls forming two surfaces of revolution, which are connected together upstream by an annular chamber end wall including injection systems passing therethrough, each including an injector and at least one swirler for producing a rotating air stream that mixes downstream with fuel from the injector, and at least one ignition spark plug mounted in an orifice of the outer wall downstream from the injection systems. The spark plug is situated circumferentially between two adjacent injection systems that are configured to produce two air/fuel mixture sheets rotating in opposite directions.

Annular combustion chamber in a turbine engine

A turbomachine combustion chamber shell ring in which dilution holes in the turbomachine combustion chamber shell ring are covered with inserts defining chambers around same on an inner face of the shell ring. Ventilation holes, through the insert, induce ventilation of portions of the shell ring surrounding the dilution holes, cool the portions, and prevent crack formation.

Turbomachine combustion chamber shell ring

A combustion chamber for a turbomachine, including two coaxial walls including air inlets, each of which is configured such that its orthogonal projection, in a plane passing through the axis of the injection system closest to the inlet and perpendicular to an axial plane passing through this axis and through the axis of the combustion chamber, has an upstream edge of convex shape when seen from downstream.

Combustion chamber for a turbomachine including improved air inlets

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 procedure for igniting a combustion chamber of a turbine engine, the chamber being fed with fuel by injectors and including an igniter mechanism igniting the fuel injected into the chamber. The procedure includes an initial stage during which fuel is injected into the chamber at a constant rate while simultaneously exciting the igniter mechanism, and in event of non-ignition of the chamber at an end of the initial stage, a second stage during which a rate at which fuel is injected is increased rapidly by 20% to 30%.

Procedure for igniting a turbine engine combustion chamber

A turbomachine combustion chamber in which a chamber end wall presents an opening for receiving a pre-vaporization bowl, and including a device for injecting air and fuel mounted on the axis thereof, the bowl being floatingly mounted relative to the chamber end wall to move in a predetermined radial direction and flaring downstream so as to form a collar, a deflector forming a thermal shield being made integrally with the bowl beside the chamber end wall so that the floating movement of the bowl-and-deflector assembly takes place in a sliding plane situated between the deflector and the chamber end wall.

Turbomachine combustion chamber

A turbomachine including an annular combustion chamber, a sectorized turbine nozzle arranged at an outlet from the chamber, and a sealing mechanism interposed axially between the chamber and the nozzle, the sealing mechanism including an annular gasket that is axially resilient. The gasket includes a first axial bearing mechanism for bearing against a downstream end of the chamber and a downstream annular lip that is sectorized, each sector of the downstream lip being in alignment with a sector of the nozzle and including a second axial bearing mechanism for bearing against an upstream end of the nozzle sector.

Sealing between a combustion chamber and a turbine nozzle in a turbomachine

A device for injecting a mixture of air and fuel into a turbomachine combustion chamber includes a centering ring for centering an injector and a primary swirler situated downstream from the ring, the ring including axial air-passing orifices and the swirler including curved air-passing channels, a number of orifices in the ring being no greater than a number of channels in the swirler, and downstream outlets of the orifices in the ring being situated between the channels in the swirler.

Device for injecting a mixture of air and fuel into a turbomachine combustion chamber

A turbomachine including a combustion chamber provided with systems for injecting fuel into the chamber, and with at least one spark plug is disclosed. The injection system located as close as possible to the spark plug is configured in order to produce a pool of fuel having an angle of opening of a greater value than that of the pools produced by the other injection systems, and having a flow of fuel greater than that of the other injection systems.

Growing community of inventors

Nangis, France

Denis Jean Maurice Sandelis