Snecma

Safran Aircraft Engines

Alain Rene Cayre

Denis Jean Maurice Sandelis

Michel Andre Albert Desaulty

Michel Andre Desaulty

Christophe Pieussergues

Denis Jean Sandelis

Romain Nicolas Lunel

Nicolas Pommier

Haris Musaefendic

Jackie Raymond Julien Prouteau

Luc Henri Claude Daguenet

Michel Pierre Cazalens

Claude Gautier

Stephane Henri Guy Touchaud

Guillaume Aurelien Godel

Olivier Kreder

Jackie Prouteau

Yoann Mery

Denis Sandelis

Michel Desaulty

Michel André Albert Desaulty

A turbine engine combustion chamber including: an outer annular housing; a flame tube connected to the outer housing. The flame tube includes an inner annular wall and an outer annular wall and a second axial outlet portion of the flame tube. The flame tube also includes a chamber base located at the inlet of the flame tube; and a fuel injection system configured to inject fuel into the flame tube via the inlet of the flame tube. The injection system includes an injector axis, and an air manifold to move air towards twists in the injection system. The twists are arranged around an implantation axis. The air manifold includes a circular portion around the injector axis. The circular portion, forms an air inlet of the manifold. The opening places the entering air flow in rotation about the implantation axis.

Bent combustion chamber from a turbine engine

A system for improving fuel-air mixing inside an injection system of a turbomachine combustion chamber. An air intake ring has an annular deflection wall, or venturi, having an internal profile provided with a discontinuity inducing an increase in the radius (&#x3c6;) of the internal profile downstream of the discontinuity. A method of atomizing fuel includes separating fuel trickling over the internal profile of the annular deflection wall from the internal profile at the level of the discontinuity so as to form droplets within a flow of air coming from an upstream air circulation space of the air intake ring.

Air intake ring for a turbomachine combustion chamber injection system and method of atomizing fuel in an injection system comprising said air intake ring

An annular combustion chamber of a turbomachine is disclosed. The combustion chamber includes two walls of revolution each having an annular groove extending around the longitudinal axis of the chamber and opening out inside the chamber. The groove has in cross section a substantially U or V shape that is splayed towards the downstream end and has lateral annular surfaces that are inclined with respect to the area of the wall at which the groove is situated.

Combustion chamber of a turbomachine including cooling grooves

An annular expansion ring centered on a main axis and suitable for being mounted on a fuel injector coaxial with the ring is disclosed. The ring presents holes that are distributed around the main axis and open out into its upstream face to enable air to pass towards the zone that is downstream from the ring. The ring includes a conical annular groove that converges downstream, that is open downstream, and that has the holes opening out into the upstream portion thereof. The axis of each of the holes makes an angle relative to the main axis that is strictly greater than the angle between the generator line of the cone defining the annular groove and the main axis, such that the air exiting from the holes impacts against the inner wall of the annular groove, i.e. its wall that is closer to the main axis.

Optimizing an anti-coke film in an injector system for a gas turbine engine

A turbomachine combustion chamber including a chamber bottom with at least one opening designed to receive a combustion bowl in the axis of which an air and fuel injection device is mounted is disclosed. The downstream end of the flared bowl includes a divergent with a double partition delimiting an annular cavity. The first outer partition includes inlet orifices arranged to cool the second inner partition by impact and the second inner partition includes outlet orifices. The inlet orifices, distributed in at least two circular rows on the periphery of the divergent, are in staggered rows with the outlet orifices.

Turbomachine combustion chamber

A device for injecting a mixture of air and fuel into a combustion chamber of a turbomachine is disclosed. The injection device includes a novel sliding bushing and a novel annular cup for retaining the sliding bushing, making it possible to improve the air feed of the injection device.

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

A shroud for a combustion chamber bottom designed to cover fuel injectors is provided with drillings on at least one of its sides to open up the cavity within the shroud and reduce noise that it produces and combustion instabilities. The drillings also have the effect of reducing instabilities and non-uniformity of the airflow around the shroud.

Shroud for a turbomachine combustion chamber

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 diffuser for a single-head annular combustion chamber of an airplane engine, the diffuser comprising a separator formed by a thin sheet connected by structural arms to inner and outer circularly-symmetrical walls of the diffuser, the diffuser angle for each diffusion stream defined by the separator lying in the range about 12&#xb0; to about 13&#xb0;.

Growing community of inventors

Pamfou, France

Alain Rene Cayre