Safran Aircraft Engines

Sébastien Christophe Chalaud

Michel Gilbert Roland Brault

Arnaud Nicolas Negri

Nathalie Nowakowski

Pierre Charles Mouton

Jacky Novi Mardjono

Romain Guillaume Cuvillier

Georges Jean Xavier Riou

Guillaume Patrice Kubiak

Nils Edouard Romain Bordoni

Bellal Waissi

Mohammed-Lamine Boutaleb

Christian Sylvain Vessot

Philippe Gérard Chanez

Lancelot Guillou

Alain Pierre Garassino

Romain Jean-Claude Ferrier

Bastien Pierre Verdier

Yves Emprin

Claude Sensiau

Lise Jeanine Léonie Domecq

Lauren Davis

Gwénolé Yann Le Pache

Guillaume Mathon-Margueritte

The outlet of a heat exchange circuit extending under a wall, such as a nacelle cowling of an aircraft engine, is divided into openings in the form of parallel slots which are elongated in the longitudinal direction and successively arranged in the transverse direction to divide the hot gas into streams while facilitating the circulation of fresh gas streams, originating from an external flow, on the intermediate laminates. The hot gas cannot fall back easily onto the outer face of the wall and risk damaging the wall, and the gas mixes more effectively with the fresh outdoor air. The openings are provided with nozzles flaring in the transverse direction and the downstream longitudinal direction to facilitate the mixing of the hot and cold gas streams.

Outlet of a hot-gas pipe of an aircraft engine passing through an engine wall

A turbomachine including at least one stator vane sector () and a fluid distribution circuit (), the stator vane sector comprising at least one vane (), a fluid inlet (), a fluid outlet (), and a channel () providing fluid flow connection between the fluid inlet and the fluid outlet while extending at least in part in the vane (), the vane and the channel being adapted, to enable heat to be exchanged between a hot fluid passing through the channel and a stream of cold air passing through the vane sector, the fluid distribution circuit () presenting a feed pipe () and a recovery pipe (), the fluid inlet () being in fluid flow connection with a branch tapping () of the feed pipe () while the fluid outlet () is in fluid flow connection with a branch tapping () of the recovery pipe ().

Turbomachine provided with a vane sector and a cooling circuit

A heat exchange and noise reduction panel the panel for an aircraft comprising: an external surface intended to be swept by an airflow and from which fins extend along a first and a second main predetermined direction; cavities forming Helmholtz resonators, linked to the first ends of channels for the passage of air, the second ends of which communicate with said airflow, such that said channels form necks, referred to as Helmholtz resonators, extending substantially along the first direction; and at least one oil flow chamber extending between said external surface and said at least one cavity, and intended to discharge the thermal energy carried by the oil, wherein said channels are formed, at least in part, inside said fins.

Panel for heat exchange and improved noise reduction for a turbomachine

A fluid supply system () for turbine engine, includes a high pressure volumetric pump (), a fluid metering device () and a control valve () configured to vary the flow rate of fluid in a bypass circuit () so as to regulate the pressure difference between an input and an output of the metering device (). The control valve () includes an obturator, the variable position of which is measured by a sensor (). An electronic regulation system () compares the measured position of the obturator with a position set-point of the obturator determined as a function of a flight condition of the aircraft and/or a measured fluid temperature and corresponding to a fluid flow rate set-point in the bypass circuit (). The flow rate of the high pressure pump () is commanded so that the measured position of the obturator adapts to the position set-point.

Fluid supply system for turbine engine, including an adjustable flow pump and a fluid metering device

An oil tank for a turbine engine comprising a closed enclosure having the shape of an arc of circle adapted to receive oil, with the enclosure having a lower portion and an upper portion at a distance from each other, and an oil level control device in the enclosure, wherein the oil level control device comprises a first sensor positioned in the lower portion of the enclosure so as to control the oil level, and a second sensor separate from the first sensor and positioned in the upper portion of the enclosure so as to control the oil level.

Oil tank comprising an oil level control device

A multi-body gas turbine engine, especially an aircraft engine, comprising at least one low-pressure rotating body, a high-pressure rotating body, and a starter designed to rotate the high-pressure body in order to start the engine, wherein the starter is coupled to the low-pressure body and the engine comprises a first disengageable coupling device disposed between the low-pressure body and the high-pressure body, for rotatably connecting the high-pressure body to the low-pressure body so as to allow the starting of the engine by means of the starter.

Gas turbine engine comprising a starter engaged with a low-pressure body

Growing community of inventors

Moissy-Cramayel, France

Sébastien Christophe Chalaud