Safran Aircraft Engines

Romain Jean-Claude Ferrier

Nicolas Joseph Sirvin

Nora El Ghannam

Romeo Brogna

Caroline Marie Frantz

Nicolas Xavier Trappier

Antoine Elie Hellegouarch

Philippe Gérard Chanez

Christian Sylvain Vessot

Jackie Raymond Julien Prouteau

Bastien Pierre Verdier

Sébastien Christophe Chalaud

Matthieu Etienne Attali

Thomas Gerard Daniel Riviere

Frederic Paul Eichstadt

Alexandre Gérard François Couilleaux

Irwin Pierre Robert Kernemp

Lauren Davis

Jonathan David Robert Langridge

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 of the &#xab;open rotor&#xbb; type or a turboprop engine comprises a nacelle defining an air inlet, a central hub and an annular air intake section surrounding the central hub and opening into a air supply main section, with the central hub comprising a central trap having an aperture for trapping the foreign objects in an air flow entering the turbomachine, and an air recovery channel having a discharge end, through which said air recovery channel opens into the main section, is provided on the central hub.

Turbomachine comprising a trap for foreign objects circulating in an air flow

A heat exchanger designed to be fixed to a turbomachine wall delimiting a gas flow stream, this exchanger including a body with a front face through which the gas flow passes; an attachment face to the wall; an external face opposite the attachment face and connected to the front face; two lateral faces connected to the front face; a cover surrounding the front face and extending along the prolongation of the external face and the lateral faces, to delimit an intake with an area smaller than the area of the front face, this intake being located upstream from the front face relative to the gas flow stream.

Heat exchanger fitted with upstream cover to reduce disturbance to fluid flow in a turbomachine

The invention relates to an aircraft propulsion assembly comprising a cradle receiving a turbine engine comprising at least one propeller having a longitudinal axis of rotation, a gas turbine engine having a longitudinal axis of rotation offset from the axis, and a reduction gear by means of which said propeller receives drive power from said engine, wherein the propeller and the gas turbine engine are designed such that axes and are offset from one another within said cradle at least by a given value in a transverse direction, the axis of the gas turbine engine being transversely closer to a proximal lateral side of the cradle than to an opposite distal lateral side of the cradle in order to create a lateral space between said engine and said distal lateral side of the cradle, thereby forming at least one region for installing equipments, components or accessories of said turbine engine.

Turbine engine having horizontally offset axes

The invention relates to a cradle () for an aircraft turbopropeller engine () of a substantially axial orientation, comprising a front arch () and a rear arch () extending transversely relative to said axial direction (A), said arches () being open at their lower ends and connected to each other by at least one axial longeron () extending between said arches (), characterised in that the longeron () is arranged in an upper portion of the cradle () and is formed in a single piece with the front arch ().

Cradle for a turbopropeller engine with integrated air inlet duct

Air inlet duct of a turbine engine, in particular an aircraft turbine engine comprising a gas generator, which extends axially between the air inlet and the gas generator and has a first axial wall part and a second wall part which is angularly offset with respect to the first part, which duct is capable of causing, in a shedding region, shedding of the boundary layer formed by an air flow along the wall of the duct; and a device for controlling said shedding of the boundary layer, characterised in that the control device comprises an air-blowing pipe which opens via at least one air-injection opening which is directly upstream of the shedding region, the blowing pipe being connected to an air intake positioned upstream of said air-injection opening or in the shedding region and comprising an air compressor means between the air intake and the air-injection opening.

Air inlet duct for an aircraft turbine engine

An air guidance device for a turbomachine includes an air supply channel of a turbomachine engine. The supply channel has an upstream section and a downstream section connected together by a diverting section, the upstream section and the diverting section being connected together via an internal elbow and an external elbow. At the internal elbow, the internal surface has a groove extending longitudinally in the longitudinal direction of the supply channel and the longitudinal edges of which are widened in the direction of the downstream end of the upstream section of the supply channel.

Growing community of inventors

Moissy-Cramayel, France

Romain Jean-Claude Ferrier