Snecma

Safran Aircraft Engines

Julien Pavillet

Julien Sayn-Urpar

Jeremy Edmond Fert

Thierry Kohn

Guilhem Seize

Jérémy Edmond Fert

Hervé Jean Albert Mouton

Lambert Olivier Marie Demoulin

Eric De Vulpillieres

Alexandre Leon

An aircraft turbomachine including a nacelle and an engine further including at least one outflowing jet of air, wherein a heat exchanger of the precooler type for supplying air to the aircraft is mounted in the nacelle. The exchanger includes a primary circuit, the inlet of which is connected to a supply of compressed air from the engine and the outlet of which is connected to an air supply for supplying air to the aircraft, and a secondary circuit supplied with air taken from said air flow.

Aircraft turbomachine comprising a heat exchanger of the precooler type

A propulsion assembly includes an engine surrounded by a nacelle, structure for draining the fluids from the engine and structure for guiding said fluids to a retention box. The retention box is arranged outside the engine and has a cavity for storing drained fluids. The retention box is fixed to a cowling of the nacelle and supported thereby.

Propulsion assembly comprising a box for retaining drained fluids

Stub for discharging drained fluids for a propulsion unit. The stub includes a cavity for storing the drained fluids and at least one orifice for discharging the fluids contained in the storage cavity, and elements for measuring a difference in pressure outside the stub and a member for draining the storage cavity. The member is able to move between a first position of closing the discharge orifice and a second position of releasing the orifice, and is configured so as to move from the first to the second position when the difference in pressure is greater than, or equal to, a predetermined value.

Drained fluid evacuation stub for a propulsion assembly

An aircraft propulsion unit comprising an engine and a nacelle including an axisymmetric casing () delimiting an air flow path, wherein this casing has at least two openings closed by removable and interchangeable panels (), at least one of these panels carrying one component () of the propulsion unit.

Casing for a propulsion unit

An aeronautic engine including: a housing made of electrically insulating material and including at least one metallic piece; a structural piece of the engine including metallic material and connected to the housing; and an equipment fixed to the housing, is provided. The equipment is connected to the structural piece by the metallic piece by an electrically conductive connecting path.

Metallisation of an electrically insulating housing of an aeronautic engine

A heat shield device for a yoke suspending an engine from an aircraft is provided. The device includes panels able to be fixed to the yoke, at least one of the panels extending radially in the direction of the axis of the engine, and a component configured to be fixed to the engine and including a groove shaped in such a way that the lower end of the panel can be inserted into it.

Growing community of inventors

Moissy-Cramayel, France

Julien Pavillet