Safran Aircraft Engines

Safran Electronics & Defense

Safran Nacelles

Safran Landing Systems

Snecma

Jérémy Edmond Fert

Hakim Maalioune

Christophe Bastide

Vincent Hupin

Bellal Waissi

Carmen Gina Ancuta

Julien Pavillet

Nicolas Vincent Pierre-Yves Cotereau

Jacques Auriol

Laurent Christian Vincent Roger Miralles

Laurent Miralles

Eric De Vulpillieres

A system for managing the deceleration of an aircraft enabling the control in real time of the position of the aircraft on a braking axis, includes a braking system; a calculator configured to: calculate, from aircraft data and from external data, a sequence of use of the braking system intended to brake the aircraft over a predetermined braking distance which associates a predetermined position on the braking axis with each braking instant; update in real time the sequence of use as a function of the difference between the position of the aircraft and the predetermined position; and a controller configured to control the braking system as a function of the sequence of use.

System for managing the deceleration of an aircraft on a runway on the ground and associated method

A lubrication system for a turbomachine which includes a reduction gear. The lubrication system includes a main branch and a bypass branch which is arranged in parallel with the main branch. The main branch includes a heat exchanger. The bypass branch includes a hydraulic resistance that is lower than the hydraulic resistance of the main branch. The reduction gear is located downstream of the main branch and the bypass branch. The lubrication system includes at least one bypass device that is configured to supply the bypass branch with lubricant when a pressure value of the lubricant is below a threshold value.

Turbomachine lubrication system comprising a bypass for preferentially supplying lubricant to a low-speed reduction gear

An aircraft turbomachine includes a lubricating circuit notably including a reservoir of lubricating fluid, a pump drawing lubricating fluid from the reservoir to inject it toward several components of the turbomachine, and an intake pipe connecting the reservoir to an intake orifice of the pump, the turbomachine further including a pneumatic starting circuit including a starting tube through which there circulates a flow of compressed air intended to supply a pneumatic starter of the turbomachine, wherein it includes a pneumatic line extending from the starting tube as far as the reservoir so as to supply the reservoir with compressed air so as to cause the lubricating fluid to circulate through the intake pipe towards the pump.

Aircraft turbomachine comprising means for priming the lubricating pump

This system () for controlling an aircraft thrust reversal means comprises a reverse idle control means (), a first detection means () configured to detect, when the reverse idle control is active, a condition for activation of the thrust reversal means, and an actuation means () configured to activate the thrust reversal means when the first detection means () detects a condition for activation of the thrust reversal means. It further comprises a second detection means () configured to detect a condition for activation of the reverse idle control, the control means () being configured to activate the reverse idle control when the second detection means () detects a condition for activating the reverse idle control.

System for controlling an aircraft thrust reversal means

Portion of a fluid drainage conduit for a turbomachine, comprising an upstream stretch, a downstream stretch fixed relative to the upstream stretch and a retention chamber onto which the upstream stretch opens. The retention chamber is capable of communicating with the downstream stretch through a first aperture and a second aperture. The drainage conduit portion comprises an obturator to obturate the second aperture. The first and second apertures are provided so that when the obturator obturates the second aperture, the retention chamber retains fluid by allowing a fluid overflow to flow from the upstream stretch to the downstream stretch through the first aperture, and when the obturator does not obturate the second aperture, the fluid can flow from the upstream stretch to the downstream stretch at least through the second aperture.

Portion of a fluid drainage conduit for a turbomachine

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

Turbine engine, comprising two structural annular casings () which are interconnected by connecting rods (), characterized in that the turbine engine further has at least one accessory gearbox () which is fixed to a first of the casings () and which is connected by the connecting rods to the other of the casings ().

Growing community of inventors

Moissy-Cramayel, France

Jérémy Edmond Fert