Safran Aircraft Engines

Snecma

Jean-Louis Muller

Pierre Charles Mouton

Albert Cornet

Thibault Maxime Adrien Mallet

Antoine Laigle

Jean-Louis Jacquerie

Francois Delamour

Nicolas Alain Bernard Potel

A method for generating an alarm is implemented by an alarm-generating device installed in an aircraft. It comprises: a step of obtaining information delivered by a sensor of said device and representative of an oil flow rate inside an oil filter of the aircraft; a step of obtaining a temperature delivered by a sensor of said device and representative of a temperature of the oil inside said filter; a step of obtaining a differential pressure at said filter; and a step of generating an alarm if the differential pressure exceeds an alarm threshold obtained on the basis of said information and of said temperature.

Method and device for generating an alarm for monitoring an oil filter in an aircraft

A method for isolating a tank of oil from a downstream portion of an oil supply system for a turbine engine is provided. The oil supply system includes the oil tank and a cutoff valve located between the oil tank and the downstream portion. The cutoff valve is configured to limit a flow of oil towards the downstream portion. The cutoff valve is fluidically linked to a fire extinguishing system by a fluid communication device. The method includes closing the cutoff valve in response to an increase in extinguishant pressure in the fluid communication device.

Isolation of an aircraft turbo engine tank in case of a fire by closing a valve sensitive to the release of an extinguishing agent

The invention relates to a device () for cooling oil for a turbine engine, such as an aircraft turbojet or turboprop engine, characterized in that it comprises a duct () for circulating a flow of cold air (F), means () for injecting oil into the duct, and means () for extracting the oil mixed with the flow of cold air (F), located in the duct (), downstream from the injection means ().

Device for cooling oil for a turbine engine

A lubrication system for a turbopropeller, includes an oil feed device for at least one enclosure and one equipment, the equipment being connected to the feed device via a displacement pump, and a pressure restricting valve mounted downstream of displacement pump and in parallel to the equipment, such that oil flows through the equipment when the same is active, and through the valve when the equipment is inactive.

Lubrication system for a turbopropeller

A circuit and a method for feeding oil to rolling bearings in a turbomachine is disclosed. The circuit includes an oil supply; an oil duct connecting the supply to lubrication enclosures, each enclosure containing at least one rolling bearing; an oil feed pump located between the supply and the lubrication enclosures; an oil recovery pump connected downstream from each lubrication enclosure; a pressurizing valve placed in the duct between the oil feed pump and the lubrication enclosures, the pressurizing valve being adapted to open when the pressure at its inlet exceeds a predetermined threshold pressure; a branch connection duct connecting the inlet of the pressurization valve to one of the lubrication enclosures in order to feed it with oil; and a feeding device which feeds the lubrication enclosures at a small oil flow rate so long as the pressure at the inlet of the pressurization valve has not reached the predetermined threshold.

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Maisons-Alfort, France

Jean-Louis Muller